本文選題：磁流變減擺器 + 擺振�。� 參考：《中國民航大學(xué)》2015年碩士論文

【摘要】：減擺器是位于飛機前起落架上用來減小滑跑時前輪擺振的阻尼器。擺振是飛機滑跑時,前輪產(chǎn)生的一種側(cè)向擺動,是由輪胎與跑道之間的作用力以及飛機機身振動而引起的一種自激振動。擺振會對飛機造成損害,減小擺振最直接有效的辦法就是安裝減擺器。普通的減擺器大多為液壓式減擺器,其成本低廉,構(gòu)造簡單,但液壓式減擺器阻尼系數(shù)固定,當(dāng)出現(xiàn)劇烈擾動時無法快速減小擺振,低速轉(zhuǎn)彎時前輪又要克服較大的阻尼力造成能量浪費。由于前起落架系統(tǒng)的運動較為復(fù)雜,加上飛機輪胎和跑道之間的相互作用力等的影響,擺振具有明顯的非線性特征,給擺振的研究帶來困難。針對這種情況,本文使用多體運動學(xué)仿真軟件ADAMS研究了磁流變減擺器對擺振的抑制效果。磁流變減擺器中的磁流變液是阻尼系數(shù)可變的材料,其阻尼系數(shù)能在規(guī)定的控制法則下隨外加磁場的改變而發(fā)生變化。ADAMS可以建立研究對象的虛擬樣機,并且能模擬復(fù)雜的非線性力,比如磁流變減擺器的阻尼力等。本文首先使用CATIA建立包括磁流變減擺器的飛機前起落架模型,并在ADAMS中根據(jù)該模型建立前起落架虛擬樣機對前輪擺振進行了非線性仿真分析,研究了在不同的減擺阻尼系數(shù)下擺振的大小變化,得到了擺振與減擺阻尼系數(shù)和滑跑速度之間的關(guān)系,初步確定了磁流變減擺器模糊控制器設(shè)計的先驗經(jīng)驗;其次建立了磁流變減擺器的力學(xué)模型,并依據(jù)所得模糊控制器設(shè)計的先驗經(jīng)驗,結(jié)合模糊控制理論建立磁流變減擺器的模糊控制器,通過模糊控制器控制磁流變減擺器的阻尼力;最后通過ADAMS-MATLAB聯(lián)合仿真,對安裝基于模糊控制理論的磁流變減擺器的飛機進行擺振實時控制和仿真分析,將仿真分析結(jié)果和安裝阻尼系數(shù)固定的普通減擺器的飛機擺振結(jié)果作對比,證明磁流變減擺器能較好地抑制擺振。
[Abstract]:A damper is a damper used to reduce the front wheel shimmy on the front landing gear of an aircraft. It is a lateral swing produced by the front wheel when the aircraft is skimming. It is a self excited vibration caused by the force between the tire and the runway and the vibration of the aircraft fuselage. The swinging will cause damage to the aircraft and reduce the most direct and effective swing of the vibration. The method is to install the pendulum. Most of the ordinary pendulum shims are hydraulic pendulum, whose cost is low and the structure is simple, but the damping coefficient of the hydraulic pendulum is fixed, the vibration can not be reduced quickly when there is severe disturbance, and the front wheel will overcome the greater damping force to cause energy waste when the low speed turn. In order to be complicated, coupled with the influence of the interaction force between the aircraft tires and the runway, the pendulum has obvious nonlinear characteristics and brings difficulties to the study of the vibration. In this case, this paper uses the multi body kinematics simulation software ADAMS to study the restraining effect of the magnetorheological pendulum on the vibration. The magnetorheological fluid in the magnetorheological pendulum is hindering. The damping coefficient can change with the external magnetic field under the prescribed control law..ADAMS can establish the virtual prototype of the research object, and can simulate the complex nonlinear force, such as the damping force of the magnetorheological pendulum. This paper first makes use of CATIA to establish the front plane of the aircraft including the magnetorheological pendulum. The model of the landing gear is modeled in ADAMS, and the front wheel shimmy is simulated by the model of the front landing gear based on the model. The change of the shimmy under the different damping coefficient is studied. The relationship between the damping coefficient and the running speed of the pendulum is obtained, and the fuzzy control of the magnetorheological pendulum is preliminarily determined. According to the prior experience of the design of the device, the mechanical model of the magnetorheological pendulum is set up, and the fuzzy controller of the magnetorheological pendulum is set up based on the prior experience designed by the fuzzy controller, and the damping force of the magnetorheological pendulum is controlled by the fuzzy controller. Finally, the installation of the ADAMS-MATLAB is combined to simulate the installation of the damper. The real time swing control and simulation analysis of the aircraft in the magnetorheological shimmy based on the fuzzy control theory are compared, and the results of the simulation analysis are compared with that of the ordinary pendulum with fixed damping coefficient. It is proved that the magnetorheological pendulum can better suppress the swinging.
【學(xué)位授予單位】：中國民航大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V226.2

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