【正文】 4 結(jié)束語通過采用具有良好特性的廣義 RBF 神經(jīng)網(wǎng)絡(luò), 對(duì)回滯系統(tǒng)直接進(jìn)行逆模型建模, 然后用逆模型實(shí)施前饋控制, 可以大大減少回滯現(xiàn)象。由于該監(jiān)測(cè)系統(tǒng)屬于機(jī)載設(shè)備, 因此應(yīng)在考慮設(shè)備體積的基礎(chǔ)上來提高系統(tǒng)的可靠性, 根據(jù)系統(tǒng)所監(jiān)測(cè)數(shù)據(jù)的調(diào)理電路特征來考慮設(shè)計(jì)冗余調(diào)理電路。信號(hào)調(diào)理部分在使用一段時(shí)間后存在著偏差, 模擬通道的誤差特性也可能隨著時(shí)間而緩慢變化, 在該系統(tǒng)中數(shù)字通道和模擬通道的數(shù)量較多, 定期手工測(cè)量每個(gè)通道的完好性和通道特性是不可能的, 所以設(shè)計(jì)一套自檢系統(tǒng)來滿足這個(gè)要求, 該系統(tǒng)的自檢系統(tǒng)包括兩個(gè)功能: 檢測(cè)調(diào)理通道的正確性。PC/ 104 多功能采集板及自檢/現(xiàn)場(chǎng)切換電路用來實(shí)現(xiàn)對(duì)系統(tǒng)自檢和現(xiàn)場(chǎng)數(shù)據(jù)采集的切換, 以及自檢電壓的發(fā)送。 地面試車方式有機(jī)的結(jié)合了機(jī)載運(yùn)行方式和數(shù)據(jù)回放方式, 將發(fā)動(dòng)機(jī)試車過程中采集到的參量經(jīng)過處理, 再通過串口將它們實(shí)時(shí)的傳送到上位機(jī)[ 4], 上位機(jī)再將數(shù)據(jù)實(shí)時(shí)的顯示出來, 同時(shí)將它們進(jìn)行保存。特別是隨著發(fā)動(dòng)機(jī)性能的提高, 狀態(tài)監(jiān)測(cè)時(shí)所需要實(shí)時(shí)監(jiān)測(cè)的參數(shù)越來越多, 多年來人們不斷探索新的測(cè)試技術(shù), 以適應(yīng)日益發(fā)展著的發(fā)動(dòng)機(jī)試驗(yàn)技術(shù)的要求。 2. 西北工業(yè)大學(xué), 陜西 西安710072)摘要: 以某型航空發(fā)動(dòng)機(jī)為研究對(duì)象, 討論了發(fā)動(dòng)機(jī)狀態(tài)監(jiān)測(cè)系統(tǒng)的設(shè)計(jì)和實(shí)現(xiàn), 主要探討了狀態(tài)監(jiān)測(cè)系統(tǒng)的總體設(shè)計(jì), 軟硬件開發(fā)及自檢系統(tǒng)和冗余設(shè)計(jì), 并在發(fā)動(dòng)機(jī)狀態(tài)監(jiān)測(cè)系統(tǒng)的設(shè)計(jì)中引入了嵌入式 PC/ 104 模塊。The data munication between upper machine and lower machine way using serial order to improve the extensibility and adaptability of engine state monitoring system, the system designed can work in three ways: airborne operation mode, data playback mode and ground test mode, including airborne operation mode can be PC / 104 modules separately in the form of the airborne launch during the real flight test, because of the PC / 104 modules, small volume, high reliability, high temperature resistance and resistance to adverse conditions, well adapted to the flight environment, to the parts of the flight state and parameters in the flight details and accurate acquisition, data processing and at the same time, all the data are stored in the solid plate, in order to perform data playback and analysis of engine performance in the future。Redundant design.0. The introduction As the power source of the airplane flight, aircraft engine research is a very plex process, the aircraft engine test as the development of the three pillars (calculation, manufacture and test), one of its importance is selfevident, it turns out, mainly consisted of engine test, rather than by calculation and the development of an aircraft engine group, is flat, how we can decide the how developed horizontal aircraft engine manufacture, condition monitoring is an important examination method of engine performance, by condition monitoring and testing work is to adjust the engine performance and breakin, check the manufacturing or overhaul quality, finally gives the engine factory performance report purpose, therefore the accurate and reliable test method for state monitoring to ensure the quality of the engine has the vital we all know, the engine vibration and high noise in the process of work and the strong jamming signal, all parameters to the variety of the monitoring system puts forward higher with the improvement of engine performance, realtime monitoring of the parameters needed for condition monitoring is being more and more people continue to explore new testing technology for many years, to adapt to the increasingly development of engine test technology requirements.1. The condition monitoring system overall design The condition monitoring system is designed for a certain type of turbofan engine, the engine monitoring system of the input signal is part of a total of 17 analog, 3 road 16 way switch frequency and quantity, including 17 analog, 3 road frequency quantity through the signal conditioning circuit into a standard signal conditioning, to lower place machine。t create any problems for digital signal, however, on the choice of design and physical ponents is difficult to guarantee the analog channel signal input and output equals the absolute, for analog signal data acquisition system of the main source of error is the system error, so the data must be taken into account the error and error correction to improve the accuracy of the data, apparently, error correction is mainly in view of the analog channel is conditioning part in use after period of time there is a deviation, error characteristics of the analog channel may over time slowly changing, digital channel and analog channel in the system is more, the number of regular manual measurement of the integrity of each channel and channel characteristics is impossible, so a selfchecking system is designed to meet this requirement, the system of selfinspection system consists of two functions: testing the correctness of the regulate channel。對(duì)于一個(gè)航空發(fā)動(dòng)機(jī)的研制群體來說, 具有怎平, 就決定著能夠研制出怎樣水平的發(fā)動(dòng)機(jī)。 上位機(jī)和下位機(jī)之間的數(shù)據(jù)通信方式采用串行通信來進(jìn)行。根據(jù)系統(tǒng)的工作環(huán)境對(duì)溫度、濕度、抗震性和抗干擾性的要求, 選用 PC/ 104 總線,同時(shí)下位機(jī)及外圍板卡都選用了 PC/ 104模塊, 以滿足航空機(jī)載設(shè)備對(duì)重量、體積等方面的要求。3 狀態(tài)的監(jiān)測(cè)和實(shí)時(shí)數(shù)據(jù)的顯示利用相關(guān)的控件和繪圖工具對(duì)采集的狀態(tài)參數(shù)進(jìn)行數(shù)字顯示和模擬表顯示, 并繪制出參數(shù)的時(shí)間曲線以便于觀測(cè)參數(shù)的動(dòng)態(tài)變化及未來趨勢(shì), 從而能夠監(jiān)視發(fā)動(dòng)機(jī)在不同時(shí)刻的工作狀態(tài), 達(dá)到狀態(tài)監(jiān)測(cè)的目的。(3) 通過 PC/ 104 A/ D 轉(zhuǎn)換板和 PC/ 104 數(shù)字 I/O板進(jìn)行自檢信號(hào)的采集。輸入控制信號(hào)