基于AMESim的机载导弹液压弹射机构动态特性研究  

Dynamic Characteristics Research of Aircraft Missile Hydraulic Catapult Mechanism Based on AMESim

作　　者：张振 王彤 吕峰 ZHANG Zhen;WANG Tong;LV Feng(Naval Aeronautical University,Yantai Shandong 264001,China;Unit 92074 of the PLA,Ningbo Zhejiang 315000,China)

机构地区：[1]海军航空大学,山东烟台264001 [2]中国人民解放军92074部队,浙江宁波315000

出　　处：《机床与液压》2021年第11期168-171,共4页Machine Tool & Hydraulics

摘　　要：针对传统机载导弹弹射装置存在的问题,设计一种以蓄能器提供弹射流量、伺服阀作为核心控制元件的液压弹射机构。论述了液压弹射机构工作原理,利用AMESim软件建立其仿真模型。仿真结果表明:在弹射过程中,蓄能器气体腔容积、液压缸无杆端活塞面积与液压杆伸出速度成正相关,液压缸有杆端活塞面积与液压杆伸出速度成负相关;在缓冲过程中,活塞杆的末速度及缓冲腔压力与凸缘前端与活塞内腔壁间隙成负相关。Aiming at the problem of the traditional catapult mechanism of aircraft missile,a hydraulic catapult mechanism with an accumulator providing catapult flow and a servo valve as the core control element was designed.The operating principle of the hydraulic catapult mechanism was discussed,and its simulation model was established by using AMESim software.The simulation results show that in the process of catapult,the volume of the accumulator gas chamber and the area of the piston at the rod-less end of the hydraulic cylinder are positively correlated with the extension velocity of the hydraulic rod,and the area of the piston at the rod-end of the hydraulic cylinder is negatively correlated with the extension velocity of the hydraulic rod;in the process of buffering,the end velocity of the piston rod and the pressure of the buffering chamber are negatively correlated with the clearance between the flange front end and the piston inner chamber wall.

关 键 词：机载导弹 液压弹射机构 动态特性 

分 类 号：TH137[机械工程—机械制造及自动化]