Journal Articles
2021
Frey, Stefan; Colombo, Camilla
Transformation of Satellite Breakup Distribution for Probabilistic Orbital Collision Hazard Analysis Journal Article
In: Journal of Guidance, Control, and Dynamics, vol. 44, no. 1, pp. 88-105, 2021.
@article{Frey2021article,
title = {Transformation of Satellite Breakup Distribution for Probabilistic Orbital Collision Hazard Analysis},
author = {Frey, Stefan and Colombo, Camilla},
url = {https://doi.org/10.2514/1.G004939},
doi = {10.2514/1.G004939},
year = {2021},
date = {2021-01-01},
journal = {Journal of Guidance, Control, and Dynamics},
volume = {44},
number = {1},
pages = {88-105},
abstract = {Fragmentation clouds from explosions or collision of payloads and rocket bodies in space pose a threat to objects in Earth orbit. Most of the fragments are too small to be tracked and can only be accounted for statistically. Here, a framework for the fully statistical treatment of a fragmentation cloud, its evolution and ramifications, without the need of simplifying assumptions, is presented. The cloud is modeled as an uncertainty around a single fragment, which can be propagated using any of the existing, nondeterministic, nonlinear orbital uncertainty propagation methods. This work is focused on providing the initial distribution and the estimation of the statistical collision probability. The NASA standard breakup model is revisited to derive a probability distribution of the initial fragment cloud. Two density transformation methods are discussed to obtain the distribution in a subset of orbital elements, suitable for mid- to long-term evolution. The fragment spatial density and the impact rates on targets in any orbit are obtained. The method is applied to show the fragment cloud distribution of a payload collision in low Earth orbit (LEO). Its collision probability with a satellite in LEO and a rocket body in the geostationary transfer orbit are estimated. The result is compared against, and shows the limitations of, sampling and methods based on finite differences.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Fragmentation clouds from explosions or collision of payloads and rocket bodies in space pose a threat to objects in Earth orbit. Most of the fragments are too small to be tracked and can only be accounted for statistically. Here, a framework for the fully statistical treatment of a fragmentation cloud, its evolution and ramifications, without the need of simplifying assumptions, is presented. The cloud is modeled as an uncertainty around a single fragment, which can be propagated using any of the existing, nondeterministic, nonlinear orbital uncertainty propagation methods. This work is focused on providing the initial distribution and the estimation of the statistical collision probability. The NASA standard breakup model is revisited to derive a probability distribution of the initial fragment cloud. Two density transformation methods are discussed to obtain the distribution in a subset of orbital elements, suitable for mid- to long-term evolution. The fragment spatial density and the impact rates on targets in any orbit are obtained. The method is applied to show the fragment cloud distribution of a payload collision in low Earth orbit (LEO). Its collision probability with a satellite in LEO and a rocket body in the geostationary transfer orbit are estimated. The result is compared against, and shows the limitations of, sampling and methods based on finite differences.
Miguel, Narcís; Colombo, Camilla
Deorbiting spacecraft with passively stabilised attitude using a simplified quasi-rhombic-pyramid sail Journal Article
In: Advances in Space Research, vol. 67, pp. 2561-2576, 2021.
@article{Miguel2021article,
title = {Deorbiting spacecraft with passively stabilised attitude using a simplified quasi-rhombic-pyramid sail},
author = {Miguel, Narcís and Colombo, Camilla},
url = {https://doi.org/10.1016/j.asr.2020.03.028},
doi = {10.1016/j.asr.2020.03.028},
year = {2021},
date = {2021-01-01},
journal = {Advances in Space Research},
volume = {67},
pages = {2561-2576},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Gonzalo, Juan Luis; Colombo, Camilla; Di Lizia, Pierluigi
Analytical Framework for Space Debris Collision Avoidance Maneuver Design Journal Article
In: Journal of Guidance, Control, and Dynamics, vol. 44, no. 3, pp. 469-487, 2021.
@article{Gonzalo2021article,
title = {Analytical Framework for Space Debris Collision Avoidance Maneuver Design},
author = {Gonzalo, Juan Luis and Colombo, Camilla and Di Lizia, Pierluigi},
url = {https://doi.org/10.2514/1.G005398},
doi = {10.2514/1.G005398},
year = {2021},
date = {2021-01-01},
journal = {Journal of Guidance, Control, and Dynamics},
volume = {44},
number = {3},
pages = {469-487},
abstract = {An analytical formulation for collision avoidance maneuvers involving a spacecraft and a space debris is presented, including solutions for the maximum deviation and minimum collision probability cases. Gauss’s planetary equations and relative motion equations are used to map maneuvers at a given time to displacements at the predicted close approach. The model is then extended to map changes in state between two times, allowing one to propagate covariance matrices. The analytical formulation reduces the optimization problem to an eigenproblem, for both maximum deviation and minimum collision probability. Two maximum deviation cases, total deviation and impact parameter, are compared for a large set of spacecraft–debris conjunction geometries derived from European Space Agency’s Meteoroid and Space Debris Terrestrial Environment Reference (MASTER-2009) model. Moreover, the maximum impact parameter and minimum collision probability maneuvers are compared assuming covariances known at the maneuver time, to evaluate the net effect of lead time in collision probability. In all cases, solutions are analyzed in the b-plane to leverage its natural separation of phasing and geometry change effects. Both uncertainties and maximum deviation grow along the time axis for long lead times, limiting the reduction in collision probability.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
An analytical formulation for collision avoidance maneuvers involving a spacecraft and a space debris is presented, including solutions for the maximum deviation and minimum collision probability cases. Gauss’s planetary equations and relative motion equations are used to map maneuvers at a given time to displacements at the predicted close approach. The model is then extended to map changes in state between two times, allowing one to propagate covariance matrices. The analytical formulation reduces the optimization problem to an eigenproblem, for both maximum deviation and minimum collision probability. Two maximum deviation cases, total deviation and impact parameter, are compared for a large set of spacecraft–debris conjunction geometries derived from European Space Agency’s Meteoroid and Space Debris Terrestrial Environment Reference (MASTER-2009) model. Moreover, the maximum impact parameter and minimum collision probability maneuvers are compared assuming covariances known at the maneuver time, to evaluate the net effect of lead time in collision probability. In all cases, solutions are analyzed in the b-plane to leverage its natural separation of phasing and geometry change effects. Both uncertainties and maximum deviation grow along the time axis for long lead times, limiting the reduction in collision probability.
Trisolini, Mirko; Colombo, Camilla
Re-entry prediction and demisability analysis for the atmospheric disposal of geosynchronous satellites Journal Article
In: Advances in Space Research, vol. 68, pp. 4321-4335, 2021.
@article{Trisolini2021article,
title = {Re-entry prediction and demisability analysis for the atmospheric disposal of geosynchronous satellites},
author = {Trisolini, Mirko and Colombo, Camilla},
url = {https://doi.org/10.1016/j.asr.2021.09.024},
doi = {10.1016/j.asr.2021.09.024},
year = {2021},
date = {2021-01-01},
journal = {Advances in Space Research},
volume = {68},
pages = {4321-4335},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Trisolini, Mirko; Lewis, Hugh G.; Colombo, Camilla
Constrained optimisation of preliminary spacecraft configurations under the design-for-demise paradigm Journal Article
In: Journal of Space Safety Engineering, vol. 8, pp. 63-74, 2021.
@article{Trisolini2021articleb,
title = {Constrained optimisation of preliminary spacecraft configurations under the design-for-demise paradigm},
author = {Trisolini, Mirko and Lewis, Hugh G. and Colombo, Camilla},
url = {https://doi.org/10.1016/j.jsse.2021.01.005},
doi = {10.1016/j.jsse.2021.01.005},
year = {2021},
date = {2021-01-01},
journal = {Journal of Space Safety Engineering},
volume = {8},
pages = {63-74},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Trisolini, Mirko; Colombo, Camilla
Propagation and Reconstruction of Reentry Uncertainties Using Continuity Equation and Simplicial Interpolation Journal Article
In: Journal of Guidance, Control, and Dynamics, vol. 44, no. 4, pp. 793-811, 2021.
@article{Trisolini2021articlec,
title = {Propagation and Reconstruction of Reentry Uncertainties Using Continuity Equation and Simplicial Interpolation},
author = {Trisolini, Mirko and Colombo, Camilla},
url = {https://doi.org/10.2514/1.G005228},
doi = {10.2514/1.G005228},
year = {2021},
date = {2021-01-01},
journal = {Journal of Guidance, Control, and Dynamics},
volume = {44},
number = {4},
pages = {793-811},
abstract = {This Paper proposes a continuum-based approach for the propagation of uncertainties in the initial conditions and parameters for the analysis and prediction of spacecraft reentries. Using the continuity equation together with the reentry dynamics, the joint probability distribution of the uncertainties is propagated in time for specific sampled points. At each time instant, the joint probability distribution function is then reconstructed from the scattered data using a gradient-enhanced linear interpolation based on a simplicial representation of the state space. Uncertainties in the initial conditions at reentry and in the ballistic coefficient for three representative test cases are considered: a three-state and a six-state steep Earth reentry and a six-state unguided lifting entry at Mars. The Paper shows the comparison of the proposed method with Monte Carlo–based techniques in terms of quality of the obtained marginal distributions and runtime as a function of the number of samples used.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
This Paper proposes a continuum-based approach for the propagation of uncertainties in the initial conditions and parameters for the analysis and prediction of spacecraft reentries. Using the continuity equation together with the reentry dynamics, the joint probability distribution of the uncertainties is propagated in time for specific sampled points. At each time instant, the joint probability distribution function is then reconstructed from the scattered data using a gradient-enhanced linear interpolation based on a simplicial representation of the state space. Uncertainties in the initial conditions at reentry and in the ballistic coefficient for three representative test cases are considered: a three-state and a six-state steep Earth reentry and a six-state unguided lifting entry at Mars. The Paper shows the comparison of the proposed method with Monte Carlo–based techniques in terms of quality of the obtained marginal distributions and runtime as a function of the number of samples used.
Limonta, S.; Trisolini, M.; Frey, S.; Colombo, C.
Fragmentation model and strewn field estimation for meteoroids entry Journal Article
In: Icarus, vol. 367, pp. 1-21, 2021.
@article{Limonta2021article,
title = {Fragmentation model and strewn field estimation for meteoroids entry},
author = {Limonta, S. and Trisolini, M. and Frey, S. and Colombo, C.},
url = {https://doi.org/10.1016/j.icarus.2021.114553},
doi = {http://dx.doi.org/10.1016/j.icarus.2021.114553},
year = {2021},
date = {2021-01-01},
journal = {Icarus},
volume = {367},
pages = {1-21},
abstract = {Everyday thousands of meteoroids enter the Earth's atmosphere. The vast majority burn up harmlessly during the descent, but the larger objects survive, occasionally experiencing intense fragmentation events, and reach the ground. These events can pose a non-negligible threat for a village or a small city; therefore, models of asteroid fragmentation, together with accurate post breakup trajectory and strewn field estimation, are needed to enable a reliable risk assessment of these hazards. In this work, a comprehensive methodology to describe meteoroids entry, fragmentation, descent, and strewn field is presented by means of a continuum approach. At breakup, a modified version of the NASA Standard Breakup Model is used to generate the fragments distribution in terms of their area-to-mass ratio and ejection velocity. This distribution, combined with the meteoroid state, is directly propagated using the continuity equation coupled with the non-linear entry dynamics. At each time step, the fragments probability density time-evolution is reconstructed using Gaussian Mixture Model interpolation. Using this information is then possible to estimate the meteoroid's ground impact probability. This approach departs from the current state-of-the-art models: it has the flexibility to include large fragmentation events while maintaining a continuum formulation for a better physical representation of the phenomenon. The methodology is also characterised by a modular structure, so that updated asteroids fragmentation models can be readily integrated into the framework, allowing a continuously improving prediction of re-entry and fragmentation events. The propagation of the fragments' density and its reconstruction, at the moment considering only one fragmentation point, is first compared against Monte Carlo simulations, and then against real observations. Both deceleration due to atmospheric drag and ablation due to aerothermodynamics effects have been considered.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Everyday thousands of meteoroids enter the Earth's atmosphere. The vast majority burn up harmlessly during the descent, but the larger objects survive, occasionally experiencing intense fragmentation events, and reach the ground. These events can pose a non-negligible threat for a village or a small city; therefore, models of asteroid fragmentation, together with accurate post breakup trajectory and strewn field estimation, are needed to enable a reliable risk assessment of these hazards. In this work, a comprehensive methodology to describe meteoroids entry, fragmentation, descent, and strewn field is presented by means of a continuum approach. At breakup, a modified version of the NASA Standard Breakup Model is used to generate the fragments distribution in terms of their area-to-mass ratio and ejection velocity. This distribution, combined with the meteoroid state, is directly propagated using the continuity equation coupled with the non-linear entry dynamics. At each time step, the fragments probability density time-evolution is reconstructed using Gaussian Mixture Model interpolation. Using this information is then possible to estimate the meteoroid's ground impact probability. This approach departs from the current state-of-the-art models: it has the flexibility to include large fragmentation events while maintaining a continuum formulation for a better physical representation of the phenomenon. The methodology is also characterised by a modular structure, so that updated asteroids fragmentation models can be readily integrated into the framework, allowing a continuously improving prediction of re-entry and fragmentation events. The propagation of the fragments' density and its reconstruction, at the moment considering only one fragmentation point, is first compared against Monte Carlo simulations, and then against real observations. Both deceleration due to atmospheric drag and ablation due to aerothermodynamics effects have been considered.
Gaias, G.; Ardaens, J. -S.; Colombo, C.
Precise Line-of-Sight Modelling for Angles-Only Relative Navigation Journal Article
In: Advances in Space Research, vol. 67, pp. 3515-3526, 2021.
@article{Gaias2021article,
title = {Precise Line-of-Sight Modelling for Angles-Only Relative Navigation},
author = {Gaias, G. and Ardaens, J. -S. and Colombo, C.},
url = {https://doi.org/10.1016/j.asr.2020.05.048},
doi = {10.1016/j.asr.2020.05.048},
year = {2021},
date = {2021-01-01},
journal = {Advances in Space Research},
volume = {67},
pages = {3515-3526},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Scala, Francesca; Gaias, Gabriella; Colombo, Camilla; Martin-Neira, Manuel
Design of optimal low-thrust manoeuvres for remote sensing multi-satellite formation flying in low Earth orbit Journal Article
In: Advances in Space Research, vol. 68, pp. 4359-4378, 2021.
@article{Scala2021article,
title = {Design of optimal low-thrust manoeuvres for remote sensing multi-satellite formation flying in low Earth orbit},
author = {Scala, Francesca and Gaias, Gabriella and Colombo, Camilla and Martin-Neira, Manuel},
url = {https://doi.org/10.1016/j.asr.2021.09.030},
doi = {10.1016/j.asr.2021.09.030},
year = {2021},
date = {2021-01-01},
journal = {Advances in Space Research},
volume = {68},
pages = {4359-4378},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Huang, S.; Colombo, C.; Bernelli Zazzera, F.
Multi-criteria design of continuous global coverage Walker and Street-of-Coverage constellations through property assessment Journal Article
In: Acta Astronautica, vol. 188, pp. 151-170, 2021.
@article{Huang2021article,
title = {Multi-criteria design of continuous global coverage Walker and Street-of-Coverage constellations through property assessment},
author = {Huang, S. and Colombo, C. and Bernelli Zazzera, F.},
url = {https://doi.org/10.1016/j.actaastro.2021.07.002},
doi = {http://dx.doi.org/10.1016/j.actaastro.2021.07.002},
year = {2021},
date = {2021-01-01},
journal = {Acta Astronautica},
volume = {188},
pages = {151-170},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
2020
Gkolias, Ioannis; Alessi, Elisa Maria; Colombo, Camilla
Dynamical taxonomy of the coupled solar radiation pressure and oblateness problem and analytical deorbiting configurations Journal Article
In: Celestial Mechanics and Dynamical Astronomy, vol. 132, pp. 55, 2020, ISBN: 1572-9478.
@article{Gkolias2020article,
title = {Dynamical taxonomy of the coupled solar radiation pressure and oblateness problem and analytical deorbiting configurations},
author = {Gkolias, Ioannis and Alessi, Elisa Maria and Colombo, Camilla},
url = {https://doi.org/10.1007/s10569-020-09992-2},
doi = {10.1007/s10569-020-09992-2},
isbn = {1572-9478},
year = {2020},
date = {2020-01-01},
journal = {Celestial Mechanics and Dynamical Astronomy},
volume = {132},
pages = {55},
abstract = {Recent works demonstrated that the dynamics caused by the planetary oblateness coupled with the solar radiation pressure can be described through a model based on singly averaged equations of motion. The coupled perturbations affect the evolution of the eccentricity, inclination and orientation of the orbit with respect to the Sun–Earth line. Resonant interactions lead to non-trivial orbital evolution that can be exploited in mission design. Moreover, the dynamics in the vicinity of each resonance can be analytically described by a resonant model that provides the location of the central and hyperbolic invariant manifolds which drive the phase space evolution. The classical tools of the dynamical systems theory can be applied to perform a preliminary mission analysis for practical applications. On this basis, in this work we provide a detailed derivation of the resonant dynamics, also in non-singular variables, and discuss its properties, by studying the main bifurcation phenomena associated with each resonance. Last, the analytical model will provide a simple analytical expression to obtain the area-to-mass ratio required for a satellite to deorbit from a given altitude in a feasible timescale.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Recent works demonstrated that the dynamics caused by the planetary oblateness coupled with the solar radiation pressure can be described through a model based on singly averaged equations of motion. The coupled perturbations affect the evolution of the eccentricity, inclination and orientation of the orbit with respect to the Sun–Earth line. Resonant interactions lead to non-trivial orbital evolution that can be exploited in mission design. Moreover, the dynamics in the vicinity of each resonance can be analytically described by a resonant model that provides the location of the central and hyperbolic invariant manifolds which drive the phase space evolution. The classical tools of the dynamical systems theory can be applied to perform a preliminary mission analysis for practical applications. On this basis, in this work we provide a detailed derivation of the resonant dynamics, also in non-singular variables, and discuss its properties, by studying the main bifurcation phenomena associated with each resonance. Last, the analytical model will provide a simple analytical expression to obtain the area-to-mass ratio required for a satellite to deorbit from a given altitude in a feasible timescale.
Colombo, C.; Di Blas, N.; Gkolias, I.; Lanzi, P.; Loiacono, D.; Stella, E.
An Educational Experience to Raise Awareness about Space Debris Journal Article
In: IEEE Access, vol. 8, pp. 85162-85178, 2020.
@article{Colombo2020article,
title = {An Educational Experience to Raise Awareness about Space Debris},
author = {Colombo, C. and Di Blas, N. and Gkolias, I. and Lanzi, P. and Loiacono, D. and Stella, E.},
url = {https://doi.org/10.1109/ACCESS.2020.2992327},
doi = {http://dx.doi.org/10.1109/ACCESS.2020.2992327},
year = {2020},
date = {2020-01-01},
journal = {IEEE Access},
volume = {8},
pages = {85162-85178},
abstract = {Space debris represents a threat to space missions and operational satellites. Failing to control its growth might lead to the inability to use near-Earth space. However, this issue is still largely unknown to most people. In this paper, we present an educational experience in virtual reality created to raise awareness about the problem of space debris. The application exploits the entity-component-system (ECS) programming pattern to manage around 20000 orbiting objects with a high frame rate to convey a fluid experience. We preliminarily validated our application, in terms of usability as well as quality of user experience, during several events involving both a broad audience (e.g., citizens of all ages, from teenagers to elders) and an experienced audience (e.g., engineering students enrolled in the aerospace degree). The results of the evaluation were extremely positive, showing once again that virtual reality can be an effective means to engage people in captivating and interactive activities, making them experience what can only be imagined - the thousands pieces of space debris surrounding our planet.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Space debris represents a threat to space missions and operational satellites. Failing to control its growth might lead to the inability to use near-Earth space. However, this issue is still largely unknown to most people. In this paper, we present an educational experience in virtual reality created to raise awareness about the problem of space debris. The application exploits the entity-component-system (ECS) programming pattern to manage around 20000 orbiting objects with a high frame rate to convey a fluid experience. We preliminarily validated our application, in terms of usability as well as quality of user experience, during several events involving both a broad audience (e.g., citizens of all ages, from teenagers to elders) and an experienced audience (e.g., engineering students enrolled in the aerospace degree). The results of the evaluation were extremely positive, showing once again that virtual reality can be an effective means to engage people in captivating and interactive activities, making them experience what can only be imagined - the thousands pieces of space debris surrounding our planet.
Romano, Matteo; Losacco, Matteo; Colombo, Camilla; Di Lizia, Pierluigi
Impact probability computation of near-Earth objects using Monte Carlo line sampling and subset simulation Journal Article
In: Celestial Mechanics and Dynamical Astronomy, vol. 132, pp. 42, 2020, ISBN: 1572-9478.
@article{Romano2020article,
title = {Impact probability computation of near-Earth objects using Monte Carlo line sampling and subset simulation},
author = {Romano, Matteo and Losacco, Matteo and Colombo, Camilla and Di Lizia, Pierluigi},
url = {https://doi.org/10.1007/s10569-020-09981-5},
doi = {10.1007/s10569-020-09981-5},
isbn = {1572-9478},
year = {2020},
date = {2020-01-01},
journal = {Celestial Mechanics and Dynamical Astronomy},
volume = {132},
pages = {42},
abstract = {This work introduces two Monte Carlo (MC)-based sampling methods, known as line sampling and subset simulation, to improve the performance of standard MC analyses in the context of asteroid impact risk assessment. Both techniques sample the initial uncertainty region in different ways, with the result of either providing a more accurate estimate of the impact probability or reducing the number of required samples during the simulation with respect to standard MC techniques. The two methods are first described and then applied to some test cases, providing evidence of the increased accuracy or the reduced computational burden with respect to a standard MC simulation. Finally, a sensitivity analysis is carried out to show how parameter setting affects the accuracy of the results and the numerical efficiency of the two methods.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
This work introduces two Monte Carlo (MC)-based sampling methods, known as line sampling and subset simulation, to improve the performance of standard MC analyses in the context of asteroid impact risk assessment. Both techniques sample the initial uncertainty region in different ways, with the result of either providing a more accurate estimate of the impact probability or reducing the number of required samples during the simulation with respect to standard MC techniques. The two methods are first described and then applied to some test cases, providing evidence of the increased accuracy or the reduced computational burden with respect to a standard MC simulation. Finally, a sensitivity analysis is carried out to show how parameter setting affects the accuracy of the results and the numerical efficiency of the two methods.
Gonzalo, J. L.; Colombo, C.; Di Lizia, P.
Introducing MISS, a new tool for collision avoidance analysis and design Journal Article
In: Journal of Space Safety Engineering, vol. 7, pp. 282-289, 2020.
