Spacecraft tracking control method based on integrated linear operator and anti-saturation technology

Abstract

The invention relates to a spacecraft tracking control method, in particular to a spacecraft tracking control method based on an integrated linear operator and an anti-saturation technology. The objective of the invention is to solve the problem of low attitude orbit tracking maneuvering control performance of a spacecraft caused by the fact that the spacecraft is subject to unfavorable working conditions such as inertia parameter uncertainty and input saturation in a short-distance space task. The method comprises the following steps: measuring and obtaining attitude and orbit states of a target and a tracking spacecraft, determining a relative pose configuration between the target and the tracking spacecraft, and obtaining a pose tracking error of the tracking spacecraft; determining a speed tracking error under a tracking spacecraft body coordinate system; defining a filtering error of the target and the tracking spacecraft under the coordinates of the tracking spacecraft body; introducing a linear operator, and determining an inertial parameter updating matrix; obtaining real-time estimation of inertial parameters; obtaining an anti-saturation auxiliary system state vector; and obtaining a control input vector to execute a pose integrated tracking control strategy. The method is applied to the field of spacecraft tracking control.

Description

technical field [0001] The present invention relates to a spacecraft tracking control method. Background technique [0002] In space missions such as spacecraft formation flying and rendezvous and docking, the traditional control technology often adopts the idea of ​​independent control of attitude and orbit. This strategy ignores the coupling effect between attitude and orbit, and it is difficult to meet the requirements of high-precision control. ; When considering model uncertainty, subject to the nonlinear existence of parameters, the uncertainty is often first classified as a part of the total disturbance of the system, and then processed by estimation structures such as neural networks or observers. It greatly increases the complexity of the closed-loop system and is difficult to apply to actual aerospace missions; for input saturation, most strategies are used to avoid saturation. This strategy will increase the difficulty and conservatism of controller design, which ...

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Problems solved by technology

[0007]The purpose of the present invention is to solve the short-distance space mission, the spacecraft is subject to the conditions of unfavorable working conditions such as inertial parameter uncertainty and input saturation, which lead to spaceflight In view of the low performance of spacecraft attitude orbit tracking maneuver control, a spacecraft tracking control method based on integrated linear operator and anti-saturation technology is proposed

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