Midcourse Correction Strategy of Interplanetary Exploration with Breakwell Spacing Ratio Method

Abstract

This paper introduces Breakwell spacing ratio method in detail and derives an analytical expression between terminal error accuracy, guidance ability and the number and time of midcourse corrections. Generally speaking, one more correction is necessary for every 3 times accuracy increasing, while every 3 times improving on guidance ability can reduce one correction. In specific applications, the last correction time should be determined first according to the terminal error accuracy and guidance ability, then other correction time can be determined so that the error propagation after each correction is a geometric progression with ratio 1/3. A simulation of a Mars exploration from May 2018 to December 2018 is taken as an example to verify the validity of theoretical analysis.

Keywords

Breakwell spacing ratio / midcourse correction / guidance strategy / fuel optimal

References

[1] Breakwell J V. Fuel requirements for crude Interplanetary Guidance[J]. Advances in Astronautical Science, 1960(5): 53-65.杨嘉墀. 航天器轨道动力学与控制(下)[M]. 北京: 宇航出版社, 2001: 336-337.
[2] Yang J C. Spacecraft orbital dynamics and control (2)[M]. Beijing: China Astronautic Publishing House, 2001: 336-337.李军锋. 基于精确动力学模型的火星探测轨道设计研究[D]. 北京: 清华大学航天航空学院, 2012.
[3] Li J F. Research on orbit design for Mars explorer by the accurate dynamic model[D]. Beijing: Tsinghua University, 2012.胡军, 周亮. 基于显式制导的月地返回轨道中途修正研究[J]. 中国空间科学技术, 2013, 33(5): 7-14.
[4] Hu J, Zhou L. Midcourse correction of Moon-Earth return trajectory based on explicit guidance[J]. Chinese Space Science and Technology, 2013, 33(5): 7-14.