本文選題：大型民機(jī) + 起落架　； 參考：《南京航空航天大學(xué)》2013年碩士論文

【摘要】：飛機(jī)地面操縱特性直接關(guān)系到飛機(jī)起降的安全，而操縱前輪轉(zhuǎn)向作為飛機(jī)地面操縱轉(zhuǎn)彎的主要方式。隨著我國(guó)大型民機(jī)的技術(shù)要求的不斷提高，研究測(cè)量民機(jī)在定常速度下轉(zhuǎn)彎的能力有助于提高我國(guó)具有自主知識(shí)產(chǎn)權(quán)的大型客機(jī)的安全性，對(duì)實(shí)現(xiàn)我國(guó)大型民機(jī)成功研制具有重要的意義。 轉(zhuǎn)彎系統(tǒng)可以分成前輪轉(zhuǎn)彎?rùn)C(jī)構(gòu)和液壓伺服操縱控制系統(tǒng)兩個(gè)部分，本文以大型民機(jī)單作動(dòng)筒式前輪轉(zhuǎn)彎系統(tǒng)為研究對(duì)象。首先闡述了全機(jī)多體動(dòng)力學(xué)的建模方法，基于LMS Virtual.labMotion建立全機(jī)的動(dòng)力學(xué)模型，并進(jìn)行全機(jī)動(dòng)態(tài)定常速度下轉(zhuǎn)彎性能仿真分析。其次闡明了電液伺服控制系統(tǒng)的數(shù)字化傳遞方程，選取合適的電液伺服閥和液壓動(dòng)力機(jī)構(gòu)，，基于MATLAB/Simulink對(duì)電液伺服控制系統(tǒng)進(jìn)行建模分析，并單獨(dú)對(duì)已經(jīng)選取的電液伺服系統(tǒng)進(jìn)行仿真，驗(yàn)證系統(tǒng)的性能。最后設(shè)置LMS Virtual.lab Motion和MATLAB/Simulink軟件平臺(tái)接口，修改完善已有的動(dòng)力學(xué)模型和轉(zhuǎn)彎系統(tǒng)模型，聯(lián)合動(dòng)力學(xué)模型和控制模型進(jìn)行仿真研究，分析飛機(jī)轉(zhuǎn)彎的輪胎參數(shù)，總結(jié)出不同轉(zhuǎn)彎速度對(duì)飛機(jī)安全性能的影響后，選取合適的轉(zhuǎn)彎速度仿真，求解最終安全的角度。 通過(guò)仿真分析，驗(yàn)證了聯(lián)合轉(zhuǎn)彎系統(tǒng)設(shè)計(jì)工作的可行性，獲得了一些有價(jià)值的設(shè)計(jì)經(jīng)驗(yàn)及結(jié)論，為以后的詳細(xì)設(shè)計(jì)工作和進(jìn)一步的實(shí)體飛機(jī)試驗(yàn)驗(yàn)證工作提供了可行性的基礎(chǔ)參數(shù)。
[Abstract]:The ground control characteristics of aircraft are directly related to the safety of aircraft take-off and landing, and the steering of front wheel is the main way of ground handling and turning of aircraft. With the continuous improvement of the technical requirements of large civil aircraft in China, the study of the ability to measure the turning of civil aircraft at constant speed will help to improve the safety of large passenger aircraft with independent intellectual property rights in our country. It is of great significance to realize the successful development of large civil aircraft in China. The turning system can be divided into two parts: front wheel turning mechanism and hydraulic servo control system. Firstly, the modeling method of multi-body dynamics of the whole machine is introduced. The dynamic model of the whole machine is established based on LMS Virtual. LabMotion, and the turning performance of the whole machine under the constant speed is simulated and analyzed. Secondly, the digital transfer equation of electro-hydraulic servo control system is expounded, and the appropriate electro-hydraulic servo valve and hydraulic power mechanism are selected, and the electro-hydraulic servo control system is modeled and analyzed based on MATLAB / Simulink. And the selected electro-hydraulic servo system is simulated to verify the performance of the system. Finally, LMS Virtual.lab Motion and MATLAB / Simulink software platform interface are set up to modify and perfect the existing dynamic model and turn system model, to simulate the joint dynamics model and control model, and to analyze the tire parameters of airplane turning. After summing up the influence of different turning speed on the aircraft safety performance, the appropriate turning speed simulation is selected to solve the final safety angle. Through simulation analysis, the feasibility of joint turning system design is verified, and some valuable design experiences and conclusions are obtained. It provides the feasible basic parameters for the detailed design work and the further solid aircraft test verification work in the future.
【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(lèi)號(hào)】：V226

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