Taking continuous low-thrust spacecraft as the research object, a long-distance online autonomous interception guidance scheme is designed, and an optimal mission time planning method is proposed. The velocity gain guidance method is used to design a closed-loop guidance scheme, where the Lambert two-point boundary value problem is quickly solved in each control cycle to obtain the current required speed of the tracking spacecraft. After that, the desired gain speed can be calculated according to the current required speed, so that the desired magnitude and direction of the control force can be attained. In addition, the thruster shutdown scheme is set according to the norm of the desired gain speed to obtain a rational shutdown moment. Also, a novel objective function related to both the interception time period and the terminal position error is proposed in the genetic algorithm, to ensure the optimal time cost and the success of the interception mission. Finally, based on the numerical simulation, the effectiveness of the optimal mission time planning method and the reliability of the autonomous intercept guidance method are verified.
Research on Mission Time Planning and Autonomous Interception Guidance Method for Low-Thrust Spacecraft in Long-Distance Interception
2020-09-01
347883 byte
Conference paper
Electronic Resource
English
The predicted interception guidance method
AIAA | 1987
|Terminal guidance technique for satellite interception utilizing constant thrust rocket motor
Engineering Index Backfile | 1960
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