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Control moment gyroscope group fault analog simulation test method and system

A technology for controlling moment gyroscopes and fault simulation, which is applied in the field of satellite simulation testing, and can solve problems such as different torque output capabilities, singularity of control moment gyroscope groups, loss of three-dimensional control ability of control moment gyroscope groups, etc.

Active Publication Date: 2019-12-13
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

However, the control torque gyroscope group composed of multiple control moment gyroscopes has two problems: (1) the configuration of the control moment gyroscope group, different configurations have different torque output capabilities; (2) the singularity of the control moment gyroscope group The problem is that when the control moment gyroscope output torque is manipulated, the control moment gyroscope group loses the three-dimensional control ability and falls into a singular state

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  • Control moment gyroscope group fault analog simulation test method and system

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Embodiment Construction

[0025] The technical solutions of the present invention will be further described below in conjunction with the drawings and embodiments.

[0026] In the test system scheme of the control moment gyroscope, to meet the requirements of test reliability and verification adequacy, it is necessary to simulate the attitude and orbit control computer in the fault simulation system to communicate with the real stand-alone control moment gyroscope group, and also communicate with the mathematical model. The switching control is completed by the fault simulation console, which completes the operation of the underlying hardware board, and completes the back and forth switching between the real stand-alone machine and the mathematical model; at the same time, the simulated fault simulation system has the ability to simulate the common internal and external frame faults of the torque gyroscope group. type of function. In order to realize the above functions, the present invention proposes ...

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Abstract

The invention discloses a control moment gyroscope group fault analog simulation test method and system, and the method employs the control moment gyroscope group fault analog simulation test system for fault analog simulation test. The system comprises a fault analog console, a mathematic model upper computer, and a mathematic model lower computer. The mathematical model lower computer carries areal-time simulation system. After the control moment gyroscope group mathematical model loaded by the mathematical model upper computer is operated, the mathematical model lower computer simulates the input and output functions of a real single machine of the control moment gyroscope group, receives an instruction of a fault simulation console, simulates the fault of the control moment gyroscopegroup, and outputs operation state data and abnormal information to the mathematical model upper computer. Various foreseeable faults of various control moment gyroscope groups can be verified, and attitude and orbit control software fault diagnosis and isolation measures after the faults occur are tested.

Description

technical field [0001] The invention belongs to the technical field of satellite simulation test, and in particular relates to a method and system for fault simulation test of a control moment gyroscope group. Background technique [0002] With the development of satellite technology, it is required to improve the time resolution and image revisit cycle, increase the timeliness of regional coverage, and require it to have functions such as fast maneuvering and arbitrary angle maneuvering. Therefore, the selection of actuators is more and more inclined to control the moment gyro group. [0003] The principle of single-frame control moment gyroscope output torque is to change the angular momentum direction of the high-speed rotor at a certain angular velocity, so as to achieve the purpose of torque output. However, a single control moment gyro only has the torque output capability of one degree of freedom. Therefore, at least three control moment gyroscopes are required for t...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor 李小斌吴敬玉王新陈撼钟超陈秀梅郭思岩
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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