PDF(2584 KB)
A Constant-Thrust Guidance Method with Yaw Maneuver for Pinpoint Landing
- LI Ji1,2, ZHANG Honghua1,2, ZHANG Xiaowen1,2, GUAN Yifeng1,2
Author information
+
1. Beijing Institute of Control Engineering, Beijing 100094, China;
2. National Key Laboratory of Space Intelligent Control, Beijing 100094, China
Show less
History
+
Received |
Revised |
Published |
16 Mar 2023 |
04 Jun 2023 |
26 Mar 2024 |
Issue Date |
|
26 Mar 2024 |
|
Abstract
To realize all the six components of terminal position and velocity control for pinpoint landing, throttleable engines are usually needed. In order to reduce economic cost and technique risk, a constant thrust guidance method with yaw maneuver for pinpoint landing was proposed in this paper. The range in the flight line was controlled by yaw maneuver which regulated the in-plane component of the thrust. And a strategy to change the sign of heading angle was performed to eliminate the position and velocity errors in the cross direction, which made the trajectory in horizon plane resemble the letter “W”. This method steered the spacecraft to a given target point with a little more fuel consumption. Simulation results show that the method proposed in this paper is easy to use and efficient.
Keywords
power descent /
pinpoint landing /
constant thrust /
explicit guidance
Cite this article
Download citation ▾
LI Ji, ZHANG Honghua, ZHANG Xiaowen, GUAN Yifeng.
A Constant-Thrust Guidance Method with Yaw Maneuver for Pinpoint Landing. Journal of Deep Space Exploration, 2024, 11(1): 47‒55 https://doi.org/10.15982/j.issn.2096-9287.2024.20230026
{{custom_sec.title}}
{{custom_sec.title}}
{{custom_sec.content}}
This is a preview of subscription content, contact
us for subscripton.
References
[1] 叶培建,于登云,孙泽州,等. 中国月球探测器的成就与展望[J]. 深空探测学报(中英文),2016,3(4):323-333.
YE P J,YU D Y,SUN Z Z,et al. Achievements and prospect of Chinese lunar probes[J]. Journal of Deep Space Exploration,2016,3(4):323-333.
[2] LEE A Y,ELY T,SOSTARIC R,et al. Preliminary design of the guidance,navigation,and control system of the Altair lunar lander[C]//Proceedings of AIAA Guidance,Navigation,and Control Conference. Toronto,Ontario, Canada:AIAA,2010.
[3] 张洪华,李骥,关轶峰,等. 嫦娥三号着陆器动力下降的自主导航[J]. 控制理论与应用,2014,31(12):1686-1694.
ZHANG H H,LI J,GUAN Y F,et al. Autonomous navigation for powered descent phase of Chang’E-3 lunar lander[J]. Control Theory & Applications,2014,31(12):1686-1694.
[4] CITRON S J,DUNIN S E,MEISSINGER H F. A terminal guidance technique for lunar landing[J]. AIAA Journal,1964,2(3):503-509.
[5] KLUMPP A R. Apollo lunar descent guidance[J]. Automatica,1974,10(2):133-146.
[6] UENO S,YAMAGUCHI Y. 3-dimensional near-minimum fuel guidance law of a lunar landing module[C]//Proceedings of AIAA Guidance,Navigation,and Control Conference and Exhibit. Portland:AIAA,1999.
[7] SOSTARIC R R. Powered descent trajectory guidance and some considerations for human lunar landing[C]//Proceedings of 30th Annual AAS guidance and control conference. Breckenridge,Colorado,USA:[s. n.],2007.
[8] 黄翔宇,张洪华,王大轶,等. “嫦娥三号”探测器软着陆自主导航与制导技术[J]. 深空探测学报(中英文),2014,1(1):52-59.
HUANG X Y,ZHANG H H,WANG D Y,et al. Autonomous navigation and guidance for Chang’e-3 soft Landing[J]. Journal of Deep Space Exploration,2014,1(1):52-59.
[9] 张洪华,关轶峰,黄翔宇,等. 嫦娥三号着陆器动力下降的制导导航与控制[J]. 中国科学:技术科学,2014,44(4):377-384.
