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CMG group return nominal configuration control method and system based on zero motion optimization and medium

A control method and zero-motion technology, which is applied in the field of CMG group return to nominal configuration control based on zero-motion optimization, can solve the problems of being unable to adapt to the frame angle to quickly return to the nominal position, and to return to the nominal speed slowly.

Active Publication Date: 2020-11-06
BEIJING INST OF CONTROL ENG
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Problems solved by technology

The existing frame corner return to nominal control method uses zero-motion calculation to try to solve this problem, but its return to nominal speed is very slow and cannot meet the needs of the frame corner to quickly return to the nominal position

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  • CMG group return nominal configuration control method and system based on zero motion optimization and medium
  • CMG group return nominal configuration control method and system based on zero motion optimization and medium

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Embodiment Construction

[0043] In order to better understand the above technical solutions, the technical solutions of the present application will be described in detail below through the accompanying drawings and specific examples. It should be understood that the embodiments of the present application and the specific features in the examples are detailed descriptions of the technical solutions of the present application, and It is not a limitation to the technical solutions of the present application, and the embodiments of the present application and the technical features in the embodiments can be combined without conflict.

[0044] A CMG group return nominal configuration control method based on zero-motion optimization provided in the embodiment of the present application in conjunction with the drawings of the description is as follows: figure 1 As shown, for further detailed description, the specific implementation of the method may include the following steps:

[0045] (1) First calculate ...

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Abstract

The invention discloses a CMG group return nominal configuration control method and system based on zero motion optimization, and a medium, which belong to the technical field of spacecraft attitude control. The method comprises the steps of firstly calculating a frame angular speed reference value according to the frame angular deviation through employing zero motion; and then setting a dynamic return nominal adjustment factor value according to the length of the frame angular deviation vector, so that the integrated frame angular speed is larger when the frame angular deviation is large, andthe integrated frame angular speed is smaller when the frame angular deviation is small. By adopting the method, the problem that the CMG group frame angle is quickly adjusted to the nominal positionunder the condition that the satellite does not influence normal control is well solved. Aiming at the multi-redundancy condition of the CMG group, the high efficiency and rapidity of CMG return nominal are realized in a zero motion mode by utilizing different zero space vector combinations, and the problem that the framework angle of an agile satellite control moment gyro rapidly returns to thenominal position, which is not solved in the prior art, is solved.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude control, and in particular relates to a zero-motion optimization-based CMG group return nominal configuration control method, system and medium. Background technique [0002] The satellite configured with the combination of control moment gyroscope as the actuator of attitude control has the ability of agile maneuvering. When the control moment gyroscope is used in combination, a set of optimized frame angular positions is usually set as the nominal value to achieve a better maneuvering effect and reduce possible singularity problems during the maneuvering process. Since the control moment gyroscope is generally manipulated through the frame angular velocity signal, the frame angular velocity command is obtained by solving the control law based on the real-time control torque demand, so the frame angle cannot be guaranteed to return to the nominal position after the implementation of large-angle...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/244B64G1/245
Inventor 雷拥军刘其睿刘洁王淑一关新张科备
Owner BEIJING INST OF CONTROL ENG
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