A Fault Diagnosis Method for Low Speed ​​Frame of Single Frame Control Moment Gyroscope

A technology for controlling torque gyro and fault diagnosis, which is applied in the field of spacecraft, can solve problems that endanger the safety of the entire star, and achieve the effect of improving reliability and accuracy, improving safety and reliability

Active Publication Date: 2019-08-09
BEIJING INST OF CONTROL ENG
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AI Technical Summary

Problems solved by technology

From the control principle of SGCMG, it can be seen that the control torque output is directly related to the low-speed frame rotation speed. Therefore, if the low-speed frame rotation fails during the control process, it will cause a large output disturbance torque to directly act on the spacecraft. If it cannot be processed in time, then It may endanger the safety of the whole star

Method used

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  • A Fault Diagnosis Method for Low Speed ​​Frame of Single Frame Control Moment Gyroscope
  • A Fault Diagnosis Method for Low Speed ​​Frame of Single Frame Control Moment Gyroscope
  • A Fault Diagnosis Method for Low Speed ​​Frame of Single Frame Control Moment Gyroscope

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Embodiment

[0062] A single-frame control moment gyro low-speed frame fault diagnosis method, the single-frame control moment gyroscope is applied to a satellite, and is used as an actuator of the satellite, and the satellite also includes an attitude and orbit control computer (AOCC), an attitude and orbit control computer (AOCC) is used to send control commands to the actuator and receive the measurement data returned by the actuator;

[0063] set m FCMG1 =10, m FCMG2 =13, m L1 = 0.5°, m L2 = 1°, m L3 = 10°, m Δδ = 0.1.

[0064] The method comprises the steps of:

[0065] (1) Determine the fault detection time interval Δt of the low-speed frame of the single-frame control torque gyro FDcmg = t k+1 -t k = 3s, with t 0 = 0 as the initial time and also as the starting time, t 1 is the end time, that is, the end time is 3s time;

[0066] (2) Calculate the integral of the low-speed frame angular velocity command sent by the AOCC to the single-frame control torque gyroscope within...

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Abstract

The invention relates to a single gimbal control moment gyro low speed framework fault diagnosis method, belongs to the spacecraft attitude determination and control technology field, particularly relates to a fault diagnosis method utilizing a single gimbal control moment gyro on a spacecraft as a spacecraft attitude control performing mechanism and is suitable for the spacecraft utilizing the single gimbal control moment gyro (SGCMG) as the performing mechanism. The method is advantaged in that deviation of an SGCMG low speed framework theory motion angle and an actual low speed framework operation angle is utilized to carry out fault detection, fault determination threshold design is combined with an SGCMG motion state, a fault diagnosis threshold is autonomously and dynamically adjusted according to the SGCMG instruction angle speed, and fault diagnosis reliability and accuracy in application occasions with relatively large SGCMG low speed framework motion speed change are improved.

Description

technical field [0001] The invention relates to a single-frame control moment gyro low-speed frame fault diagnosis method, which belongs to the technical field of spacecraft attitude determination and control, and particularly relates to a single-frame control moment gyro applied to a spacecraft as a spacecraft attitude control executive mechanism. A diagnostic method for spacecraft using a single frame control moment gyroscope (SGCMG) as the actuator. Background technique [0002] Single Frame Controlled Moment Gyro (SGCMG) generates gyro torque by controlling low-speed frame rotation to cause high-speed rotor precession, and then obtains a large control torque output. It is currently the preferred control actuator for spacecraft that has a large demand for control torque. From the control principle of SGCMG, it can be seen that the control torque output is directly related to the low-speed frame rotation speed. Therefore, if the low-speed frame rotation fails during the co...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B23/02
Inventor 张春青雷拥军刘其睿瞿涵顾斌
Owner BEIJING INST OF CONTROL ENG
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