Direct transcription of low-thrust trajectories with finite trajectory elements

Zuiani, Federico; Vasile, Massimiliano; Palmas, Alessandro; Avanzini, Giulio

doi:10.1016/j.actaastro.2011.09.011

Cited by 46 publications

(39 citation statements)

References 18 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…(10) is not satisfied and the second object is, therefore, not part of the locally pruned database for the current leg.   12â rccos   hh (11) Because a coplanar transfer is taken into account for the simplified trajectory description, a maximum value of  is selected as threshold in order to consider the second object to be part or not of the locally pruned database. This way, objects are not considered where a change of the inclination and/or the longitude of the ascending node would be too large in the three-dimensional case.…”

Section: Local Pruning Of the Databasementioning

confidence: 99%

“…Several methodologies for low-thrust mission design have been studied, for example by using shape-based methods [7,9] or by dividing the trajectory into segments [10] or finite elements [11]. In order to compare high-thrust with low-thrust mission design, Izzo [12] discussed a way to solve two-dimensional versions of Lambert's problem with Petropoulos' shape-based function [13].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Solar-Sail Trajectory Design for a Multiple Near-Earth-Asteroid Rendezvous Mission

Peloni

Ceriotti

Dachwald

2016

Journal of Guidance, Control, and Dynamics

View full text Add to dashboard Cite

Section: Local Pruning Of the Databasementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Solar-Sail Trajectory Design for a Multiple Near-Earth-Asteroid Rendezvous Mission

Peloni

Ceriotti

Dachwald

2016

Journal of Guidance, Control, and Dynamics

View full text Add to dashboard Cite

“…In [68] the cooperative and noncooperative differential games, for a spacecraft rendezvous and formation-flying, are rewritten in the nonlinear multi objective programming problem by using the DFET method [75].…”

Section: Literature Reviewmentioning

confidence: 99%

Game Theoretic Strategies for Spacecraft Rendezvous and Motion Synchronization

Innocenti

Tartaglia

2016

AIAA Guidance, Navigation, and Control Conference

View full text Add to dashboard Cite

One of the main challenges for autonomous spacecraft relative guidance and control is extending the algorithms for autonomous rendezvous and docking (AR&D) operations to multiple collaborative spacecraft.In this thesis, the autonomous rendezvous problem, between two active spacecraft, is formulated as a two player nonzero-sum differential game. The local-vertical local-horizontal (LVLH) rotating reference frame is used to describe the dynamic of the game.The State-Dependent Riccati equation (SDRE) method is applied to extend the Linear Quadratic differential game theory to obtain a feedback control law for nonlinear equation of relative motion. In the simulations both the spacecraft use continuous thrust engines. A comparison among Pareto and Nash equilibrium has been performed.A multiplayer sequential game strategy is used to extend the control law to many spacecraft for relative motion synchronization in an on-orbit self assembly strategy. 2 SommarioUno dei possibili sviluppi della guida e del controllo relativo nello spazio è quella di estendere gli algoritmi per operazioni di rendezvous e di docking autonome a più veicoli spaziali che collaborano tra di loro. Il problema del rendezvous tra due veicoli spaziali viene risolto utilizzando la teoria dei giochi differenziali lineari quadratici. La dinamica del gioco viene descritta in un sistema di riferimento cartesiano non inerziale.Per estendere l'utilizzo della teoria dei giochi differenziali lineari quadratici alle equazioni non lineari di moto relativo è stata utilizzata le tecnica di parametrizzazione in funzione dello stato o linearizzazione estesa. Nelle simulazioni è stato valutato il confronto tra le prestazioni e le traiettorie ottenute con l'equilibrio di Pareto e quello di Nash quando entrambi i veicoli spaziali agiscono sotto spinta continua.Una strategia sequenziale è stata utilizzata per estendere il gioco differenziali a più di due giocatori per avere la sincronizzazione del moto relativo durante operazioni di assemblaggio nello spazio.3

show abstract

“…The simulation model is based on combination of averaging with an analytical solution of low-thrust motion in non-singular orbital elements including the effect of solar pressure, J 2 and the eclipse periods encountered during de-orbiting [16]- [19]. A simple control parametrization is introduced, which aims at ensuring sufficient flexibility while keeping the number of degrees of freedom low.…”

Section: De-orbiting With Low-thrust Propulsionmentioning

confidence: 99%

Effectiveness of GNSS disposal strategies

et al. 2014

View full text Add to dashboard Cite

The management of the Global Navigation Satellite Systems (GNSS) and of the Medium Earth Orbit (MEO) region as a whole is a subject that cannot be deferred, due to the growing exploitation and launch rate in that orbital regime. The advent of the European Galileo and the Chinese Beidou constellations significantly added complexity to the system and call for an adequate global view on the four constellations presently in operation. The operation procedures, including maintenance and disposal practices, of the constellations currently deployed were analyzed in order to asses a proper reference simulation scenario. The complex dynamics of the MEO region with all the geopotential and lunisolar resonances was studied to better identify the proper end-of-life orbit for every proposed strategy, taking into account and, whenever possible, exploiting the orbital dynamics in this peculiar region of space. The possibility to exploit low thrust propulsion or non gravitational perturbations with passive de-orbiting devices (and a combination of the two) was analyzed, in view of possible applications in the design of the future generations of the constellations satellites. Several upgrades in the long-term evolution software SDM and DAMAGE were undertaken to properly handle the constellation simulations in every aspect from constellation maintenance to orbital dynamics. A thorough approach considering the full time evolving covariance matrix associated to every object was implemented in SDM to compute the collision risk and associated maneuver rate for the constellation satellites. Once the software upgrades will be completed, the effectiveness of the different disposal strategies will be analyzed in terms of residual collision risk and avoidance maneuvers rate. This work was performed under the ESA/GSP Contract No. 4000107201/12/F/MOS.

show abstract

Direct transcription of low-thrust trajectories with finite trajectory elements

Cited by 46 publications

References 18 publications

Solar-Sail Trajectory Design for a Multiple Near-Earth-Asteroid Rendezvous Mission

Solar-Sail Trajectory Design for a Multiple Near-Earth-Asteroid Rendezvous Mission

Game Theoretic Strategies for Spacecraft Rendezvous and Motion Synchronization

Effectiveness of GNSS disposal strategies

Contact Info

Product

Resources

About