@article{Gonzalo2020article,
title = {Introducing MISS, a new tool for collision avoidance analysis and design},
author = {Gonzalo, J. L. and Colombo, C. and Di Lizia, P.},
url = {https://doi.org/10.1016/j.jsse.2020.07.010},
doi = {10.1016/j.jsse.2020.07.010},
year = {2020},
date = {2020-01-01},
journal = {Journal of Space Safety Engineering},
volume = {7},
pages = {282-289},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Trisolini, Mirko; Lewis, Hugh G.; Colombo, Camilla
Predicting the vulnerability of spacecraft components: Modelling debris impact effects through vulnerable-zones Journal Article
In: Advances in Space Research, vol. 65, pp. 2692-2710, 2020.
@article{Trisolini2020article,
title = {Predicting the vulnerability of spacecraft components: Modelling debris impact effects through vulnerable-zones},
author = {Trisolini, Mirko and Lewis, Hugh G. and Colombo, Camilla},
url = {https://doi.org/10.1016/j.asr.2020.03.010},
doi = {10.1016/j.asr.2020.03.010},
year = {2020},
date = {2020-01-01},
journal = {Advances in Space Research},
volume = {65},
pages = {2692-2710},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Gaias, Gabriella; Colombo, Camilla; Lara, Martin
Analytical Framework for Precise Relative Motion in Low Earth Orbits Journal Article
In: Journal of Guidance, Control, and Dynamics, vol. 43, no. 5, pp. 915-927, 2020.
@article{Gaias2020article,
title = {Analytical Framework for Precise Relative Motion in Low Earth Orbits},
author = {Gaias, Gabriella and Colombo, Camilla and Lara, Martin},
url = {https://doi.org/10.2514/1.G004716},
doi = {10.2514/1.G004716},
year = {2020},
date = {2020-01-01},
journal = {Journal of Guidance, Control, and Dynamics},
volume = {43},
number = {5},
pages = {915-927},
abstract = {This work presents a practical and efficient analytical framework for the precise modeling of the relative motion in low Earth orbits. Developed to support the design and verification of relative guidance navigation and control algorithms devoted to spacecraft rendezvous for active debris removal applications, only the orbital perturbation due to nonspherically symmetric mass distribution is considered. The relative motion is modeled in mean relative orbital elements, revisiting the available formulations to include the first-order expansion of the effects due to any even zonal harmonics and the second-order expansion of the unperturbed and J2 terms. Mean/osculating orbital element conversions are obtained by merging a second-order Hamiltonian approach applied to the J2 problem with the Kaula linear perturbation method for the remaining terms of the geopotential. The paper describes the main building blocks of the framework as well as their interfaces because the key aspect to achieve precision is to set up a fully consistent environment. The results show the achievable accuracy under realistic operational conditions for possible guidance and navigation applications.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
This work presents a practical and efficient analytical framework for the precise modeling of the relative motion in low Earth orbits. Developed to support the design and verification of relative guidance navigation and control algorithms devoted to spacecraft rendezvous for active debris removal applications, only the orbital perturbation due to nonspherically symmetric mass distribution is considered. The relative motion is modeled in mean relative orbital elements, revisiting the available formulations to include the first-order expansion of the effects due to any even zonal harmonics and the second-order expansion of the unperturbed and J2 terms. Mean/osculating orbital element conversions are obtained by merging a second-order Hamiltonian approach applied to the J2 problem with the Kaula linear perturbation method for the remaining terms of the geopotential. The paper describes the main building blocks of the framework as well as their interfaces because the key aspect to achieve precision is to set up a fully consistent environment. The results show the achievable accuracy under realistic operational conditions for possible guidance and navigation applications.
Huang, S.; Colombo, C.; Bernelli Zazzera, F.
Low-thrust planar transfer for co-planar low Earth orbit satellites considering self-induced collision avoidance Journal Article
In: Aerospace Science and Technology, vol. 106, pp. 1-19, 2020.
@article{Huang2020article,
title = {Low-thrust planar transfer for co-planar low Earth orbit satellites considering self-induced collision avoidance},
author = {Huang, S. and Colombo, C. and Bernelli Zazzera, F.},
url = {https://doi.org/10.1016/j.ast.2020.106198},
doi = {http://dx.doi.org/10.1016/j.ast.2020.106198},
year = {2020},
date = {2020-01-01},
journal = {Aerospace Science and Technology},
volume = {106},
pages = {1-19},
abstract = {This paper deals with the planar transfer problems (orbit raising and de-orbiting) for co-planar satellites with low-thrust propulsion, taking the self-induced collision avoidance into consideration at the mission design stage. A Blended Error-Correction steering law, with which the thrust direction changes in a self-adaptive way, is developed by blending two types of efficient steering laws and offsetting the errors of the instantaneous orbit with respect to the target orbit. The semi-analytical solutions for orbital elements, which reduce the computational load of propagating long-duration trajectories, are derived by computing the analytical incremental changes in orbital elements after every revolution with an orbital averaging technique. Based on the analytical Blended Error-Correction steering law and semi-analytical solutions, transfers can be computed quickly for any starting times. Finally, the self-induced collision, which is modeled by miss distance, is avoided by scheduling properly the timing to start transfer for every satellite.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
This paper deals with the planar transfer problems (orbit raising and de-orbiting) for co-planar satellites with low-thrust propulsion, taking the self-induced collision avoidance into consideration at the mission design stage. A Blended Error-Correction steering law, with which the thrust direction changes in a self-adaptive way, is developed by blending two types of efficient steering laws and offsetting the errors of the instantaneous orbit with respect to the target orbit. The semi-analytical solutions for orbital elements, which reduce the computational load of propagating long-duration trajectories, are derived by computing the analytical incremental changes in orbital elements after every revolution with an orbital averaging technique. Based on the analytical Blended Error-Correction steering law and semi-analytical solutions, transfers can be computed quickly for any starting times. Finally, the self-induced collision, which is modeled by miss distance, is avoided by scheduling properly the timing to start transfer for every satellite.
Nugnes, Marco; Colombo, Camilla; Tipaldi, Massimo
A System-Level Engineering Approach for Preliminary Performance Analysis and Design of Global Navigation Satellite System Constellations Journal Article
In: International Review of Aerospace Engineering (IREASE), vol. 13, no. 3, 2020, ISSN: 2533-2279, (doi:10.15866/irease.v13i3.18424).
@article{Nugnes2020article,
title = {A System-Level Engineering Approach for Preliminary Performance Analysis and Design of Global Navigation Satellite System Constellations},
author = {Nugnes, Marco and Colombo, Camilla and Tipaldi, Massimo},
url = {https://www.praiseworthyprize.org/jsm/index.php?journal=irease&page=article&op=view&path%5B%5D=24354},
issn = {2533-2279},
year = {2020},
date = {2020-01-01},
journal = {International Review of Aerospace Engineering (IREASE)},
volume = {13},
number = {3},
abstract = {This paper presents a system-level engineering approach for the preliminary coverage performance analysis and the design of a generic Global Navigation Satellite System (GNSS) constellation. This analysis accounts for both the coverage requirements and the robustness to transient or catastrophic failures of the constellation. The European GNSS, Galileo, is used as reference case to prove the effectiveness of the proposed tool. This software suite, named GNSS Coverage Analysis Tool (G-CAT), requires as input the state vector of each satellite of the constellation and provides the performance of the GNSS constellation in terms of coverage. The tool offers an orbit propagator, an attitude propagator, an algorithm to identify the visibility region on the Earth’s surface from each satellite, and a counter function to compute how many satellites are in view from given locations on the Earth’s surface. Thanks to its low computational burden, the tool can be adopted to compute the optimal number of satellites per each orbital plane by verifying if the coverage and accuracy requirements are fulfilled under the assumption of uniform in-plane angular spacing between coplanar satellites.},
note = {doi:10.15866/irease.v13i3.18424},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
This paper presents a system-level engineering approach for the preliminary coverage performance analysis and the design of a generic Global Navigation Satellite System (GNSS) constellation. This analysis accounts for both the coverage requirements and the robustness to transient or catastrophic failures of the constellation. The European GNSS, Galileo, is used as reference case to prove the effectiveness of the proposed tool. This software suite, named GNSS Coverage Analysis Tool (G-CAT), requires as input the state vector of each satellite of the constellation and provides the performance of the GNSS constellation in terms of coverage. The tool offers an orbit propagator, an attitude propagator, an algorithm to identify the visibility region on the Earth’s surface from each satellite, and a counter function to compute how many satellites are in view from given locations on the Earth’s surface. Thanks to its low computational burden, the tool can be adopted to compute the optimal number of satellites per each orbital plane by verifying if the coverage and accuracy requirements are fulfilled under the assumption of uniform in-plane angular spacing between coplanar satellites.
2019
Frey, S.; Colombo, C.; Lemmens, S.
Extension of the King-Hele orbit contraction method for accurate, semi-analytical propagation of non-circular orbits Journal Article
In: Advances in Space Research, vol. 64, pp. 1-17, 2019.
@article{Frey2019article,
title = {Extension of the King-Hele orbit contraction method for accurate, semi-analytical propagation of non-circular orbits},
author = {Frey, S. and Colombo, C. and Lemmens, S.},
url = {https://doi.org/10.1016/j.asr.2019.03.016},
doi = {10.1016/j.asr.2019.03.016},
year = {2019},
date = {2019-01-01},
journal = {Advances in Space Research},
volume = {64},
pages = {1-17},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Gkolias, I.; Daquin, J.; Skoulidou, D. K.; Tsiganis, K.; Efthymiopoulos, C.
Chaotic transport of navigation satellites Journal Article
In: Chaos, vol. 29, pp. 1-8, 2019.
@article{Gkolias2019article,
title = {Chaotic transport of navigation satellites},
author = {Gkolias, I. and Daquin, J. and Skoulidou, D. K. and Tsiganis, K. and Efthymiopoulos, C.},
url = {https://doi.org/10.1063/1.5124682},
doi = {10.1063/1.5124682},
year = {2019},
date = {2019-01-01},
journal = {Chaos},
volume = {29},
pages = {1-8},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Gkolias, Ioannis; Colombo, Camilla
Towards a sustainable exploitation of the geosynchronous orbital region Journal Article
In: Celestial Mechanics and Dynamical Astronomy, vol. 131, pp. 19, 2019, ISBN: 1572-9478.
@article{Gkolias2019articleb,
title = {Towards a sustainable exploitation of the geosynchronous orbital region},
author = {Gkolias, Ioannis and Colombo, Camilla},
url = {https://doi.org/10.1007/s10569-019-9895-3},
doi = {10.1007/s10569-019-9895-3},
isbn = {1572-9478},
year = {2019},
date = {2019-01-01},
journal = {Celestial Mechanics and Dynamical Astronomy},
volume = {131},
pages = {19},
abstract = {In this work the orbital dynamics of Earth satellites about the geosynchronous altitude are explored, with primary goal to assess current mitigation guidelines as well as to discuss the future exploitation of the region. A thorough dynamical mapping was conducted in a high-definition grid of orbital elements, enabled by a fast and accurate semi-analytical propagator, which considers all the relevant perturbations. The results are presented in appropriately selected stability maps to highlight the underlying mechanisms and their interplay, which can lead to stable graveyard orbits or fast re-entry pathways. The natural separation of the long-term evolution between equatorial and inclined satellites is discussed in terms of post-mission disposal strategies. Moreover, we confirm the existence of an effective cleansing mechanism for inclined geosynchronous satellites and discuss its implications in terms of current guidelines as well as alternative mission designs that could lead to a sustainable use of the geosynchronous orbital region.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
In this work the orbital dynamics of Earth satellites about the geosynchronous altitude are explored, with primary goal to assess current mitigation guidelines as well as to discuss the future exploitation of the region. A thorough dynamical mapping was conducted in a high-definition grid of orbital elements, enabled by a fast and accurate semi-analytical propagator, which considers all the relevant perturbations. The results are presented in appropriately selected stability maps to highlight the underlying mechanisms and their interplay, which can lead to stable graveyard orbits or fast re-entry pathways. The natural separation of the long-term evolution between equatorial and inclined satellites is discussed in terms of post-mission disposal strategies. Moreover, we confirm the existence of an effective cleansing mechanism for inclined geosynchronous satellites and discuss its implications in terms of current guidelines as well as alternative mission designs that could lead to a sustainable use of the geosynchronous orbital region.
Gkolias, Ioannis; Efthymiopoulos, Christos; Celletti, Alessandra; Pucacco, Giuseppe
Accurate modelling of the low-order secondary resonances in the spin-orbit problem Journal Article
In: Communications in Nonlinear Science & Numerical Simulation, vol. 77, pp. 181-202, 2019.
@article{Gkolias2019articlec,
title = {Accurate modelling of the low-order secondary resonances in the spin-orbit problem},
author = {Gkolias, Ioannis and Efthymiopoulos, Christos and Celletti, Alessandra and Pucacco, Giuseppe},
url = {http://doi.org/10.1016/j.cnsns.2019.04.015},
doi = {http://dx.doi.org/10.1016/j.cnsns.2019.04.015},
year = {2019},
date = {2019-01-01},
journal = {Communications in Nonlinear Science & Numerical Simulation},
volume = {77},
pages = {181-202},
abstract = {We provide an analytical approximation to the dynamics in each of the three most important low order secondary resonances (1:1, 2:1, and 3:1) bifurcating from the synchronous primary resonance in the gravitational spin-orbit problem. To this end we extend the perturbative approach introduced in [10], based on normal form series computations. This allows to recover analytically all non-trivial features of the phase space topology and bifurcations associated with these resonances. Applications include the characterization of spin states of irregular planetary satellites or double systems of minor bodies with irregular shapes. The key ingredients of our method are: i) The use of a detuning parameter measuring the distance from the exact resonance, and ii) an efficient scheme to ‘book-keep’ the series terms, which allows to simultaneously treat all small parameters entering the problem. Explicit formulas are provided for each secondary resonance, yielding i) the time evolution of the spin state, ii) the form of phase portraits, iii) initial conditions and stability for periodic solutions, and iv) bifurcation diagrams associated with the periodic orbits. We give also error estimates of the method, based on analyzing the asymptotic behavior of the remainder of the normal form series.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
We provide an analytical approximation to the dynamics in each of the three most important low order secondary resonances (1:1, 2:1, and 3:1) bifurcating from the synchronous primary resonance in the gravitational spin-orbit problem. To this end we extend the perturbative approach introduced in [10], based on normal form series computations. This allows to recover analytically all non-trivial features of the phase space topology and bifurcations associated with these resonances. Applications include the characterization of spin states of irregular planetary satellites or double systems of minor bodies with irregular shapes. The key ingredients of our method are: i) The use of a detuning parameter measuring the distance from the exact resonance, and ii) an efficient scheme to ‘book-keep’ the series terms, which allows to simultaneously treat all small parameters entering the problem. Explicit formulas are provided for each secondary resonance, yielding i) the time evolution of the spin state, ii) the form of phase portraits, iii) initial conditions and stability for periodic solutions, and iv) bifurcation diagrams associated with the periodic orbits. We give also error estimates of the method, based on analyzing the asymptotic behavior of the remainder of the normal form series.
Alessi, Elisa Maria; Colombo, Camilla; Rossi, Alessandro
Phase space description of the dynamics due to the coupled effect of the planetary oblateness and the solar radiation pressure perturbations Journal Article
In: Celestial Mechanics and Dynamical Astronomy, vol. 131, pp. 43, 2019, ISBN: 1572-9478.
@article{Alessi2019article,
title = {Phase space description of the dynamics due to the coupled effect of the planetary oblateness and the solar radiation pressure perturbations},
author = {Alessi, Elisa Maria and Colombo, Camilla and Rossi, Alessandro},
url = {https://doi.org/10.1007/s10569-019-9919-z},
doi = {10.1007/s10569-019-9919-z},
isbn = {1572-9478},
year = {2019},
date = {2019-01-01},
journal = {Celestial Mechanics and Dynamical Astronomy},
volume = {131},
pages = {43},
abstract = {The aim of this work is to provide an analytical model to characterize the equilibrium points and the phase space associated with the singly averaged dynamics caused by the planetary oblateness coupled with the solar radiation pressure perturbations. A two-dimensional differential system is derived by considering the classical theory, supported by the existence of an integral of motion comprising semi-major axis, eccentricity and inclination. Under the single resonance hypothesis, the analytical expressions for the equilibrium points in the eccentricity-resonant angle space are provided, together with the corresponding linear stability. The Hamiltonian formulation is also given. The model is applied considering, as example, the Earth as major oblate body, and a simple tool to visualize the structure of the phase space is presented. Finally, some considerations on the possible use and development of the proposed model are drawn.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
The aim of this work is to provide an analytical model to characterize the equilibrium points and the phase space associated with the singly averaged dynamics caused by the planetary oblateness coupled with the solar radiation pressure perturbations. A two-dimensional differential system is derived by considering the classical theory, supported by the existence of an integral of motion comprising semi-major axis, eccentricity and inclination. Under the single resonance hypothesis, the analytical expressions for the equilibrium points in the eccentricity-resonant angle space are provided, together with the corresponding linear stability. The Hamiltonian formulation is also given. The model is applied considering, as example, the Earth as major oblate body, and a simple tool to visualize the structure of the phase space is presented. Finally, some considerations on the possible use and development of the proposed model are drawn.
Miguel, Narcís; Colombo, Camilla
Attitude and orbit coupling of planar helio-stable solar sails Journal Article
In: Celestial Mechanics and Dynamical Astronomy, vol. 131, pp. 59, 2019, ISBN: 1572-9478.
@article{Miguel2019article,
title = {Attitude and orbit coupling of planar helio-stable solar sails},
author = {Miguel, Narcís and Colombo, Camilla},
url = {https://doi.org/10.1007/s10569-019-9937-x},
doi = {10.1007/s10569-019-9937-x},
isbn = {1572-9478},
year = {2019},
date = {2019-01-01},
journal = {Celestial Mechanics and Dynamical Astronomy},
volume = {131},
pages = {59},
abstract = {The coupled attitude and orbit dynamics of solar sails is studied. The shape of the sail is a simplified quasi-rhombic pyramid that provides the structure helio-stability properties. After adimensionalization, the system is put in the form of a fast–slow dynamical system where the different timescales are explicitly related to the physical parameters of the system. The orientation of the body frame with respect to the inertial orbit frame is a fast phase that can be averaged out. This gives rise to a simplified formulation that only consists of the orbit dynamics perturbed by a flat sail with fixed attitude perpendicular to the direction of the sunlight. The results are exemplified using numerical simulations.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
The coupled attitude and orbit dynamics of solar sails is studied. The shape of the sail is a simplified quasi-rhombic pyramid that provides the structure helio-stability properties. After adimensionalization, the system is put in the form of a fast–slow dynamical system where the different timescales are explicitly related to the physical parameters of the system. The orientation of the body frame with respect to the inertial orbit frame is a fast phase that can be averaged out. This gives rise to a simplified formulation that only consists of the orbit dynamics perturbed by a flat sail with fixed attitude perpendicular to the direction of the sunlight. The results are exemplified using numerical simulations.
Farres, A.; Heiligers, J.; Miguel, N.
Road Map to L4/L5 with a Solar Sail Journal Article
In: Aerospace Science and Technology, vol. 95, pp. 1-16, 2019.
@article{Farres2019article,
title = {Road Map to L4/L5 with a Solar Sail},
author = {Farres, A. and Heiligers, J. and Miguel, N.},
url = {http://doi.org/10.1016/j.ast.2019.105458},
doi = {http://dx.doi.org/10.1016/j.ast.2019.105458},
year = {2019},
date = {2019-01-01},
journal = {Aerospace Science and Technology},
volume = {95},
pages = {1-16},
abstract = {This paper explores the capability of solar sails to transfer a probe from the displaced Sun-Earth L1 and L2 libration points to the region of practical stability (RPS) around the triangular equilibrium points L4 and L5. If the sailcraft arrives inside the RPS with zero synodical velocity, it will remain there with minor station keeping requirements. Moreover, the location of the RPS is ideal for space weather missions as the Sun can be observed from a different angle compared to spacecraft orbiting the L1 point. The unstable manifolds of the displaced L1 and L2 points come close to these regions providing opportunities for natural transfer trajectories. By varying the solar sail orientation along the manifold, the dynamics can be altered and simple transfer trajectories that reach the RPS with few sail maneuvers are enabled. However, these trajectories are not optimal from a transfer time perspective, but can serve as suitable initial guesses for a direct optimization method to find minimum-time transfers between the displaced L1 and L2 points and the RPS at L4 and L5.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
This paper explores the capability of solar sails to transfer a probe from the displaced Sun-Earth L1 and L2 libration points to the region of practical stability (RPS) around the triangular equilibrium points L4 and L5. If the sailcraft arrives inside the RPS with zero synodical velocity, it will remain there with minor station keeping requirements. Moreover, the location of the RPS is ideal for space weather missions as the Sun can be observed from a different angle compared to spacecraft orbiting the L1 point. The unstable manifolds of the displaced L1 and L2 points come close to these regions providing opportunities for natural transfer trajectories. By varying the solar sail orientation along the manifold, the dynamics can be altered and simple transfer trajectories that reach the RPS with few sail maneuvers are enabled. However, these trajectories are not optimal from a transfer time perspective, but can serve as suitable initial guesses for a direct optimization method to find minimum-time transfers between the displaced L1 and L2 points and the RPS at L4 and L5.
Gonzalo, Juan Luis; Bombardelli, Claudio
Multiple scales asymptotic solution for the constant radial thrust problem Journal Article
In: Celestial Mechanics and Dynamical Astronomy, vol. 131, pp. 37, 2019, ISBN: 1572-9478.
@article{Gonzalo2019article,
title = {Multiple scales asymptotic solution for the constant radial thrust problem},
author = {Gonzalo, Juan Luis and Bombardelli, Claudio},
url = {https://doi.org/10.1007/s10569-019-9915-3},
doi = {10.1007/s10569-019-9915-3},
isbn = {1572-9478},
year = {2019},
date = {2019-01-01},
journal = {Celestial Mechanics and Dynamical Astronomy},
volume = {131},
pages = {37},
abstract = {An approximate analytical solution for the two-body problem perturbed by a radial, low acceleration is obtained, using a regularized formulation of the orbital motion and the method of multiple scales. Formulating the dynamics with the Dromo special perturbation method allows us to separate the two characteristic periods of the problem in a clear and physically significative way, namely the orbital period and a period depending on the magnitude of the perturbing acceleration. This second period becomes very large compared to the orbital one for low-thrust cases, allowing us to develop an accurate approximate analytical solution through the method of multiple scales. Compared to a regular expansion, the multiple scales solution retains the qualitative contributions of both characteristic periods and has a longer validity range in time. Looking at previous solutions for this problem, our approach has the advantage of not requiring the evaluation of special functions or an initially circular orbit. Furthermore, the simple expression reached for the long period provides additional insight into the problem. Finally, the behavior of the asymptotic solution is assessed through several test cases, finding a good agreement with high-precision numerical solutions. The results presented not only advance in the study of the two-body problem with constant radial thrust, but also confirm the utility of the method of multiple scales for tackling problems in orbital mechanics.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
An approximate analytical solution for the two-body problem perturbed by a radial, low acceleration is obtained, using a regularized formulation of the orbital motion and the method of multiple scales. Formulating the dynamics with the Dromo special perturbation method allows us to separate the two characteristic periods of the problem in a clear and physically significative way, namely the orbital period and a period depending on the magnitude of the perturbing acceleration. This second period becomes very large compared to the orbital one for low-thrust cases, allowing us to develop an accurate approximate analytical solution through the method of multiple scales. Compared to a regular expansion, the multiple scales solution retains the qualitative contributions of both characteristic periods and has a longer validity range in time. Looking at previous solutions for this problem, our approach has the advantage of not requiring the evaluation of special functions or an initially circular orbit. Furthermore, the simple expression reached for the long period provides additional insight into the problem. Finally, the behavior of the asymptotic solution is assessed through several test cases, finding a good agreement with high-precision numerical solutions. The results presented not only advance in the study of the two-body problem with constant radial thrust, but also confirm the utility of the method of multiple scales for tackling problems in orbital mechanics.
