Gain switching method of spacecraft rendezvous system and maximal attraction domain estimation

Abstract

The invention discloses a gain switching method of a spacecraft rendezvous system and maximal attraction domain estimation. The method comprises steps that firstly, a spacecraft rendezvous relative movement model is established, secondly, the gain switching method of the spacecraft rendezvous system is proposed, and lastly, the maximal attraction domain estimation of a closed loop system can be given through the gain switching method. According to the method, a spacecraft asymmetric performer saturation control problem is converted into a performer symmetric saturation control problem, controller calculation only requires solving linear matrix inequalities, calculation is simple and easy to carry out, dynamic performance of the closed loop system is improved, and the maximal attraction domain estimation of the closed loop system is further given.

Description

technical field [0001] The invention belongs to the field of aerospace, and in particular relates to a gain switching method of an actuator asymmetrically saturated spacecraft rendezvous system and a maximum attraction domain estimation. Background technique [0002] Spacecraft orbital rendezvous means that a spacecraft (called the tracking spacecraft) actively tracks and approaches another spacecraft (called the target spacecraft) so that the two can implement the space mission of docking. Roughly speaking, rendezvous refers to a target aircraft running on a circular or elliptical orbit, and the tracking aircraft near its orbit adjusts its own orbit to finally follow the target aircraft so that they finally have the same orbital parameters. Spacecraft rendezvous is a prerequisite for some advanced space operations. [0003] The orbital rendezvous of the spacecraft is constrained by the acceleration generated by the thruster. When the acceleration obtained according to the ...

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Problems solved by technology

[0003] The orbital rendezvous of the spacecraft is constrained by the acceleration generated by the thruster. When the acceleration obtained according to the design of the controller exceeds the maximum acceleration, the actual control system will not be able to operate as designed, which will affect the control quality of the control system and stability, resulting in the failure of the spacecraft rendezvous mission to be successfully completed

Most of the existing research methods focus on the actuator symmetric saturation problem of the spacecraft rendezvous system, but there are few related research results on the control problem of the actuator asymmetric saturation.

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