【摘要】：隨著科學(xué)技術(shù)的不斷發(fā)展,飛機(jī)成為現(xiàn)代生活中重要的交通工具之一。中央翼是飛機(jī)整體的重要組成部件,位于飛機(jī)中段的內(nèi)部,無完整的外形。它起著連接飛機(jī)左右外翼的重要作用,承受著兩翼的升力和機(jī)身的重力,是整架飛機(jī)的重要受力部件。因此,中央翼的安裝及加工精度對(duì)整架飛機(jī)的平衡和受力有著重要的影響。中央翼完成安裝后,需要對(duì)其端面進(jìn)行數(shù)控孔加工。但是中央翼在安裝型架上和在進(jìn)行端面孔加工時(shí)所處的狀態(tài)是相互垂直的,即需要將中央翼從安裝型架上取下之后翻轉(zhuǎn)90°。原有的翻轉(zhuǎn)機(jī)構(gòu)雖然能使中央翼順利地完成翻轉(zhuǎn),但是翻轉(zhuǎn)過程較復(fù)雜,效率低下,且存在著一定的安全隱患。飛機(jī)中央翼翻轉(zhuǎn)機(jī)構(gòu)設(shè)計(jì)的目的在于設(shè)計(jì)一機(jī)構(gòu),使中央翼方便、快捷地進(jìn)行翻轉(zhuǎn),減小機(jī)構(gòu)對(duì)生產(chǎn)工人造成的安全隱患,節(jié)省翻轉(zhuǎn)過程中的人力和物力,提高生產(chǎn)效率。本文依據(jù)項(xiàng)目委托企業(yè)的實(shí)際要求和翻轉(zhuǎn)機(jī)構(gòu)的發(fā)展趨勢,結(jié)合中央翼翻轉(zhuǎn)時(shí)的實(shí)際情況,進(jìn)行方案設(shè)計(jì)。通過CATIA三維設(shè)計(jì)軟件對(duì)其進(jìn)行建模、利用虛擬樣機(jī)技術(shù)對(duì)其進(jìn)行建模、仿真,驗(yàn)證方案的可行性,最后通過ANSYS有限元軟件對(duì)翻轉(zhuǎn)機(jī)構(gòu)的重要部件進(jìn)行分析。本文主要的研究內(nèi)容為:1.依據(jù)翻轉(zhuǎn)機(jī)構(gòu)的設(shè)計(jì)要求及中央翼的下架路線,進(jìn)行翻轉(zhuǎn)機(jī)構(gòu)的方案設(shè)計(jì),確定翻轉(zhuǎn)原理、吊點(diǎn)的選擇、動(dòng)力源及其控制方式的選擇。2.翻轉(zhuǎn)機(jī)構(gòu)中重要部件的設(shè)計(jì),包括吊梁、吊掛、支撐架的設(shè)計(jì)及截面尺寸的確定及強(qiáng)度校核、帶傳動(dòng)的摩擦力的計(jì)算和該翻轉(zhuǎn)機(jī)構(gòu)是否會(huì)出現(xiàn)帶傳動(dòng)的打滑現(xiàn)象的研究。3.在Recurdyn中建立翻轉(zhuǎn)機(jī)構(gòu)的簡化模型,并通過添加約束、載荷、驅(qū)動(dòng)等,建立虛擬樣機(jī)的模型,通過運(yùn)動(dòng)學(xué)仿真分析驗(yàn)證模型的正確性,得出在運(yùn)轉(zhuǎn)過程中的一系列動(dòng)態(tài)參數(shù)。4.在CATIA中建立吊梁的模型,并通過數(shù)據(jù)接口導(dǎo)入ANSYS Workbench,利用ANSYS Workbench軟件對(duì)橫梁進(jìn)行靜力學(xué)分析,得到梁所受的應(yīng)力變化和梁的變形,并通過梁的應(yīng)變疲勞分析,得出梁在使用一定次數(shù)后,吊梁各個(gè)部位的安全系數(shù)、壽命及其各個(gè)部位的損傷。5.利用ANSYS Workbench軟件的響應(yīng)曲面分析工具分析吊梁橫截面的各個(gè)尺寸對(duì)梁的總體變形和等效應(yīng)力的影響,并得出在梁的總體變形和等效應(yīng)力不變的情況下,使其質(zhì)量最小的橫截面尺寸參數(shù)。
[Abstract]:With the development of science and technology, aircraft has become one of the most important means of transportation in modern life. The central wing is an important component of the aircraft. It is located in the middle of the aircraft and has no complete shape. It plays an important role in connecting the left and right wings of the aircraft, bearing the lift of the two wings and the gravity of the fuselage. It is an important force component of the whole aircraft. Therefore, the installation and machining accuracy of the central wing have an important effect on the balance and force of the whole aircraft. After the central wing is installed, it is necessary to carry out NC hole machining on its end surface. But the central wing is perpendicular to each other on the mounting frame and in the machining of the end hole, that is to say, it is necessary to remove the central wing from the mounting frame and turn it over 90 擄. Although the original turnover mechanism can make the central wing complete the turnover smoothly, the turnover process is more complex, inefficient and has certain security hidden trouble. The purpose of the design of the aircraft central wing turnover mechanism is to design a mechanism to make the center wing flip conveniently and quickly, to reduce the hidden danger of safety caused by the mechanism to the production workers, to save the manpower and material resources in the turnover process, and to improve the production efficiency. According to the actual requirements of the project entrustment enterprise and the development trend of the turnover mechanism, combined with the actual situation of the central wing turnover, the project design is carried out in this paper. It is modeled by CATIA 3D design software, modeled by virtual prototyping technology, simulated and verified the feasibility of the scheme. Finally, the important parts of the flip mechanism are analyzed by ANSYS finite element software. The main contents of this paper are: 1: 1. According to the design requirements of the turnover mechanism and the dismount route of the central wing, the scheme design of the turnover mechanism is carried out, and the turnover principle, the choice of the lifting point, the choice of the power source and its control mode are determined. The design of the important parts in the reversing mechanism includes the design of the suspension beam, the hanging, the design of the support frame, the determination of the cross section size and the strength check, the calculation of the friction force of the belt transmission and the study on whether the sliding phenomenon of the belt transmission will occur in the flip mechanism. The simplified model of the flip mechanism is established in Recurdyn, and the model of virtual prototype is built by adding constraints, loads, drives, etc. The correctness of the model is verified by kinematics simulation analysis, and a series of dynamic parameters .4in the process of operation are obtained. The model of suspension beam is established in CATIA, and the data interface is imported into ANSYS Workbench. The static analysis of the beam is carried out by using ANSYS Workbench software. The stress changes and the deformation of the beam are obtained, and the strain fatigue analysis of the beam is carried out. After a certain number of times, the safety factor, life span and damage of each part of the beam are obtained. The response surface analysis tool of ANSYS Workbench software is used to analyze the influence of the dimensions of the cross section of the suspension beam on the total deformation and equivalent stress of the beam, and it is obtained that the total deformation and equivalent stress of the beam are invariant. Cross section size parameter that minimizes its mass.
【學(xué)位授予單位】：陜西理工學(xué)院
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：V261

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