García-Pelayo, Ricardo; Gonzalo, Juan Luis; Bombardelli, Claudio
Rate and Collision Probability of Tethers and Sails Against Debris or Spacecraft Journal Article
In: Journal of Guidance, Control, and Dynamics, vol. 42, no. 6, pp. 1330-1342, 2019.
@article{García-Pelayo2019article,
title = {Rate and Collision Probability of Tethers and Sails Against Debris or Spacecraft},
author = {García-Pelayo, Ricardo and Gonzalo, Juan Luis and Bombardelli, Claudio},
url = {https://doi.org/10.2514/1.G003941},
doi = {10.2514/1.G003941},
year = {2019},
date = {2019-01-01},
journal = {Journal of Guidance, Control, and Dynamics},
volume = {42},
number = {6},
pages = {1330-1342},
abstract = {The work done on probability of collision between spherical objects in orbit is extended here to the case of one spherical object and one circular or rectangular object. The former is a model for spacecraft or debris, whereas the latter is a model for a sail or a tether. Two kinds of computations are done. The first kind is the computation of the collision rate when the flux of one object (typically debris) with respect to the other object is known. This information is important when planning a mission. The second kind is the computation of the collision probability for a particular pair of objects whose probability density functions of the positions are known. This information is necessary to decide whether an evasive maneuver will be performed or not.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
The work done on probability of collision between spherical objects in orbit is extended here to the case of one spherical object and one circular or rectangular object. The former is a model for spacecraft or debris, whereas the latter is a model for a sail or a tether. Two kinds of computations are done. The first kind is the computation of the collision rate when the flux of one object (typically debris) with respect to the other object is known. This information is important when planning a mission. The second kind is the computation of the collision probability for a particular pair of objects whose probability density functions of the positions are known. This information is necessary to decide whether an evasive maneuver will be performed or not.
Gonzalo, J. L.; Bombardelli, C.
Optimal constant-thrust radius change in circular orbit Journal Article
In: Journal of Guidance Control and Dynamics, vol. 42, pp. 1693-1708, 2019.
@article{Gonzalo2019articleb,
title = {Optimal constant-thrust radius change in circular orbit},
author = {Gonzalo, J. L. and Bombardelli, C.},
url = {https://doi.org/10.2514/1.G003134},
doi = {10.2514/1.G003134},
year = {2019},
date = {2019-01-01},
journal = {Journal of Guidance Control and Dynamics},
volume = {42},
pages = {1693-1708},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Maury, Thibaut; Loubet, Philippe; Trisolini, Mirko; Gallice, Aurélie; Sonnemann, Guido; Colombo, Camilla
Assessing the impact of space debris on orbital resource in life cycle assessment: A proposed method and case study Journal Article
In: Science of the Total Environment, vol. 667, pp. 780-791, 2019.
@article{Maury2019article,
title = {Assessing the impact of space debris on orbital resource in life cycle assessment: A proposed method and case study},
author = {Maury, Thibaut and Loubet, Philippe and Trisolini, Mirko and Gallice, Aurélie and Sonnemann, Guido and Colombo, Camilla},
url = {https://doi.org/10.1016/j.scitotenv.2019.02.438},
doi = {http://dx.doi.org/10.1016/j.scitotenv.2019.02.438},
year = {2019},
date = {2019-01-01},
journal = {Science of the Total Environment},
volume = {667},
pages = {780-791},
abstract = {The space sector is a new area of development for Life Cycle Assessment (LCA) studies. However, it deals with strong particularities which complicate the use of LCA. One of the most important is that the space industry is the only human activity crossing all stages of the atmosphere during the launch event or the atmospheric re-entry. As a result, interactions occur not only with the natural environment but also with the orbital environment during the use phase and the end-of-life of space missions. In this context, there is a lack of indicators and methods to characterise the complete life-cycle of space systems including their impact on the orbital environment. The end-of-life of spacecraft is of particular concern: space debris proliferation is today a concrete threat for all space activities. Therefore, the proposed work aims at characterising the orbital environment in term of space debris crossing the orbital resource. A complete methodology and a set of characterisation factors at midpoint level are provided. They are based on two factors: (i) the exposure to space debris in a given orbit and (ii) the severity of a potential spacecraft break-up leading to the release of new debris in the orbital environment. Then, we demonstrate the feasibility of such approach through three theoretical post-mission disposal scenarios based on the Sentinel-1A mission parameters. The results are discussed against the propellant consumption needed in each case with the purpose of addressing potential ‘burden shifting’ that could occur between the Earth environment and the orbital one.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
The space sector is a new area of development for Life Cycle Assessment (LCA) studies. However, it deals with strong particularities which complicate the use of LCA. One of the most important is that the space industry is the only human activity crossing all stages of the atmosphere during the launch event or the atmospheric re-entry. As a result, interactions occur not only with the natural environment but also with the orbital environment during the use phase and the end-of-life of space missions. In this context, there is a lack of indicators and methods to characterise the complete life-cycle of space systems including their impact on the orbital environment. The end-of-life of spacecraft is of particular concern: space debris proliferation is today a concrete threat for all space activities. Therefore, the proposed work aims at characterising the orbital environment in term of space debris crossing the orbital resource. A complete methodology and a set of characterisation factors at midpoint level are provided. They are based on two factors: (i) the exposure to space debris in a given orbit and (ii) the severity of a potential spacecraft break-up leading to the release of new debris in the orbital environment. Then, we demonstrate the feasibility of such approach through three theoretical post-mission disposal scenarios based on the Sentinel-1A mission parameters. The results are discussed against the propellant consumption needed in each case with the purpose of addressing potential ‘burden shifting’ that could occur between the Earth environment and the orbital one.
Nugnes, Marco; Colombo, Camilla; Tipaldi, Massimo
Coverage Area Determination for Conical Fields of View Considering an Oblate Earth Journal Article
In: Journal of Guidance, Control, and Dynamics, vol. 42, no. 10, pp. 2233-2245, 2019.
@article{Nugnes2019article,
title = {Coverage Area Determination for Conical Fields of View Considering an Oblate Earth},
author = {Nugnes, Marco and Colombo, Camilla and Tipaldi, Massimo},
url = {https://doi.org/10.2514/1.G004156},
doi = {10.2514/1.G004156},
year = {2019},
date = {2019-01-01},
journal = {Journal of Guidance, Control, and Dynamics},
volume = {42},
number = {10},
pages = {2233-2245},
abstract = {This paper introduces a new analytical method for the determination of the coverage area modeling the Earth as an oblate ellipsoid of rotation. Starting from the knowledge of the satellite’s position vector and the direction of the navigation antenna line of sight, the surface generated by the intersection of the oblate ellipsoid and the assumed conical field of view is decomposed in many ellipses, obtained by cutting the Earth’s surface with every plane containing the navigation antenna line of sight. The geometrical parameters of each ellipse can be derived analytically together with the points of intersection of the conical field of view with the ellipse itself by assuming a proper value of the half-aperture angle or the minimum elevation angle from which the satellite can be considered visible from the Earth’s surface. The method can be applied for different types of pointing (geocentric, geodetic, and generic) according to the mission requirements. Finally, numerical simulations compare the classical spherical approach with the new ellipsoidal method in the determination of the coverage area, and also show the dependence of the coverage errors on some relevant orbital parameters.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
This paper introduces a new analytical method for the determination of the coverage area modeling the Earth as an oblate ellipsoid of rotation. Starting from the knowledge of the satellite’s position vector and the direction of the navigation antenna line of sight, the surface generated by the intersection of the oblate ellipsoid and the assumed conical field of view is decomposed in many ellipses, obtained by cutting the Earth’s surface with every plane containing the navigation antenna line of sight. The geometrical parameters of each ellipse can be derived analytically together with the points of intersection of the conical field of view with the ellipse itself by assuming a proper value of the half-aperture angle or the minimum elevation angle from which the satellite can be considered visible from the Earth’s surface. The method can be applied for different types of pointing (geocentric, geodetic, and generic) according to the mission requirements. Finally, numerical simulations compare the classical spherical approach with the new ellipsoidal method in the determination of the coverage area, and also show the dependence of the coverage errors on some relevant orbital parameters.
2018
Daquin, Jérôme; Gkolias, Ioannis; Rosengren, Aaron J.
Drift and Its Mediation in Terrestrial Orbits Journal Article
In: Frontiers in Applied Mathematics and Statistics, vol. 4, pp. 1-14, 2018.
@article{Daquin2018article,
title = {Drift and Its Mediation in Terrestrial Orbits},
author = {Daquin, Jérôme and Gkolias, Ioannis and Rosengren, Aaron J.},
url = {https://doi.org/10.3389/fams.2018.00035},
doi = {http://dx.doi.org/10.3389/fams.2018.00035},
year = {2018},
date = {2018-01-01},
journal = {Frontiers in Applied Mathematics and Statistics},
volume = {4},
pages = {1-14},
abstract = {The slow deformation of terrestrial orbits in the medium range, subject to lunisolar resonances, is well approximated by a family of Hamiltonian flow with 2.5 degree-of-freedom. The action variables of the system may experience chaotic variations and large drift that we may quantify. Using variational chaos indicators, we compute high-resolution portraits of the action space. Such refined meshes allow to reveal the existence of tori and structures filling chaotic regions. Our elaborate computations allow us to isolate precise initial conditions near specific zones of interest and study their asymptotic behaviour in time. Borrowing classical techniques of phase-space visualization, we highlight how the drift is mediated by the complement of the numerically detected KAM tori.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
The slow deformation of terrestrial orbits in the medium range, subject to lunisolar resonances, is well approximated by a family of Hamiltonian flow with 2.5 degree-of-freedom. The action variables of the system may experience chaotic variations and large drift that we may quantify. Using variational chaos indicators, we compute high-resolution portraits of the action space. Such refined meshes allow to reveal the existence of tori and structures filling chaotic regions. Our elaborate computations allow us to isolate precise initial conditions near specific zones of interest and study their asymptotic behaviour in time. Borrowing classical techniques of phase-space visualization, we highlight how the drift is mediated by the complement of the numerically detected KAM tori.
Rossi, Alessandro; Colombo, Camilla; Tsiganis, Kleomenis; Beck, James; Rodriguez, Jonathan; Walker, Scott; Letterio, Federico; Dalla Vedova, Florio; Schaus, Volker; Popova, Rada; Francesconi, Alessandro; Stokes, Hedley; Schleutker, Thorn; Alessi, Elisa; Schettino, Giulia; Gkolias, Ioannis; Skoulidou, Despoina; Holbrough, Ian; Bernelli Zazzera, Franco; Stoll, Enrico; Kim, Youngkyu
ReDSHIFT: A Global Approach to Space Debris Mitigation Journal Article
In: Aerospace, vol. 5, pp. 1-15, 2018.
@article{Rossi2018article,
title = {ReDSHIFT: A Global Approach to Space Debris Mitigation},
author = {Rossi, Alessandro and Colombo, Camilla and Tsiganis, Kleomenis and Beck, James and Rodriguez, Jonathan and Walker, Scott and Letterio, Federico and Dalla Vedova, Florio and Schaus, Volker and Popova, Rada and Francesconi, Alessandro and Stokes, Hedley and Schleutker, Thorn and Alessi, Elisa and Schettino, Giulia and Gkolias, Ioannis and Skoulidou, Despoina and Holbrough, Ian and Bernelli Zazzera, Franco and Stoll, Enrico and Kim, Youngkyu},
url = {https://doi.org/10.3390/aerospace5020064},
doi = {10.3390/aerospace5020064},
year = {2018},
date = {2018-01-01},
journal = {Aerospace},
volume = {5},
pages = {1-15},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Trisolini, Mirko; Lewis, Hugh G.; Colombo, Camilla
Spacecraft design optimisation for demise and survivability Journal Article
In: Aerospace Science and Technology, vol. 77, pp. 638-657, 2018.
@article{Trisolini2018article,
title = {Spacecraft design optimisation for demise and survivability},
author = {Trisolini, Mirko and Lewis, Hugh G. and Colombo, Camilla},
url = {https://doi.org/10.1016/j.ast.2018.04.006},
doi = {http://dx.doi.org/10.1016/j.ast.2018.04.006},
year = {2018},
date = {2018-01-01},
journal = {Aerospace Science and Technology},
volume = {77},
pages = {638-657},
abstract = {Among the mitigation measures introduced to cope with the space debris issue there is the de-orbiting of decommissioned satellites. Guidelines for re-entering objects call for a ground casualty risk no higher than 10−4. To comply with this requirement, satellites can be designed through a design-for-demise philosophy. Still, a spacecraft designed to demise through the atmosphere has to survive the debris-populated space environment for many years. The demisability and the survivability of a satellite can both be influenced by a set of common design choices such as the material selection, the geometry definition, and the position of the components inside the spacecraft. Within this context, two models have been developed to analyse the demise and the survivability of satellites. Given the competing nature of the demisability and the survivability requirements, a multi-objective optimisation framework was developed, with the aim to identify trade-off solutions for the preliminary design of satellites. As the problem is nonlinear and involves the combination of continuous and discrete variables, classical derivative based approaches are unsuited and a genetic algorithm was selected instead. The genetic algorithm uses the developed demisability and survivability criteria as the fitness functions of the multi-objective algorithm. The paper presents a test case, which considers the preliminary optimisation of tanks in terms of material, geometry, location, and number of tanks for a representative Earth observation mission. The configuration of the external structure of the spacecraft is fixed. Tanks were selected because they are sensitive to both design requirements: they represent critical components in the demise process and impact damage can cause the loss of the mission because of leaking and ruptures. The results present the possible trade off solutions, constituting the Pareto front obtained from the multi-objective optimisation.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Among the mitigation measures introduced to cope with the space debris issue there is the de-orbiting of decommissioned satellites. Guidelines for re-entering objects call for a ground casualty risk no higher than 10−4. To comply with this requirement, satellites can be designed through a design-for-demise philosophy. Still, a spacecraft designed to demise through the atmosphere has to survive the debris-populated space environment for many years. The demisability and the survivability of a satellite can both be influenced by a set of common design choices such as the material selection, the geometry definition, and the position of the components inside the spacecraft. Within this context, two models have been developed to analyse the demise and the survivability of satellites. Given the competing nature of the demisability and the survivability requirements, a multi-objective optimisation framework was developed, with the aim to identify trade-off solutions for the preliminary design of satellites. As the problem is nonlinear and involves the combination of continuous and discrete variables, classical derivative based approaches are unsuited and a genetic algorithm was selected instead. The genetic algorithm uses the developed demisability and survivability criteria as the fitness functions of the multi-objective algorithm. The paper presents a test case, which considers the preliminary optimisation of tanks in terms of material, geometry, location, and number of tanks for a representative Earth observation mission. The configuration of the external structure of the spacecraft is fixed. Tanks were selected because they are sensitive to both design requirements: they represent critical components in the demise process and impact damage can cause the loss of the mission because of leaking and ruptures. The results present the possible trade off solutions, constituting the Pareto front obtained from the multi-objective optimisation.
Trisolini, Mirko; Lewis, Hugh G.; Colombo, Camilla
Demisability and survivability sensitivity to design-for-demise techniques Journal Article
In: Acta Astronautica, vol. 145, pp. 357-384, 2018.
@article{Trisolini2018articleb,
title = {Demisability and survivability sensitivity to design-for-demise techniques},
author = {Trisolini, Mirko and Lewis, Hugh G. and Colombo, Camilla},
url = {https://doi.org/10.1016/j.actaastro.2018.01.050},
doi = {http://dx.doi.org/10.1016/j.actaastro.2018.01.050},
year = {2018},
date = {2018-01-01},
journal = {Acta Astronautica},
volume = {145},
pages = {357-384},
abstract = {The paper is concerned with examining the effects that design-for-demise solutions can have not only on the demisability of components, but also on their survivability that is their capability to withstand impacts from space debris. First two models are introduced. A demisability model to predict the behaviour of spacecraft components during the atmospheric re-entry and a survivability model to assess the vulnerability of spacecraft structures against space debris impacts. Two indices that evaluate the level of demisability and survivability are also proposed. The two models are then used to study the sensitivity of the demisability and of the survivability indices as a function of typical design-for-demise options. The demisability and the survivability can in fact be influenced by the same design parameters in a competing fashion that is while the demisability is improved, the survivability is worsened and vice versa. The analysis shows how the design-for-demise solutions influence the demisability and the survivability independently. In addition, the effect that a solution has simultaneously on the two criteria is assessed. Results shows which, among the design-for-demise parameters mostly influence the demisability and the survivability. For such design parameters maps are presented, describing their influence on the demisability and survivability indices. These maps represent a useful tool to quickly assess the level of demisability and survivability that can be expected from a component, when specific design parameters are changed.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
The paper is concerned with examining the effects that design-for-demise solutions can have not only on the demisability of components, but also on their survivability that is their capability to withstand impacts from space debris. First two models are introduced. A demisability model to predict the behaviour of spacecraft components during the atmospheric re-entry and a survivability model to assess the vulnerability of spacecraft structures against space debris impacts. Two indices that evaluate the level of demisability and survivability are also proposed. The two models are then used to study the sensitivity of the demisability and of the survivability indices as a function of typical design-for-demise options. The demisability and the survivability can in fact be influenced by the same design parameters in a competing fashion that is while the demisability is improved, the survivability is worsened and vice versa. The analysis shows how the design-for-demise solutions influence the demisability and the survivability independently. In addition, the effect that a solution has simultaneously on the two criteria is assessed. Results shows which, among the design-for-demise parameters mostly influence the demisability and the survivability. For such design parameters maps are presented, describing their influence on the demisability and survivability indices. These maps represent a useful tool to quickly assess the level of demisability and survivability that can be expected from a component, when specific design parameters are changed.
Hou, Z.; Geng, Y.; Huang, S.
Minimum Residual Vibrations for Flexible Satellites with Frequency Uncertainty Journal Article
In: IEEE Transactions On Aerospace and Electronic Systems, vol. 54, pp. 1029-1038, 2018.
@article{Hou2018article,
title = {Minimum Residual Vibrations for Flexible Satellites with Frequency Uncertainty},
author = {Hou, Z. and Geng, Y. and Huang, S.},
url = {https://doi.org/10.1109/TAES.2017.2773321},
doi = {10.1109/TAES.2017.2773321},
year = {2018},
date = {2018-01-01},
journal = {IEEE Transactions On Aerospace and Electronic Systems},
volume = {54},
pages = {1029-1038},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
Hou, Z.; Geng, Y.; Wu, B.; Huang, S.
Spacecraft angular velocity trajectory planning for SGCMG singularity avoidance Journal Article
In: Acta Astronautica, vol. 151, pp. 284-295, 2018.
@article{Hou2018articleb,
title = {Spacecraft angular velocity trajectory planning for SGCMG singularity avoidance},
author = {Hou, Z. and Geng, Y. and Wu, B. and Huang, S.},
url = {https://doi.org/10.1016/j.actaastro.2018.06.008},
doi = {http://dx.doi.org/10.1016/j.actaastro.2018.06.008},
year = {2018},
date = {2018-01-01},
journal = {Acta Astronautica},
volume = {151},
pages = {284-295},
abstract = {A trajectory planning method for angular velocity of spacecraft is developed to avoid the impassable singular states for singular gimbal control moment gyroscope (SGCMG) systems in this paper. A new set of attitude parameters, named σ-parameters, is first developed. Based on the properties of σ-parameters, two approximate decoupled rotations are presented. To achieve a rapid attitude maneuver, both of the decoupled motions are designed as simple bang-off-bang type maneuvers. Then, a type of SGCMG singularity-free angular velocity trajectory on the conic surface is developed. Thereafter, an attitude controller based on σ-parameters is developed to track the reference trajectory. To avoid the impassable singular state, suitable axes of the approximate decoupled two rotations are chosen to achieve the fastest maneuver under the condition that the minimum distance from the angular momentum trajectory to the impassable surface is greater than a safety distance. Finally, simulations are performed to verify the effectiveness of the proposed SGCMG singularity avoidance method.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
A trajectory planning method for angular velocity of spacecraft is developed to avoid the impassable singular states for singular gimbal control moment gyroscope (SGCMG) systems in this paper. A new set of attitude parameters, named σ-parameters, is first developed. Based on the properties of σ-parameters, two approximate decoupled rotations are presented. To achieve a rapid attitude maneuver, both of the decoupled motions are designed as simple bang-off-bang type maneuvers. Then, a type of SGCMG singularity-free angular velocity trajectory on the conic surface is developed. Thereafter, an attitude controller based on σ-parameters is developed to track the reference trajectory. To avoid the impassable singular state, suitable axes of the approximate decoupled two rotations are chosen to achieve the fastest maneuver under the condition that the minimum distance from the angular momentum trajectory to the impassable surface is greater than a safety distance. Finally, simulations are performed to verify the effectiveness of the proposed SGCMG singularity avoidance method.
2017
Frey, S.; Lemmens, S.
Status of the Space Environment: Current Level of Adherence to the Space Debris Mitigation Policy Journal Article
In: Journal of the British Interplanetary Society, vol. 70, pp. 118-124, 2017.
@article{Frey2017article,
title = {Status of the Space Environment: Current Level of Adherence to the Space Debris Mitigation Policy},
author = {Frey, S. and Lemmens, S.},
url = {http://www.jbis.org.uk/paper.php?p=2017.70.118},
year = {2017},
date = {2017-01-01},
journal = {Journal of the British Interplanetary Society},
volume = {70},
pages = {118-124},
abstract = {To counter an ever increasing number of man-made objects orbiting Earth which are endangering current and future space missions, the Space Debris Mitigation (SDM) guidelines, issued by the Inter-Agency Space Debris Coordination Committee (IADC), were first published in 2002. These guidelines were a model for various international and national standardisation and regulation activities on SDM. One part of the research conducted at the Space Debris Office at the European Space Operations Centre (ESOC) is to study and monitor the level of implementation of these guidelines. This report summarises the status of the near Earth space environment by illustrating the number of objects orbiting Earth. The current and historical environment is assessed, with a focus on the interference of the IADC protected regions, the Low Earth Orbit (LEO) and the Geostationary Orbit (GEO). It includes an estimate of the evolution of the collision risk of payloads and rocket bodies with space debris, computed with ESA's Meteoroid and Space Debris Terrestrial Environment Reference (MASTER) tool. And it illustrates the current level of adherence to the SDM guidelines in terms of end-of-life operations and the release of mission related objects.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
To counter an ever increasing number of man-made objects orbiting Earth which are endangering current and future space missions, the Space Debris Mitigation (SDM) guidelines, issued by the Inter-Agency Space Debris Coordination Committee (IADC), were first published in 2002. These guidelines were a model for various international and national standardisation and regulation activities on SDM. One part of the research conducted at the Space Debris Office at the European Space Operations Centre (ESOC) is to study and monitor the level of implementation of these guidelines. This report summarises the status of the near Earth space environment by illustrating the number of objects orbiting Earth. The current and historical environment is assessed, with a focus on the interference of the IADC protected regions, the Low Earth Orbit (LEO) and the Geostationary Orbit (GEO). It includes an estimate of the evolution of the collision risk of payloads and rocket bodies with space debris, computed with ESA's Meteoroid and Space Debris Terrestrial Environment Reference (MASTER) tool. And it illustrates the current level of adherence to the SDM guidelines in terms of end-of-life operations and the release of mission related objects.
