【正文】 為 r = , 神經(jīng)網(wǎng)絡(luò)逆模型的輸出為 v ( t) , 如圖 3 所示, 回滯系統(tǒng)在由神經(jīng)網(wǎng)絡(luò)逆模型單獨(dú)作用下的輸出為 w 1 ( t ) ,回滯環(huán)大為削弱,回滯現(xiàn)象基本消除。這種方法也可以推廣到其他類型的回滯系統(tǒng)的控制中。假設(shè) w ( t ) 等于 0,則系統(tǒng)是不穩(wěn)定的, 因?yàn)閷τ谌我?x , 0。自檢過程的實(shí)現(xiàn)過程如下:( 1) PC/ 104下位機(jī)中的自檢程序通過PC/ 104多功能采集板向端口K 發(fā)出 5 V 的自檢電壓, 此時系統(tǒng)進(jìn)入自檢狀態(tài)。狀態(tài)監(jiān)測系統(tǒng)軟件設(shè)計(jì)該狀態(tài)監(jiān)測系統(tǒng)軟件模塊的目標(biāo)是開發(fā)一套適用于航空發(fā)動機(jī)狀態(tài)監(jiān)測的平臺系統(tǒng), 它可以實(shí)時的對發(fā)動機(jī)工作過程中高壓轉(zhuǎn)速、油門角度、噴口位移、油針位置、燃油流量、振動 X、振動 Y、大氣溫度、T 5 溫度、T 7 溫度、燃油溫度、滑油溫度、液壓溫度、車臺靜壓、外函靜壓、高壓出壓、燃油進(jìn)油壓力、滑油壓力、液壓油壓力等 17路模擬量和 3路頻率量, 以及16 路開關(guān)量進(jìn)行數(shù)據(jù)采集、處理、存儲、通信、狀態(tài)顯示和報警等操作, 軟件分別運(yùn)行在上位機(jī)和下位機(jī)上, 系統(tǒng)具體功能包括:1實(shí)時狀態(tài)參數(shù)的采集和處理在該系統(tǒng)中, 完成發(fā)動機(jī)各種狀態(tài)參數(shù)的實(shí)時采集, 并對采集的狀態(tài)參數(shù)進(jìn)行相關(guān)的處理和運(yùn)算, 并對偏離正常值一定的范圍的狀態(tài)參數(shù)作上標(biāo)記, 以便事后對發(fā)動機(jī)工作狀況進(jìn)行分析。綜合考慮各方面因素, 系統(tǒng)的上位機(jī)和下位機(jī)都采用微機(jī), 同時選用成熟的A/ D 轉(zhuǎn)換板和數(shù)字 I/ O 板來采集信號, 并自行設(shè)計(jì)信號調(diào)理電路對信號進(jìn)行隔離、濾波、放大等處理, 變換成標(biāo)準(zhǔn)信號。在數(shù)據(jù)處理部分中需要對發(fā)動機(jī)的狀態(tài)參數(shù)進(jìn)行連續(xù)的監(jiān)測,因此在采用的同時需要對信號進(jìn)行處理、保存和傳輸, 同時上位機(jī)需要對信號進(jìn)行實(shí)時接收并顯示, 如果采樣值超過其上下限則給與報警, 包括下位機(jī)的蜂鳴和上位機(jī)的屏幕報警。 PC/ 104。s upper machine and lower machine USES the microputer, and selects the maturity of the A/D conversion board and digital I/O board to collect signals, and designed the signal disposal circuit of signal isolation, filtering and amplification processing, transformation into A standard used to develop ways to meet the system to the working environment temperature, humidity, vibration resistance and antiinterference requirements, choose the PC / 104 bus, and lower place machine and peripheral boards have to choose the PC / 104 module, in order to meet the aircraft airborne equipment requirement for the weight, volume, etc.2．condition monitoring system hardware design Based on the system overall design, the whole monitoring system hardware is shown in figure 1 USES hardware structure classifiers, by A P4 PC and A PC / 104 into A unit, under the lower machine and PC / 104 motherboard, peripheral interface card, and all kinds of circuit, and various peripheral interface card circuit including: 3 PC / 104 A/D conversion board, 2 pieces of PC / 104 digital I/O board, light 1 PC / 104 multifunction acquisition board, terminal board, signal disposal circuit switching circuit and field/ / 104 motherboards, PC / 104 A/D conversion board and PC / 104 digital light every I/O board implementation of engine simulation signal measure and frequency A/D conversion and collection, as well as to the amount of engine digital signal isolation, and signal data processing of collection, storage and / 104 multifunction acquisition boards and selfinspection/scene switching circuit is used to implement the system selfchecking and site data acquisition of switching, and sending selfchecking conditioning circuit to isolation, filtering, amplifying the signal, they transform into standard signal, and then into a are used to implement the data acquisition machine by sending data receiving, storage, display and alarm. monitoring system software design Of the condition monitoring system software module39。沈陽航空航天大學(xué)畢業(yè)設(shè)計(jì)外文翻譯學(xué) 院自動化學(xué)院專 業(yè)運(yùn)載器這測試技術(shù)班 級94070301學(xué) 號2009040510011姓 名李萬峰指導(dǎo)教師崔建國負(fù)責(zé)教師崔建國沈陽航空航天大學(xué)2013年6月9沈陽航空航天大學(xué)畢業(yè)設(shè)計(jì)（外文翻譯）Aeroengine condition monitoring system design studyDesign research abstract: the aircraft engine condition monitoring system for a certain type of aircraft engine as the research object, discussed the engine state monitoring system design and implementation, this paper mainly discusses the status monitoring system of the overall design, system software and hardware development and testing and redundancy design, and in the design of engine state monitoring system, introduced the embedded PC / 104 order to make the state monitoring system has a better scalability and adaptability, the system designed can work in three ways: airborne operation mode, data playback mode and ground test run mode, through these way for automatic monitoring of engine state parameter, for the state of the engine trend analysis, fault diagnosis, and as to provide scientific basis for maintenance.Key words: the engine condition monitoring。Ground test methods organic bination of the airborne playback mode, operation mode and data will be collected in the process of engine test parameters are processed, then realtime transmitting them via a serial port to the PC [4], PC can display the data in real time again at the same time to save order to improve the reliability of the system, make the system selfcheck function and redundant Yu Jiegou, according to the system fault conditions to change the modulation circuit or to the requirements of aircraft engine test of 20 analog qua