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- Isolated Measuring Method of the Firing Signal of Solid Rocket Motor Test 发动机地面试验点火信号在线隔离测量方法研究
- Solid rocket motor test 固体火箭发动机试验
- The thrust vector control(TVC) performance test of solid rocket motor is presented in this paper. 本文介绍了固体火箭发动机水下推力矢量特性试验。
- Four nozzles, canted outboard, split the exhaust of the solid rocket motor into four equal tails. 四个向外倾斜的喷管把固体火箭发动机的排气流分成四个相等的尾巴。
- The influence of structure axial vibration on the internal ballistics of solid rocket motor was investigated. 文中研究了固体发动机结构的轴向振动对燃烧室内弹道性能的影响。
- Rocket motor test shows that the new UDMH/NTO bipropellant can satisfy the requirement of gel propellant of rocket motor design. 发动机试验表明:新的UDMH/NTO双组元凝胶体系能够满足发动机设计对凝胶推进剂的要求。
- Investigated charring erosive characters of internal insulation of solid rocket motor under flight acceleration. 研究了固体火箭发动机内绝热层在飞行加速度条件下的炭化烧蚀特性。
- A response surface method(RSM) for structure reliability analysis of solid rocket motor(SRM) grain was presented. 发展了一种固体火箭发动机药柱结构可靠度分析的响应面法。
- Buckling analysis on rear dome of solid rocket motor case was studied by means of ANSYS. 用ANSYS软件对固体发动机壳体后封头进行了外压屈曲分析。
- Crose J G.Reliability of solid rocket motor cases and nozzles[R].NTI S,N93-22103. 王松柏.;固体火箭发动机壳体结构的动态可靠性设计[J]
- Finite element method is used in the study of nozzle damping of instable combustion in a solid rocket motor. 应用有限单元法研究固体火箭发动机不稳定燃烧中的喷管阻尼，并用波衰减对比法进行了试验研究。
- Carbon/carbon composites have become the most ideal materials for nozzles of solid rocket motor (SRM). 摘要C/C复合材料已成为固体火箭发动机(SRM)最理想的喷管材料。
- With the development of national defense and aerospace industry, detachmentdetection for solid rocket motor is the most pressing issue. 随着国防和航空航天事业的发展,大型固体火箭发动机的脱粘检测成为紧迫问题。
- The mechanism of solid rocket motor laser ignition,composition of practical laser ignition system and its key technologies are summaried. 概述了固体火箭发动机激光点火的机理、实用激光点火系统的组成和主要技术关键。
- The erosive property and principle of copper-infiltrated graphite as solid rocket motor(SRM) throat insert and tailpipe nozzle bushing are presented. 介绍了石墨渗铜材料作为固体火箭发动机(SRM)喉衬与长尾管衬套的烧蚀特性和机理。
- It is an effective new processing way for loading of the solid rocket motor with high loading density, high propellant mass fraction propellant. 为今后高装填密度、高质量比的发动机装药开拓出一条新途径。
- New insight also was offered on Chinese solid rocket motor technology work, important for both missile and space launch applications. 研究还提供了对于导弹和航天发射都具有重要影响的固体火箭发动机技术工作。
- The insulation layer, artificial debond layer and propellant grain in solid rocket motor chamber (SRM) are all polymer composite systems. 固体火箭发动机燃烧室内绝热层、人工脱黏层及推进剂药柱,均为高分子材料复合体系。
- In a 1985 controversial test, a U.S.Air Force F-15 launched a miniature kill vehicle propelled by SRAM/Altair solid rocket motors to impact and destroy the USAF Solwind science spacecraft. 在1985年的拦截试验中，一架美国空军的F-15战斗机发射了一枚由SRAM/Altair固体火箭发动机推动的袖珍拦截器，击中并摧毁了美国空军太阳风科学卫星。
- Eagar M A,Jordan F W.A robust ballistic design approach for the space shuttle advanced solid rocket motor[R].AIAA 93-2058. 李晓斌;张为华;陈小前.;近似方法在多学科设计优化中的应用研究
