文章摘要
王彤,张振,吕峰.基于AMESim机载导弹液压弹射机构仿真研究[J].机床与液压,2021,49(2):113-116.
WANG Tong,ZHANG Zhen,LV Feng.Simulation Research of Aircraft Missile Hydraulic Catapult Mechanism Based on AMESim[J].Machine Tool & Hydraulics,2021,49(2):113-116
基于AMESim机载导弹液压弹射机构仿真研究
Simulation Research of Aircraft Missile Hydraulic Catapult Mechanism Based on AMESim
  
DOI:10.3969/j.issn.1001-3881.2021.02.25
中文关键词: 机载导弹  液压弹射机构  AMESim仿真
英文关键词: Aircraft missile  Hydraulic catapult mechanism  AMESim simulation
基金项目:
作者单位E-mail
王彤 海军航空大学 snoopywto@126.com 
张振 海军航空大学  
吕峰 中国人民解放军92074部队  
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中文摘要:
      针对传统机载导弹弹射装置存在的问题,设计出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。论述液压弹射机构工作原理,对其元件参数进行了计算,利用AMESim软件建立其仿真模型。仿真结果表明:液压弹射机构能够在60 ms内使导弹运动速度达到8 m/s,在20 ms内达到98%的缓冲效率
英文摘要:
      Aiming at the problem of the traditional ejection device of aircraft missile,a hydraulic catapult mechanism was designed in which accumulator supplied ejection flow and servo valve was taken as core control element.The operating principle of the hydraulic catapult mechanism was described,the component parameters were calculated and the simulation model was created based on AMESim.The simulation results show that the hydraulic catapult mechanism can make the missile speed up to 8 m/s in 60 ms time;the buffer efficiency is up to 98% within the 20 ms
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