【摘要】：飛機(jī)的全靜壓系統(tǒng)是飛機(jī)的必備系統(tǒng),其工作是否正常直接影響飛行安全,因此在維護(hù)過程中,對(duì)飛行器全靜壓系統(tǒng)的測(cè)試至關(guān)重要。本課題所設(shè)計(jì)的全靜壓測(cè)試器可以用在需要進(jìn)行飛機(jī)進(jìn)行全靜壓測(cè)試的內(nèi)場(chǎng)維修和外場(chǎng)維修中,系統(tǒng)按照測(cè)試人員的操作指令,為飛機(jī)全靜壓系統(tǒng)分別提供相應(yīng)的氣壓源,同時(shí)有自動(dòng)泄露檢測(cè)等常用功能。系統(tǒng)具備完整性和創(chuàng)新性,便于操作,能夠?qū)崿F(xiàn)對(duì)全靜壓系統(tǒng)的全自動(dòng)測(cè)試,控制精度高,可以代替進(jìn)口的高價(jià)設(shè)備,具備完全的自主知識(shí)產(chǎn)權(quán),并實(shí)現(xiàn)了設(shè)備的自主維護(hù),節(jié)約了民航領(lǐng)域相關(guān)環(huán)節(jié)的成本。本課題在分析控制系統(tǒng)的結(jié)構(gòu)和要求的基礎(chǔ)上,建立了系統(tǒng)的數(shù)學(xué)模型,針對(duì)氣壓控制系統(tǒng)設(shè)計(jì)了PID算法控制器,解決了小流量氣壓控制系統(tǒng)的控制問題;根據(jù)設(shè)備指標(biāo)對(duì)執(zhí)行機(jī)構(gòu)和其它器件進(jìn)行了選擇,根據(jù)操作要求對(duì)整個(gè)系統(tǒng)的結(jié)構(gòu)、硬件、軟件進(jìn)行了設(shè)計(jì),完成了組裝和調(diào)試工作;對(duì)研制完成的設(shè)備進(jìn)行了實(shí)驗(yàn)驗(yàn)證,與仿真結(jié)果相互對(duì)比,表明系統(tǒng)達(dá)到了設(shè)計(jì)的最初目標(biāo)。
[Abstract]:The total static pressure system of aircraft is an essential system for aircraft. Whether its work is normal or not directly affects flight safety. Therefore, in the maintenance process, it is very important to test the total static pressure system of aircraft. The total static pressure tester designed in this paper can be used in the internal field maintenance and the outside field maintenance which need the aircraft to carry out the full static pressure test. The system provides the corresponding air pressure source for the aircraft total static pressure system according to the operation instruction of the tester. At the same time has automatic leak detection and other common functions. The system has the advantages of integrity, innovation, easy operation, automatic test of the total static pressure system, high control precision, can replace the imported high price equipment, complete independent intellectual property rights, and realize the independent maintenance of the equipment. The cost of related links in civil aviation field is saved. On the basis of analyzing the structure and requirements of the control system, this paper establishes the mathematical model of the system, designs the PID algorithm controller for the pneumatic control system, and solves the control problem of the small flow pneumatic control system. According to the equipment index, the actuator and other devices are selected, the structure, hardware and software of the whole system are designed according to the operation requirements, and the assembly and debugging are completed. The experimental results are compared with the simulation results, and the results show that the system has reached the initial goal of the design.
【學(xué)位授予單位】：中國(guó)民航大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2014
【分類號(hào)】：V267

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