A method for attitude control of non-cooperative target assembly spacecraft

Abstract

The invention provides a non-cooperative target assembly spacecraft attitude control method, which includes the steps of: redefining the coordinate system of the assembly spacecraft; on-orbit identification of the assembly moment of inertia; and an algorithm for the attitude control of the assembly spacecraft ; The present invention uses the moment of inertia on-orbit identification algorithm with good real-time performance, high identification accuracy, easy engineering implementation, and provides reliable parameter basis for controller design; for the problems of uncertain parameters and large external disturbance torque, the self-adaptive sliding mode controller is used Through appropriate initial parameters, the attitude stabilization control of the combined spacecraft is realized.

Description

technical field The invention relates to a spacecraft attitude control technology, in particular to an on-orbit operation method for a space non-cooperative target. Background technique With the improvement of space research and application capabilities, the demand for space on-orbit operation technology is increasingly urgent. All space powers have realized its importance, and have carried out corresponding research plans around the future on-orbit operation system. These studies can be used It is used for tasks such as clearing orbital garbage and on-orbit maintenance. The targets of the research include fuel-exhausted satellites, space debris, abandoned satellites, etc. The combination of these target spacecraft and active spacecraft is not like a large-scale combination such as a space station, whose parameters can be obtained in advance through ground experiments. Therefore, in-orbit The research on the control method of combined spacecraft under the background of serv...

AI Technical Summary

Problems solved by technology

After the in-orbit operating vehicle captures the non-cooperative target, the configuration and mass characteristic parameters have changed greatly compared with before, which brings great difficulties to the control of the assembly

First of all, the uncertainty of the knowledge of the target spacecraft, as well as some load or configuration changes caused by the spacecraft’s in-orbit operation, make these quality characteristic parameters unable to be calculated by means of ground experiments.

Secondly, the space target spacecraft often has a certain speed of motion, and the momentum of the assembly will change suddenly after docking or capture, which may cause the instability of the base

Images