Article

Mars Entry Guidance Based on Predicted Corrector Algorithm

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  • School of Automation, Beijing Institute of Technology, Beijing 100081, China

Received date: 01 Aug 2015

Revised date: 20 Oct 2015

Published date: 20 May 2022

Abstract

This paper describes the development and evaluation of the common numerical predicted corrector algorithm and gives an improved algorithm for the Mars entry guidance. First, it introduces two guidance strategies:tracking the reference trajectory and predicted corrector algorithm, finding that the common predicted corrector algorithm can be less sensitive to initial dispersions, but needs fast on-board computation. Second, the downrange algorithm, lateral control logic and heading alignment are described in details, which are provided to improve the horizontal accuracy of the vehicles. Furthermore, the segmented guidance predicted corrector algorithm is used to shorten the on-board computational time. Simulation results show that this entry guidance algorithm demonstrates reliable and robust performance in situations with high uncertainties.

Cite this article

XIA Yuanqing, SHEN Ganghui, SUN Haoran, ZHOU Liuyu . Mars Entry Guidance Based on Predicted Corrector Algorithm[J]. Journal of Deep Space Exploration, 2015 , 2(4) : 338 -344 . DOI: 10.15982/j.issn.2095-7777.2015.04.007

References

[1] Martin J L Turner. Expedition Mars:how we are going to get to Mars[M]. Berlin:Springer, 2004.
[2] Barlow N G. Mars:an introduction to its interior, surface and atmosphere[M]. Cambridge:UK:Cambridge University Press, 2008.
[3] 胡中为,徐伟彪.行星科学[M].北京:科学出版社,2008:40-60.[Hu Z W, Xu W B. Planetary science[M]. Beijing:Science Press, 2008:40-60.]
[4] Andrew B, James G, Ralph. Planetary landers and entry probes[M]. Cambridge UK:Cambridge University Press, 2010.
[5] 周美江.火星EDL轨迹优化和进入制导研究[D].哈尔滨:哈尔滨工业大学,2012.[Zhou M J. Trajectory optimization for Mars EDL and research on the entry guidance[D]. Harbin:Harbin Institute of Technology, 2012.]
[6] Manrique J B. Advance in spacecraft atmospheric entry guidance[D]. Irvine:University of California, 2010.
[7] Xia Y Q, Chen R F, Pu F, et al. Active disturbance rejection control for drag tracking in mars entry guidance[J]. Advances in Space Research, 2014,53(5):853-861.
[8] Mease K D, Kremer J P. Shuttle entry guidance revisited using nonlinear geometric method[J]. Journal of Guidance, Control and Dynamics, 1994,17(6):1350-1356.
[9] Kluever C A. Entry guidance performance for Mars precision landing[J]. Journal of Guidance, Control, and Dynamics, 2008,31(6):1537-1544.
[10] Brunner C W, Lu P. Skip entry trajectory planning and guidance[J]. Journal of Guidance, Control, and Dynamics, 2008, 31(5):1210-1219.
[11] Powell R W. Numerical roll reversal, predictor-corrector aero capture and precision landing guidance algorithm for Mars Surveyor program 2001 missions[C]//AIAA Atmospheric Flight Mechanics Conference.[S.l.]:AIAA, 1998.
[12] Carman G L, Ives D G, Geller D K. Apollo-derived Mars precision lander guidance[C]//AIAA Atmospheric Flight Mechanics Conference. Boston. MA, USA:AIAA, 1998.
[13] Mease K D, Leavitt J A, Benito J, et al. Advanced hypersonic entry guidance for Mars pinpoint landing[C]//Proceedings of the NASA science technology conference. MD, USA:AIAA, 2007.
[14] Xue S B, Lu P. Constrained predictor-corrector entry guidance[J]. Journal of Guidance, Control, and Dynamics, 2015,33(4):1273-1281.
[15] Shen G H, Xia Y Q, Sun H R. A 6 DOF mathematical model of parachute in Mars EDL[J]. Advances in Space Research, 2015, 55(7):1823-1831.
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