Frey, Stefan; Lemmens, Stijn; Bastida Virgili, Benjamin; Flohrer, Tim; Gass, Volker
Impact of End-of-Life manoeuvres on the collision risk in protected regions Journal Article
In: Acta Astronautica, vol. 138, pp. 417-422, 2017.
@article{Frey2017articleb,
title = {Impact of End-of-Life manoeuvres on the collision risk in protected regions},
author = {Frey, Stefan and Lemmens, Stijn and Bastida Virgili, Benjamin and Flohrer, Tim and Gass, Volker},
url = {https://doi.org/10.1016/j.actaastro.2017.06.012},
doi = {http://dx.doi.org/10.1016/j.actaastro.2017.06.012},
year = {2017},
date = {2017-01-01},
journal = {Acta Astronautica},
volume = {138},
pages = {417-422},
abstract = {The Inter-Agency Space Debris Coordination Committee (IADC) Space Debris Mitigation Guidelines, issued in 2002 and revised in 2007, address the post mission disposal of objects in orbit. After their mission, objects crossing the Low Earth Orbit (LEO) should have a remaining lifetime in orbit not exceeding 25 years. Objects near the Geostationary Orbit (GEO) region should be placed in an orbit that remains outside of the GEO protected region. In this paper, the impact of satellites and rocket bodies performing End-of-Life (EOL) orbital manoeuvres on the collision risk in the LEO and GEO protected regions is investigated. The cases of full or partial compliance with the IADC post mission disposal guideline are studied. ESA's Meteoroid and Space Debris Terrestrial Environment Reference (MASTER) model is used to compare the space debris flux rate of the object during the remaining lifetime estimated for the pre-EOL-manoeuvre and for the post-EOL-manoeuvre orbit. The study shows that, on average, the probability of collision can be significantly decreased by performing an EOL-manoeuver.},
keywords = {},
pubstate = {published},
tppubtype = {article}
}
The Inter-Agency Space Debris Coordination Committee (IADC) Space Debris Mitigation Guidelines, issued in 2002 and revised in 2007, address the post mission disposal of objects in orbit. After their mission, objects crossing the Low Earth Orbit (LEO) should have a remaining lifetime in orbit not exceeding 25 years. Objects near the Geostationary Orbit (GEO) region should be placed in an orbit that remains outside of the GEO protected region. In this paper, the impact of satellites and rocket bodies performing End-of-Life (EOL) orbital manoeuvres on the collision risk in the LEO and GEO protected regions is investigated. The cases of full or partial compliance with the IADC post mission disposal guideline are studied. ESA's Meteoroid and Space Debris Terrestrial Environment Reference (MASTER) model is used to compare the space debris flux rate of the object during the remaining lifetime estimated for the pre-EOL-manoeuvre and for the post-EOL-manoeuvre orbit. The study shows that, on average, the probability of collision can be significantly decreased by performing an EOL-manoeuver.
Inproceedings
2021
Olivieri, L.; Giacomuzzo, C.; Duran, C.; Giudici, L.; Colombo, C.; Francesconi, A.
Investigation of ENVISAT Catastrophic Fragmentation Scenarios Inproceedings
In: 72nd International Astronautical Congress (IAC 2021), pp. 1-13, Dubai, United Arab Emirates, 2021.
@inproceedings{Olivieri2021inproceedings,
title = {Investigation of ENVISAT Catastrophic Fragmentation Scenarios},
author = {Olivieri, L. and Giacomuzzo, C. and Duran, C. and Giudici, L. and Colombo, C. and Francesconi, A.},
url = {http://hdl.handle.net/11311/1190342},
year = {2021},
date = {2021-10-01},
booktitle = {72nd International Astronautical Congress (IAC 2021)},
volume = {IAC-21-A6},
pages = {1-13},
address = {Dubai, United Arab Emirates},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Giudici, L.; Colombo, C.
Keplerian Map Theory for High-Fidelity Prediction of the Third-Body Perturbative Effect Inproceedings
In: 72nd International Astronautical Congress (IAC 2021), pp. 1-10, Dubai, United Arab Emirates, 2021.
@inproceedings{Giudici2021inproceedings,
title = {Keplerian Map Theory for High-Fidelity Prediction of the Third-Body Perturbative Effect},
author = {Giudici, L. and Colombo, C.},
url = {http://hdl.handle.net/11311/1190341},
year = {2021},
date = {2021-10-01},
booktitle = {72nd International Astronautical Congress (IAC 2021)},
volume = {IAC-21-C1},
pages = {1-10},
address = {Dubai, United Arab Emirates},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Muciaccia, A.; Romano, M.; Colombo, C.
Detection and Characterisation of In-Orbit Fragmentations over Short and Long Periods of Time Inproceedings
In: 72nd International Astronautical Congress (IAC 2021), pp. 1-11, Dubai, United Arab Emirates, 2021.
@inproceedings{Muciaccia2021inproceedingsb,
title = {Detection and Characterisation of In-Orbit Fragmentations over Short and Long Periods of Time},
author = {Muciaccia, A. and Romano, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1191258},
year = {2021},
date = {2021-10-01},
booktitle = {72nd International Astronautical Congress (IAC 2021)},
volume = {IAC-21,A6,9,9,x66214},
pages = {1-11},
address = {Dubai, United Arab Emirates},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Colombo, C.; Trisolini, M.; Gonzalo, J. L.; Giudici, L.; Frey, S.; Kerr, E.; Sánchez-Ortiz, N.; Del Campo, B.; Letizia, F.; Lemmens, S.
Assessing the Impact of a Space Mission on the Sustainability of the Space Environment Inproceedings
In: 72nd International Astronautical Congress (IAC 2021), pp. 1-10, Dubai, United Arab Emirates, 2021.
@inproceedings{Colombo2021inproceedingsb,
title = {Assessing the Impact of a Space Mission on the Sustainability of the Space Environment},
author = {Colombo, C. and Trisolini, M. and Gonzalo, J. L. and Giudici, L. and Frey, S. and Kerr, E. and Sánchez-Ortiz, N. and Del Campo, B. and Letizia, F. and Lemmens, S.},
url = {http://hdl.handle.net/11311/1191257},
year = {2021},
date = {2021-10-01},
booktitle = {72nd International Astronautical Congress (IAC 2021)},
volume = {IAC-21,A6,2,6,x66244},
pages = {1-10},
address = {Dubai, United Arab Emirates},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Gonzalo, J. L.; Colombo, C.; Di Lizia, P.
Computationally Efficient Approaches for Low-Thrust Collision Avoidance Activities Inproceedings
In: 72nd International Astronautical Congress (IAC 2021), pp. 1-10, Dubai, United Arab Emirates, 2021.
@inproceedings{Gonzalo2021inproceedingsc,
title = {Computationally Efficient Approaches for Low-Thrust Collision Avoidance Activities},
author = {Gonzalo, J. L. and Colombo, C. and Di Lizia, P.},
url = {http://hdl.handle.net/11311/1191256},
year = {2021},
date = {2021-10-01},
booktitle = {72nd International Astronautical Congress (IAC 2021)},
volume = {IAC-21,A6,10-B6},
pages = {1-10},
address = {Dubai, United Arab Emirates},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Trisolini, M.; Colombo, C.; Tsuda, Y.
Ejecta Dynamics Around Asteroids in View of In-Orbit Particle Collection Missions Inproceedings
In: 72nd International Astronautical Congress (IAC 2021), pp. 1-10, Dubai, United Arab Emirates, 2021.
@inproceedings{Trisolini2021inproceedings,
title = {Ejecta Dynamics Around Asteroids in View of In-Orbit Particle Collection Missions},
author = {Trisolini, M. and Colombo, C. and Tsuda, Y.},
url = {http://hdl.handle.net/11311/1189549},
year = {2021},
date = {2021-10-01},
booktitle = {72nd International Astronautical Congress (IAC 2021)},
volume = {IAC-21-C1},
pages = {1-10},
address = {Dubai, United Arab Emirates},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Trozzi, V.; Colombo, C.; Trisolini, M.
Analysis of Possible Definitions of the Space Environment Capacity to Pursue Long-Term Sustainability of Space Activities Inproceedings
In: 72nd International Astronautical Congress (IAC 2021), pp. 1-14, Dubai, United Arab Emirates, 2021.
@inproceedings{Trozzi2021inproceedings,
title = {Analysis of Possible Definitions of the Space Environment Capacity to Pursue Long-Term Sustainability of Space Activities},
author = {Trozzi, V. and Colombo, C. and Trisolini, M.},
url = {http://hdl.handle.net/11311/1189586},
year = {2021},
date = {2021-10-01},
booktitle = {72nd International Astronautical Congress (IAC 2021)},
volume = {IAC-21,A6,IP,22,x66198},
pages = {1-14},
address = {Dubai, United Arab Emirates},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Brenna, M. P.; Colombo, C.; Scala, F.; Trisolini, M.
CubeSat Mission Concept for Environmental Analysis in Low Earth Orbit Inproceedings
In: 72nd International Astronautical Congress (IAC 2021), pp. 1-15, Dubai, United Arab Emirates, 2021.
@inproceedings{Brenna2021inproceedings,
title = {CubeSat Mission Concept for Environmental Analysis in Low Earth Orbit},
author = {Brenna, M. P. and Colombo, C. and Scala, F. and Trisolini, M.},
url = {http://hdl.handle.net/11311/1189550},
year = {2021},
date = {2021-10-01},
booktitle = {72nd International Astronautical Congress (IAC 2021)},
volume = {IAC-21-B4,2,7,x65474},
pages = {1-15},
address = {Dubai, United Arab Emirates},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Borelli, G.; Gaias, G.; Colombo, C.; Vallini, L.
Rendezvous and Proximity Operations Design of an Active Debris Removal Service to a Large Constellation Fleet Inproceedings
In: 72nd International Astronautical Congress (IAC 2021), pp. 1-13, Dubai, United Arab Emirates, 2021.
@inproceedings{Borelli2021inproceedingsb,
title = {Rendezvous and Proximity Operations Design of an Active Debris Removal Service to a Large Constellation Fleet},
author = {Borelli, G. and Gaias, G. and Colombo, C. and Vallini, L.},
url = {http://hdl.handle.net/11311/1189708},
year = {2021},
date = {2021-10-01},
booktitle = {72nd International Astronautical Congress (IAC 2021)},
volume = {IAC-21-A6},
pages = {1-13},
address = {Dubai, United Arab Emirates},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Zuliani, C.; Santoro, V.; Nugnes, M.; Colombo, C.
Social Benefits Assessment of Earth Observation Missions Through the SDG2030 Inproceedings
In: 72nd International Astronautical Congress (IAC 2021), pp. 1-20, Dubai, United Arab Emirates, 2021.
@inproceedings{Zuliani2021inproceedings,
title = {Social Benefits Assessment of Earth Observation Missions Through the SDG2030},
author = {Zuliani, C. and Santoro, V. and Nugnes, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1191240},
year = {2021},
date = {2021-10-01},
booktitle = {72nd International Astronautical Congress (IAC 2021)},
volume = {IAC-21,B1,5,3,x66303},
pages = {1-20},
address = {Dubai, United Arab Emirates},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Pavanello, Z.; Branz, F.; Francesconi, A.; Cenedese, A.; Antonello, R.; Basana, F.; Iob, P.; Vertuani, D.; Massari, M.; Colombo, C.; Lovera, M.; Invernizzi, D.; Ghignoni, P.; Ticozzi, L.; Borelli, G.; Opromolla, R.; Grassi, M.; Fasano, G.; Nocerino, A.; Lombardi, C.; Vela, C.; Huertas Garcia, I.; Simplicio, P.
Combined Control and Navigation Approach to the Robotic Capture of Space Vehicles Inproceedings
In: 72nd International Astronautical Congress (IAC 2021), pp. 1-13, Dubai, United Arab Emirates, 2021.
@inproceedings{Pavanello2021inproceedings,
title = {Combined Control and Navigation Approach to the Robotic Capture of Space Vehicles},
author = {Pavanello, Z. and Branz, F. and Francesconi, A. and Cenedese, A. and Antonello, R. and Basana, F. and Iob, P. and Vertuani, D. and Massari, M. and Colombo, C. and Lovera, M. and Invernizzi, D. and Ghignoni, P. and Ticozzi, L. and Borelli, G. and Opromolla, R. and Grassi, M. and Fasano, G. and Nocerino, A. and Lombardi, C. and Vela, C. and Huertas Garcia, I. and Simplicio, P.},
url = {http://hdl.handle.net/11311/1189477},
year = {2021},
date = {2021-10-01},
booktitle = {72nd International Astronautical Congress (IAC 2021)},
volume = {IAC-21,C1,1,6,x65166},
pages = {1-13},
address = {Dubai, United Arab Emirates},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Scala, F.; Colombo, C.; Martín-Neira, M.
Design of Natural Collision-Free Trajectories for the Mission Extension Phase of a Remote Sensing Formation Flying Mission Inproceedings
In: 72nd International Astronautical Congress (IAC 2021), pp. 1-11, Dubai, United Arab Emirates, 2021.
@inproceedings{Scala2021inproceedingsc,
title = {Design of Natural Collision-Free Trajectories for the Mission Extension Phase of a Remote Sensing Formation Flying Mission},
author = {Scala, F. and Colombo, C. and Martín-Neira, M.},
url = {http://hdl.handle.net/11311/1189478},
year = {2021},
date = {2021-10-01},
booktitle = {72nd International Astronautical Congress (IAC 2021)},
volume = {IAC-21,C1,1,5,x65552},
pages = {1-11},
address = {Dubai, United Arab Emirates},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Navarro, V.; Grieco, R.; Soja, B.; Nugnes, M.; Klopotek, G.; Tagliaferro, G.; See, L.; Falzarano, R.; Weinacker, R.; Ventura Traveset, J.
Data Fusion and Machine Learning for Innovative GNSS Science Use Cases Inproceedings
In: 34th International Technical Meeting of the Satellite Division of the Institute of Navigation (ION GNSS+ 2021), pp. 2656-2669, St. Louis, MO, USA, 2021.
@inproceedings{Navarro[10.33012/2021.18115]inproceedings,
title = {Data Fusion and Machine Learning for Innovative GNSS Science Use Cases},
author = {Navarro, V. and Grieco, R. and Soja, B. and Nugnes, M. and Klopotek, G. and Tagliaferro, G. and See, L. and Falzarano, R. and Weinacker, R. and Ventura Traveset, J.},
url = {https://doi.org/10.33012/2021.18115},
doi = {10.33012/2021.18115},
year = {2021},
date = {2021-09-20},
booktitle = {34th International Technical Meeting of the Satellite Division of the Institute of Navigation (ION GNSS+ 2021)},
pages = {2656-2669},
address = {St. Louis, MO, USA},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Campiti, G.; Masat, A.; Colombo, C.
Dynamic Programming Applied to Resonant Flyby Design Inproceedings
In: 2021 AAS/AIAA Astrodynamics Specialist Conference, pp. 1-19, Virtual Conference, 2021.
@inproceedings{Campiti2021inproceedings,
title = {Dynamic Programming Applied to Resonant Flyby Design},
author = {Campiti, G. and Masat, A. and Colombo, C.},
url = {http://hdl.handle.net/11311/1189604},
year = {2021},
date = {2021-08-01},
booktitle = {2021 AAS/AIAA Astrodynamics Specialist Conference},
volume = {AAS 21-725},
pages = {1-19},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Duran, C.; Giudici, L.; Colombo, C.
Modelling the Whole Space Debris Environment Through a Spatial Density Approach Inproceedings
In: 2021 AAS/AIAA Astrodynamics Specialist Conference, pp. 1-20, Virtual Conference, 2021.
@inproceedings{Duran2021inproceedings,
title = {Modelling the Whole Space Debris Environment Through a Spatial Density Approach},
author = {Duran, C. and Giudici, L. and Colombo, C.},
url = {http://hdl.handle.net/11311/1191122},
year = {2021},
date = {2021-08-01},
booktitle = {2021 AAS/AIAA Astrodynamics Specialist Conference},
volume = {AAS 21-712},
pages = {1-20},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Colombo, C.; Scala, F.; Trisolini, M.; Gonzalo, J. L.; Antonetti, S.; Di Tolle, F.; Radaelli, R.; Lisi, F.; Marrocchi, L.; Aliberti, M.; Francesconi, A.; Olivieri, L.; Tipaldi, M.
The Environmental CubeSat Mission E.Cube for Low Earth Orbit Data Acquisition Inproceedings
In: 26th Conference of the Italian Association of Aeronautics and Astronautics (AIDAA 2021), pp. 1-6, Online Event, 2021.
@inproceedings{Colombo2021inproceedings,
title = {The Environmental CubeSat Mission E.Cube for Low Earth Orbit Data Acquisition},
author = {Colombo, C. and Scala, F. and Trisolini, M. and Gonzalo, J. L. and Antonetti, S. and Di Tolle, F. and Radaelli, R. and Lisi, F. and Marrocchi, L. and Aliberti, M. and Francesconi, A. and Olivieri, L. and Tipaldi, M.},
url = {http://hdl.handle.net/11311/1186118},
year = {2021},
date = {2021-08-01},
booktitle = {26th Conference of the Italian Association of Aeronautics and Astronautics (AIDAA 2021)},
pages = {1-6},
address = {Online Event},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Opromolla, R.; Branz, F.; Francesconi, A.; Cenedese, A.; Antonello, R.; Iob, P.; Pavanello, Z.; Vertuani, D.; Grassi, M.; Fasano, G.; Nocerino, A.; Lombardi, C.; Vela, C.; Massari, M.; Colombo, C.; Lovera, M.; Invernizzi, D.; Ghignoni, P.; Ticozzi, L.; Borelli, G.; Huertas, I.; Simplicio, P.
Chaser-Robotic Arm Combined Control and Optical Relative Navigation for Space Target Capture Inproceedings
In: 26th Conference of the Italian Association of Aeronautics and Astronautics (AIDAA 2021), pp. 1-11, Online Event, 2021.
@inproceedings{Opromolla2021inproceedings,
title = {Chaser-Robotic Arm Combined Control and Optical Relative Navigation for Space Target Capture},
author = {Opromolla, R. and Branz, F. and Francesconi, A. and Cenedese, A. and Antonello, R. and Iob, P. and Pavanello, Z. and Vertuani, D. and Grassi, M. and Fasano, G. and Nocerino, A. and Lombardi, C. and Vela, C. and Massari, M. and Colombo, C. and Lovera, M. and Invernizzi, D. and Ghignoni, P. and Ticozzi, L. and Borelli, G. and Huertas, I. and Simplicio, P.},
url = {http://hdl.handle.net/11311/1186193},
year = {2021},
date = {2021-08-01},
booktitle = {26th Conference of the Italian Association of Aeronautics and Astronautics (AIDAA 2021)},
pages = {1-11},
address = {Online Event},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Gonzalo, J. L.; Colombo, C.
Lightweight Algorithms for Collision Avoidance Applications Inproceedings
In: 11th International ESA Conference on Guidance, Navigation & Control Systems, ESA GNC & ICATT 2021, pp. 1-15, Virtual Conference, 2021.
@inproceedings{Gonzalo2021inproceedingsb,
title = {Lightweight Algorithms for Collision Avoidance Applications},
author = {Gonzalo, J. L. and Colombo, C.},
url = {http://hdl.handle.net/11311/1181034},
year = {2021},
date = {2021-06-01},
booktitle = {11th International ESA Conference on Guidance, Navigation & Control Systems, ESA GNC & ICATT 2021},
pages = {1-15},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Romano, M.; Muciaccia, A.; Trisolini, M.; Di Lizia, P.; Colombo, C.; Di Cecco, A.; Salotti, L.
Characterising In-Orbit Fragmentations with the Puzzle Software Inproceedings
In: 11th International ESA Conference on Guidance, Navigation & Control Systems, ESA GNC & ICATT 2021, pp. 1-14, Virtual Conference, 2021.
@inproceedings{Romano2021inproceedings,
title = {Characterising In-Orbit Fragmentations with the Puzzle Software},
author = {Romano, M. and Muciaccia, A. and Trisolini, M. and Di Lizia, P. and Colombo, C. and Di Cecco, A. and Salotti, L.},
url = {http://hdl.handle.net/11311/1192036},
year = {2021},
date = {2021-06-01},
booktitle = {11th International ESA Conference on Guidance, Navigation & Control Systems, ESA GNC & ICATT 2021},
pages = {1-14},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Masat, A.; Romano, M.; Colombo, C.
Kustaanheimo-Stiefel Variables to Halve the Cost of Monte Carlo Planetary Protection Compliance Analysis Inproceedings
In: 11th International ESA Conference on Guidance, Navigation & Control Systems, ESA GNC & ICATT 2021, pp. 1-14, Virtual Conference, 2021.
@inproceedings{Masat2021inproceedings,
title = {Kustaanheimo-Stiefel Variables to Halve the Cost of Monte Carlo Planetary Protection Compliance Analysis},
author = {Masat, A. and Romano, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1183121},
year = {2021},
date = {2021-06-01},
booktitle = {11th International ESA Conference on Guidance, Navigation & Control Systems, ESA GNC & ICATT 2021},
pages = {1-14},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Muciaccia, A.; Romano, M.; Colombo, C.; Trisolini, M.
In-Orbit Fragmentations Localisation: Study and Characterisation of the Events Inproceedings
In: SpaceOps 2021 Virtual Edition, pp. 1-20, Cape Town, South Africa, 2021.
@inproceedings{Muciaccia2021inproceedings,
title = {In-Orbit Fragmentations Localisation: Study and Characterisation of the Events},
author = {Muciaccia, A. and Romano, M. and Colombo, C. and Trisolini, M.},
url = {http://hdl.handle.net/11311/1192038},
year = {2021},
date = {2021-05-01},
booktitle = {SpaceOps 2021 Virtual Edition},
volume = {SpaceOps-2021, 7, x1512},
pages = {1-20},
address = {Cape Town, South Africa},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Scala, F.; Trisolini, M.; Colombo, C.
