Planet steady state controlling method replacing momentum wheels with control moment gyroscope

Abstract

The invention discloses a planet steady state controlling method replacing momentum wheels with a control moment gyroscope. When the number of the momentum wheels which work normally is three, the momentum wheels in a traditional way can only work in an angular momentum zero passing way to realize the state steady controlling, and the controlling precision is lowered. Aiming at the problem, the invention puts forward that a back-up control moment gyroscope high-speed rotor is used as an angular momentum fixing momentum wheel, a fixing bias angular momentum of a certain direction is provided by rotating a low-speed frame angle, so that the rest three momentum wheels can work in a bias state, the system can stay in a steady state controlling mode of a zero-momentum controlling system formed by the back-up control moment gyroscope high-speed rotor and the momentum wheels which work in a bias angular momentum state, and the problem that the precision when the momentum wheels are in zero passing use is damaged is solved. The planet steady state controlling method enables the cold back-up control moment gyroscope to play the back-up role of side-sway maneuver and steady state controlling, and improves the reliability of on-rail use of a planet activating mechanism.

Description

technical field [0001] The invention relates to a satellite steady-state control method for controlling a moment gyroscope instead of a momentum wheel, and belongs to the field of satellite attitude control. Background technique [0002] In order to meet the requirements of fast side-sway maneuver and high-precision attitude stability control, the actuators of the first-class satellites adopt the mixed configuration of control moment gyroscope (CMG) and momentum wheel. Among them, the control moment gyro (CMG) generally includes the main control moment gyro (CMG) and the backup control moment gyro (CMG). Two types of actuators with different characteristics achieve different control functions: the control torque gyro with a large output torque realizes the rapid maneuvering requirements of the satellite, while the momentum wheel with a relatively small output torque but high precision realizes high-precision steady-state control of the satellite Require. Among them, the hi...

AI Technical Summary

Problems solved by technology

[0003] In summary, when the number of workable momentum wheels in the satellite control system based on hybrid actuators is reduced to three, a new method needs to be proposed, which not only satisfies the steady-state control of the satellite, but also avoids the zero crossing of the momentum wheels as much as possible. Loss of precision issues using

Images