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Trajectory correction for lunar flyby transfers to libration point orbits using continuous thrust

Astrodynamics 2022年第3期6卷 285-300页

作者： Yi Qi Anton de Ruiter School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China Department of Aerospace Engineering Ryerson UniversityTorontoON M5B 2K3Canada

Trajectory corrections for lunar flyby transfers to Sun–Earth/Moon libration point orbits(LPOs)with continuous thrusts are investigated using an ephemeris *** lunar flyby transfer has special geometrical and dynamical structures;therefore,its trajectory correction strategy is considerably different from that of previous studies and should be specifically *** this paper,we first propose a control strategy based on the backstepping technique with a dead-band scheme using an ephemeris *** initial error caused by the launch time error is *** the perturbed transfers significantly diverge from the reference transfers after the spacecraft passes by the Moon,we adopt two sets of control parameters in two portions before and after the lunar flyby,***,practical constraints owing to the navigation and propellant systems are introduced in the dynamical model of the trajectory *** a prograde type 2 orbit as an example,numerical simulations show that our control strategy can efficiently address trajectory corrections for lunar flyby transfers with different practical *** addition,we analyze the effects of the navigation intervals and dead-band scheme on trajectory ***,trajectory corrections for different lunar flyby transfers are depicted and compared.

关键词： libration point orbit trajectory correction Earth-Moon system continuous thrust backstepping technique

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Near-optimal cumulative longitude low-thrust orbit transfer

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Journal of Systems Engineering and Electronics 2009年第6期20卷 1271-1277页

作者： Yue Xincheng Yang Ying Geng Zhiyong State Key Lab. for Turbulence and Complex System Dept. of Mechanics and Aerospace Engineering Coll. of Engineering Peking Univ. Beijing 100871 P. R. China

The indirect method for the continuous low-thrust near minimum cumulative longitude orbit transfer problem is *** movement of the satellite is described by the Gauss equation using the modified equinoctial elements and replacing time as the system independent variable by the cumulative *** maximum principle is adapted to design the optimal control in order to minimize the final cumulative longitude, and the twopoint-boundary-value problem is derived from the orbit transfer *** single shooting method is applied in a numerical experiment, and the simulations demonstrate that the orbit transfer mission is fulfilled and the product of the maximal thrust and the minimum cumulative longitude is near constant.

关键词： minimum cumulative longitude orbit transfer continuous thrust maximum principle shooting method.

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Nash-equilibrium strategies of orbital TargetAttacker-Defender game with a non-maneuvering target

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Chinese Journal of Aeronautics 2024年第10期37卷 365-379页

作者： Yifeng LI Xi LIANG Zhaohui DANG School of Astronautics Northwestern Polytechnical UniversityXi’an 710072China Beijing Institute of Astronautical Systems Engineering Beijing 100076China

This study investigates the orbital Target-Attacker-Defender(TAD)game problem in the context of space *** this game,the Attacker and the Defender compete for a Target that is unable to maneuver due to its original mission *** paper establishes three TAD game models based on the thrust output capabilities:unconstrained thrust output,thrust constrained by an upper bound,and fixed thrust *** models are then solved using differential game theory to obtain Nash equilibrium solutions for the game problems,and the correctness and effectiveness of the solution methods are verified through ***,an analysis of the winning mechanisms of the game is conducted,identifying key factors that influence the game’s outcomes,including weight coefficients in payoffs,the maximum thrust acceleration limit,and the initial game *** the unique characteristics of space missions,a specific focus is given to the analysis of the Defender’s initial states in the hovering formation and in-plane circling formation,revealing overall success patterns for defense strategies from these two *** summary,this study provides valuable insights into the control strategies and winning mechanisms of orbital TAD games,deepening our understanding of these games and offering practical guidance to improve success rates in real-world scenarios.

关键词： Target-Attacker-Defender problem Differential game TPBVP continuous thrust Orbital game

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