磁流变减摆器建模仿真及控制算法研究
本文选题:磁流变减摆器 + 摆振 ; 参考:《中国民航大学》2015年硕士论文
【摘要】:减摆器是位于飞机前起落架上用来减小滑跑时前轮摆振的阻尼器。摆振是飞机滑跑时,前轮产生的一种侧向摆动,是由轮胎与跑道之间的作用力以及飞机机身振动而引起的一种自激振动。摆振会对飞机造成损害,减小摆振最直接有效的办法就是安装减摆器。普通的减摆器大多为液压式减摆器,其成本低廉,构造简单,但液压式减摆器阻尼系数固定,当出现剧烈扰动时无法快速减小摆振,低速转弯时前轮又要克服较大的阻尼力造成能量浪费。由于前起落架系统的运动较为复杂,加上飞机轮胎和跑道之间的相互作用力等的影响,摆振具有明显的非线性特征,给摆振的研究带来困难。针对这种情况,本文使用多体运动学仿真软件ADAMS研究了磁流变减摆器对摆振的抑制效果。磁流变减摆器中的磁流变液是阻尼系数可变的材料,其阻尼系数能在规定的控制法则下随外加磁场的改变而发生变化。ADAMS可以建立研究对象的虚拟样机,并且能模拟复杂的非线性力,比如磁流变减摆器的阻尼力等。本文首先使用CATIA建立包括磁流变减摆器的飞机前起落架模型,并在ADAMS中根据该模型建立前起落架虚拟样机对前轮摆振进行了非线性仿真分析,研究了在不同的减摆阻尼系数下摆振的大小变化,得到了摆振与减摆阻尼系数和滑跑速度之间的关系,初步确定了磁流变减摆器模糊控制器设计的先验经验;其次建立了磁流变减摆器的力学模型,并依据所得模糊控制器设计的先验经验,结合模糊控制理论建立磁流变减摆器的模糊控制器,通过模糊控制器控制磁流变减摆器的阻尼力;最后通过ADAMS-MATLAB联合仿真,对安装基于模糊控制理论的磁流变减摆器的飞机进行摆振实时控制和仿真分析,将仿真分析结果和安装阻尼系数固定的普通减摆器的飞机摆振结果作对比,证明磁流变减摆器能较好地抑制摆振。
[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.
【学位授予单位】:中国民航大学
【学位级别】:硕士
【学位授予年份】:2015
【分类号】:V226.2
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