Sequential Convex Optimization Method for Lunar Landing during Powered Descent Phase

被引：0
|
作者：
Deng Y. [1 ]
Mu R. [1 ]
Peng N. [2 ]
Wu P. [1 ]
机构：
[1] Harbin Institute of Technology, School of Astronautics, Harbin
[2] Shanghai Aerospace Electronic Technology Institute, Shanghai
来源：
Yuhang Xuebao/Journal of Astronautics | 2022年 / 43卷 / 08期
关键词：
Fuel optimal control; Lunar soft landing; Nonlinear programming; Precision landing; Sequential convex optimization;
D O I：
10.3873/j.issn.1000-1328.2022.08.005
中图分类号：
学科分类号：
摘要：
Aiming at the problem that it is difficult to estimate and compensate the time varying inertial acceleration and gravitational acceleration during the powered descent phase of the lunar lander, an online guidance algorithm based on sequential convex optimization is proposed. Firstly, based on the lander dynamic model considering the lunar surface curvature and lunar rotation, the model and constraints are convexified to obtain a second order cone programming (SOCP) problem. Then, the classical convex optimization method is improved to estimate and compensate the time varying acceleration profile in real time, which improves the performance of the existing optimization algorithm and enables the lander to land with high precision under the premise of saving fuel as much as possible. The simulation results show that compared with the classical explicit guidance law, the proposed algorithm consumes less fuel in the powered descent phase. The shooting analysis results under various position deviations show that the proposed algorithm can meet the performance requirements. Even if the initial position has a large fluctuation of ±2500 m, it can still complete the powered descent guidance with high precision speed and position. © 2022 China Spaceflight Society. All rights reserved.
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页码：1029 / 1039
页数：10
相关论文
共 19 条
  • [1] GAO Feng, JING Wuxing, GAO Changsheng, Et al., A guidance algorithm for pinpoint soft landing of economical lunar lander, Journal of Astronautics, 42, 10, pp. 1246-1256, (2021)
  • [2] ZHANG Honghua, GUAN Yifeng, HUANG Xiangyu, Et al., Guidance navigation and control for Chang' E-3 powered descent, Sci Sin Tech, 44, pp. 377-384, (2014)
  • [3] LONG J, GAO A, CUI P, Et al., Mars atmospheric entry guid ance for optimal terminal altitude, Acta Astronautica, 155, pp. 274-286, (2019)
  • [4] PENG Qibo, LI Haiyang, SHEN Hongxin, Rapid lunar exact landing trajectory optimization via gauss pseudospectral method, Journal of Astronautics, 31, 4, pp. 1012-1016, (2010)
  • [5] PENG Qibo, LI Haiyang, SHEN Hongxin, Et al., Lunar exact- landing traaectory optimization via the method combining GPM with direct shooting method, 34, 2, pp. 119-124, (2012)
  • [6] SACHAN K, PADHI R., Waypoint constrained multi-phase optimal guidance of spacecraft for soft lunar landing, Unma nned Systems, 7, 2, pp. 83-104, (2019)
  • [7] WANG Z, LIU L, LONG T., Minimum-time trajectory planning for multi-unmanned-aerial-vehicle cooperation using sequential convex programming, Journal of Guidance, Control, and Dynamics, 40, 11, pp. 2976-2982, (2017)
  • [8] LIU X, SHEN Z, PING L., Entry trajectory optimization by second-order cone programming, Journal of Guidance, Control,and Dynamics, 39, 2, pp. 227-241, (2015)
  • [9] LIN Xiaohui, YU Wenjin, Constrained trajectory optimization for lunar pin-point landing based on convex optimization theory, Journal of Astronautics, 34, 7, pp. 901-908, (2013)
  • [10] ACIKMESE B, PLOEN S R., Convex programming approach to powered descent guidance for mars landing [J], Journal of Guidance, Control, and Dynamics, 30, 5, pp. 1353-1366, (2007)
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