SGCMG fault in-orbit plan design method based on robustness pseudo-inverse control rate

Abstract

The present invention discloses a SGCMG (Single Gimbal Control Moment Gyroscope) fault in-orbit plan design method based on a robustness pseudo-inverse control rate when a satellite employs the SGCMG as an attitude control execution mechanism. The method comprises: determining the angular momentum H and the moment matrix C of a gyroscope group according to the configuration of a control moment gyroscope group and the direction arrangement of each single-frame control moment gyroscope frame shaft; designing a robustness pseudo-inverse control rate; and based on a robustness pseudo-inverse algorithm, basically ensuring the normal ground control of the satellite attitude in the condition of n-3 SGCMG faults (n is the number of SGCMGs in the control moment gyroscope group) through satellite autonomous diagnosis and planning design aiming at the faults easily happening in orbit of the control moment gyroscope, wherein the faults comprise the on-off fault, the unstable rotor speed fault, the communication fault, the external frame blocking and the external frame rotate speed unchanging fault. The SGCMG fault in-orbit plan design method based on the robustness pseudo-inverse control rate can improve the satellite in-orbit real-time autonomous diagnosis capability, reduce the dependence on the ground, avoid the delay of ground solution measures, enhance safety and reduce the whole-spacecraft risk.

Description

technical field [0001] The invention relates to a single-frame control moment gyroscope fault (SGCMG) on-orbit pre-plan design method, in particular to an SGCMG fault on-orbit pre-plan design method based on robust pseudo-inverse manipulation rate. Background technique [0002] With the development of space technology, the structure and size of modern satellites are becoming more and more complex, the moment of inertia of the star is large, and it has the requirement of fast attitude maneuvering, which puts forward the requirements of large output angular momentum and large torque output for the actuator on the star. The single-frame control moment gyro can control the high angular momentum to the required target orientation in a short period of time by controlling the rotation of the outer frame, and output continuous and more accurate torque. The range of output torque is large, which can meet the large-inertia satellite large-angle Attitude rapid maneuvering requires meet...

AI Technical Summary

Problems solved by technology

[0007] Therefore, due to the complex structure of the control torque gyroscope, there are many fault conditions that are prone to occur on-orbit, and the following faults are prone to occur during on-orbit use: on-off state, unstable inner rotor speed, communication failure, outer frame stuck, outer frame speed constant , when the above failure occurs, it will have a great impact on the attitude of the star, and in severe cases, it will affect the mission of the entire star

Images