Attitude Control of the Disposal Phase of the eCube Mission for Atmospheric Data Acquisition Inproceedings
In: SpaceOps 2021 Virtual Edition, pp. 1-17, Cape Town, South Africa, 2021.
@inproceedings{Scala2021inproceedings,
title = {Attitude Control of the Disposal Phase of the eCube Mission for Atmospheric Data Acquisition},
author = {Scala, F. and Trisolini, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1172793},
year = {2021},
date = {2021-05-01},
booktitle = {SpaceOps 2021 Virtual Edition},
volume = {SpaceOps-2021,7,x1504},
pages = {1-17},
address = {Cape Town, South Africa},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Scala, F.; Colombo, C.; Gaias, G. V. M.; Martin-Neira, M.
GNSS-based Navigation for a Remote Sensing Three-Satellite Formation Flying Inproceedings
In: SpaceOps 2021 Virtual Edition, pp. 1-18, Cape Town, South Africa, 2021.
@inproceedings{Scala2021inproceedingsb,
title = {GNSS-based Navigation for a Remote Sensing Three-Satellite Formation Flying},
author = {Scala, F. and Colombo, C. and Gaias, G. V. M. and Martin-Neira, M.},
url = {http://hdl.handle.net/11311/1172794},
year = {2021},
date = {2021-05-01},
booktitle = {SpaceOps 2021 Virtual Edition},
volume = {SpaceOps-2020,7,x1482},
pages = {1-18},
address = {Cape Town, South Africa},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Gonzalo, J. L.; Colombo, C.
On-Board Collision Avoidance Applications Based on Machine Learning and Analytical Methods Inproceedings
In: 8th European Conference on Space Debris, ESA/ESOC, pp. 1-6, Virtual Conference, 2021.
@inproceedings{Gonzalo2021inproceedings,
title = {On-Board Collision Avoidance Applications Based on Machine Learning and Analytical Methods},
author = {Gonzalo, J. L. and Colombo, C.},
url = {http://hdl.handle.net/11311/1173736},
year = {2021},
date = {2021-04-01},
booktitle = {8th European Conference on Space Debris, ESA/ESOC},
pages = {1-6},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Colombo, C.; Trisolini, M.; Scala, F.; Brenna, M. P.; Gonzalo, J. L.; Antonetti, S.; Di Tolle, F.; Redaelli, R.; Lisi, F.; Marrocchi, L.; Alberti, M.; Francesconi, A.; Olivieri, L.; Tipaldi, M.
e.Cube Mission: the Environmental CubeSat Inproceedings
In: 8th European Conference on Space Debris, ESA/ESOC, pp. 1-9, Virtual Conference, 2021.
@inproceedings{Colombo2021inproceedingsc,
title = {e.Cube Mission: the Environmental CubeSat},
author = {Colombo, C. and Trisolini, M. and Scala, F. and Brenna, M. P. and Gonzalo, J. L. and Antonetti, S. and Di Tolle, F. and Redaelli, R. and Lisi, F. and Marrocchi, L. and Alberti, M. and Francesconi, A. and Olivieri, L. and Tipaldi, M.},
url = {http://hdl.handle.net/11311/1173740},
year = {2021},
date = {2021-04-01},
booktitle = {8th European Conference on Space Debris, ESA/ESOC},
pages = {1-9},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Colombo, C.; Huang, S.; Borelli, G.; Cavenago, F.; Nugnes, M.; Gonzalo, J. L.; Gaias, G.; Massari, M.; Vallini, L.; Petit, M.; Guerrieri, P.; Valli, M.; Antonetti, S.
Mission Analysis and Design for an Active Debris Removal Service for Large Constellations Inproceedings
In: 8th European Conference on Space Debris, ESA/ESOC, pp. 1-11, Virtual Conference, 2021.
@inproceedings{Colombo2021inproceedingsd,
title = {Mission Analysis and Design for an Active Debris Removal Service for Large Constellations},
author = {Colombo, C. and Huang, S. and Borelli, G. and Cavenago, F. and Nugnes, M. and Gonzalo, J. L. and Gaias, G. and Massari, M. and Vallini, L. and Petit, M. and Guerrieri, P. and Valli, M. and Antonetti, S.},
url = {http://hdl.handle.net/11311/1173735},
year = {2021},
date = {2021-04-01},
booktitle = {8th European Conference on Space Debris, ESA/ESOC},
pages = {1-11},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Colombo, C.; Trisolini, M.; Gonzalo, J. L.; Giudici, L; Frey, S.; Sánchez Ortiz, N.; Kerr, E.; Letizia, F.; Lemmens, S.
Design of a Software to Assess the Impact of a Space Mission on the Space Environment Inproceedings
In: 8th European Conference on Space Debris, ESA/ESOC, pp. 1-10, Virtual Conference, 2021.
@inproceedings{Colombo2021inproceedingse,
title = {Design of a Software to Assess the Impact of a Space Mission on the Space Environment},
author = {Colombo, C. and Trisolini, M. and Gonzalo, J. L. and Giudici, L and Frey, S. and Sánchez Ortiz, N. and Kerr, E. and Letizia, F. and Lemmens, S.},
url = {http://hdl.handle.net/11311/1173725},
year = {2021},
date = {2021-04-01},
booktitle = {8th European Conference on Space Debris, ESA/ESOC},
pages = {1-10},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Trisolini, M.; Colombo, C.
Integrating Density-Based Uncertainty Propagation with Object-Oriented Re-Entry Models Inproceedings
In: 8th European Conference on Space Debris, ESA/ESOC, pp. 1-10, Virtual Conference, 2021.
@inproceedings{Trisolini2021inproceedingsb,
title = {Integrating Density-Based Uncertainty Propagation with Object-Oriented Re-Entry Models},
author = {Trisolini, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1171672},
year = {2021},
date = {2021-04-01},
booktitle = {8th European Conference on Space Debris, ESA/ESOC},
pages = {1-10},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Borelli, G.; Trisolini, M.; Massari, M.; Colombo, C.
A Comprehensive Ranking Framework for Active Debris Removal Missions Candidates Inproceedings
In: 8th European Conference on Space Debris, ESA/ESOC, pp. 1-10, Virtual Conference, 2021.
@inproceedings{Borelli2021inproceedings,
title = {A Comprehensive Ranking Framework for Active Debris Removal Missions Candidates},
author = {Borelli, G. and Trisolini, M. and Massari, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1173681},
year = {2021},
date = {2021-04-01},
booktitle = {8th European Conference on Space Debris, ESA/ESOC},
pages = {1-10},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Romano, M.; Muciaccia, A.; Trisolini, M.; Colombo, C.; Di Lizia, P.; Di Cecco, A.; Salotti, L.
PUZZLE Software for the Characterisation of In-Orbit Fragmentations Inproceedings
In: 8th European Conference on Space Debris, ESA/ESOC, pp. 1-14, Virtual Conference, 2021.
@inproceedings{Romano2021inproceedingsb,
title = {PUZZLE Software for the Characterisation of In-Orbit Fragmentations},
author = {Romano, M. and Muciaccia, A. and Trisolini, M. and Colombo, C. and Di Lizia, P. and Di Cecco, A. and Salotti, L.},
url = {http://hdl.handle.net/11311/1173713},
year = {2021},
date = {2021-04-01},
booktitle = {8th European Conference on Space Debris, ESA/ESOC},
pages = {1-14},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Masat, A.; Romano, M.; Colombo, C.
Combined B-Plane and Picard-Chebyshev Approach for the Continuous Design of Perturbed Interplanetary Resonant Trajectories Inproceedings
In: 31st AAS/AIAA Space Flight Mechanics Meeting, pp. 1-20, Virtual Conference, 2021.
@inproceedings{Masat2021inproceedingsb,
title = {Combined B-Plane and Picard-Chebyshev Approach for the Continuous Design of Perturbed Interplanetary Resonant Trajectories},
author = {Masat, A. and Romano, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1189603},
year = {2021},
date = {2021-02-01},
booktitle = {31st AAS/AIAA Space Flight Mechanics Meeting},
volume = {AAS 21-289},
pages = {1-20},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Nugnes, M.; Colombo, C.
In: 31st AAS/AIAA Space Flight Mechanics Meeting, pp. 1-16, Virtual Conference, 2021.
@inproceedings{Nugnes2021inproceedings,
title = {A New Methodology for the Solution of the Stiffness Problem Applied to Low-Thrust Trajectory Optimisation in Terms of Orbital Elements Using Differential Dynamic Programming},
author = {Nugnes, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1169867},
year = {2021},
date = {2021-02-01},
booktitle = {31st AAS/AIAA Space Flight Mechanics Meeting},
volume = {AAS 21-369},
pages = {1-16},
address = {Virtual Conference},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Polli, E. M.; Gonzalo, J. L.; Colombo, C.
Statistical Analysis of the Environmental Impact of Satellite Constellations Inproceedings
In: 2nd Global Virtual Workshop (GVW-II) of the Stardust-R network, Virtual Event, 2021.
@inproceedings{Polli2021inproceedings,
title = {Statistical Analysis of the Environmental Impact of Satellite Constellations},
author = {Polli, E. M. and Gonzalo, J. L. and Colombo, C.},
year = {2021},
date = {2021-01-01},
booktitle = {2nd Global Virtual Workshop (GVW-II) of the Stardust-R network},
address = {Virtual Event},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Fusaro, C.; Trisolini, M.; Colombo, C.
Interface Between the Long-Term Propagation and the Destructive Re-Entry Phases Exploiting the Overshoot Boundary Inproceedings
In: 11th International Association for the Advancement of Space Safety Conference 'Managing Risk in Space’ (IAASS), pp. 1-10, Virtual Event, 2021.
@inproceedings{Fusaro2021inproceedings,
title = {Interface Between the Long-Term Propagation and the Destructive Re-Entry Phases Exploiting the Overshoot Boundary},
author = {Fusaro, C. and Trisolini, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1189551},
year = {2021},
date = {2021-00-01},
booktitle = {11th International Association for the Advancement of Space Safety Conference 'Managing Risk in Space’ (IAASS)},
pages = {1-10},
address = {Virtual Event},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
2020
Gonzalo, J. L.; Colombo, C.
Collision Avoidance Algorithms for Space Traffic Management Applications Inproceedings
In: 71st International Astronautical Congress (IAC 2020), pp. 1-8, The CyberSpace Edition, 2020.
@inproceedings{Gonzalo2020inproceedings,
title = {Collision Avoidance Algorithms for Space Traffic Management Applications},
author = {Gonzalo, J. L. and Colombo, C.},
url = {http://hdl.handle.net/11311/1148386},
year = {2020},
date = {2020-10-01},
booktitle = {71st International Astronautical Congress (IAC 2020)},
volume = {IAC-20-A6},
pages = {1-8},
address = {The CyberSpace Edition},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Huang, S.; Colombo, C.; Gonzalo, J. L.; Masserini, A.; Nugnes, M.; Vallini, L.; Petit, M.
Preliminary Mission Analysis of Active Debris Removal Service for Large Constellations Inproceedings
In: 71st International Astronautical Congress (IAC 2020), pp. 1-6, The CyberSpace Edition, 2020.
@inproceedings{Huang2020inproceedings,
title = {Preliminary Mission Analysis of Active Debris Removal Service for Large Constellations},
author = {Huang, S. and Colombo, C. and Gonzalo, J. L. and Masserini, A. and Nugnes, M. and Vallini, L. and Petit, M.},
url = {http://hdl.handle.net/11311/1149719},
year = {2020},
date = {2020-10-01},
booktitle = {71st International Astronautical Congress (IAC 2020)},
volume = {IAC-20, A6, VP, 14, x60342},
pages = {1-6},
address = {The CyberSpace Edition},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Limonta, S.; Trisolini, M.; Frey, S.; Colombo, C.
Modelling the Break-Up and Re-Entry Propagation of Meteorites Through a Continuum Approach Inproceedings
In: 71st International Astronautical Congress (IAC 2020), pp. 1-18, The CyberSpace Edition, 2020.
@inproceedings{Limonta2020inproceedings,
title = {Modelling the Break-Up and Re-Entry Propagation of Meteorites Through a Continuum Approach},
author = {Limonta, S. and Trisolini, M. and Frey, S. and Colombo, C.},
url = {http://hdl.handle.net/11311/1148757},
year = {2020},
date = {2020-10-01},
booktitle = {71st International Astronautical Congress (IAC 2020)},
volume = {IAC-20-C1},
pages = {1-18},
address = {The CyberSpace Edition},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Scala, F.; Gaias, G.; Colombo, C.; Martín-Neira, M.
Formation Flying L-Band Aperture Synthesis: Design Challenges and Innovative Formation Architecture Concept Inproceedings
In: 71st International Astronautical Congress (IAC 2020), pp. 1-10, The CyberSpace Edition, 2020.
@inproceedings{Scala2020inproceedings,
title = {Formation Flying L-Band Aperture Synthesis: Design Challenges and Innovative Formation Architecture Concept},
author = {Scala, F. and Gaias, G. and Colombo, C. and Martín-Neira, M.},
url = {http://hdl.handle.net/11311/1153224},
year = {2020},
date = {2020-10-01},
booktitle = {71st International Astronautical Congress (IAC 2020)},
volume = {IAC-20-C1},
pages = {1-10},
address = {The CyberSpace Edition},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Scalera, M. A.; Nugnes, M.; Colombo, C.
In: 71st International Astronautical Congress (IAC 2020), pp. 1-15, The CyberSpace Edition, 2020.
@inproceedings{Scalera2020inproceedings,
title = {A System-Level Engineering Approach to Define the Social Value Rating of Earth Remote Sensing Missions Through Sustainable Development Goals},
author = {Scalera, M. A. and Nugnes, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1148348},
year = {2020},
date = {2020-10-01},
booktitle = {71st International Astronautical Congress (IAC 2020)},
pages = {1-15},
address = {The CyberSpace Edition},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Trisolini, M.; Colombo, C.
Modeling Re-Entry Break-Up Uncertainties with Continuity Equation and Gaussian Mixture Models Interpolation Inproceedings
In: 2020 AAS/AIAA Astrodynamics Specialist Conference, pp. 2229-2240, Virtual Event, 2020.
@inproceedings{Trisolini2020inproceedings,
title = {Modeling Re-Entry Break-Up Uncertainties with Continuity Equation and Gaussian Mixture Models Interpolation},
author = {Trisolini, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1146009},
year = {2020},
date = {2020-08-01},
booktitle = {2020 AAS/AIAA Astrodynamics Specialist Conference},
volume = {AAS 20-636},
pages = {2229-2240},
address = {Virtual Event},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Scala, F.; Gaias, G. V. M.; Colombo, C.; Martin Neira, M.
Three Satellites Formation Flying: Deployment and Formation Acquisition Using Relative Orbital Elements Inproceedings
In: 2020 AAS/AIAA Astrodynamics Specialist Conference, pp. 3981-3997, Virtual Event, 2020.
@inproceedings{Scala2020inproceedingsb,
title = {Three Satellites Formation Flying: Deployment and Formation Acquisition Using Relative Orbital Elements},
author = {Scala, F. and Gaias, G. V. M. and Colombo, C. and Martin Neira, M.},
url = {http://hdl.handle.net/11311/1146013},
year = {2020},
date = {2020-08-01},
booktitle = {2020 AAS/AIAA Astrodynamics Specialist Conference},
volume = {AAS 20-625},
pages = {3981-3997},
address = {Virtual Event},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Borelli, G.; Gaias, G. V. M.; Colombo, C.
Rotational Control with Plume Impingement to Aid Rigid Capture of an Uncooperative Failed Satellite Inproceedings
In: 2020 AAS/AIAA Astrodynamics Specialist Conference, pp. 4085-4104, Virtual Event, 2020.
@inproceedings{Borelli2020inproceedings,
title = {Rotational Control with Plume Impingement to Aid Rigid Capture of an Uncooperative Failed Satellite},
author = {Borelli, G. and Gaias, G. V. M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1146010},
year = {2020},
date = {2020-08-01},
booktitle = {2020 AAS/AIAA Astrodynamics Specialist Conference},
volume = {AAS 20-670},
pages = {4085-4104},
address = {Virtual Event},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
2019
Frey, S.; Colombo, C.; Lemmens, S.
Application of Density-Based Propagation to Fragment Clouds using the Starling Suite Inproceedings
In: 1st International Orbital Debris Conference (IOC), pp. 1-10, Sugar Land, TX, US, 2019.
@inproceedings{Frey2019inproceedingsb,
title = {Application of Density-Based Propagation to Fragment Clouds using the Starling Suite},
author = {Frey, S. and Colombo, C. and Lemmens, S.},
url = {http://hdl.handle.net/11311/1123138},
year = {2019},
date = {2019-12-01},
booktitle = {1st International Orbital Debris Conference (IOC)},
pages = {1-10},
address = {Sugar Land, TX, US},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Gonzalo, J. L.; Colombo, C.; Di Lizia, P.
Introducing MISS, a New Tool for Collision Avoidance Analysis and Design Inproceedings
In: 1st International Orbital Debris Conference (IOC), pp. 1-10, Sugar Land, TX, US, 2019.
@inproceedings{Gonzalo2019inproceedingsc,
title = {Introducing MISS, a New Tool for Collision Avoidance Analysis and Design},
author = {Gonzalo, J. L. and Colombo, C. and Di Lizia, P.},
url = {http://hdl.handle.net/11311/1123120},
year = {2019},
date = {2019-12-01},
booktitle = {1st International Orbital Debris Conference (IOC)},
pages = {1-10},
address = {Sugar Land, TX, US},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Masat, A.; Romano, M.; Colombo, C.
Orbital Resonance Analysis in Monte Carlo Simulations for Planetary Protection and Defence Inproceedings
In: 25th Conference of the Italian Association of Aeronautics and Astronautics (AIDAA 2019), pp. 611-621, Roma, Italy, 2019.
@inproceedings{Masat2019inproceedings,
title = {Orbital Resonance Analysis in Monte Carlo Simulations for Planetary Protection and Defence},
author = {Masat, A. and Romano, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1111358},
year = {2019},
date = {2019-09-01},
booktitle = {25th Conference of the Italian Association of Aeronautics and Astronautics (AIDAA 2019)},
pages = {611-621},
address = {Roma, Italy},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Borelli, G.; Nugnes, M.; Colombo, C.
Low Thrust Multiple Revolution Transfer Design Using Artificial Potential Guidance in the Phase Space Inproceedings
In: 25th Conference of the Italian Association of Aeronautics and Astronautics (AIDAA 2019), pp. 458-465, Roma, Italy, 2019.
@inproceedings{Borelli2019inproceedings,
title = {Low Thrust Multiple Revolution Transfer Design Using Artificial Potential Guidance in the Phase Space},
author = {Borelli, G. and Nugnes, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1111219},
year = {2019},
date = {2019-09-01},
booktitle = {25th Conference of the Italian Association of Aeronautics and Astronautics (AIDAA 2019)},
pages = {458-465},
address = {Roma, Italy},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Menzio, D.; Colombo, C.
Flyby in the Spatial Three-Body Problem Inproceedings
In: 2019 AAS/AIAA Astrodynamics Specialist Conference, pp. 2033-2047, Portland, ME, USA, 2019.
@inproceedings{Menzio2019inproceedings,
title = {Flyby in the Spatial Three-Body Problem},
author = {Menzio, D. and Colombo, C.},
url = {http://hdl.handle.net/11311/1145837},
year = {2019},
date = {2019-08-01},
booktitle = {2019 AAS/AIAA Astrodynamics Specialist Conference},
volume = {AAS 19-909},
pages = {2033-2047},
address = {Portland, ME, USA},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Colombo, C.; Miguel Banos, N.; Gkolias, I.
Modulating Solar Sail Control for End-Of-life Disposal with Solar Sails Inproceedings
In: 5th International Symposium on Solar Sailing, pp. 1-13, Aachen, Germany, 2019.
@inproceedings{Colombo2019inproceedingsb,
title = {Modulating Solar Sail Control for End-Of-life Disposal with Solar Sails},
author = {Colombo, C. and Miguel Banos, N. and Gkolias, I.},
url = {http://hdl.handle.net/11311/1123523},
year = {2019},
date = {2019-07-01},
booktitle = {5th International Symposium on Solar Sailing},
pages = {1-13},
address = {Aachen, Germany},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Miguel Banos, N.; Colombo, C.
Stable Attitude Deorbiting Using a Simplified Planar Quasi-Rhombic-Pyramid Sail Inproceedings
In: 5th International Symposium on Solar Sailing, pp. 1-13, Aachen, Germany, 2019.
@inproceedings{Miguel2019inproceedings,
title = {Stable Attitude Deorbiting Using a Simplified Planar Quasi-Rhombic-Pyramid Sail},
author = {Miguel Banos, N. and Colombo, C.},
url = {http://hdl.handle.net/11311/1123526},
year = {2019},
date = {2019-07-01},
booktitle = {5th International Symposium on Solar Sailing},
pages = {1-13},
address = {Aachen, Germany},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Dalla Vedova, F.; Miguel Banos, N.; Colombo, C.
Photonic Propulsion: an Option for Space Resources Transportation to and from the Main Belt Inproceedings
In: 5th International Symposium on Solar Sailing, pp. 1-15, Aachen, Germany, 2019.
@inproceedings{Dalla2019inproceedings,
title = {Photonic Propulsion: an Option for Space Resources Transportation to and from the Main Belt},
author = {Dalla Vedova, F. and Miguel Banos, N. and Colombo, C.},
url = {http://hdl.handle.net/11311/1123525},
year = {2019},
date = {2019-07-01},
booktitle = {5th International Symposium on Solar Sailing},
pages = {1-15},
address = {Aachen, Germany},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Gaias, G.; Ardaens, J. -S.; Colombo, C.
Precise Line-of-Sight Modelling for Angles-Only Relative Navigation Inproceedings
In: 10th International Workshop on Satellite Constellations and Formation Flying (IWSCFF 2019), pp. 1-16, Glasgow, UK, 2019.
@inproceedings{Gaias2019inproceedingsb,
title = {Precise Line-of-Sight Modelling for Angles-Only Relative Navigation},
author = {Gaias, G. and Ardaens, J. -S. and Colombo, C.},
url = {http://hdl.handle.net/11311/1099115},
year = {2019},
date = {2019-07-01},
booktitle = {10th International Workshop on Satellite Constellations and Formation Flying (IWSCFF 2019)},
volume = {IWSCFF 19-48},
pages = {1-16},
address = {Glasgow, UK},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Romano, M.; Colombo, C.; Sanchez Perez, J. M.
Line Sampling procedure for extensive planetary protection analysis Inproceedings
In: 4th International Workshop on Key Topics in Orbit Propagation Applied to Space Situational Awareness (KePASSA), pp. 46-46, Logrono, Spain, 2019.
@inproceedings{Romano2019inproceedings,
title = {Line Sampling procedure for extensive planetary protection analysis},
author = {Romano, M. and Colombo, C. and Sanchez Perez, J. M.},
url = {http://hdl.handle.net/11311/1086695},
year = {2019},
date = {2019-04-01},
booktitle = {4th International Workshop on Key Topics in Orbit Propagation Applied to Space Situational Awareness (KePASSA)},
pages = {46-46},
address = {Logrono, Spain},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Gonzalo, J. L.; Colombo, C.; Di Lizia, P.
