Super-finishing super-stable super-agile control variable envelope control law design method of spacecraft

Abstract

The invention relates to a super-finishing super-stable super-agile control variable envelope control law design method of a spacecraft, wherein the design method is suitable for the field of spacecraft attitude control with both agile maneuvering requirements and high-precision pointing control requirements. An installation inclination angle of an existing control moment gyro group is fixed, andangular momentum envelope of the control moment gyro group is difficult to fully utilize. In order to solve the problem, the super-finishing super-stable super-agile control variable envelope controllaw design method of a spacecraft is designed. On the basis that an original control moment gyro group installation structure is fixed, a control variable of an installation inclination angle is introduced, so that the agile maneuverability of a spacecraft is improved; an installation inclination angle is added based on one-degree-of-freedom singularity avoidance of an original low-speed frame, sothat two-degree-of-freedom singularity avoidance is formed, and the low-speed frame can be quickly separated from singularity. Analysis results show that when the installation inclination angle is variable, the maximum angular velocity of agile maneuver of the spacecraft is increased to 3.2 (degree / s) from 2.83 (degree / s), and the agile maneuver performance of the spacecraft is further improved.

Description

technical field [0001] The invention relates to a design method of a spacecraft three-super-control variable envelope manipulation law, which belongs to the field of spacecraft control. Background technique [0002] In recent years, space missions represented by very high-resolution earth observation have put forward requirements for fast and agile maneuvering of spacecraft and high-precision steady-state control after maneuvering in place. This requires the actuator to have a large torque output capability and the ability to flexibly change the angular momentum envelope. After the installation configuration of the existing control moment gyroscope is determined, its installation inclination angle is fixed. This is not conducive to the flexible change of the entire angular momentum envelope by the actuator to meet the different agile maneuvering requirements of the spacecraft. [0003] The existing control moment gyroscope fixed inclination angle installation and its angul...

AI Technical Summary

Problems solved by technology

[0006] 2. Unable to meet the needs of various agile maneuvers of spacecraft

At this time, the control moment gyroscope group installed at a fixed inclination angle is difficult to meet the various agile maneuvering needs of the spacecraft.

[0008] 3. It is impossible to realize the rapid avoidance of singularities in the low-speed frame of the control torque gyroscope

[0009] In the existing steering law design of the control moment gyroscope group installed at a fixed inclination, when the low-speed frame of the control moment gyroscope is close to the singularity state, only one degree of freedom of the low-speed frame can be used to effectively avoid the singularity, although the high-speed rotor can also participate in the singularity avoidance of the low-speed frame , but its efficiency is relatively low, and it is difficult to realize the rapid singularity avoidance of the low-speed frame of the control torque gyro

Images