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A multi-probe star sensor on-orbit autonomous fault diagnosis and repair method

A technology of star sensor and fault diagnosis, applied in the field of satellite attitude control, can solve the problems of disturbance between data, wrong operation results, faults of imaging detectors, etc., and achieve the effect of improving product accuracy, fault tolerance and reliability.

Active Publication Date: 2021-04-13
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0014] Second, imaging detector failure
[0017] Third, memory failure
[0018] On the one hand, the failure of the memory is due to the dense array of internal cells in the memory, and there may be data disturbance between each other, including the mutual influence of data between rows, columns and cells; on the other hand, during the satellite flight, the star sensor signal processing The interior of the circuit, such as static random access memory, is sensitive to space radiation, and is prone to single event phenomenon, causing bit flips in instruction registers, stack pointer registers, interrupt vector tables and connection pointers, etc., resulting in disordered operation of product software
Since the operation code and operation data of the computer program are stored in the memory, depending on the location of the fault, two results may occur in the operation of the product program: one is to change the operation code, causing the program to run away or perform wrong operations; The second is to change the number of operands, resulting in wrong operation results

Method used

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  • A multi-probe star sensor on-orbit autonomous fault diagnosis and repair method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0059] Example 1 (the power supply status of the product probe is abnormal during power-on)

[0060] A multi-probe star sensor on-orbit autonomous fault diagnosis and repair method, the method is used for diagnosing the output image state of the probe and the power supply short circuit state of the probe, the steps of diagnosing the power supply state of the probe in the method include:

[0061] (1) The product is powered on and the hardware and software initialization is completed;

[0062] (2) Power off all probes of the product;

[0063] (3) Power on the probe 1, if the voltage status of the probe 1 is normal, then the working status of the probe 1 is normal, that is, the power supply is not interrupted, and the next step is performed;

[0064] (4) Power on the probe 2, if the voltage status of the probe 2 is normal, then the working status of the probe 2 is normal, that is, the power supply is not interrupted, and the next step is performed;

[0065] (5) Power on the pro...

Embodiment 2

[0067] Example 2 (the power supply status of the probe is abnormal during the working process of the product)

[0068] A multi-probe star sensor on-orbit autonomous fault diagnosis and repair method, the method is used for diagnosing the output image state of the probe and the power supply short circuit state of the probe, the steps of diagnosing the power supply state of the probe in the method include:

[0069] (1) Diagnose the working status of all probes. If the power supply voltage of all probes is found to be abnormal, set the working status of the product as abnormal, and proceed to the next step;

[0070] (2) Power off all probes;

[0071] (3) Power on the probe 1 again, the voltage status of the probe 1 is normal, and the working status of the probe 1 is normal, that is, the power supply is not interrupted, and the next step is performed;

[0072] (4) Power on the probe 2 again, if the voltage state of the probe 2 is abnormal, then set the working state of the probe ...

Embodiment 3

[0075] Example 3 (the output image state of a single probe is abnormal during the working process of the product)

[0076] (1) During the normal operation of the product, the output image status of all probes is monitored every cycle, and it is diagnosed that the probe 2 fails to output image data for 5 consecutive seconds, and the next step is performed;

[0077] (2) Power off the probe 2;

[0078] (3) After waiting for 2 seconds, power on the probe 2 again, and complete the reconfiguration of the probe's detector and ASIC / FPGA related registers;

[0079] (4) Re-initialize the FPGA / ASIC corresponding to probe 2;

[0080] (5) Diagnose the output image status of probe 2 again. If probe 2 still cannot output image data, repeat steps (1) to (5). After repeating 3 times, probe 2 still cannot output image data, and then set probe 2 to work. After the status is abnormal, power off the probe 2.

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Abstract

The invention relates to an on-orbit autonomous fault diagnosis and repair method of a multi-probe star sensor, belonging to the technical field of satellite attitude control. The multi-probe star sensor performs information fusion processing based on the star point information in the field of view of multiple probes to further improve product accuracy. After multiple probes are fused, the index is better than 0.6″ (3σ), and the index for a single probe is better than 1. ″(3σ), its technical characteristics are very high precision, high dynamic and high dynamic performance, and it is mainly used in remote sensing satellites and high-resolution earth observation satellites; Software-based independent fault diagnosis and repair method; at the same time, for the single-point problem of power supply and distribution in the product hardware design, the fault tolerance of the single machine and the system is improved; at the same time, it can perform real-time diagnosis and processing of multiple different faults of the product on orbit, effectively improving the The reliability of star sensor products.

Description

technical field [0001] The invention relates to an on-orbit autonomous fault diagnosis and repair method of a multi-probe star sensor, belonging to the technical field of satellite attitude control. Background technique [0002] The star sensor is an attitude measurement sensor with the highest measurement accuracy in aerospace applications. It uses the precisely positioned stars in the celestial sphere as an absolute reference system, and determines the attitude of the aircraft by detecting stars in different positions on the celestial sphere. The three-axis pose of the coordinate system. With the advantages of high precision, no drift and high reliability, it is a key component of satellite attitude measurement. [0003] The star sensor is a complex system composed of optical, mechanical and electrical components. Its working environment is special, and it must have high reliability and safety for long-term operation. It is inevitable for the star sensor system to fail d...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C25/00G01R31/52H02H3/10
CPCG01C25/00H02H3/10
Inventor 郑然程会艳关健张腾飞隋杰李玉明武延鹏杜建伟顾斌蒋志雄王玉爽赵江涛
Owner BEIJING INST OF CONTROL ENG
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