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Integrated electronic system health management module and method for small satellites

An integrated electronic system and health management technology, applied in the field of integrated electronic system health management devices, can solve the problems of signal interference, satellite deorbit, increase maintenance cost, etc.

Inactive Publication Date: 2018-08-07
HARBIN ENG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Once the software or hardware of the traditional small satellite fails, it will not be able to operate normally, which will cause data errors, signal interference, and seriously cause the satellite to deorbit or even fall. , another small satellite with the same configuration needs to be launched, increasing maintenance costs

Method used

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  • Integrated electronic system health management module and method for small satellites
  • Integrated electronic system health management module and method for small satellites
  • Integrated electronic system health management module and method for small satellites

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Experimental program
Comparison scheme
Effect test

specific Embodiment approach 1

[0017] Specific implementation mode 1: Fault detection of the integrated electronic system of the small satellite. Fault detection is the basis for judging the occurrence of faults. It is to extract the parameters that characterize the occurrence of faults from the detection data, and to judge whether the integrated electronic system of the small satellite is faulty.

[0018] The present invention includes ADSP-SC589 type DSP 1, Flash memory 2, SRAM 3, PROM 4, 82C250 type CAN bus level conversion chip 5.

[0019] DSP1 is connected with PROM4. PROM4 is a non-volatile memory with small capacity but high reliability of on-track data. The boot file of DSP1 is stored on PROM4. DSP1 is connected with Flash2. Flash2 is a non-volatile memory with large capacity but lower in-track data reliability than PROM4. Flash2 is divided into three sections to store program files at different addresses. DSP1 is connected with SRAM3, and SRAM3 belongs to 32-bit memory, which is used as the memory...

specific Embodiment approach 2

[0031] Embodiment 2: On the basis of Embodiment 1, the fault isolation of the integrated electronic system of the small satellite is realized. Through fault isolation, the specific location of the fault source can be identified, that is, DSP 1 detects the small The health status of each subsystem or sub-part of the satellite integrated electronic system is determined separately, and the faulty subsystem or sub-part is finally determined.

specific Embodiment approach 3

[0032] Specific implementation mode 3: On the basis of implementation scheme 2, realize the fault identification of the small satellite integrated electronic system, that is, make a judgment on the fault degree of each part of the system, and identify the fault symptoms of system components that have no obvious faults. Aiming at the non-linear characteristics of the small satellite integrated electronic system, this scheme adopts the fault identification method based on the linearization processing technology.

[0033] Firstly, the state observer of the integrated electronic system of the small satellite is designed, and the formula is as follows:

[0034]

[0035] y(t)=H(x(t))+E·f(t)

[0036] In the formula: x(t) is the state variable, u(t) is the control input variable, y(t) is the system output variable, f(t) is the fault signal, G(·), H(·) are the system State function and observation function, F and E are known matrices.

[0037] Secondly, it is linearized at the (0,...

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Abstract

The invention provides an integrated electronic system health management module and method for small satellites. The system comprises an ADSP-SC589 type DSP 1, a Flash memory 2, an SRAM 3, a PROM 4 and an 82C250 type CAN bus level conversion chip 5. Autonomous fault detection, fault isolation and fault identification of small satellites in orbit operation can be realized, health state determination of a small satellite integrated electronic system is carried out according to the result, and the important reference information is provided for upgrade and improvement of small satellite follow-upsystems. The system is advantaged in that autonomous fault prediction for the small satellites in orbit operation can be realized, a fault source generating a fault, the fault size and the fault generation time are predicted, the basis is provided for self repair of the small satellites, the service life of the small satellites is prolonged, and maintenance cost of the small satellites is reduced.

Description

technical field [0001] The invention relates to a small satellite integrated electronic system health management device and health management method. Background technique [0002] With the development of small satellite technology, it is necessary to reduce the maintenance cost of small satellites. This requires small satellites to be able to perform on-orbit autonomous fault detection, fault isolation, fault identification, fault prediction, and health status judgment. The fault-tolerant and self-repair capabilities can independently perform self-repair operations based on the output data information of the health management system module. Once the software or hardware of the traditional small satellite fails, it will not be able to operate normally, which will cause data errors, signal interference, and seriously cause the satellite to deorbit or even fall. , need to launch another small satellite with the same configuration, increasing maintenance costs. In addition, th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
CPCG05B23/0213G05B2219/24065
Inventor 刘源王艺鹏程建华赵琳郝勇王硕赵坤李亮李慧丁继成
Owner HARBIN ENG UNIV
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