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基于多層前饋神經(jīng)網(wǎng)絡(luò )的航天器在線(xiàn)故障檢測系統設計
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成都信息工程大學(xué) 網(wǎng)絡(luò )空間安全學(xué)院

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Design of Spacecraft Online Fault Detection System Based on Multilayer Feedforward Neural Network
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    摘要:

    航天器在故障定位過(guò)程中易受原始電源信號的干擾,導致識別效果較差,為了解決該問(wèn)題,提出了基于多層前饋神經(jīng)網(wǎng)絡(luò )的航天器在線(xiàn)故障檢測系統設計。根據航天器在線(xiàn)故障檢測原理及物聯(lián)網(wǎng)技術(shù)設計系統總體架構,并分別對硬件部分及軟件部分進(jìn)行設計。硬件部分結合工業(yè)標準?PC組件,設計PXI機箱結構,完成對PXI測量模塊的控制,利用MXI-4接口工具實(shí)現遠程遙控,解決干擾信號對系統定位識別干擾。設計FPGA的EP3C10芯片外圍結構,確定電路板主、子適配器管腳連接方式,利用2個(gè)高速?AD轉換器差分采樣,通過(guò)?FIFO存儲采樣結果。通過(guò)電子負載板繼電器控制模塊,控制信號阻斷性能。構建基于多層前饋神經(jīng)網(wǎng)絡(luò )識別模型,依據確定性邏輯推理規則得出識別門(mén)限值,依據閾值設定具體識別流程,判斷則判定參數有故障,完成系統設計。實(shí)驗結果表明,該系統信號阻斷效果優(yōu)異,在距離為2和6 m時(shí)達到最大信號幅值0.9,故障模式的檢測結果與理想結果一致,能夠為航天器穩定運行提供設備支持。

    Abstract:

    In the process of fault location, the spacecraft is susceptible to the interference of the original power signal, which leads to a poor recognition effect. To solve this problem, a design of a spacecraft online fault detection system based on a multilayer feedforward neural network is proposed. According to the spacecraft online fault detection principle and the Internet of Things technology, the overall architecture of the system is designed, and the hardware and software parts are designed respectively. The hardware part combines the industry standard PC components to design the PXI chassis structure, complete the control of the PXI measurement module, and use the MXI-4 interface tool to achieve remote control to solve the interference signal to the system positioning identification interference. Design the peripheral structure of the EP3C10 chip of FPGA, determine the connection mode of the main and sub adapter pins of the circuit board, use 2 high-speed AD converter differential sampling, and store the sampling results through the FIFO. Through the electronic load board relay control module, control signal blocking performance. A recognition model based on a multi-layer feed-forward neural network is constructed, a recognition threshold is obtained according to deterministic logic inference rules, a specific recognition process is set according to the threshold, and the judgment determines that the parameter is faulty and the system design is completed. Experimental results show that the signal blocking effect of the system is excellent, and the maximum signal amplitude is 0.9 at distances of 2 and 6 m. The detection results of the failure mode are consistent with the ideal results, which can provide equipment support for the stable operation of the spacecraft.

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戴峻峰,趙建.基于多層前饋神經(jīng)網(wǎng)絡(luò )的航天器在線(xiàn)故障檢測系統設計計算機測量與控制[J].,2020,28(8):93-97.

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  • 收稿日期:2020-05-21
  • 最后修改日期:2020-06-10
  • 錄用日期:2020-06-10
  • 在線(xiàn)發(fā)布日期: 2020-08-13
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