Drag- and SRP- induced effects in uncertainty evolution for close approaches Inproceedings
In: 4th International Workshop on Key Topics in Orbit Propagation Applied to Space Situational Awareness (KePASSA), pp. 45-45, Logroño, Spain., 2019.
@inproceedings{Gonzalo2019inproceedings,
title = {Drag- and SRP- induced effects in uncertainty evolution for close approaches},
author = {Gonzalo, J. L. and Colombo, C. and Di Lizia, P.},
url = {http://hdl.handle.net/11311/1086689},
year = {2019},
date = {2019-04-01},
booktitle = {4th International Workshop on Key Topics in Orbit Propagation Applied to Space Situational Awareness (KePASSA)},
pages = {45-45},
address = {Logroño, Spain.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Garcia-Pelayo, R.; Gonzalo, Juan Luis
Probability of Collision Between a Rectangular Cuboid and Small Debris Inproceedings
In: 5th CEAS Specialist Conference on Guidance, Navigation and Control - EuroGNC, pp. 1-12, Milano, Italy, 2019.
@inproceedings{Garcia-Pelayo2019inproceedings,
title = {Probability of Collision Between a Rectangular Cuboid and Small Debris},
author = {Garcia-Pelayo, R. and Gonzalo, Juan Luis},
url = {http://hdl.handle.net/11311/1121160},
year = {2019},
date = {2019-04-01},
booktitle = {5th CEAS Specialist Conference on Guidance, Navigation and Control - EuroGNC},
pages = {1-12},
address = {Milano, Italy},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Trisolini, M.; Colombo, C.
A Density-Based Approach to the Propagation of Re-Entry Uncertainties Inproceedings
In: 27th International Symposium on Space Flight Dynamics (ISSFD), pp. 1-9, Melbourne, Australia, 2019.
@inproceedings{Trisolini2019inproceedings,
title = {A Density-Based Approach to the Propagation of Re-Entry Uncertainties},
author = {Trisolini, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1078106},
year = {2019},
date = {2019-02-01},
booktitle = {27th International Symposium on Space Flight Dynamics (ISSFD)},
pages = {1-9},
address = {Melbourne, Australia},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Gaias, G.; Lara, M.; Colombo, C.
Accurate Osculating/Mean Orbital Elements Conversions for Spaceborne Formation Flying Inproceedings
In: 27th International Symposium on Space Flight Dynamics (ISSFD), pp. 1-15, Melbourne, Australia, 2019.
@inproceedings{Gaias2019inproceedings,
title = {Accurate Osculating/Mean Orbital Elements Conversions for Spaceborne Formation Flying},
author = {Gaias, G. and Lara, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1076492},
year = {2019},
date = {2019-02-01},
booktitle = {27th International Symposium on Space Flight Dynamics (ISSFD)},
pages = {1-15},
address = {Melbourne, Australia},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Scala, F.; Colombo, C.; Gkolias, I.
Design of disposal orbits for high altitude spacecraft with a semi-analytical model Inproceedings
In: 27th International Symposium on Space Flight Dynamics (ISSFD), pp. 1-21, Melbourne, Australia, 2019.
@inproceedings{Scala2019inproceedings,
title = {Design of disposal orbits for high altitude spacecraft with a semi-analytical model},
author = {Scala, F. and Colombo, C. and Gkolias, I.},
url = {http://hdl.handle.net/11311/1079482},
year = {2019},
date = {2019-02-01},
booktitle = {27th International Symposium on Space Flight Dynamics (ISSFD)},
pages = {1-21},
address = {Melbourne, Australia},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Frey, S.; Colombo, C.; Lemmens, S.
Interpolation and Integration of Phase Space Density for Estimation of Fragmentation Cloud Distribution Inproceedings
In: Spaceflight Mechanics 2019, pp. 2229-2240, Kaanapali, Maui, HI, USA, 2019.
@inproceedings{Frey2019inproceedings,
title = {Interpolation and Integration of Phase Space Density for Estimation of Fragmentation Cloud Distribution},
author = {Frey, S. and Colombo, C. and Lemmens, S.},
year = {2019},
date = {2019-01-01},
booktitle = {Spaceflight Mechanics 2019},
volume = {168},
pages = {2229-2240},
address = {Kaanapali, Maui, HI, USA},
abstract = {To calculate the effects of on-orbit fragmentations on current or future space missions, accurate estimates of the fragment density and its time evolution are required. Current operational tools estimate the risks involved through representative objects. Such tools, however, cannot accurately estimate the fragment density at any point in space and time. Rather, they directly calculate the number of close approaches from the representative objects. As such, they require a large number of Monte Carlo (MC) simulations to accurately find the collision risk over a large domain. Instead, the continuity equation can be applied to model the fragment density as a continuum, and propagate it forward in time. To model the evolution in any orbital region, the continuum can be propagated semi-analytically along its characteristics. The difficulty arises in estimating the density in between the cloud of samples. Here, the underlying density distribution is estimated by fitting a Gaussian Mixture Model (GMM) to the characteristics. An example of a break-up in three dimensions is given. It is shown that the model can accurately be fitted at different snapshots after the fragmentation, even with a low number of sample points. Given an analytical expression of the density enables the subsequent integration of the collision risk at any point in the phase space.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
To calculate the effects of on-orbit fragmentations on current or future space missions, accurate estimates of the fragment density and its time evolution are required. Current operational tools estimate the risks involved through representative objects. Such tools, however, cannot accurately estimate the fragment density at any point in space and time. Rather, they directly calculate the number of close approaches from the representative objects. As such, they require a large number of Monte Carlo (MC) simulations to accurately find the collision risk over a large domain. Instead, the continuity equation can be applied to model the fragment density as a continuum, and propagate it forward in time. To model the evolution in any orbital region, the continuum can be propagated semi-analytically along its characteristics. The difficulty arises in estimating the density in between the cloud of samples. Here, the underlying density distribution is estimated by fitting a Gaussian Mixture Model (GMM) to the characteristics. An example of a break-up in three dimensions is given. It is shown that the model can accurately be fitted at different snapshots after the fragmentation, even with a low number of sample points. Given an analytical expression of the density enables the subsequent integration of the collision risk at any point in the phase space.
Li, L.; Zhang, J.; Gkolias, I.; Colombo, C.
Constellation design and low-thrust station-keeping strategy for satellites in inclined geosynchronous orbits Inproceedings
In: 10th International Conference on Mechanical and Aerospace Engineering (ICMAE 2019), pp. 108-114, Brussels, Belgium, 2019.
@inproceedings{Li2019inproceedings,
title = {Constellation design and low-thrust station-keeping strategy for satellites in inclined geosynchronous orbits},
author = {Li, L. and Zhang, J. and Gkolias, I. and Colombo, C.},
url = {http://doi.org/10.1109/ICMAE.2019.8881038},
doi = {http://dx.doi.org/10.1109/ICMAE.2019.8881038},
year = {2019},
date = {2019-01-01},
booktitle = {10th International Conference on Mechanical and Aerospace Engineering (ICMAE 2019)},
pages = {108-114},
address = {Brussels, Belgium},
abstract = {Small constellations of satellites in Inclined Geosynchronous Orbits (IGSO) provide an alternative to the increasingly crowded Geostationary Equatorial Orbit (GEO) belt. Satellite platforms equipped with electric propulsion systems increase in popularity since they broaden the mission design opportunities due to the potentially significant propellant savings. This work focuses on low-thrust IGSO constellation design and station-keeping strategies. An analytical procedure based on a Hamiltonian formulation with respect to the ecliptic plane is used for the selection of suitable frozen orbits. Considering appropriate dynamical modelling, the low-thrust station-keeping problem is transformed into a Two Point Boundary Value Problem (TPBVP), which is then solved by an impulsive-solution-based initial costate guess.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Small constellations of satellites in Inclined Geosynchronous Orbits (IGSO) provide an alternative to the increasingly crowded Geostationary Equatorial Orbit (GEO) belt. Satellite platforms equipped with electric propulsion systems increase in popularity since they broaden the mission design opportunities due to the potentially significant propellant savings. This work focuses on low-thrust IGSO constellation design and station-keeping strategies. An analytical procedure based on a Hamiltonian formulation with respect to the ecliptic plane is used for the selection of suitable frozen orbits. Considering appropriate dynamical modelling, the low-thrust station-keeping problem is transformed into a Two Point Boundary Value Problem (TPBVP), which is then solved by an impulsive-solution-based initial costate guess.
Losacco, M.; Romano, M.; Di Lizia, P.; Colombo, C.; Armellin, R.; Morselli, A.; Sanchez Perez, J. M.
In: 1st NEO and Debris Detection Conference, pp. 1-12, Darmstadt, Germany, 2019.
@inproceedings{Losacco2019inproceedings,
title = {Advanced Monte Carlo Sampling Techniques For Orbital Conjunctions Analysis And Near Earth Objects Impact Probability Computation},
author = {Losacco, M. and Romano, M. and Di Lizia, P. and Colombo, C. and Armellin, R. and Morselli, A. and Sanchez Perez, J. M.},
url = {https://conference.sdo.esoc.esa.int/proceedings/neosst1/paper/482/NEOSST1-paper482.pdf},
year = {2019},
date = {2019-01-01},
booktitle = {1st NEO and Debris Detection Conference},
pages = {1-12},
address = {Darmstadt, Germany},
abstract = {This paper presents a survey of past and new results of the application of advanced sampling techniques for orbital conjunction analysis and Near Earth Objects impact probability computation. The theoretical background of the methods is presented, along with the results of their applications and a critical discussion of the benefits introduced.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
This paper presents a survey of past and new results of the application of advanced sampling techniques for orbital conjunction analysis and Near Earth Objects impact probability computation. The theoretical background of the methods is presented, along with the results of their applications and a critical discussion of the benefits introduced.
Trisolini, M.; Colombo, C.
A Density-Based Approach to the Propagation of Re-Entry Uncertainties Inproceedings
In: Spaceflight Mechanics 2019, pp. 2241-2253, Kaanapali, Maui, HI, USA, 2019.
@inproceedings{Trisolini2019inproceedingsb,
title = {A Density-Based Approach to the Propagation of Re-Entry Uncertainties},
author = {Trisolini, M. and Colombo, C.},
year = {2019},
date = {2019-01-01},
booktitle = {Spaceflight Mechanics 2019},
volume = {168},
pages = {2241-2253},
address = {Kaanapali, Maui, HI, USA},
abstract = {The proposed study aims at implementing a density-based approach for the propagation of uncertainties in the initial conditions and parameters for the analysis and prediction of spacecraft re-entries. Using the continuity equation together with the re-entry dynamics, the joint probability distribution function of the uncertainties is propagated and the final uncertainties in the re-entry corridor, impact location, and casualty area are quantified. The paper considers uncertainties in the initial conditions at re-entry and in the ballistic coefficient of the satellite for different types of re-entry scenarios, studying the effects that such uncertainties have on the impact location and entry corridor.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
The proposed study aims at implementing a density-based approach for the propagation of uncertainties in the initial conditions and parameters for the analysis and prediction of spacecraft re-entries. Using the continuity equation together with the re-entry dynamics, the joint probability distribution function of the uncertainties is propagated and the final uncertainties in the re-entry corridor, impact location, and casualty area are quantified. The paper considers uncertainties in the initial conditions at re-entry and in the ballistic coefficient of the satellite for different types of re-entry scenarios, studying the effects that such uncertainties have on the impact location and entry corridor.
Huang, S.; Colombo, C.; Alessi, E. M.; Hou, Z.
Large Constellation De-Orbiting with Low-Thrust Propulsion Inproceedings
In: Spaceflight Mechanics 2019, pp. 2313-2334, Kaanapali, Maui, HI, USA, 2019.
@inproceedings{Huang2019inproceedingsb,
title = {Large Constellation De-Orbiting with Low-Thrust Propulsion},
author = {Huang, S. and Colombo, C. and Alessi, E. M. and Hou, Z.},
year = {2019},
date = {2019-01-01},
booktitle = {Spaceflight Mechanics 2019},
volume = {168},
pages = {2313-2334},
address = {Kaanapali, Maui, HI, USA},
abstract = {This paper deals with the propulsive phase of de-orbiting phase for coplanar satellites in large constellations. The design is conducted via two layers: the first layer is to design a time-optimal deorbiting trajectory for a single satellite; the second layer is to find the optimal de-orbit timing for each satellite to start the de-orbiting in order to minimize the total transfer time as well as the inner constellation collision risk. For the first layer, two de-orbit strategies are considered: the first strategy aims at lowering the perigee; the second strategy aims at reaching a natural de-orbiting corridor. For each strategy, the quasi time-optimal steering law is developed, and the secular variations of the orbital elements are derived by using the averaging technique. For the second layer, the inner constellation collision risk is evaluated by miss distance; the optimal de-orbit timings are found for different de-orbit sequences by using a multi-objective optimization technique.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
This paper deals with the propulsive phase of de-orbiting phase for coplanar satellites in large constellations. The design is conducted via two layers: the first layer is to design a time-optimal deorbiting trajectory for a single satellite; the second layer is to find the optimal de-orbit timing for each satellite to start the de-orbiting in order to minimize the total transfer time as well as the inner constellation collision risk. For the first layer, two de-orbit strategies are considered: the first strategy aims at lowering the perigee; the second strategy aims at reaching a natural de-orbiting corridor. For each strategy, the quasi time-optimal steering law is developed, and the secular variations of the orbital elements are derived by using the averaging technique. For the second layer, the inner constellation collision risk is evaluated by miss distance; the optimal de-orbit timings are found for different de-orbit sequences by using a multi-objective optimization technique.
Nugnes, M.; Colombo, C.
Introduction to a Keplerian-Orbital-Element-Based Optimisation Approach Via Differential Dynamic Programming Inproceedings
In: 4th International Workshop on Key Topics in Orbit Propagation Applied to Space Situational Awareness (KePASSA), Logrono, Spain, 2019.
@inproceedings{Nugnes2019inproceedings,
title = {Introduction to a Keplerian-Orbital-Element-Based Optimisation Approach Via Differential Dynamic Programming},
author = {Nugnes, M. and Colombo, C.},
year = {2019},
date = {2019-01-01},
booktitle = {4th International Workshop on Key Topics in Orbit Propagation Applied to Space Situational Awareness (KePASSA)},
address = {Logrono, Spain},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Colombo, C.; Scala, F.; Gkolias, I.
Surfing the phase space of Earth’s oblateness and third body perturbations Inproceedings
In: Spaceflight Mechanics 2019, pp. 3209-3227, Kaanapali, Maui, HI, USA, 2019.
@inproceedings{Colombo2019inproceedings,
title = {Surfing the phase space of Earth’s oblateness and third body perturbations},
author = {Colombo, C. and Scala, F. and Gkolias, I.},
year = {2019},
date = {2019-01-01},
booktitle = {Spaceflight Mechanics 2019},
volume = {168},
pages = {3209-3227},
address = {Kaanapali, Maui, HI, USA},
abstract = {In this work, we exploit the luni-solar perturbations for the post-mission disposal of satellites in high-altitude orbits. Starting from the double-averaged dynamical system, the representation of the dynamics is reduced to a one degree-of-freedom Hamiltonian, depending on the orbit eccentricity and the perigee orientation in the equatorial frame. An analytical method is proposed for designing the disposal maneuver with the goal to achieve natural re-entry by exploiting the long-term effect of the natural perturbations, enhanced by impulsive maneuvers. The optimal initial conditions to apply the impulsive maneuver, such that a fast re-entry is achieved, are selected via a gradient based method in the phase space.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
In this work, we exploit the luni-solar perturbations for the post-mission disposal of satellites in high-altitude orbits. Starting from the double-averaged dynamical system, the representation of the dynamics is reduced to a one degree-of-freedom Hamiltonian, depending on the orbit eccentricity and the perigee orientation in the equatorial frame. An analytical method is proposed for designing the disposal maneuver with the goal to achieve natural re-entry by exploiting the long-term effect of the natural perturbations, enhanced by impulsive maneuvers. The optimal initial conditions to apply the impulsive maneuver, such that a fast re-entry is achieved, are selected via a gradient based method in the phase space.
Alessi, E. M.; Gkolias, I.; Colombo, C.
Time Characterization of the Coupled Solar Radiation Pressure-Planetary Oblateness Dynamics Inproceedings
In: 70th International Astronautical Congress (IAC 2019), pp. 1-10, Washington DC, USA, 2019.
@inproceedings{Alessi2019inproceedings,
title = {Time Characterization of the Coupled Solar Radiation Pressure-Planetary Oblateness Dynamics},
author = {Alessi, E. M. and Gkolias, I. and Colombo, C.},
url = {http://hdl.handle.net/11311/1118881},
year = {2019},
date = {2019-00-01},
booktitle = {70th International Astronautical Congress (IAC 2019)},
volume = {IAC-19},
pages = {1-10},
address = {Washington DC, USA},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Colombo, C.; Vicario de Miguel, G.; Skoulidou, D. K.; Miguel Banos, N.; Alessi, E. M.; Gkolias, I.; Carzana, L.; Letterio, F.; Schettino, G.; Tsiganis, K.; Rossi, A.
ReDSHIFT Disposal Module for the Design of End-Of-life Disposal Trajectories for LEO to GEO Missions Inproceedings
In: 70th International Astronautical Congress (IAC 2019), pp. 1-16, Washington DC, USA, 2019.
@inproceedings{Colombo2019inproceedingsc,
title = {ReDSHIFT Disposal Module for the Design of End-Of-life Disposal Trajectories for LEO to GEO Missions},
author = {Colombo, C. and Vicario de Miguel, G. and Skoulidou, D. K. and Miguel Banos, N. and Alessi, E. M. and Gkolias, I. and Carzana, L. and Letterio, F. and Schettino, G. and Tsiganis, K. and Rossi, A.},
url = {http://hdl.handle.net/11311/1118894},
year = {2019},
date = {2019-00-01},
booktitle = {70th International Astronautical Congress (IAC 2019)},
volume = {IAC-19},
pages = {1-16},
address = {Washington DC, USA},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Popova, R.; Rossi, A.; Kim, Y.; Colombo, C.; Alessi, E. M.; Gkolias, I.; Schaus, V.; Tsiganis, K.; Beck, J.
In: 70th International Astronautical Congress (IAC 2019), pp. 1-15, Washington DC, USA, 2019.
@inproceedings{Popova2019inproceedings,
title = {The Path to Establishing an Effective Framework for Space Debris Remediation on the Basis of Mitigation: Legal Proposals Resulting from the Technical Results of the Redshift Project},
author = {Popova, R. and Rossi, A. and Kim, Y. and Colombo, C. and Alessi, E. M. and Gkolias, I. and Schaus, V. and Tsiganis, K. and Beck, J.},
url = {http://hdl.handle.net/11311/1118898},
year = {2019},
date = {2019-00-01},
booktitle = {70th International Astronautical Congress (IAC 2019)},
volume = {IAC-19},
pages = {1-15},
address = {Washington DC, USA},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Rossi, A.; Alessi, E. M.; Schettino, G.; Beck, J.; Holbrough, I.; Schleutker, T.; Letterio, F.; Vicario de Miguel, G.; Becedas Rodríguez, J.; Dalla Vedova, F.; Stokes, H.; Colombo, C.; Gkolias, I.; Bernelli Zazzera, F.; Miguel Banos, N.; Walker, S.; Romei, F.; Tsiganis, K.; Skoulidou, D.; Stoll, E.; Schaus, V.; Popova, R.; Kim, Y.; Francesconi, A.; Olivieri, L.; Gerardin, S.
The H2020 ReDSHIFT Project: a Successful European Effort Towards Space Debris Mitigation Inproceedings
In: 70th International Astronautical Congress (IAC 2019), pp. 1-12, Washington DC, USA, 2019.
@inproceedings{Rossi2019inproceedings,
title = {The H2020 ReDSHIFT Project: a Successful European Effort Towards Space Debris Mitigation},
author = {Rossi, A. and Alessi, E. M. and Schettino, G. and Beck, J. and Holbrough, I. and Schleutker, T. and Letterio, F. and Vicario de Miguel, G. and Becedas Rodríguez, J. and Dalla Vedova, F. and Stokes, H. and Colombo, C. and Gkolias, I. and Bernelli Zazzera, F. and Miguel Banos, N. and Walker, S. and Romei, F. and Tsiganis, K. and Skoulidou, D. and Stoll, E. and Schaus, V. and Popova, R. and Kim, Y. and Francesconi, A. and Olivieri, L. and Gerardin, S.},
url = {http://hdl.handle.net/11311/1118889},
year = {2019},
date = {2019-00-01},
booktitle = {70th International Astronautical Congress (IAC 2019)},
volume = {IAC-19},
pages = {1-12},
address = {Washington DC, USA},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Gonzalo, J. L.; Colombo, C.; Di Lizia, P.
A semi-analytical approach to low-thrust collision avoidance manoeuvre design Inproceedings
In: 70th International Astronautical Congress (IAC 2019), pp. 1-9, Washington DC, USA, 2019.
@inproceedings{Gonzalo2019inproceedingsb,
title = {A semi-analytical approach to low-thrust collision avoidance manoeuvre design},
author = {Gonzalo, J. L. and Colombo, C. and Di Lizia, P.},
url = {http://hdl.handle.net/11311/1116451},
year = {2019},
date = {2019-00-01},
booktitle = {70th International Astronautical Congress (IAC 2019)},
volume = {Paper IAC-19-A6},
pages = {1-9},
address = {Washington DC, USA},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
García Pelayo, R.; Gonzalo, J. L.; Bombardelli, C.
Rate and collision probability of tethers and sails Inproceedings
In: 6th International Conference on Tethers in Space, pp. 1-25, Madrid, Spain, 2019.
@inproceedings{García2019inproceedings,
title = {Rate and collision probability of tethers and sails},
author = {García Pelayo, R. and Gonzalo, J. L. and Bombardelli, C.},
url = {http://hdl.handle.net/11311/1121358},
year = {2019},
date = {2019-00-01},
booktitle = {6th International Conference on Tethers in Space},
pages = {1-25},
address = {Madrid, Spain},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Huang, S.; Colombo, C.; Alessi, E. M.
Trade-Off Study on Large Constellation Deorbiting using Low-Thrust and De-Orbiting Balloons Inproceedings
In: 10th International Workshop on Satellite Constellations and Formation Flying (IWSCFF 2019), pp. 1-21, Glasgow, UK, 2019.
@inproceedings{Huang2019inproceedings,
title = {Trade-Off Study on Large Constellation Deorbiting using Low-Thrust and De-Orbiting Balloons},
author = {Huang, S. and Colombo, C. and Alessi, E. M.},
url = {http://hdl.handle.net/11311/1120861},
year = {2019},
date = {2019-00-01},
booktitle = {10th International Workshop on Satellite Constellations and Formation Flying (IWSCFF 2019)},
volume = {IWSCFF 19-1953},
pages = {1-21},
address = {Glasgow, UK},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Nugnes, M.; Colombo, C.
