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- safety of solid rocket motor 固体发动机安全性
- 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。
- 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。
- 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。
- 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]
- 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。
- 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。
- A kind of viscoelastic spectral stochastic finite element method(VSSFEM) was developed and stochastic analysis of solid rocket motor grains was presented. 发展了一种粘弹性谱随机有限元法(VSSFEM),并将其用于固体火箭发动机装药结构随机分析。
- Considering the features of solid rocket motor jet, a kind of experimental equipment based on the pitot tube technology for measuring the multi-point pressures was developed. 结合固体火箭燃气射流的特点,开发了基于皮托管技术的多点压力参数实验测量装置,运用实验的方法,对燃气射流流场进行了研究。
- By measuring the thrust and lateral forces of solid rocket motor during firing conditions,the thrust vector control performances of jet tab TVC and movable nozzle TVC were studied. 通过测量固体火箭发动机水下工作过程中的推力和侧向力,研究了扰流片和摆喷管两种推力矢量方式的水下推力矢量特性。
- The results show that the model with high precision will find promising engineering application in research of solid rocket motors. 结果表明,该模型精度较高,在固体火箭发动机研究方面具有较好的工程应用价值。
- Post-thrust calculation of solid rocket motor 固体火箭发动机后效推力计算
- Gap design of solid rocket motor nozzle structures 固体火箭发动机喷管结构缝隙设计
- Based on the concept of Design for Cost (DFC) proposed by NASA, the paper explores the methods to realize DFC from both quantitative and qualitative approaches and applies them into the process of concept design of Solid Rocket Motors. 本文在NASA提出的面向成本设计(DFC)概念的基础上，从定量和定性两条途径探索了实现DFC的方法和手段，并将其应用于固体火箭发动机概念设计过程中。
- Safety limits design system of heat protection for combustion chamber and nozzle of solid rocket motor 固体火箭发动机燃烧室和喷管热防护安全限设计系统
- Swabbing technology characteristics of solid rocket motor liner 固体火箭发动机衬层涂覆工艺特性
- Noise Analysis on the Launch Process of Solid Rocket Motor 固体发动机发射过程噪声测试分析
- Optimization Design for Cost of Solid Rocket Motors 固体火箭发动机面向成本优化设计
