无人机气液压弹射系统建模与弹射过程仿真分析

Modeling of Pneudraulic Launching System of UAV and Simulation Analysis of Launching Process

无人机气液压弹射系统分为液压缸驱动式和液压马达驱动式两种,采用液压马达驱动的无人机气液压弹射系统在国内研究较少。以蓄能器组作为弹射过程中的主动力源,以液压马达作为驱动元件,分析了液压马达式驱动气液压弹射系统的工作原理,运用AMESim软件对弹射系统进行建模与仿真,在不同条件下得到了无人机的速度-位移曲线。对各参数权重进行分析,分析结果表明蓄能器组充气压力、无人机与载物车综合质量以及液压马达排量是影响起飞速度的关键参数,为无人机气液压弹射系统的设计与调试提供了参考。

The pneudraulic launching system of unmanned aerial vehicle （UAV） contains two kinds of driving methods, which are drived by hydraulic cylinder or hydraulic motor. For the pneudraulic launching system of UAV drived by hydraulic motor, few studies are carried out at home. This paper uses the accumulator set as launching energy source, the hydraulic motor as driving component, analyzing the principle of the pneudraulic launching system drived by hydraulic motor, modeling and simulation based on AMESim, obtaining the velocity-displacement curves of UAV under different conditions. Analyzing the weight of each parameter, the results indicate that the accumulator gas charge pressure, the mass of UAV and the vehicle and the hydraulic motor displacement are the key parameters affecting takeoff velocity, which provides a reference for the design and debugging of pneudraulic launching system of UAV.