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On-board autonomic fault diagnosis method controlled based on control moment gyro group

A technology for controlling torque gyroscope and fault diagnosis, which is applied in the field of satellite control, can solve the problems of no effective control torque output of the system, limited introduction of control torque gyroscope fault identification and fault diagnosis, and influence on system attitude control. Effectiveness and timeliness, clearly defined results

Inactive Publication Date: 2020-02-07
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

However, when the control torque gyro enters the engineering application, it will inevitably introduce defects or potential failure modes of the product itself. If these defects or potential failure modes are not identified, making abnormal data introduced into the control torque gyro group control, there is a high probability that it will cause The system control moment gyro group enters the passive singular state, resulting in no effective control moment output of the system, which ultimately affects the system attitude control
[0004] At present, the application and research results of the existing control moment gyroscope group satellite control are mostly based on the control algorithm and control moment gyro control law design, but the product engineering application of the control moment gyroscope and the fault identification and fault diagnosis of the control moment gyroscope itself are limited.

Method used

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  • On-board autonomic fault diagnosis method controlled based on control moment gyro group
  • On-board autonomic fault diagnosis method controlled based on control moment gyro group
  • On-board autonomic fault diagnosis method controlled based on control moment gyro group

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Embodiment 1

[0036] In order to describe the specific fault degree, the number of faults and the fault threshold are defined to describe the tolerance of the system to the fault of the control torque gyroscope, and its physical meaning is the fault tolerance of the system within the controllable range of the system. Carry out hierarchical multidimensional diagnosis for the control moment gyro (CMG) fault type, the specific steps are as follows:

[0037] The single-frame dual-degree-of-freedom control moment gyro controls the vector pointing of the constant angular momentum, and uses the rotation of the outer frame to quickly exchange the angular momentum of the satellite, thereby realizing the attitude control of the spacecraft. The main performance indicators of CMG are as follows:

[0038] Frame speed stability: ≤0.005(° / s)(3σ, speed |ω|<0.1(° / s));

[0039] ≤0.01(° / s)(3σ, 0.1≤speed|ω|≤0.5(° / s));

[0040] ≤2% (3σ, speed |ω|>0.5(° / s));

[0041] Frame angle control accuracy: ≤2′;

[0042]...

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Abstract

The invention discloses an on-board autonomic fault diagnosis method controlled based on a control moment gyro group, comprising step 1 of checking a communication state of an on-board computer with acontrol moment gyro; step 2 of diagnosing a working state according to control moment gyro return; and step 3 of diagnosing data according to control moment gyro return. The control moment gyro is output of two degrees of freedom. According to a control manner of the control moment gyro, data of an internal frame and data of an external frame are respectively diagnosed, wherein diagnosis of a rotational speed is performed for the internal frame and diagnosis of a rotational speed and a position is performed for the external frame. The invention has the advantages of timely and effectively diagnosing a potential data abnormality, and, by designing a system fault value threshold and a fault cumulative frequency threshold, timely disposing a fault reflector, to avoid introduction of abnormal data into system control and also facilitate rapid response of the system to a fault, such that its engineering application is relatively simple and it is also convenient to be implemented.

Description

technical field [0001] The invention relates to the technical field of satellite control, in particular to an engineering application method for controlling the satellite attitude by using a single-frame dual-degree-of-freedom control moment gyroscope and realizing autonomous fault diagnosis of the satellite control moment gyroscope. Background technique [0002] With the increasing requirements of satellite missions on the platform, it has become a trend to use a Control Moment Gyroscope (CMG) with a large torque output to achieve rapid and large-angle attitude maneuvering and stable control of satellites. The focus of the single-frame control moment gyro group control system design is to control the gyro group angular momentum management and group singularity avoidance. According to the control moment gyro configuration, the system needs to analyze the configuration benefit, failure benefit and internal singular state of the gyroscope group, and design a reasonable control...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
CPCG05B23/0243G05B2219/24065
Inventor 陈秀梅李小斌王新陈为伟陈撼
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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