Low-Thrust Many-Revolution Trajectory Optimization via Differential Dynamic Programming and a Sundman Transformation

被引：0
作者：
Jonathan D. Aziz
Jeffrey S. Parker
Daniel J. Scheeres
Jacob A. Englander
机构：
[1] University of Colorado,Colorado Center for Astrodynamics Research
[2] Advanced Space,Colorado Center for Astrodynamics Research
[3] University of Colorado,undefined
[4] NASA/GSFC,undefined
来源：
The Journal of the Astronautical Sciences | 2018年 / 65卷
关键词：
Low-thrust; Trajectory optimization; Differential dynamic programming; Sundman transformation;
D O I：
暂无
中图分类号：
学科分类号：
摘要：
Low-thrust trajectories about planetary bodies characteristically span a high count of orbital revolutions. Directing the thrust vector over many revolutions presents a challenging optimization problem for any conventional strategy. This paper demonstrates the tractability of low-thrust trajectory optimization about planetary bodies by applying a Sundman transformation to change the independent variable of the spacecraft equations of motion to an orbit angle and performing the optimization with differential dynamic programming. Fuel-optimal geocentric transfers are computed with the transfer duration extended up to 2000 revolutions. The flexibility of the approach to higher fidelity dynamics is shown with Earth’s J2 perturbation and lunar gravity included for a 500 revolution transfer.
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页码：205 / 228
页数：23
相关论文
共 29 条
  • [1] Edelbaum T(1961)Propulsion requirements for controllable satellites ARS J. 31 1079-1089
  • [2] Wiesel WE(1985)Optimal many-revolution orbit transfer J. Guid. Control. Dyn. 8 155-157
  • [3] Alfano S(1964)Optimum low-thrust rendezvous and station keeping AIAA J. 2 1196-1201
  • [4] Edelbaum TN(1996)Optimal low-thrust rendezvous using equinoctial orbit elements Acta Astronaut. 38 1-14
  • [5] Kéchichian JA(2009)Optimal low-thrust transfer in general circular orbit using analytic averaging of the system dynamics J. Astronaut. Sci. 57 369-392
  • [6] Kéchichian JA(2008)Inclusion of higher order harmonics in the modeling of optimal low-thrust orbit transfer J. Astronaut. Sci. 56 41-70
  • [7] Kéchichian JA(1998)Simple guidance scheme for low-thrust orbit transfers J. Guid. Control. Dyn. 21 1015-1017
  • [8] Kluever CA(2002)Lyapunov-based transfer between elliptic Keplerian orbits Discrete Contin. Dyn. Syst.-Ser. B 2 57-67
  • [9] Chang DE(2000)Very low-thrust trajectory optimization using a direct SQP method J. Comput. Appl. Math. 120 27-40
  • [10] Chichka DF(2003)Optimal low thrust trajectories to the moon SIAM J. Appl. Dyn. Syst. 2 144-170
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