【摘要】：以數(shù)控技術(shù)為基礎(chǔ)的柔性化制造、安裝技術(shù),以其優(yōu)秀的柔性自動化性能而得到廣泛關(guān)注。以該技術(shù)為代表的數(shù)字化裝配系統(tǒng),給傳統(tǒng)機(jī)械制造業(yè)帶來了巨大變革。飛機(jī)發(fā)動機(jī)作為飛機(jī)的動力部件,其安裝質(zhì)量將決定飛機(jī)的整體飛行性能。將數(shù)字化安裝系統(tǒng)應(yīng)用于飛機(jī)發(fā)動機(jī)安裝過程,不僅能提高生產(chǎn)效率、降低成本,更能保證高質(zhì)量的發(fā)動機(jī)安裝。本文從國內(nèi)外飛機(jī)發(fā)動機(jī)數(shù)字化安裝系統(tǒng)的研究現(xiàn)狀以及國內(nèi)飛機(jī)發(fā)動機(jī)安裝現(xiàn)場實(shí)際情況出發(fā),對飛機(jī)發(fā)動機(jī)數(shù)字化安裝系統(tǒng)進(jìn)行了設(shè)計(jì),并且針對伺服系統(tǒng)以及控制算法進(jìn)行了研究。首先,本文根據(jù)飛機(jī)發(fā)動機(jī)數(shù)字化安裝平臺的技術(shù)指標(biāo)與功能要求,基于開放式數(shù)控系統(tǒng)的設(shè)計(jì)理念,對控制系統(tǒng)進(jìn)行了軟、硬件的總體設(shè)計(jì)。在此基礎(chǔ)上考慮控制精度指標(biāo)以及設(shè)備的經(jīng)濟(jì)性,進(jìn)行了半閉環(huán)的伺服系統(tǒng)結(jié)構(gòu)設(shè)計(jì),并且針對機(jī)械結(jié)構(gòu)的引入誤差建立了機(jī)械誤差補(bǔ)償表,實(shí)現(xiàn)對機(jī)械誤差的補(bǔ)償。其次,針對伺服系統(tǒng)模型未知、系統(tǒng)參數(shù)難以獲得的實(shí)際情況,設(shè)計(jì)了基于最小二乘法的階躍響應(yīng)的系統(tǒng)辨識實(shí)驗(yàn)。通過最小二乘法將不同階次模型對響應(yīng)曲線進(jìn)行擬合,將擬合效果最好的模型作為系統(tǒng)等效模型,從而辨識出控制系統(tǒng)模型。根據(jù)系統(tǒng)控制精度以及動態(tài)響應(yīng)性能的要求,進(jìn)行了控制系統(tǒng)位置環(huán)控制器的設(shè)計(jì),分別對傳統(tǒng)PID控制器、遺傳優(yōu)化的PID控制器、BP神經(jīng)網(wǎng)絡(luò)PID控制器以及遺傳優(yōu)化的BP神經(jīng)網(wǎng)絡(luò)PID控制器的控制效果進(jìn)行了仿真研究,綜合考慮算法復(fù)雜程度、控制穩(wěn)定性以及實(shí)際控制指標(biāo),選取了遺傳優(yōu)化的PID控制器作為控制系統(tǒng)位置環(huán)控制器。最后,針對控制系統(tǒng)各項(xiàng)設(shè)計(jì)指標(biāo),進(jìn)行了控制系統(tǒng)性能測試實(shí)驗(yàn)。通過搭建的控制系統(tǒng)硬件平臺以及設(shè)計(jì)的人機(jī)交互軟件,進(jìn)行了控制系統(tǒng)軟、硬件系統(tǒng)的聯(lián)調(diào)。針對系統(tǒng)動態(tài)響應(yīng)性能以及定位精度的設(shè)計(jì)指標(biāo),進(jìn)行了控制系統(tǒng)動態(tài)性能實(shí)驗(yàn)以及定位精度實(shí)驗(yàn)。實(shí)驗(yàn)結(jié)果表明：設(shè)計(jì)的控制系統(tǒng)滿足動態(tài)性能設(shè)計(jì)要求以及定位精度設(shè)計(jì)指標(biāo),有效地提高了飛機(jī)發(fā)動機(jī)安裝效率與安裝精度。
[Abstract]:The flexible manufacturing and installation technology based on numerical control technology has been paid more and more attention for its excellent flexible automation performance. The digital assembly system represented by this technology has brought great changes to the traditional mechanical manufacturing industry. Aircraft engine as a power component of aircraft, its installation quality will determine the overall flight performance of the aircraft. The application of the digital installation system to the aircraft engine installation process can not only improve the production efficiency, reduce the cost, but also guarantee the high quality engine installation. In this paper, the digital installation system of aircraft engine is designed based on the status quo of domestic and foreign aircraft engine digital installation system and the actual situation of domestic aircraft engine installation site. And the servo system and control algorithm are studied. Firstly, according to the technical specifications and function requirements of the aircraft engine digital installation platform, based on the design concept of open numerical control system, the software and hardware of the control system are designed. On this basis, considering the control precision index and the economy of the equipment, the structure design of the semi-closed loop servo system is carried out, and the mechanical error compensation table is established for the introduction of the mechanical structure error to realize the compensation of the mechanical error. Secondly, aiming at the actual situation that the servo system model is unknown and the system parameters are difficult to obtain, a step response identification experiment based on the least square method is designed. The response curve is fitted with different order models by the least square method, and the model with the best fitting effect is regarded as the equivalent model of the system, and the control system model is identified. According to the requirements of system control precision and dynamic response performance, the position loop controller of the control system is designed. The control effects of genetic optimization PID controller and genetic optimization BP neural network PID controller are simulated and studied. The algorithm complexity, control stability and actual control index are considered synthetically. The genetic optimization PID controller is selected as the position loop controller of the control system. Finally, the performance of the control system is tested according to the design index of the control system. Through the hardware platform of the control system and the human-computer interactive software, the software and hardware of the control system are adjusted. According to the dynamic response performance of the system and the design index of the positioning accuracy, the dynamic performance experiment and the positioning precision experiment of the control system are carried out. The experimental results show that the designed control system meets the requirements of dynamic performance design and positioning accuracy design, and effectively improves the installation efficiency and accuracy of aircraft engine.
【學(xué)位授予單位】：大連理工大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V263;TP273

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本文編號：2149333