基于PID主动控制技术的直升机起落架缓冲器设计

发布时间：2018-03-15 11:38

本文选题：起落架缓冲器　切入点：动力学仿真　出处：《南京航空航天大学》2016年硕士论文　论文类型：学位论文

【摘要】：起落架是直升机地面支撑、安全滑行,吸收着陆冲击能量的重要部件,为了提高起落架的性能,本文采用PID主动控制技术优化起落架整体性能。以直升机起落架缓冲器为研究对象,建立了起落架缓冲器的动力学分析模型,并对缓冲器进行参数设计,然后在ADAMS/Aircraft软件中建立起落架的虚拟样机模型并进行落震仿真试验,接着用粒子群算法优化PID参数后运用Matlab/Simulink建立控制系统下的起落架仿真模型,同样完成不同条件下的落震仿真试验,最后由两种仿真结果的对比得出结论。本文的主要工作内容如下:1.以直升机的广泛应用为背景,阐述起落架的重要性,介绍起落架缓冲器的发展,引入本文采用的虚拟样机技术和PID控制方法,简叙本文的研究内容和研究方法。2.以摇臂式起落架为基础,采用经典的二质量块模型,建立起落架的动力学分析模型。阐述本文中采用双腔油气式缓冲器的优点,通过运动学和动力学微分方程的建立进行起落架的参数设计。3.根据上述的参数在ADAMS/Aircraft中建立起落架系统的虚拟样机模型,然后展开落震仿真试验,并对仿真结果进行分析与探讨。4.建立主动控制系统下起落架缓冲器的数学模型,并推导整个系统的动力学方程,给出了主动控制起落架的具体实现形式。5.采用粒子群算法优化PID参数,并Matlab/Simulink模块完成起落架仿真框图模型,然后同样进行落震仿真试验,得出仿真结果。最后,对上述两种方案的仿真结果进行分析比较。结果表明,添加PID主动控制技术后的起落架性能与普通起落架相比有了明显的改善。
[Abstract]:Landing gear is an important part of helicopter ground support, safety glide, absorb landing impact energy, in order to improve the performance of landing gear, In this paper, PID active control technology is used to optimize the overall performance of landing gear. Taking helicopter landing gear buffer as the research object, the dynamic analysis model of landing gear buffer is established, and the parameters of the buffer are designed. Then the virtual prototype model of landing gear is established in ADAMS/Aircraft software and the simulation test of landing gear is carried out. Then the parameters of PID are optimized by particle swarm optimization and then the simulation model of landing gear under control system is established by Matlab/Simulink. At last, the conclusion is drawn from the comparison of the two simulation results. The main work of this paper is as follows: 1.The importance of landing gear is expounded based on the extensive application of helicopter. This paper introduces the development of landing gear buffer, introduces the virtual prototyping technology and PID control method adopted in this paper, briefly describes the research contents and research methods of this paper .2.Based on the rocker landing gear, the classical two-mass block model is adopted. The dynamic analysis model of landing gear is established. According to the above parameters, the virtual prototype model of the landing gear system is established in ADAMS/Aircraft, and then the simulation test of the landing gear system is carried out. The mathematical model of landing gear buffer under active control system is established, and the dynamic equation of the whole system is deduced. The realization form of active control landing gear is given. The particle swarm optimization algorithm is used to optimize the PID parameters, and the Matlab/Simulink module completes the simulation block diagram model of the landing gear. Then, the simulation test of the landing gear is also carried out, and the simulation results are obtained. The simulation results of the above two schemes show that the performance of the landing gear after the addition of PID active control technology is obviously improved than that of the common landing gear.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V275.1;V226

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