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

【摘要】：飛機地面操縱特性直接關系到飛機起降的安全，而操縱前輪轉(zhuǎn)向作為飛機地面操縱轉(zhuǎn)彎的主要方式。隨著我國大型民機的技術要求的不斷提高，研究測量民機在定常速度下轉(zhuǎn)彎的能力有助于提高我國具有自主知識產(chǎn)權的大型客機的安全性，對實現(xiàn)我國大型民機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)彎機構和液壓伺服操縱控制系統(tǒng)兩個部分，本文以大型民機單作動筒式前輪轉(zhuǎn)彎系統(tǒng)為研究對象。首先闡述了全機多體動力學的建模方法，基于LMS Virtual.labMotion建立全機的動力學模型，并進行全機動態(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力機構，，基于MATLAB/Simulink對電液伺服控制系統(tǒng)進行建模分析，并單獨對已經(jīng)選取的電液伺服系統(tǒng)進行仿真，驗證系統(tǒng)的性能。最后設置LMS Virtual.lab Motion和MATLAB/Simulink軟件平臺接口，修改完善已有的動力學模型和轉(zhuǎn)彎系統(tǒng)模型，聯(lián)合動力學模型和控制模型進行仿真研究，分析飛機轉(zhuǎn)彎的輪胎參數(shù)，總結(jié)出不同轉(zhuǎn)彎速度對飛機安全性能的影響后，選取合適的轉(zhuǎn)彎速度仿真，求解最終安全的角度。 通過仿真分析，驗證了聯(lián)合轉(zhuǎn)彎系統(tǒng)設計工作的可行性，獲得了一些有價值的設計經(jīng)驗及結(jié)論，為以后的詳細設計工作和進一步的實體飛機試驗驗證工作提供了可行性的基礎參數(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.
【學位授予單位】：南京航空航天大學
【學位級別】：碩士
【學位授予年份】：2013
【分類號】：V226

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