Adaptive fault-tolerant attitude control method in initial state stage of satellite

Abstract

The invention discloses an adaptive fault-tolerant attitude control method in an initial state stage of a satellite. The method comprises steps: in an initial state control stage after successful satellite and rocket separation, a satellite rotational inertia uncertainty model during a solar panel unfolding process is built; a satellite attitude dynamic model is built; a preset performance function is used to build an attitude nonlinear mapping model; and based on the built satellite rotational inertia uncertainty model during the solar panel unfolding process, the satellite attitude dynamic model and the attitude nonlinear mapping model, a backstepping method is used to design an adaptive fault-tolerant controller. Through the method, the rotational inertia uncertainty of the satellite inthe initial state control stage and the attitude stability problem in the case of actuator failure and under effects of an external disturbance torque can be solved, the fault-tolerant ability and the robustness of the attitude control system are ensured, and the attitude convergence speed, overshoot and convergence errors are ensured to meet the preset requirements.

Description

technical field [0001] The invention relates to the technical field of spacecraft control, in particular to an adaptive fault-tolerant attitude control method in the initial state stage of a satellite. Background technique [0002] Aerospace technology is gradually affecting people's daily life, among which artificial satellites are playing an increasingly important role in communication, navigation, meteorology and other aspects. After the satellite and rocket are separated, the satellite enters the initial state control stage. In the initial state control stage, the solar panels installed on the satellite will slowly unfold. The deployment of solar panels will inevitably change the moment of inertia of the entire satellite, which will bring certain challenges to the attitude stability control of the satellite. Although the initial state control period is relatively short compared to the entire satellite life, since the initial state control is the basis of the satellite'...

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Problems solved by technology

[0004] The purpose of the present invention is to overcome the deficiencies of the prior art, and provide an adaptive fault-tolerant attitude control method in the initial state stage of the satellite, aiming at the uncertainty of the entire star's moment of inertia caused by the deployment of the solar panels in the initial state control stage of the satellite. For the problems of actuator failure and various external disturbance torques, an adaptive fault-tolerant control method based on backstepping method is proposed, which is a fault-tolerant control method that does not require specific actuator fault information and interference information and can guarantee attitude preset performance , which solves the attitude stability problem of the satellite in the initial state control stage when the moment of inertia is uncertain, the actuator fails and is affected by the external disturbance moment, ensures the fault tolerance and robustness of the attitude control system, and ensures the attitude convergence speed, Overshoot and convergence error meet pre-set requirements

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