Satellite attitude control system failure diagnosis device and method based on state observer and equivalent space

A state observer and fault diagnosis technology, applied in the field of aerospace, can solve the problems of low control accuracy, poor effectiveness of fault diagnosis algorithms, and high hardware complexity, achieve simple and effective algorithms, facilitate on-orbit real-time fault diagnosis, and overcome limitations. Effect

Active Publication Date: 2011-09-07
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] The purpose of the present invention is to solve the problems of high hardware complexity, low control precision, and poor effectiveness of fault diagnosis algorithms in traditional fault diagnosis methods, and to provide a satellite attitude control system fault diagnosis device and method based on state observers and equivalent spaces

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  • Satellite attitude control system failure diagnosis device and method based on state observer and equivalent space
  • Satellite attitude control system failure diagnosis device and method based on state observer and equivalent space
  • Satellite attitude control system failure diagnosis device and method based on state observer and equivalent space

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specific Embodiment approach 1

[0027] Specific implementation mode one: the following combination figure 1 Describe this embodiment, a satellite attitude control system fault diagnosis device based on state observer and equivalent space described in this embodiment, the devices that are prone to failure on the satellite include actuators and sensors, and gyroscopes in various sensors The utilization rate of the sensor is the highest, and the probability of failure is also the highest. Therefore, the present invention is mainly aimed at the satellite attitude control system fault diagnosis device designed for fault diagnosis of actuators and gyro sensors. The satellite attitude control system fault diagnosis device includes satellite attitude Dynamic model construction module 1, fault diagnosis observer 2, equivalent vector space description module 3 and fault diagnosis and isolation module 4,

[0028] The satellite attitude dynamics model building block 1 constructs the satellite attitude dynamics model acc...

specific Embodiment approach 2

[0031] Specific implementation mode two: the following combination figure 1 Describe this embodiment, this embodiment is further described to embodiment one: the satellite attitude dynamics model that the satellite attitude dynamics model construction module 1 builds is:

[0032] x · 1 ( t ) x · 2 ( t ) x · 3 ( t ) = ...

specific Embodiment approach 3

[0038] Specific implementation mode three: the following combination figure 1 Describe this embodiment, this embodiment will further explain Embodiment 1: the observation equation of the fault diagnosis observer 2 is:

[0039] x ^ · 1 ( t ) x ^ · 2 ( t ) x ^ · 3 ...

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Abstract

The invention discloses a satellite attitude control system failure diagnosis device based on a state observer and an equivalent space and a satellite attitude control system failure diagnosis method based on the state observer and the equivalent space, which belong to the field of aerospace and aim to solve the problems of high hardware complexity, low control accuracy and low failure diagnosis algorithm effectiveness of the conventional failure diagnosis method. The method provided by the invention comprises the following steps that: 1, a failure diagnosis observer outputs a satellite triaxial angular rate residual according to output signals of an actuator and a gyro sensor; 2, an equivalent vector space description module constructs equivalent space descriptions of the gyro sensor according to the output signal of the gyro sensor, wherein an output equivalent vector p is used for judging whether the gyro sensor fails or not; and 3, a failure diagnosis and isolation module outputs a failure separation result indicating that the actuator or the gyro sensor fails according to the satellite triaxial angular rate residual obtained by the step 1 and the equivalent vector p obtained by the step 2, and further judges which axis of the failing part fails.

Description

technical field [0001] The invention relates to a fault detection and isolation method for a sensor and an actuator of a satellite attitude control system based on a state observer and an equivalent space, and belongs to the field of aerospace. Background technique [0002] The satellite attitude control system is an important part to ensure the normal operation of the satellite. It consists of satellite body, attitude sensitive measurement components (such as gyro inertial group, sun sensor, GPS and other sensors), attitude control execution components (such as flywheel, torque gyro, Actuators such as jet devices) and attitude controllers (such as CPU, DSP and other processors), satellite attitude control system failures mostly occur in sensors (also known as sensors) and actuators. [0003] At present, fault diagnosis technology has been greatly developed in the aerospace field, and many theoretical research results and certain practical results have been obtained. Accord...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
Inventor 沈毅纪延琚张淼王振华
Owner HARBIN INST OF TECH
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