A Design Method of Variable Envelope Manipulation Law for Spacecraft Three-super-control

Abstract

The invention discloses a design method for a spacecraft three-super-control variable envelope control law, which is suitable for the field of spacecraft attitude control with both agile maneuvering requirements and high-precision pointing control requirements. The installation inclination angle of the existing control moment gyroscope group is fixed, and it is difficult to make full use of the angular momentum envelope of the control moment gyroscope group. Aiming at this, a design method of spacecraft three-super-control variable envelope maneuvering law is designed. On the basis of the fixed installation configuration of the original control moment gyroscope group, the control variable of the installation inclination angle is introduced to improve the agile maneuverability of the spacecraft; on the basis of the original low-speed frame with one degree of freedom to avoid singularity, the installation inclination angle is increased to form two The degree of freedom avoids singularity, and realizes that the low-speed frame can quickly escape from the singularity. The analysis results show that when the inclination angle is variable, the maximum angular velocity of the agile maneuvering of the spacecraft is increased from 2.83(° / s) to 3.2(° / s), which further improves the agile maneuvering performance of the spacecraft.

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...

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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

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