Satellite sensor fault detection and positioning method based on self-encoding observer

A technology of fault detection and positioning method, which is applied to instruments, measuring devices, integrated navigators, etc., and can solve problems such as insufficient fault positioning accuracy of sensors

Active Publication Date: 2020-04-28
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
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Problems solved by technology

[0003] Purpose of the invention: Aiming at the problem of insufficient fault location accuracy of sensors in satellite attitude control systems in the prior art, the present invention p

Method used

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  • Satellite sensor fault detection and positioning method based on self-encoding observer
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  • Satellite sensor fault detection and positioning method based on self-encoding observer

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Embodiment 1

[0073] The method of the present invention is based on the self-encoding observer to detect and locate the fault of the satellite attitude sensor, the training stage and the application stage, such as figure 1 As shown, the specific steps are as follows:

[0074] (1) Design multiple self-encoding observers according to the attitude sensor equipped on the satellite, and use the sensor's fault-free data to train the self-encoding observer, so that the encoder can compress the sensor signal, and the self-encoding observer can start from The sensor signal is back-calculated from the data compressed by the encoder.

[0075] (2) Input the sensor signal into the autoencoder observer, and compare the input and output of the autoencoder observer to obtain the residual error.

[0076] (3) After the residuals are generated, feature information is extracted from the residuals. The residual feature information includes the mean value, mean square error and Shannon information entropy of t...

Embodiment 2

[0137] The attitude sensor is configured as Figure 5 The satellite carries out fault detection and location, a kind of satellite attitude sensor fault location method based on self-encoder observer of the present invention The specific implementation steps are as follows:

[0138] (1) According to the type and number of measurement signals of the attitude sensor configured on the satellite, the measurement signal types include vector type, attitude type and angular velocity type, and the number of self-encoding observers is designed to be 7:

[0139] Table 1 Autoencoder observer design

[0140]

[0141] And according to the input signal requirements of these 7 self-encoder observers, the output signal of the satellite attitude sensor is collected when there is no fault, and the self-encoder observer is trained.

[0142] Among them, Γ 1 The tracking effect of the autoencoder observer on the sensor signal is as follows: Figure 6 As shown, due to the slow change of the or...

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Abstract

The invention discloses a satellite sensor fault detection and positioning method based on a self-encoding observer. According to the method, fault detection and positioning are carried out on a satellite attitude sensor based on a self-encoding observer. To be specific, according to an observer design based on an auto-encoder and a support vector machine system, self-coding observers are built according to a satellite attitude measurement method, inputs and outputs of the observers are compared to generate residual errors, the support vector machine is used for detecting faults according to mean values, mean square errors and information entropies of the residual errors, and detection results of the multiple self-coding observers are combined to locate fault sensors. According to the invention, fault detection and fault positioning can be carried out in combination with signals of a plurality of satellite attitude sensors, and the reliability and ground monitoring capability of a satellite attitude control system are improved.

Description

technical field [0001] The invention belongs to the satellite attitude sensor fault diagnosis technology, in particular to a satellite attitude sensor fault location method based on an autoencoder observer. Background technique [0002] With the continuous development of aerospace technology, the complexity of aerospace missions continues to increase, and the density of spacecraft system functions also continues to increase. As a system with complex structures and functions, spacecraft research and development is time-consuming and expensive. The spacecraft attitude control subsystem is one of the most important subsystems of the spacecraft. In order to ensure the reliability of the spacecraft, multiple attitude sensors are often configured redundantly, but it also increases the complexity of the fault diagnosis method design, so that the fault diagnosis method can be Decreased transplantability. Therefore, it is urgent to propose a method that can fuse multiple attitude se...

Claims

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Application Information

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IPC IPC(8): G01C25/00G01C21/24
CPCG01C25/00G01C21/24
Inventor 程月华叶正宇姜斌陆宁云何漫丽薛琪
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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