solid rocket

The composite skirts for solid rocket motor shells fabricated by VARTM ( VacuumAssisted Resin Transfer Molding) had poor mechanical properties because the fiber volume fraction was very small.

VARTM工艺成型的固体火箭发动机壳体复合材料连接裙段构件纤维体积含量较低，复合材料力学性能不佳。

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This law can explain how the solid rocket booster causes the missile's initial acceleration.

这个定律能够解释固体火箭推进器是怎样使得导弹获得初加速度的.

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Compensation technology investigation for impulse thrust of solid rocket motor

固体火箭发动机脉冲推力补偿技术的研究

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The Analysis of Test Failure of Solid Rocket Engine

固体火箭发动机试验故障分析

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Rotating acceleration has inevitable influence on the work process of Solid Rocket Motor: flow of combustion chamber and nozzle is changed; the pressure, mass flow rate and the specific impulse of Solid Rocket Motor are affected by the spinning.

旋转产生的加速度必然对固体火箭发动机的工作过程产生影响：使燃烧室和喷管中的燃气流动发生变化，对燃烧室工作压力质量流率及冲量产生影响。

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It was considered that the establishment of radiographic IQI standard for solid rocket motor chamber was necessary.

认识到建立固体火箭发动机燃烧室X射线探伤像质计标准势在必行。

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D R Greatrix . Acceleration-Base Combustion Augmentation Modelling for Non-Cylindrical Grain Solid Rocket Motors � � R ］. AIAA 95～2876.

曹泰岳,常显奇,等. 固体火箭发动机燃烧过程理论基础[M]. 长沙:国防科技大学出版社.

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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.

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Introduced the Method of electronic optical data speed acquisition of ultraviolet radiation of solid rocket plume.

详述了固体火箭羽烟紫外辐射的光电高速采集方法,并实时对导弹逼近告警.

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Analysis of Test Failure Reason on Solid Rocket Motor

某固体火箭发动机试验失败原因分析

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Engineering Analysis of Large Solid Rocket Motor Head Area Heat Shield in Ground Spinning Test Firing

大型固体发动机旋转试车头部热防护工程分析

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A solid rocket booster causes the initial acceleration and launch of the cruise missile.

一个固体火箭推进器给导弹以初加速度并将其发射出去.

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Analytical Method of Static Test for Single Chamber Dual Thrust Solid Rocket Motor

单室双推力固体发动机静止试验分析方法

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The tentative design of constant altitude flight solid rocket composed of the sustainer, the booster and its simple control method is presented.

介绍了主发动机加助推器和简易控制方法实现固体火箭等高飞行的设计方案。

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Numerical computation of solid rocket motor insulation layer temperature by finite element method

固体火箭发动机绝热层温度场的有限元计算方法

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The experiment result can use to internal insulation design of solid rocket motor.

实验结果可作为发动机绝热层设计的依据.

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The solid rocket boosters come from Utah . They ride on a train to Florida.

固体火箭推进器来自犹他州,由火车运送至佛州.

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Effect of thermal contact resistance on the cook-off time of solid rocket motor

接触热阻对固体火箭发动机烤燃时间的影响

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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。

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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.

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It's verified that a series of intense pressure impulses can occur in the combustion chamber after the thrust reversal nozzles of the solid rocket motor are suddenly opened.

实验表明，突然打开固体火箭发动机反向喷管后，燃烧室中可能出现强烈的压力冲击，这种压力冲击来自喷管喉部节流和形成准稳态流动之前的非定常过程。

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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.

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Design optimization for solid rocket motor based on graph morphing

基于图形变形法的固体火箭发动机优化设计

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Constant Temperature Remote Control System for Solid Rocket Engine Pushing Core Model

固体火箭发动机插芯恒温远程控制系统

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The X-ray attenuation property of solid rocket motor chamber material was described and the testing method for X-ray attenuation coefficient was given. The type, material and location of image quality indicator ( IQI) for radiographic examination of solid rocket motor chamber were proposed.

阐明固体火箭发动机燃烧室材料的X射线吸收特性，给出材料线吸收系数的切向与径向测试方法，提出固体火箭发动机燃烧室X射线探伤像质计类型、材料和放置的建议。

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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。

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Using pressure-controlled T-burner the anthors have determined the pressure coupling responses of three smokeless solid propellants. From the experiment results we have believed that the combustion catalyst may play an important role in eliminating the combustion instability in a solid rocket motor.

用压力可控T形燃烧器测量了三种无烟推进剂压力耦合响应函数，总结到一些实验规律，提出燃烧催化剂对抑制不稳定燃烧可能起到的重要作用。

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A study of the maximum solid rocket engine thrust nozzle surface for one-dimensional two-phase flows

固体火箭发动机一元两相流动最大推力喷管型面研究

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Graph Morphing applied in design optimization for solid rocket motor

图形变形法在固体火箭发动机设计优化中的应用

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Simulation and Experiment of Thrust Performance for Solid Rocket Motor with Angle-cut Nozzle

斜切喷管固体火箭发动机推力特性仿真与试验

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