An Orbit Maneuver Optimal Algorithm Based On Time Performance Index
In space battle application, orbital design is the most important part: such as design for intercepting orbit, meanwhile, considering the optimization of intercepting orbit, it has very important meanings to design an intercepting orbit with minimal flight time. By the way of analytic method and using optimal algorithm, on the premise of Keplerian orbit under two-body hypothesis and one-off impulse orbit maneuver, this paper discusses design for optimal intercepting orbit with minimal flight time under constraint of the magnitude of initial velocity impulse, and gets the optimal launch point (or orbitchanging point) on initial orbit by iterative search algorithm. It gives the mathematic model and process of calculation in the paper, and by means of model simulation in three different cases, we prove that it is a simple, quick and effective arithmetic for orbital desiga We believe that it would provide more reference for orbit optimal design in space application.
orbital design minimal flight time intercepting orbit optimal algorithm Keplerian orbit
Xu Kaichuan Wang Jianxin Zhao Zilong Wang Mingxin
Department of Helicopter Mechanical Engineering, Army Aviation Institute, Beijing 101123, China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
7-10
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）