ZHANG H H,GUAN Y F,HUANG X Y,et al. Guidance navigation and control for Chang’e-3 powered descent[J]. Scientia Sinica Technologica,2014,44(4):377-384.
[10] TOPCU U,CASOLIVA J,MEASE K D. Fuel efficient powered descent guidance for Mars landing[C]//Proceedings of AIAA Guidance,Navigation,and Control Conference and Exhibit. San Francisco,California:AIAA,2005.
[11] TOPCU U,CASOLIVA J,MEASE K D. Minimum-fuel powered descent for Mars pinpoint landing[J]. Journal of Spacecraft and Rockets,2007,44(2):324-331.
[12] 彭祺擘,李海阳,沈红新,等,基于Gauss伪谱法和直接打靶法结合的月球定点着陆轨道优化[J]. 国防科技大学学报,2012,34(2):119-124.
PENG Q B,LI H Y,SHEN H X,et al. Lunar exact-landing trajectory optimization via the method combining GPM with direct shooting method[J]. Journal of National University of Defense Technology,2012,34(2):119-124.
[13] 彭祺擘,李海阳,沈红心. 基于高斯-伪谱法的月球定点着陆轨道快速优化设[J]. 宇航学报,2010,31(4):1012-1016.
PENG Q B,LI H Y,SHEN H X. Rapid lunar exact-landing trajectory optimization via Gauss pseudospectral method[J]. Journal of Astronautics,2021,31(4):1012-1016.
[14] ACIKMESE,A B,PLOEN S R. A powered descent guidance algorithm for Mars Pinpoint Landing[C]//Proceedings of AIAA Guidance,Navigation,and Control Conference and Exhibit. San Francisco,California:AIAA,2005.
[15] ACIKMESE B,PLOEN S R. Convex programming approach to powered descent guidance for Mars landing [J]. Journal of Guidance,Control,and Dynamics. 2007,30(5):1353-1366.
[16] DUERI D,ACIKMESE B. Customized real-time interior-point methods for onboard powered-descent guidance[J]. Journal of Guidance,Control,and Dynamics. 2017,40(2):197-212.
[17] SCHARF D P,ACIKMESE B,DUERI D. Implementation and experimental demonstration of onboard powered-descent guidance[J]. Journal of Guidance,Control,and Dynamics. 2017,40(2):213-229.
[18] 林晓辉,于文进. 基于凸优化理论的含约束月球定点着陆轨道优化[J]. 宇航学报,2013,34(7):901-908.
LIN X H,YU W J. Constrained trajectory optimization for lunar pin-point landing based on convex optimization theory [J]. Journal of Astronautics,2014,34(7):901-908.
[19] 邓雁鹏,穆荣军,彭娜,等. 月面着陆动力下降段最优轨迹序列凸优化方法[J]. 宇航学报,2022,43(8):1029-1039.
DENG Y P,MU R J,PENG N,et al. Sequential convex optimization method for lunar landing during powered descent phase[J]. Journal of Astronautics,2022,43(8):1029-1039.
[20] SPRINGMANN P N. Lunar descent using sequential engine Shutdown[D]. Cambridge:Massachusetts Institute of Technology,2006.
[21] 高峰,荆武兴,高长生,等. 经济型月球探测器精确定点软着陆制导算法[J]. 宇航学报,2021,42(10):1246-1256.
GAO F,JING W X,GAO C S,et al. A guidance algorithm for pinpoint soft landing of economical lunar lander[J]. Journal of Astronautics,2021,42(10):1246-1256.
[22] 乔衍迪,张泽旭,邓涵之,等. 月球探测器动力下降段最优轨迹参数化方法[J]. 宇航学报,2021,42(6):740-748.
QIAO Y D,ZHANG Z X,DENG H Z,et al. Control variables parameterization method of powered descent trajectory for lunar explorer[J]. Journal of Astronautics. 2021,42(6):740-748.
[23] MCHENRY R L,BRAND T J,LONG A D,et al. Space shuttle ascent guidance,navigation,and control[J]. Journal of the Astronautical Sciences,1979,27(1):1-38.