發(fā)布時(shí)間：2018-05-08 04:12

  本文選題：飛行動(dòng)力學(xué) + 風(fēng)切變��； 參考：《南京航空航天大學(xué)》2013年碩士論文

【摘要】：低空風(fēng)切變對(duì)飛機(jī)起飛著陸構(gòu)成嚴(yán)重威脅。隨著飛機(jī)自身系統(tǒng)可靠性的提高，由于低空風(fēng)切變等大氣擾動(dòng)現(xiàn)象直接導(dǎo)致或間接誘發(fā)飛行員操縱失誤，從而造成飛行事故或不安全事件的比例正不斷上升。論文采用動(dòng)力學(xué)建模和仿真的手段，以提高低空風(fēng)切變下飛機(jī)進(jìn)場著陸的安全性為目標(biāo)，設(shè)計(jì)飛機(jī)進(jìn)近下滑道跟蹤、自動(dòng)著陸等控制律，并進(jìn)一步研究改出風(fēng)切變的若干安全控制策略問題。論文主要研究內(nèi)容有： (1)研究建立了典型風(fēng)切變模型和飛行動(dòng)力學(xué)模型。建立反映風(fēng)場本質(zhì)特性的微下?lián)舯┝黠L(fēng)切變模型。參考B747飛機(jī)建模數(shù)據(jù)，建立了該機(jī)動(dòng)力學(xué)模型并進(jìn)行了配平和模型驗(yàn)證。 (2)設(shè)計(jì)實(shí)現(xiàn)若干基本飛行控制律。先后設(shè)計(jì)了飛機(jī)俯仰控制律、自動(dòng)著陸控制律以及協(xié)調(diào)轉(zhuǎn)彎控制律。將控制律代入動(dòng)力學(xué)模型中，對(duì)其進(jìn)行反復(fù)設(shè)計(jì)-驗(yàn)證研究。 (3)考查若干風(fēng)切變改出策略的安全性。引入能量高度、F因子、飛行安全包線等安全性指標(biāo)，在基本飛行控制律基礎(chǔ)上，運(yùn)用動(dòng)力學(xué)仿真實(shí)現(xiàn)風(fēng)切變改出控制。先后對(duì)3種縱向改出策略、從弱風(fēng)一側(cè)實(shí)施的橫側(cè)改出策略進(jìn)行了安全性分析。 (4)以提高飛機(jī)進(jìn)近下滑道跟蹤的抗風(fēng)切變干擾能力為目標(biāo)，研究實(shí)現(xiàn)了最優(yōu)控制下滑道跟蹤。仿真結(jié)果表明，，最優(yōu)控制律可有效提高飛機(jī)在風(fēng)切變干擾下的下滑道跟蹤和飛行狀態(tài)保持能力。
[Abstract]:Low-altitude wind shear poses a serious threat to the take-off and landing of aircraft. With the improvement of the reliability of the aircraft system the proportion of flight accidents or unsafe events is increasing because of the low altitude wind shear and other atmospheric disturbances which directly or indirectly induce pilots to control errors. By means of dynamic modeling and simulation, aiming at improving the safety of aircraft approach landing under low altitude wind shear, the control law of aircraft approach and glide path tracking and automatic landing is designed in this paper. Furthermore, some security control strategies for windshear are studied. The main contents of this thesis are as follows: The typical wind shear model and flight dynamics model are established. A wind shear model reflecting the essential characteristics of wind field is established. With reference to the modeling data of B747 aircraft, the dynamic model of the aircraft is established, and the balancing and model verification are carried out. Design and implement some basic flight control laws. The pitch control law, automatic landing control law and coordinated turning control law are designed successively. The control law is added to the dynamic model, and the design and verification of the control law are carried out repeatedly. To examine the safety of some windshear change-out policies. Based on the basic flight control law and the introduction of energy height factor F factor and flight safety envelope, wind shear control is realized by dynamic simulation. This paper analyzes the safety of three vertical strategies, which are implemented from the weak wind side to the horizontal side. 4) aiming at improving the ability of aircraft approach glide track to resist wind shear interference, the tracking of sliding track under optimal control is studied and realized. The simulation results show that the optimal control law can effectively improve the glide track tracking and flight state retention of aircraft under wind shear interference.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2013
【分類號(hào)】：V328

【參考文獻(xiàn)】

相關(guān)期刊論文 前2條

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2 常凡凡;李愛軍;王長青;;大型客機(jī)CAT Ⅲ級(jí)自動(dòng)著陸機(jī)載設(shè)備需求[J];航空工程進(jìn)展;2011年02期

本文編號(hào)：1859897