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Single frame control moment gyro control method based on moment output capability optimization

A technology for controlling the torque gyroscope and output capability, which is applied in the direction of aerospace vehicle guidance devices, etc., and can solve problems such as large torque errors and inability to effectively avoid singularities

Inactive Publication Date: 2013-04-17
CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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Problems solved by technology

[0036] The present invention provides a single-frame control torque gyro based on the optimal torque output capability to solve the problem that the existing single-frame control torque gyro control law cannot effectively avoid the singularity, and will bring a large torque error when escaping from the singularity. manipulation method

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  • Single frame control moment gyro control method based on moment output capability optimization
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  • Single frame control moment gyro control method based on moment output capability optimization

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specific Embodiment approach 1

[0081] Specific implementation mode 1. Combination Figure 1 to Figure 5 Describe this embodiment, based on the single-frame control torque gyro manipulation method with optimal torque output capability, the method is realized by the following steps:

[0082] Step 1. The satellite attitude control system obtains the current expected torque T from the CMG system according to the current attitude information c ;

[0083] Step 2. According to the current expected torque T obtained in step 1 c , calculate to make the CMG system output the expected torque T c Optimal frame angular velocity

[0084] The optimal frame angular velocity described in step 2 The calculation process is:

[0085] According to the desired torque T c and the current angular momentum h of the ith CMG unit i , to obtain the output expected torque T of the i-th CMG unit c The best angular momentum h di ,which is:

[0086] h di = ...

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Abstract

The invention provides a single frame control moment gyro control method based on moment output capability optimization, relating to the prompt satellite attitude control field and solving the problems that the existing single frame control moment gyro control rule can not effectively avoid strange and big moment error can be caused when escaping strange. The method includes the concrete steps that: a satellite attitude control system obtains the current expected moment Tc output by CMG system according to the current attitude information; capability optimized frame angular velocity for the CMG system to output the expected moment Tc is calculated; and a frame rotating speed instruction of CMG system is obtained according to the expected moment Tc and the optimal frame angular velocity, so as to realize satellite attitude control. The method of the invention can effectively avoid strange problem, and meanwhile output moment error can be reduced, thus improving satellite attitude control accuracy.

Description

technical field [0001] The invention relates to the field of agile satellite attitude control, in particular to a single-frame control moment gyroscope group's high-precision moment output and a manipulation method for effective singularity avoidance. Background technique [0002] With the development of the aerospace industry, people have higher and higher requirements for the accuracy of the ground photography of the future earth observation satellites. High-precision ground photography resolution means a relatively small field of view aperture angle, and to achieve large-scale photography of sensitive areas requires the satellite to have fast maneuverability, which also requires the satellite attitude control system to provide a large enough the control torque. So far, the attitude control actuators that can provide large torque mainly include Control Moment Gyros (hereinafter referred to as CMG) and jet thrusters. Compared with jet thrusters, CMG not only has torque am...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/28
Inventor 孙志远张刘戴路徐开杨秀彬陈茂胜
Owner CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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