Low-thrust Trajectory Optimisation through Differential Dynamic Programming Method based on Keplerian Orbital Elements Inproceedings
In: 70th International Astronautical Congress (IAC 2019), pp. 1-9, Washington DC, USA, 2019.
@inproceedings{Nugnes2019inproceedingsb,
title = {Low-thrust Trajectory Optimisation through Differential Dynamic Programming Method based on Keplerian Orbital Elements},
author = {Nugnes, M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1117583},
year = {2019},
date = {2019-00-01},
booktitle = {70th International Astronautical Congress (IAC 2019)},
volume = {Paper IAC-19-C1},
pages = {1-9},
address = {Washington DC, USA},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
2018
Gaias, G. V. M.; Colombo, C.
Semi-Analytical Framework for Precise Relative Motion in Low Earth Orbits Inproceedings
In: 7th International Conference on Astrodynamics Tools and Techniques (ICATT), pp. 1-10, Oberpfaffenhofen, Germany, 2018.
@inproceedings{Gaias2018inproceedings,
title = {Semi-Analytical Framework for Precise Relative Motion in Low Earth Orbits},
author = {Gaias, G. V. M. and Colombo, C.},
url = {http://hdl.handle.net/11311/1075027},
year = {2018},
date = {2018-11-01},
booktitle = {7th International Conference on Astrodynamics Tools and Techniques (ICATT)},
pages = {1-10},
address = {Oberpfaffenhofen, Germany},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Rossi, A.; Colombo, C.; Beck, J.; Becedas Rodríguez, J.; Dalla Vedova, F.; Schaus, V.; Francesconi, A.; Walker, S.; Tsiganis, K.; Popova, R.; Schleutker, T.; Holbrough, I.; Stokes, H.; Alessi, E. M.; Gkolias, I.; Kim, Y.; Schettino, G.; Skoulidou, D. K.; Stoll, E.; Letterio, F.
Results from the H2020 Redshift Project: a Global Approach to Space Debris Mitigation Inproceedings
In: 69th International Astronautical Congress (IAC 2018), pp. 1-11, Bremen, Germany, 2018.
@inproceedings{Rossi2018inproceedings,
title = {Results from the H2020 Redshift Project: a Global Approach to Space Debris Mitigation},
author = {Rossi, A. and Colombo, C. and Beck, J. and Becedas Rodríguez, J. and Dalla Vedova, F. and Schaus, V. and Francesconi, A. and Walker, S. and Tsiganis, K. and Popova, R. and Schleutker, T. and Holbrough, I. and Stokes, H. and Alessi, E. M. and Gkolias, I. and Kim, Y. and Schettino, G. and Skoulidou, D. K. and Stoll, E. and Letterio, F.},
url = {http://hdl.handle.net/11311/1066415},
year = {2018},
date = {2018-10-01},
booktitle = {69th International Astronautical Congress (IAC 2018)},
volume = {IAC-18,A6,4,6,x45666},
pages = {1-11},
address = {Bremen, Germany},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Romano, M.; Colombo, C.; Sánchez Pérez, J. M.
Efficient Planetary Protection Analysis for Interplanetary Missions Inproceedings
In: 69th International Astronautical Congress (IAC 2018), pp. 1-9, Bremen, Germany, 2018.
@inproceedings{Romano2018inproceedings,
title = {Efficient Planetary Protection Analysis for Interplanetary Missions},
author = {Romano, M. and Colombo, C. and Sánchez Pérez, J. M.},
url = {http://hdl.handle.net/11311/1066334},
year = {2018},
date = {2018-10-01},
booktitle = {69th International Astronautical Congress (IAC 2018)},
volume = {IAC-18-A3},
pages = {1-9},
address = {Bremen, Germany},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Menzio, D.; Colombo, C.
Adapted Syzygy Functions for the Preliminary Design of Multiple Gravity Assisted Trajectories Inproceedings
In: 69th International Astronautical Congress (IAC 2018), pp. 1-11, Bremen, Germany, 2018.
@inproceedings{Menzio2018inproceedingsb,
title = {Adapted Syzygy Functions for the Preliminary Design of Multiple Gravity Assisted Trajectories},
author = {Menzio, D. and Colombo, C.},
url = {http://hdl.handle.net/11311/1066713},
year = {2018},
date = {2018-10-01},
booktitle = {69th International Astronautical Congress (IAC 2018)},
volume = {IAC-18-C1},
pages = {1-11},
address = {Bremen, Germany},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Colombo, C.; Rossi, A.; Dalla Vedova, F.; Francesconi, A.; Bombardelli, C.; Trisolini, M.; Gonzalo, J. L.; Di Lizia, P.; Giacomuzzo, C.; Bayajid Khan, S.; Garcia-Pelayo, R.; Braun, V.; Bastida Virgili, B.; Krag, H.
Effects of Passive De-Orbiting Through Drag and Solar Sails and Electrodynamic Tethers on the Space Debris Environment Inproceedings
In: 69th International Astronautical Congress (IAC 2018), pp. 1-16, Bremen, Germany, 2018.
@inproceedings{Colombo2018inproceedings,
title = {Effects of Passive De-Orbiting Through Drag and Solar Sails and Electrodynamic Tethers on the Space Debris Environment},
author = {Colombo, C. and Rossi, A. and Dalla Vedova, F. and Francesconi, A. and Bombardelli, C. and Trisolini, M. and Gonzalo, J. L. and Di Lizia, P. and Giacomuzzo, C. and Bayajid Khan, S. and Garcia-Pelayo, R. and Braun, V. and Bastida Virgili, B. and Krag, H.},
url = {http://hdl.handle.net/11311/1071822},
year = {2018},
date = {2018-10-01},
booktitle = {69th International Astronautical Congress (IAC 2018)},
pages = {1-16},
address = {Bremen, Germany},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Menzio, Davide; Colombo, C.
An Analysis Of The Pork-Chop Plot For Direct And Multi-Revolution Flyby Missions Inproceedings
In: 4th IAA Conference on Dynamics and Control of Space Systems (DyCoSS 2018), pp. 1739-1753, Changsha, China, 2018.
@inproceedings{Menzio2018inproceedings,
title = {An Analysis Of The Pork-Chop Plot For Direct And Multi-Revolution Flyby Missions},
author = {Menzio, Davide and Colombo, C.},
url = {http://hdl.handle.net/11311/1056553},
year = {2018},
date = {2018-05-01},
booktitle = {4th IAA Conference on Dynamics and Control of Space Systems (DyCoSS 2018)},
pages = {1739-1753},
address = {Changsha, China},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Hou, Z.; Wang, X.; Li, Z.; Liang, B.; Huang, S.
Hybrid Control for Rapid Spacecraft Attitude Maneuvers Inproceedings
In: 4th IAA Conference on Dynamics and Control of Space Systems (DyCoSS 2018), pp. 1049-1066, Changsha, China, 2018.
@inproceedings{Hou2018inproceedings,
title = {Hybrid Control for Rapid Spacecraft Attitude Maneuvers},
author = {Hou, Z. and Wang, X. and Li, Z. and Liang, B. and Huang, S.},
url = {http://hdl.handle.net/11311/1058302},
year = {2018},
date = {2018-05-01},
booktitle = {4th IAA Conference on Dynamics and Control of Space Systems (DyCoSS 2018)},
pages = {1049-1066},
address = {Changsha, China},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Frey, S.; Colombo, C.; Lemmens, S.
Evolution of Fragmentation Cloud in Highly Eccentric Earth Orbits Through Continuum Modelling Inproceedings
In: 69th International Astronautical Congress (IAC 2018), pp. 1-8, Bremen, Germany, 2018.
@inproceedings{Frey2018inproceedings,
title = {Evolution of Fragmentation Cloud in Highly Eccentric Earth Orbits Through Continuum Modelling},
author = {Frey, S. and Colombo, C. and Lemmens, S.},
year = {2018},
date = {2018-01-01},
booktitle = {69th International Astronautical Congress (IAC 2018)},
pages = {1-8},
address = {Bremen, Germany},
abstract = {A considerable number of fragments orbit around the Earth in Highly Eccentric Orbits (HEOs), mainly in the geostationary transfer orbit. These are believed to have originated in part from the 100 plus fragmentations of parent objects in the same orbit. Many of these objects are characterised by a high area-to-mass ratio, and, as such, especially susceptible to forces induced by atmospheric drag and solar radiation pressure. The complicated dynamics make it difficult to model the evolution of a cloud of such objects, as the spreading depends heavily on their area-to-mass ratios which is difficult to assess. Assumptions on the rapid distribution of a HEO fragment cloud into a band limited by its parent orbit inclination were shown to be inaccurate, and thus oversimplify the problem at hand. Moreover, the time to form a uniformly distributed cloud is higher than the time it takes many of the particles to re-enter. This work aims to increase the understanding of these complex dynamics by accurately modelling the evolution of a cloud of fragments in HEO. The fragment cloud is modelled as a continuum, and its phase space density, rather than single objects, is propagated in time using averaged dynamics in Keplerian elements. Such an approach is not only much faster in terms of computational load when compared to the individual propagation of fragments, but it also improves the accuracy of the density estimation. The perturbations considered are atmospheric drag using a model that was specifically developed for highly eccentric orbits, solar radiation pressure, third bodies and a non-spherical central body implemented in the PlanODyn suite.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
A considerable number of fragments orbit around the Earth in Highly Eccentric Orbits (HEOs), mainly in the geostationary transfer orbit. These are believed to have originated in part from the 100 plus fragmentations of parent objects in the same orbit. Many of these objects are characterised by a high area-to-mass ratio, and, as such, especially susceptible to forces induced by atmospheric drag and solar radiation pressure. The complicated dynamics make it difficult to model the evolution of a cloud of such objects, as the spreading depends heavily on their area-to-mass ratios which is difficult to assess. Assumptions on the rapid distribution of a HEO fragment cloud into a band limited by its parent orbit inclination were shown to be inaccurate, and thus oversimplify the problem at hand. Moreover, the time to form a uniformly distributed cloud is higher than the time it takes many of the particles to re-enter. This work aims to increase the understanding of these complex dynamics by accurately modelling the evolution of a cloud of fragments in HEO. The fragment cloud is modelled as a continuum, and its phase space density, rather than single objects, is propagated in time using averaged dynamics in Keplerian elements. Such an approach is not only much faster in terms of computational load when compared to the individual propagation of fragments, but it also improves the accuracy of the density estimation. The perturbations considered are atmospheric drag using a model that was specifically developed for highly eccentric orbits, solar radiation pressure, third bodies and a non-spherical central body implemented in the PlanODyn suite.
Gkolias, I.; Lara, M.; Colombo, C.
An Ecliptic Perspective for Analytical Satellite Theories Inproceedings
In: 2018 AAS/AIAA Astrodynamics Specialist Conference, pp. 337-351, Snowbird, UT, USA, 2018.
@inproceedings{Gkolias2018inproceedings,
title = {An Ecliptic Perspective for Analytical Satellite Theories},
author = {Gkolias, I. and Lara, M. and Colombo, C.},
year = {2018},
date = {2018-01-01},
booktitle = {2018 AAS/AIAA Astrodynamics Specialist Conference},
volume = {167},
pages = {337-351},
address = {Snowbird, UT, USA},
abstract = {Traditionally, the forces in analytical theories for Earth satellite orbits are expressed in a coordinate frame which involves the equatorial plane. However, for distant satellites, the Moon and Sun attractions are equally important, and those forces are expressed more conveniently in a frame associated to the ecliptic. In this work, we develop an analytical satellite theory in which all the forces are expressed with respect to the ecliptic plane. The main advantage of the method is that, after the averaging process, all timedependent terms disappear from the formulation yielding a model suitable for preliminary orbit design.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Traditionally, the forces in analytical theories for Earth satellite orbits are expressed in a coordinate frame which involves the equatorial plane. However, for distant satellites, the Moon and Sun attractions are equally important, and those forces are expressed more conveniently in a frame associated to the ecliptic. In this work, we develop an analytical satellite theory in which all the forces are expressed with respect to the ecliptic plane. The main advantage of the method is that, after the averaging process, all timedependent terms disappear from the formulation yielding a model suitable for preliminary orbit design.
Gkolias, I.; Colombo, C.
Disposal Design for Geosynchronous Satellites Revisited Inproceedings
In: 2018 AAS/AIAA Astrodynamics Specialist Conference, pp. 1843-1857, Snowbird, UT, USA, 2018.
@inproceedings{Gkolias2018inproceedingsb,
title = {Disposal Design for Geosynchronous Satellites Revisited},
author = {Gkolias, I. and Colombo, C.},
year = {2018},
date = {2018-01-01},
booktitle = {2018 AAS/AIAA Astrodynamics Specialist Conference},
volume = {167},
pages = {1843-1857},
address = {Snowbird, UT, USA},
abstract = {The orbits at geosynchronous altitude provide a valuable natural resource for the human kind. In the absence of atmospheric drag, human intervention is needed to keep the region clean of space debris. Current postmission disposal guidelines deal efficiently with the geostationary lowinclination, low-eccentricity satellites but fail to efficiently regulate the whole geosynchronous region. In this work, we revisit the problem of geosynchronous disposal orbits, trying to identify all possible mechanisms for designing effective disposal strategies. Massive numerical simulations are coupled with optimization techniques and semi-analytical modelling to achieve this goal.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
The orbits at geosynchronous altitude provide a valuable natural resource for the human kind. In the absence of atmospheric drag, human intervention is needed to keep the region clean of space debris. Current postmission disposal guidelines deal efficiently with the geostationary lowinclination, low-eccentricity satellites but fail to efficiently regulate the whole geosynchronous region. In this work, we revisit the problem of geosynchronous disposal orbits, trying to identify all possible mechanisms for designing effective disposal strategies. Massive numerical simulations are coupled with optimization techniques and semi-analytical modelling to achieve this goal.
Miguel, N.; Colombo, C.
Planar Orbit and Attitude Dynamics of an Earth-Orbiting Solar Sail Under J2 and Atmospheric Drag Effects Inproceedings
In: 2018 AAS/AIAA Astrodynamics Specialist Conference, pp. 299-319, Snowbird, UT, USA, 2018.
@inproceedings{Miguel2018inproceedings,
title = {Planar Orbit and Attitude Dynamics of an Earth-Orbiting Solar Sail Under J2 and Atmospheric Drag Effects},
author = {Miguel, N. and Colombo, C.},
year = {2018},
date = {2018-01-01},
booktitle = {2018 AAS/AIAA Astrodynamics Specialist Conference},
volume = {167},
pages = {299-319},
address = {Snowbird, UT, USA},
abstract = {In this paper we study planar orbit and attitude dynamics of an uncontrolled spacecraft taking on-board a deorbiting device such as a drag or solar sail. The dynamics is studied in mean Keplerian elements and restricted to rotations around one of the principal axes of the spacecraft. We consider spacecraft with a simplified version of a solar sail with pyramidal shape to restrict ourselves to planar motion, and we investigate stable or slowly-varying attitudes affected by disturbances due to the Earth oblateness effect, solar radiation pressure, and atmospheric drag, with special emphasis on orbits above 800 km of altitude. A sensitivity analysis on the aperture of the sail is performed.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
In this paper we study planar orbit and attitude dynamics of an uncontrolled spacecraft taking on-board a deorbiting device such as a drag or solar sail. The dynamics is studied in mean Keplerian elements and restricted to rotations around one of the principal axes of the spacecraft. We consider spacecraft with a simplified version of a solar sail with pyramidal shape to restrict ourselves to planar motion, and we investigate stable or slowly-varying attitudes affected by disturbances due to the Earth oblateness effect, solar radiation pressure, and atmospheric drag, with special emphasis on orbits above 800 km of altitude. A sensitivity analysis on the aperture of the sail is performed.
Gonzalo, J. L.; Colombo, C.; Di Lizia, P.
Collision Avoidance Manoeuvre Design and Application to Passive Deorbiting Missions Inproceedings
In: Workshop 2018AMC70, Pisa, Italy, 2018.
@inproceedings{Gonzalo2018inproceedings,
title = {Collision Avoidance Manoeuvre Design and Application to Passive Deorbiting Missions},
author = {Gonzalo, J. L. and Colombo, C. and Di Lizia, P.},
year = {2018},
date = {2018-01-01},
booktitle = {Workshop 2018AMC70},
address = {Pisa, Italy},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
GONZALO GÓMEZ, JUAN LUIS; Colombo, C.; Di Lizia, P.
Analysis and Design of Collision Avoidance Maneuvers for Passive De-Orbiting Missions Inproceedings
In: 2018 AAS/AIAA Astrodynamics Specialist Conference, pp. 2189-2208, Snowbird, UT, USA, 2018.
@inproceedings{GONZALO2018inproceedingsb,
title = {Analysis and Design of Collision Avoidance Maneuvers for Passive De-Orbiting Missions},
author = {GONZALO GÓMEZ, JUAN LUIS and Colombo, C. and Di Lizia, P.},
year = {2018},
date = {2018-01-01},
booktitle = {2018 AAS/AIAA Astrodynamics Specialist Conference},
volume = {167},
pages = {2189-2208},
address = {Snowbird, UT, USA},
abstract = {Collision avoidance maneuvers (CAMs) for passive de-orbiting missions using sails are studied, maneuvering either the sail or the incoming object. Analytical expressions for the CAM are obtained leveraging the proximal motion equations, maximizing the total or b-plane-contained deviation, or minimizing collision probability. When the sail performs the CAM, different attitude-related strategies are investigated. Representative test cases are proposed using data from ESA's MASTER tool or conjunction data messages. The required amount of propellant or sail maneuverability as function of lead time is traded-off, and the evolution in time of the covariance matrix is investigated.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Collision avoidance maneuvers (CAMs) for passive de-orbiting missions using sails are studied, maneuvering either the sail or the incoming object. Analytical expressions for the CAM are obtained leveraging the proximal motion equations, maximizing the total or b-plane-contained deviation, or minimizing collision probability. When the sail performs the CAM, different attitude-related strategies are investigated. Representative test cases are proposed using data from ESA's MASTER tool or conjunction data messages. The required amount of propellant or sail maneuverability as function of lead time is traded-off, and the evolution in time of the covariance matrix is investigated.
Huang, Simeng; Colombo, C.; Bernelli Zazzera, F.
Orbit Raising and De-Orbit for Coplanar Satellite Constellations with Low-Thrust Propulsion Inproceedings
In: 4th IAA Conference on Dynamics and Control of Space Systems (DyCoSS 2018), pp. 95-122, Changsha, China, 2018.
@inproceedings{Huang2018inproceedings,
title = {Orbit Raising and De-Orbit for Coplanar Satellite Constellations with Low-Thrust Propulsion},
author = {Huang, Simeng and Colombo, C. and Bernelli Zazzera, F.},
year = {2018},
date = {2018-01-01},
booktitle = {4th IAA Conference on Dynamics and Control of Space Systems (DyCoSS 2018)},
volume = {165},
pages = {95-122},
address = {Changsha, China},
abstract = {This paper deals with the planar transfer problem (i.e. orbit raising and deorbiting phases) for low Earth orbit coplanar satellites constellation. The objectives are to minimize the total time of transfer and to maximize the miss distance during these phases so as to minimize the collision hazard. A Blended Error- Correction (BEC) steering law, consisting of tangential thrust and inertial thrust based on the offset in mean orbital parameters, is developed to design the transfer trajectory for a single satellite. The semi-analytical technique is used to evaluate the variation in orbital parameters over one orbit revolution to reduce the computation load. The numerical results show that the BEC steering law is able to identify near time-optimal solutions and the semi-analytical results have good accuracy. For multiple satellites transfer, the orbit transfer trajectory designed for a single satellite is used as a baseline for a global multi-satellite analysis of the miss distance among pair satellites during the orbit raising and de-orbiting phases. Considering limits on the transfer starting time for de-orbit mission, multi-objective optimization is used to find out the optimal transfer starting time for each satellite.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
This paper deals with the planar transfer problem (i.e. orbit raising and deorbiting phases) for low Earth orbit coplanar satellites constellation. The objectives are to minimize the total time of transfer and to maximize the miss distance during these phases so as to minimize the collision hazard. A Blended Error- Correction (BEC) steering law, consisting of tangential thrust and inertial thrust based on the offset in mean orbital parameters, is developed to design the transfer trajectory for a single satellite. The semi-analytical technique is used to evaluate the variation in orbital parameters over one orbit revolution to reduce the computation load. The numerical results show that the BEC steering law is able to identify near time-optimal solutions and the semi-analytical results have good accuracy. For multiple satellites transfer, the orbit transfer trajectory designed for a single satellite is used as a baseline for a global multi-satellite analysis of the miss distance among pair satellites during the orbit raising and de-orbiting phases. Considering limits on the transfer starting time for de-orbit mission, multi-objective optimization is used to find out the optimal transfer starting time for each satellite.
Nugnes, M.; Colombo, C.; Tipaldi, M.
A system engineering tool for the optimisation of a GNSS constellation design Inproceedings
In: 5th IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace), pp. 300-304, Roma, Italy, 2018.
@inproceedings{Nugnes2018inproceedings,
title = {A system engineering tool for the optimisation of a GNSS constellation design},
author = {Nugnes, M. and Colombo, C. and Tipaldi, M.},
url = {https://doi.org/10.1109/MetroAeroSpace.2018.8453600},
doi = {http://dx.doi.org/10.1109/MetroAeroSpace.2018.8453600},
year = {2018},
date = {2018-01-01},
booktitle = {5th IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace)},
pages = {300-304},
address = {Roma, Italy},
abstract = {This paper introduces a system engineering tool for the optimisation of a generic GNSS constellation design by using Galileo as reference. The optimisation is performed by taking into account both the percentage of global coverage and the accuracy in the position determination. The tool executes the optimisation not only for nominal and ideal cases, but also for off-nominal configurations involving catastrophic or transient failures of the constellation satellites. The analysis of the GNSS robustness to failures changes considerably the number of satellites to be used per plane with respect to the original configuration designed in nominal conditions.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
This paper introduces a system engineering tool for the optimisation of a generic GNSS constellation design by using Galileo as reference. The optimisation is performed by taking into account both the percentage of global coverage and the accuracy in the position determination. The tool executes the optimisation not only for nominal and ideal cases, but also for off-nominal configurations involving catastrophic or transient failures of the constellation satellites. The analysis of the GNSS robustness to failures changes considerably the number of satellites to be used per plane with respect to the original configuration designed in nominal conditions.
Letterio, F.; Alessi, E. M.; Gkolias, I.; Skoulidou, D. K.; Schaus, V.; Beck, J.; Vicario de Miguel, G.; Schettino, G.; Rossi, A.; Colombo, C.; Tsiganis, K.; Holbrough, I.; Miguel, N.
ReDSHIFT Software Tool for the Design and Computation of Mission End-of-Life Disposal Inproceedings
In: 7th International Conference on Astrodynamics Tools and Techniques (ICATT), pp. 1-9, Oberpfaffenhofen, Germany, 2018.
