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- SPRINT (Solid Propellant Rocket Intercept Missile) 固体推进火箭截击导弹
- Solid Propellant Rocket Intercept 固体推进剂火箭拦截
- Solid Propellant Rocket Intercept Missile 固体推进剂火箭拦截导弹
- Solid Propellant Rocket Intercept Early Missile Test Radar 固体推进剂火箭拦截的早期导弹试验雷达
- Solid Propellant Rocket Intercept Operations Shelter 固体推进剂火箭拦截作战掩体
- Solid Propellant Rocket Intercept Air Directed Defense System 固体推进剂火箭拦截对空防御系统
- Solid Propellant Rocket Intercept Air-Directed Defense 固体推进剂火箭拦截对空防御
- Solid Propellant Rocket Intercept Electromagnetic Radiation Evaluation 固体本推进剂火箭拦截电磁辐射评估
- Solid Propellant Rocket Intercept Missile Electromagnetic Radiation Evaluation 固体推进剂火箭拦截导弹电磁辐射评估
- Propellant Rocket Intercept 固体火箭拦截
- We shall try by means of a highly simplified development to expose certain advantages and disadvantages of solid propellant rocket systems. 我们想通过相当简单的推导来试图阐明固体推进剂火箭系统的某些优缺点。
- According to the requirement of pasty propellant rocket motor, a composite plasma igniting plan was adopted. 摘要根据膏体推进剂火箭发动机。
- J.J. Choury,carbon/carbon materials for nozzle of solid propellant rocket motors[J].AIAA76-609. 崔红;李瑞珍;苏君明等.;多元基体抗烧蚀炭/炭复合材料的微观结构分析[J]
- To appreciate the unsteady environment existing in liquid propellant rocket chambers it is necessary that the steady state be well understood. 为了分析液体推进剂火箭发动机燃烧室中存在的非稳态环境，必须很好地了解稳态状态。
- The results of the experiments show that the technique is a rapid, effective method for the disbond detecting of solid propellant rocket motors. 实验研究结果表明,该技术可对固体火箭发动机钢筒与绝热层之间的脱粘作快速有效的检测。
- This pa per presents plume temperature measurements of a mounted solid propellant rocket engine measured using a 6-target 8-wavelength pyrometer. 对于固体火箭发动机羽焰温度的测量是困难的,了解其温度分布对于研究发动机内燃烧流场的特性有重要价值。
- It is an important and basic issue to choose monitoring parameters of Liquid propellant Rocket Engine (LRE) monitoring system in ground test. 摘要确定监测参数是液体火箭发动机地面试验监控系统的一个重要而基础的问题。
- The dynamic models of engine parts in a new high-performance staged combustion cycle liquid propellant rocket through the module codified were built. 通过模块化编程，建立了新一代高性能补燃发动机启动过程的部件模型。
- The principle of coriolis force mass flowmeter and its application in gelled propellant rocket engine test are introduced,results of the test are also analyzed. 介绍了科氏力质量流量计的原理及其在凝胶发动机试车中的应用,并对热试车的测量数据进行了分析。
- To overcome the difficulties on acquiring enough fault modes from ground and flight test data, the failure process for liquid propellant rocket propulsion systems was modeled. 为克服由于试验或飞行数据不足而无法获取系统足够故障模式的问题，开展了液体火箭推进系统故障过程建模与计算机仿真研究工作。
