SPACECRAFT EVASION STRATEGY USING ACTIVE MANEUVERS BASED ON MANEUVERING-TARGET ACCELERATION ESTIMATION

With the development of space control technology, the safety of spacecraft in orbit has been paid more and more attention. The autonomous approach of the spacecraft with active maneuverability to the target spacecraft is a serious threat to the safety of the spacecraft in orbit. In the close orbital pursuit-evasion (PE) game of spacecraft, the acquisition of relative position, velocity and acceleration is the basis of the PE game strategy of both sides. In the case of incomplete information acquisition by both sides, an evasion control strategy based on the filtering estimation of maneuvering target and the maximizing line-of-sight yaw rate is proposed. The escaper obtains navigation information such as the relative position, velocity, and acceleration of the chaser based on the current statistical model filtering algorithm, and the chaser obtains navigation information of the escaper also based on the current statistical model filtering algorithm. The chaser uses the proportional guidance law to approach the escaper autonomously. The escaper calculates the line-of-sight direction and line-of-sight yaw rate relative to the chaser, and uses an active evasion strategy based on maximizing the line-of-sight yaw rate to escape. The different evasion strategies and different operating conditions are simulated. The results show that when the maneuverability of the escaper reaches more than 60% of the chaser, the escaper can escape successfully by using the proposed evasion strategy; the evasion strategy is not sensitive to the measurement accuracy and operating frequency of observation equipment, and the effect of evasion strategy is related to the response time, the earlier the escaper receives the warning information, the better the evasion strategy will be.