@inproceedings{Letterio2018inproceedings,
title = {ReDSHIFT Software Tool for the Design and Computation of Mission End-of-Life Disposal},
author = {Letterio, F. and Alessi, E. M. and Gkolias, I. and Skoulidou, D. K. and Schaus, V. and Beck, J. and Vicario de Miguel, G. and Schettino, G. and Rossi, A. and Colombo, C. and Tsiganis, K. and Holbrough, I. and Miguel, N.},
url = {http://hdl.handle.net/11311/1121783},
year = {2018},
date = {2018-00-01},
booktitle = {7th International Conference on Astrodynamics Tools and Techniques (ICATT)},
pages = {1-9},
address = {Oberpfaffenhofen, Germany},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Garcıa Pelayo, R.; Gonzalo, J. L.; Bombardelli, C.
Rate and Collision Probability of Tethers and Sails Against Debris or Spacecraft Inproceedings
In: 7th International Conference on Astrodynamics Tools and Techniques (ICATT), pp. 1-11, Oberpfaffenhofen, Germany, 2018.
@inproceedings{Garcıa2018inproceedings,
title = {Rate and Collision Probability of Tethers and Sails Against Debris or Spacecraft},
author = {Garcıa Pelayo, R. and Gonzalo, J. L. and Bombardelli, C.},
url = {http://hdl.handle.net/11311/1121309},
year = {2018},
date = {2018-00-01},
booktitle = {7th International Conference on Astrodynamics Tools and Techniques (ICATT)},
pages = {1-11},
address = {Oberpfaffenhofen, Germany},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
2017
Menzio, Davide; Colombo, Camilla
The Combined Lambert-Tisserand Method Applied to the Single Flyby Problem Inproceedings
In: 68th International Astronautical Congress (IAC 2017), pp. 765-776, Adelaide, Australia, 2017.
@inproceedings{Menzio2017inproceedings,
title = {The Combined Lambert-Tisserand Method Applied to the Single Flyby Problem},
author = {Menzio, Davide and Colombo, Camilla},
url = {http://hdl.handle.net/11311/1034741},
year = {2017},
date = {2017-09-01},
booktitle = {68th International Astronautical Congress (IAC 2017)},
pages = {765-776},
address = {Adelaide, Australia},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Colombo, C.; Gkolias, Ioannis
Analysis of Orbit Stability in the Geosynchronous Region for End-Of-life Disposal Inproceedings
In: 7th European Conference on Space Debris, ESA/ESOC, pp. 1-14, Darmstadt, Germany, 2017.
@inproceedings{Colombo2017inproceedingsb,
title = {Analysis of Orbit Stability in the Geosynchronous Region for End-Of-life Disposal},
author = {Colombo, C. and Gkolias, Ioannis},
url = {http://hdl.handle.net/11311/1047164},
year = {2017},
date = {2017-04-01},
booktitle = {7th European Conference on Space Debris, ESA/ESOC},
pages = {1-14},
address = {Darmstadt, Germany},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Trisolini, M.; Lewis, H. G.; Colombo, C.
On the Demisability and Survivability of Modern Spacecraft Inproceedings
In: 7th European Conference on Space Debris, ESA/ESOC, pp. 1-15, Darmstadt, Germany, 2017.
@inproceedings{Trisolini2017inproceedings,
title = {On the Demisability and Survivability of Modern Spacecraft},
author = {Trisolini, M. and Lewis, H. G. and Colombo, C.},
url = {http://hdl.handle.net/11311/1047143},
year = {2017},
date = {2017-04-01},
booktitle = {7th European Conference on Space Debris, ESA/ESOC},
pages = {1-15},
address = {Darmstadt, Germany},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Colombo, C.; Letizia, F.; Trisolini, M.; Lewis, H.; Chanoine, A.; Duvernois, P. A.; Austin, J.; Lemmens, S.
Life Cycle Assessment Indicator for Space Debris Inproceedings
In: 7th European Conference on Space Debris, ESA/ESOC, pp. 1-12, Darmstadt, Germany, 2017.
@inproceedings{Colombo2017inproceedings,
title = {Life Cycle Assessment Indicator for Space Debris},
author = {Colombo, C. and Letizia, F. and Trisolini, M. and Lewis, H. and Chanoine, A. and Duvernois, P. A. and Austin, J. and Lemmens, S.},
url = {http://hdl.handle.net/11311/1047157},
year = {2017},
date = {2017-04-01},
booktitle = {7th European Conference on Space Debris, ESA/ESOC},
pages = {1-12},
address = {Darmstadt, Germany},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Frey, Stefan; Colombo, Camilla; Lemmens, S.; Krag, H.
Evolution of Fragmentation Cloud in Highly Eccentric Orbit Using Representative Objects Inproceedings
In: 68th International Astronautical Congress (IAC 2017), pp. 3526-3536, Adelaide, Australia, 2017.
@inproceedings{Frey2017inproceedings,
title = {Evolution of Fragmentation Cloud in Highly Eccentric Orbit Using Representative Objects},
author = {Frey, Stefan and Colombo, Camilla and Lemmens, S. and Krag, H.},
year = {2017},
date = {2017-01-01},
booktitle = {68th International Astronautical Congress (IAC 2017)},
pages = {3526-3536},
address = {Adelaide, Australia},
abstract = {Many historical on-orbit satellite fragmentations occurred in Highly Eccentric Orbits (HEOs) such as the Geostationary Transfer Orbit (GTO). Such fragmentations produce fragment clouds that interfere with the Low Earth Orbit (LEO) environment and pose a threat to operational satellites. Objects in HEO undergo complex dynamics due to the influence of perturbations varying as a function mainly of their altitude and area-to-mass ratio. The evolution of such a cloud, including small objects down to 1 mm, is not well understood. This paper describes a method to model the evolution of a fragmentation cloud in HEO under the influence of atmospheric drag and Earth's oblateness. Semi-analytical techniques are applied to propagate represen- tative objects constituting the cloud; rather than following the evolution of many distinct fragments. The proposed method is applied on a GTO upper stage using the standard NASA break-up model to nd the distribution right after the fragmentation. The evolution of the fragment cloud is analysed statistically and time of closures are calculated for the formation of the torus along the parent orbit and the band around Earth. Assumptions on the evolution of the cloud that are valid in LEO are shown to be invalid for clouds in HEO.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Many historical on-orbit satellite fragmentations occurred in Highly Eccentric Orbits (HEOs) such as the Geostationary Transfer Orbit (GTO). Such fragmentations produce fragment clouds that interfere with the Low Earth Orbit (LEO) environment and pose a threat to operational satellites. Objects in HEO undergo complex dynamics due to the influence of perturbations varying as a function mainly of their altitude and area-to-mass ratio. The evolution of such a cloud, including small objects down to 1 mm, is not well understood. This paper describes a method to model the evolution of a fragmentation cloud in HEO under the influence of atmospheric drag and Earth's oblateness. Semi-analytical techniques are applied to propagate represen- tative objects constituting the cloud; rather than following the evolution of many distinct fragments. The proposed method is applied on a GTO upper stage using the standard NASA break-up model to nd the distribution right after the fragmentation. The evolution of the fragment cloud is analysed statistically and time of closures are calculated for the formation of the torus along the parent orbit and the band around Earth. Assumptions on the evolution of the cloud that are valid in LEO are shown to be invalid for clouds in HEO.
Gkolias, Ioannis; Colombo, Camilla
End-of-life disposal of geosynchronous satellites Inproceedings
In: 68th International Astronautical Congress (IAC 2017), pp. 3613-3619, Adelaide, Australia, 2017.
@inproceedings{Gkolias2017inproceedings,
title = {End-of-life disposal of geosynchronous satellites},
author = {Gkolias, Ioannis and Colombo, Camilla},
year = {2017},
date = {2017-01-01},
booktitle = {68th International Astronautical Congress (IAC 2017)},
journal = {Proceedings of the International Astronautical Congress},
volume = {6},
pages = {3613-3619},
address = {Adelaide, Australia},
abstract = {End-of-life disposal of spacecraft in the GEO region is required for the further exploitation of this particularly important orbital regime. The orbital dynamics around the geostationary ring can be exploited for designing graveyard orbits or looking for re-entry solutions. Here we present an end-of-life trajectory design method based on a detailed cartography of the orbital space. Given a post-mission orbit of a decommissioned satellite and the available fuel on board, efficient two-burn transfers are calculated for each reachable orbit on the grid. Furthermore, an analysis of cost (delta-v) versus stability of target orbit or re-entry time is performed by means of finding the Pareto optimal solutions for each case.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
End-of-life disposal of spacecraft in the GEO region is required for the further exploitation of this particularly important orbital regime. The orbital dynamics around the geostationary ring can be exploited for designing graveyard orbits or looking for re-entry solutions. Here we present an end-of-life trajectory design method based on a detailed cartography of the orbital space. Given a post-mission orbit of a decommissioned satellite and the available fuel on board, efficient two-burn transfers are calculated for each reachable orbit on the grid. Furthermore, an analysis of cost (delta-v) versus stability of target orbit or re-entry time is performed by means of finding the Pareto optimal solutions for each case.
Romano, Matteo; Colombo, Camilla; Sánchez Pérez, J. M.
Verification of Planetary Protection Requirements with Symplectic Methods and Monte Carlo Line Sampling Inproceedings
In: 68th International Astronautical Congress (IAC 2017), pp. 7574-7588, Adelaide, Australia, 2017.
@inproceedings{Romano2017inproceedings,
title = {Verification of Planetary Protection Requirements with Symplectic Methods and Monte Carlo Line Sampling},
author = {Romano, Matteo and Colombo, Camilla and Sánchez Pérez, J. M.},
url = {https://iafastro.directory/iac/paper/id/41062/summary/},
year = {2017},
date = {2017-01-01},
booktitle = {68th International Astronautical Congress (IAC 2017)},
pages = {7574-7588},
address = {Adelaide, Australia},
abstract = {Verification of the compliance to planetary protection requirements is an important task of interplanetary mission design, aiming to reduce the risk of biological contamination of scientifically interesting celestial bodies. This kind of analysis requires efficient and reliable numerical tools to propagate uncertainties over times up to 100 years with high precision. This paper presents a plan to improve the techniques used for planetary protection analysis in the SNAPPshot numerical tool developed at the University of Southampton for an ESA study. The Line Sampling method is presented as an alternative Monte Carlo approach to sample more efficiently the initial uncertainties, reducing the computational effort to estimate the probability of impact between uncontrolled objects and a celestial body. Symplectic integration methods are introduced as a strategy to obtain a more accurate propagation of the spacecraft trajectory starting from the initial conditions, thanks to their formulation that includes the conservation of total energy. Preliminary results are included to show the advantages and the current limitations of the proposed approaches.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
Verification of the compliance to planetary protection requirements is an important task of interplanetary mission design, aiming to reduce the risk of biological contamination of scientifically interesting celestial bodies. This kind of analysis requires efficient and reliable numerical tools to propagate uncertainties over times up to 100 years with high precision. This paper presents a plan to improve the techniques used for planetary protection analysis in the SNAPPshot numerical tool developed at the University of Southampton for an ESA study. The Line Sampling method is presented as an alternative Monte Carlo approach to sample more efficiently the initial uncertainties, reducing the computational effort to estimate the probability of impact between uncontrolled objects and a celestial body. Symplectic integration methods are introduced as a strategy to obtain a more accurate propagation of the spacecraft trajectory starting from the initial conditions, thanks to their formulation that includes the conservation of total energy. Preliminary results are included to show the advantages and the current limitations of the proposed approaches.
Gonzalo, J. L.; Bombardelli, C.; Topputo, F.
Unified Formulation for Element-Based Indirect Trajectory Optimization Inproceedings
In: 26th International Symposium on Space Flight Dynamics, pp. 1-6, Matsuyama, Japan, 2017.
@inproceedings{Gonzalo2017inproceedings,
title = {Unified Formulation for Element-Based Indirect Trajectory Optimization},
author = {Gonzalo, J. L. and Bombardelli, C. and Topputo, F.},
url = {http://issfd.org/ISSFD_2017/paper/ISTS-2017-d-116__ISSFD-2017-116.pdf},
year = {2017},
date = {2017-01-01},
booktitle = {26th International Symposium on Space Flight Dynamics},
pages = {1-6},
address = {Matsuyama, Japan},
abstract = {A general mathematical framework is presented to treat low thrust trajectory optimization problems using the indirect method and employing a generic set of orbital elements (e.g. classical elements, equinoctial, etc.). An algebraic manipulation of the optimality conditions stemming from Pontryagin Maximum Principle reveals the existence of a new quadratic form of the costate, which governs the costate contribution in all the equations of the first order necessary optimality conditions. The quadratic form provides a simple tool for the mathematical development of the optimality conditions for any chosen set of orbital elements and greatly simplifies the computation of a state transition matrix needed in order to improve the convergence of the associated two-point boundary value problem. Objective functions corresponding to minimum-time, minimum-energy and minimum-fuel problems are considered.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
A general mathematical framework is presented to treat low thrust trajectory optimization problems using the indirect method and employing a generic set of orbital elements (e.g. classical elements, equinoctial, etc.). An algebraic manipulation of the optimality conditions stemming from Pontryagin Maximum Principle reveals the existence of a new quadratic form of the costate, which governs the costate contribution in all the equations of the first order necessary optimality conditions. The quadratic form provides a simple tool for the mathematical development of the optimality conditions for any chosen set of orbital elements and greatly simplifies the computation of a state transition matrix needed in order to improve the convergence of the associated two-point boundary value problem. Objective functions corresponding to minimum-time, minimum-energy and minimum-fuel problems are considered.
Gonzalo, J. L; Topputo, Francesco; Armellin, Roberto
Indirect Optimization of End-of-Life Disposal for Galileo Constellation Using Low Thrust Propulsion Inproceedings
In: 26th International Symposium on Space Flight Dynamics, pp. 1-6, Matsuyama, Japan, 2017.
@inproceedings{Gonzalo2017inproceedingsb,
title = {Indirect Optimization of End-of-Life Disposal for Galileo Constellation Using Low Thrust Propulsion},
author = {Gonzalo, J. L and Topputo, Francesco and Armellin, Roberto},
url = {http://issfd.org/ISSFD_2017/paper/ISTS-2017-d-103__ISSFD-2017-103.pdf},
year = {2017},
date = {2017-01-01},
booktitle = {26th International Symposium on Space Flight Dynamics},
pages = {1-6},
address = {Matsuyama, Japan},
abstract = {In this work, the end-of-life disposal of satellites in the Galileo constellation using low thrust propulsion is studied. Indirect optimization methods are employed to design transfer maneuvers to remove the satellite from its original operational orbit into previously computed orbits leading to its natural re-entry within 100 years due to lunisolar perturbation effects. The dynamics are formulated using the modified equinoctial elements, which allow expressing the boundary conditions in a simple way at the cost of more complex equations compared to the use of Cartesian coordinates. A special focus is placed in defining an efficient and robust algorithm for solving the two point boundary value problem arising from the first order optimality conditions, including the integration of the analytically-derived variational equations to obtain the State Transition Matrix, and the accurate detection of thrust-switching events. The numerical results obtained for several test cases show the practical feasibility of this end-of-life disposal approach at thrust levels compatible with electric thrusters likely to be used by the next generation of Galileo satellites.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
In this work, the end-of-life disposal of satellites in the Galileo constellation using low thrust propulsion is studied. Indirect optimization methods are employed to design transfer maneuvers to remove the satellite from its original operational orbit into previously computed orbits leading to its natural re-entry within 100 years due to lunisolar perturbation effects. The dynamics are formulated using the modified equinoctial elements, which allow expressing the boundary conditions in a simple way at the cost of more complex equations compared to the use of Cartesian coordinates. A special focus is placed in defining an efficient and robust algorithm for solving the two point boundary value problem arising from the first order optimality conditions, including the integration of the analytically-derived variational equations to obtain the State Transition Matrix, and the accurate detection of thrust-switching events. The numerical results obtained for several test cases show the practical feasibility of this end-of-life disposal approach at thrust levels compatible with electric thrusters likely to be used by the next generation of Galileo satellites.
Trisolini, Mirko; Lewis, Hugh G.; Colombo, Camilla
Demisability and survivability multi-objective optimisation for preliminary spacecraft design Inproceedings
In: 68th International Astronautical Congress (IAC 2017), pp. 366-385, Adelaide, Australia, 2017.
@inproceedings{Trisolini2017inproceedingsb,
title = {Demisability and survivability multi-objective optimisation for preliminary spacecraft design},
author = {Trisolini, Mirko and Lewis, Hugh G. and Colombo, Camilla},
year = {2017},
date = {2017-01-01},
booktitle = {68th International Astronautical Congress (IAC 2017)},
volume = {1},
pages = {366-385},
address = {Adelaide, Australia},
abstract = {In a period where the evolution of the space environment is causing increasing concerns for the future of space exploitation and sustainability, the design-for-demise philosophy has gained an increased interest. However, building a spacecraft such that most of it will demise through design-for-demise strategies may lead to designs that are more vulnerable to space debris impacts, thus compromising the reliability of the mission. Demisable designs will tend to favour lighter materials, thinner structures, and more exposed components, whereas survivability oriented designs will favour denser materials, thicker structures, and more protected components. Given the competing nature of the demisability and the survivability, we developed a multi-objective optimisation framework to evaluate the effect of preliminary design choices on the survivability and demisability of spacecraft components since the early stages of the mission design. The framework relies on a demisability and a survivability model, whose output is used to compute the fitness functions of the multi-objective optimisation. The paper presents the latest development of the survivability model, including a novel methodology to compute the vulnerability of spacecraft components. In addition, a representative test case of tank assemblies of Earth observation and remote sensing missions is studied with the multiobjective optimisation framework.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
In a period where the evolution of the space environment is causing increasing concerns for the future of space exploitation and sustainability, the design-for-demise philosophy has gained an increased interest. However, building a spacecraft such that most of it will demise through design-for-demise strategies may lead to designs that are more vulnerable to space debris impacts, thus compromising the reliability of the mission. Demisable designs will tend to favour lighter materials, thinner structures, and more exposed components, whereas survivability oriented designs will favour denser materials, thicker structures, and more protected components. Given the competing nature of the demisability and the survivability, we developed a multi-objective optimisation framework to evaluate the effect of preliminary design choices on the survivability and demisability of spacecraft components since the early stages of the mission design. The framework relies on a demisability and a survivability model, whose output is used to compute the fitness functions of the multi-objective optimisation. The paper presents the latest development of the survivability model, including a novel methodology to compute the vulnerability of spacecraft components. In addition, a representative test case of tank assemblies of Earth observation and remote sensing missions is studied with the multiobjective optimisation framework.
Huang, S.; Colombo, C.; Bernelli Zazzera, F.
Comparative Assessment Of Different Constellation Geometries For Space-Based Application Inproceedings
In: 68th International Astronautical Congress (IAC 2017), pp. 887-903, Adelaide, Australia, 2017.
@inproceedings{Huang2017inproceedings,
title = {Comparative Assessment Of Different Constellation Geometries For Space-Based Application},
author = {Huang, S. and Colombo, C. and Bernelli Zazzera, F.},
year = {2017},
date = {2017-01-01},
booktitle = {68th International Astronautical Congress (IAC 2017)},
pages = {887-903},
address = {Adelaide, Australia},
abstract = {As services from space are becoming an asset for life on Earth and the demand for data from space increases, the international interest in satellite constellations is increasingly growing. GPS (Global Positioning System) provides positioning and navigation. Iridium contains a relatively larger number of satellites for communication purpose. Molniya is a high elliptical orbits constellation providing high latitude coverage. Disaster Monitoring constellation consists of remote sensing satellites and brings responsiveness needed for emergencies. Recently, some companies, such as OneWeb, Samsung and Space-X, have made public their plan to deploy mega constellations of nanosatellites for global internet. Different constellation geometries have been proposed to meet various mission requirements, each one having specific advantages in terms of coverage, responsiveness, cost, etc. Thus, designing a constellation is a trade-off choice. The choice for a constellation is highly influenced by many factors, such as the system cost, the interaction with space environment (radiation and space debris), and the targeted terrestrial coverage. The design of a constellation requires selecting the parameters that best meet the mission requirements. To accomplish this, several studies on the comparison of satellite constellations proposed detailed analysis, e.g. the multi-criteria comparison for responsive constellations, the coverage assessment of elliptical constellations. However, most of them only focused on one or few performances, lacking of generalisation. A general study of constellation geometry can provide a basis for understanding the constellation design. This will allow the process of constellation design to be expedited by offering a proposal of an existing constellation style. This paper comparatively assesses different constellation geometries, including the classical proposed geometries and some less used configurations, and chooses the constellation geometry best suitable for a given mission (e.g. remote sensing, global internet). In this work, several parameters of constellation design will be considered to make a quantitative assessment: coverage (global or local), frequency of ground track repetition, responsiveness (i.e., how fast a satellite can be launched and the data return to Earth after launch), robustness to failure and speed of replenishment, end of life disposal, number of satellites and orbital altitude. The assessment will be conducted in a parametric approach. Each factor will be quantitatively evaluated by deriving a fitness function. Then, a series of weighting coefficients adapted to the given mission requirements will be chosen for the global fitness functions. Through multi objective optimisation, the constellation geometry best suitable for the given mission requirements will be derived.},
keywords = {},
pubstate = {published},
tppubtype = {inproceedings}
}
As services from space are becoming an asset for life on Earth and the demand for data from space increases, the international interest in satellite constellations is increasingly growing. GPS (Global Positioning System) provides positioning and navigation. Iridium contains a relatively larger number of satellites for communication purpose. Molniya is a high elliptical orbits constellation providing high latitude coverage. Disaster Monitoring constellation consists of remote sensing satellites and brings responsiveness needed for emergencies. Recently, some companies, such as OneWeb, Samsung and Space-X, have made public their plan to deploy mega constellations of nanosatellites for global internet. Different constellation geometries have been proposed to meet various mission requirements, each one having specific advantages in terms of coverage, responsiveness, cost, etc. Thus, designing a constellation is a trade-off choice. The choice for a constellation is highly influenced by many factors, such as the system cost, the interaction with space environment (radiation and space debris), and the targeted terrestrial coverage. The design of a constellation requires selecting the parameters that best meet the mission requirements. To accomplish this, several studies on the comparison of satellite constellations proposed detailed analysis, e.g. the multi-criteria comparison for responsive constellations, the coverage assessment of elliptical constellations. However, most of them only focused on one or few performances, lacking of generalisation. A general study of constellation geometry can provide a basis for understanding the constellation design. This will allow the process of constellation design to be expedited by offering a proposal of an existing constellation style. This paper comparatively assesses different constellation geometries, including the classical proposed geometries and some less used configurations, and chooses the constellation geometry best suitable for a given mission (e.g. remote sensing, global internet). In this work, several parameters of constellation design will be considered to make a quantitative assessment: coverage (global or local), frequency of ground track repetition, responsiveness (i.e., how fast a satellite can be launched and the data return to Earth after launch), robustness to failure and speed of replenishment, end of life disposal, number of satellites and orbital altitude. The assessment will be conducted in a parametric approach. Each factor will be quantitatively evaluated by deriving a fitness function. Then, a series of weighting coefficients adapted to the given mission requirements will be chosen for the global fitness functions. Through multi objective optimisation, the constellation geometry best suitable for the given mission requirements will be derived.