發(fā)布時(shí)間：2018-03-17 04:02

  本文選題：直升機(jī)　切入點(diǎn)：主減隔振　出處：《南京航空航天大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

【摘要】：旋翼的槳轂力是引起直升機(jī)機(jī)體振動(dòng)的主要振源。旋翼槳轂力通過旋翼軸、主減速器及其與機(jī)身連接裝置傳遞到機(jī)身,使機(jī)身產(chǎn)生強(qiáng)烈的振動(dòng)。因此,在直升機(jī)主減速器和機(jī)體之間進(jìn)行隔振便成為了一種高效的直升機(jī)減振措施。液彈隔振器是一種構(gòu)造簡(jiǎn)單、質(zhì)量輕、占用空間小的高效隔振設(shè)備。近年來,國外一些直升機(jī)的主減隔振方案越來越多地采用了液彈隔振器。隨著對(duì)直升機(jī)振動(dòng)水平要求不斷地提高,傳統(tǒng)的被動(dòng)式隔振器越來越難完成振動(dòng)控制目標(biāo)。隔振效果更好、適應(yīng)能力更強(qiáng)的半主動(dòng)隔振已成為了研究熱點(diǎn)。本文設(shè)計(jì)提出了一種能夠用于直升機(jī)主減半主動(dòng)隔振的新型液彈隔振器。建立了液彈隔振器的動(dòng)力學(xué)模型及其動(dòng)力學(xué)方程,推導(dǎo)了隔振器的隔振頻率公式,分析了影響液彈隔振器隔振頻率的參數(shù)。在此基礎(chǔ)上,選擇隔振器的剛度作為受控參數(shù),設(shè)計(jì)了一種變剛度鋼板彈簧。選擇一種三環(huán)音圈電機(jī)作為作動(dòng)器來改變彈簧片之間的間隙以改變變剛度彈簧的剛度,達(dá)到調(diào)節(jié)隔振器的隔振頻率以適應(yīng)振源頻率變化的目的。利用設(shè)計(jì)的變剛度鋼板彈簧,設(shè)計(jì)了一種變剛度液彈隔振器。還為變剛度液彈隔振器設(shè)計(jì)了一種變阻尼機(jī)構(gòu),以改善隔振器的隔振效果。用MSC.ADAMS對(duì)變剛度液彈隔振器的工作性能進(jìn)行動(dòng)力學(xué)仿真,得到了頻響結(jié)果。仿真結(jié)果與計(jì)算結(jié)果吻合度良好,表明設(shè)計(jì)的變剛度液彈隔振器能夠完成半主動(dòng)隔振中的任務(wù)。最終建立了變剛度液彈隔振器的CATIA裝配模型。
[Abstract]:The rotor hub force is the main vibration source of helicopter body. The rotor hub force is transmitted to the fuselage through the rotor shaft, the main reducer and its connecting device to the fuselage, which makes the fuselage produce strong vibration. Vibration isolation between the main reducer and the airframe of the helicopter has become an effective measure for the vibration reduction of the helicopter. The liquid-bomb isolator is an efficient vibration isolation device with simple construction, light weight and small space occupation. More and more hydro-bomb vibration isolators are used in the main vibration isolation schemes of some foreign helicopters. With the increasing demands on the helicopter vibration level, the traditional passive vibration isolators are more and more difficult to achieve the vibration control goal, and the vibration isolation effect is better. Semi-active vibration isolation with stronger adaptability has become a hot topic. In this paper, a new type of liquid-bomb vibration isolator which can be used for helicopter main halving active vibration isolation is proposed. The dynamic model and dynamic equation of liquid-bomb vibration isolator are established. The vibration isolation frequency formula of the vibration isolator is derived, and the parameters affecting the vibration isolation frequency of the liquid bomb vibration isolator are analyzed. On this basis, the stiffness of the isolator is selected as the controlled parameter. A variable stiffness leaf spring is designed. A three-ring coil motor is chosen as actuator to change the gap between the springs to change the stiffness of the variable stiffness spring. In order to adjust the vibration isolation frequency of the vibration isolator to adapt to the change of vibration source frequency, a variable stiffness liquid-bomb vibration isolator is designed by using the designed variable stiffness leaf spring. A variable damping mechanism is also designed for the variable stiffness liquid bomb vibration isolator. In order to improve the isolation effect of the vibration isolator, the dynamic simulation of the working performance of the variable stiffness liquid-bomb isolator is carried out by using MSC.ADAMS, and the frequency response results are obtained. The simulation results are in good agreement with the calculated results. It is shown that the variable stiffness liquid-bomb vibration isolator can accomplish the task of semi-active vibration isolation. Finally, the CATIA assembly model of the variable stiffness liquid-bomb vibration isolator is established.
【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】：2016
【分類號(hào)】：V275.1

【參考文獻(xiàn)】

相關(guān)期刊論文 前3條

1 張大衛(wèi);馮曉梅;;音圈電機(jī)的技術(shù)原理[J];中北大學(xué)學(xué)報(bào)(自然科學(xué)版);2006年03期

2 李五洲;;反共振隔振裝置隔振原理分析[J];直升機(jī)技術(shù);2004年01期

3 顧仲權(quán);動(dòng)力反共振隔振[J];噪聲與振動(dòng)控制;1989年06期

相關(guān)碩士學(xué)位論文 前3條

1 張楊;帶液彈隔振器的直升機(jī)主減隔振系統(tǒng)動(dòng)力學(xué)建模與仿真[D];南京航空航天大學(xué);2013年

2 龔亮;液彈隔振器設(shè)計(jì)與試驗(yàn)研究[D];南京航空航天大學(xué);2012年

3 鄧旭東;直升機(jī)高性能主減隔振系統(tǒng)分析與仿真研究[D];南京航空航天大學(xué);2011年

，

本文編號(hào)：1623044