摘要
以某型全液压驱动式发射平台的多管火箭发射系统为研究对象,利用半相对灵敏度分析法,分析了液压系统的泄漏因素参数对火箭发射装置性能指标的影响规律,利用虚拟试验获得了高低油缸在高温、低温和常温下的泄漏参数变化的阈值及液压马达的泄漏系数阈值,为全液压驱动的多管火箭武器液压元件的维护和更新提供了定量化的理论依据。
Semi-relative sensitivity analysis method was employed to analyze the rules that leakage factor parameters affect rocket launcher performances. Simulation threshold values of variable leakage parameters for hydraulic erecting mechanism at high temperature, low temperature and constant temperature, and leakage coefficients for hydraulic motor were got with virtual experiment technology, which provide theoretical guidance for maintenance and update of hydraulic components for the new multiple launch rocket system.
出处
《机床与液压》
北大核心
2009年第11期93-96,109,共5页
Machine Tool & Hydraulics
关键词
液压
泄漏评估
虚拟试验
发射装置
Hydraulic
Leakage evaluation
Virtual experiment
Rocket Launcher
