Satellite proximate interception vector guidance based on differential games  

作　　者：Dong YE Mingming SHI Zhaowei SUN 

机构地区：[1]Research Center of Satellite Technology, Harbin Institute of Technology, Harbin Institute of Technology [2]Faculty of Science and Engineering, University of Groningen

出　　处：《Chinese Journal of Aeronautics》2018年第6期1352-1361,共10页中国航空学报（英文版）

基　　金：co-supported by the National Natural Science Foundation of China (Nos.61603115,91438202 and91638301);China Postdoctoral Science Foundation (No.2015M81455);the Open Fund of National Defense Key Discipline Laboratory of Micro-Spacecraft Technology of China (No.HIT.KLOF.MST.201601);the Heilongjiang Postdoctoral Fund of China (No.LBH-Z15085)

摘　　要：This paper studies the proximate satellite interception guidance strategies where both the interceptor and target can perform orbital maneuvers with magnitude limited thrusts. This problem is regarded as a pursuit-evasion game since satellites in both sides will try their best to capture or escape. In this game, the distance of these two players is small enough so that the highly nonlinear earth-centered gravitational dynamics can be reduced to the linear Clohessy-Wiltshire（CW） equations. The system is then simplified by introducing the zero effort miss variables. Saddle solution is formulated for the pursuit-evasion game and time-to-go is estimated similarly as that for the exoatmospheric interception. Then a vector guidance is derived to ensure that the interception can be achieved in the optimal time. The proposed guidance law is validated by numerical simulations.This paper studies the proximate satellite interception guidance strategies where both the interceptor and target can perform orbital maneuvers with magnitude limited thrusts. This problem is regarded as a pursuit-evasion game since satellites in both sides will try their best to capture or escape. In this game, the distance of these two players is small enough so that the highly nonlinear earth-centered gravitational dynamics can be reduced to the linear Clohessy-Wiltshire（CW） equations. The system is then simplified by introducing the zero effort miss variables. Saddle solution is formulated for the pursuit-evasion game and time-to-go is estimated similarly as that for the exoatmospheric interception. Then a vector guidance is derived to ensure that the interception can be achieved in the optimal time. The proposed guidance law is validated by numerical simulations.

关 键 词：Differential games Saddle solution Satellite interception Time-to-go estimation Zero effort miss trajectory 

分 类 号：TJ861[兵器科学与技术—武器系统与运用工程] V448.2[航空宇航科学与技术—飞行器设计]