CAJ | 학술논문

介绍了一种无人机气动弹射系统的组成、结构、工作原理和发射过程。通过对其物理模型进行简化，采用基于封闭矢量环法与力平衡方程的联立约束法分析推导了该无人机弹射系统的动力学求解数学模型。在Matlab／Simulink环境中创建了弹射系统发射过程的动态仿真模型，得到了无人机的加速度和速度随时间变化的曲线等参数。并将遗传算法与Simulink有机结合，方便实现了气动弹射系统的仿真与优化。结果表明：该无人机弹射系统改善了现有弹射系统弹射加速度有明显峰值、发射轨道利用率低、发射长度过长等不足，为无人机气动弹射系统的工程研制提供了重要的理论参考，优化后进一步缩短了发射长度，减小了最大过载和加速度波动，为无人机气动弹射的系统级建模、动态仿真与性能优化提供了一个工作平台。
개소료일충무인궤기동탄사계통적조성、결구、공작원리화발사과정。통과대기물리모형진행간화，채용기우봉폐시량배법여력평형방정적련립약속법분석추도료해무인궤탄사계통적동역학구해수학모형。재Matlab／Simulink배경중창건료탄사계통발사과정적동태방진모형，득도료무인궤적가속도화속도수시간변화적곡선등삼수。병장유전산법여Simulink유궤결합，방편실현료기동탄사계통적방진여우화。결과표명：해무인궤탄사계통개선료현유탄사계통탄사가속도유명현봉치、발사궤도이용솔저、발사장도과장등불족，위무인궤기동탄사계통적공정연제제공료중요적이론삼고，우화후진일보축단료발사장도，감소료최대과재화가속도파동，위무인궤기동탄사적계통급건모、동태방진여성능우화제공료일개공작평태。
The constitution, structure, working principle and launching process of an UAV pneumatic launcher are described.Dynamic mathematical model of the pneumatic launcher is analyzed and established by using the simulta-neous constraint method based on the closing-vector-circle method and the equations of force balance by simplifying its physical model.In order to get the parameters such as the variations of velocity and acceleration with time, the dynamic simulation model of the launching process is established in the environment of Matlab/Simulink.By combi-ning Genetic Algorithm with Simulink, the simulation and optimization of the pneumatic launcher are realized .The results and their analysis show preliminarily that: the pneumatic catapult launcher suppresses the drawbacks of the existing launch devices such as requiring substantial space, acceleration peak,and low efficiency of track;it offers significant theoretical reference for the manufacture of the UAV pneumatic launcher .After optimization,the launch -ing length is shortened, the maximum of acceleration decreased and the acceleration wave is reduced.A working platform is offered for the modeling, simulation and optimization of the UAV pneumatic launcher.