rocket motor

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

互联网摘选

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。

互联网摘选

Extend-range solid propellant rocket motor is an important part of the hybrid base-burner-rocket extending range shell.

增程固体火箭发动机是底排 — 火箭复合增程炮弹的主要部件之一.

互联网摘选

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。

互联网摘选

Nowadays, the six-component model based on the six-component test stand has been mainly used to measure the thrust misalignment of the solid rocket motor.

目前，国内外主要采用六分力试验台进行火箭发动机推力矢量偏心测量。

互联网摘选

Influence of mixture ratio of primary flow on secondary combustion flame stability of ejector rocket motor

一次燃气混合比对引射火箭二次燃烧火焰稳定的影响

互联网摘选

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。

互联网摘选

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

互联网摘选

Numerical solutions of full Navier-Stokes equations with chemical reaction flow were established for the nozzle flow of the LOX/ HTPB hybrid rocket motor.

利用二维轴对称N-S方程和组分方程对选用液氧/端羟基聚丁二烯推进剂的固液混合火箭发动机喷管流动进行了计算。

互联网摘选

A boundary layer numerical solution was used for the computation of combustion in hybrid rocket motor according to the boundary burning theory. Various value of mass transfer number and the oxidizer mass flux were considered in the calculation.

针对固液混合火箭发动机典型的边界层燃烧理论，用边界层的方法对固液混合火箭发动机燃烧进行了计算，计算采用二维轴对称的层流边界层方程，化学模型采用有限速率模型。

互联网摘选

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。

互联网摘选

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。

互联网摘选

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。

互联网摘选

High speed rotation affects the performance of solid propellant rocket motor.

在高速旋转条件下,固体火箭发动机的工作性能将受很大影响.

互联网摘选

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

互联网摘选

Then we use FLUENT to establish the quasi-steady and unsteady numerical models of pintle thrust controlled solid rocket motor, and verify the model with internal ballistic of pintle controlled solid rocket motor.

然后用FLUENT建立了喉栓式固体火箭发动机准稳态流场和非稳态流场的数值模型，用内弹道计算结果对数值模型进行了校验。

互联网摘选

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.

互联网摘选

The paper research fire angle of the projectile, firing time of the rocket motor, assisted time of the rocket motor, flying attitude of the glide phase and the terminal phase guidance law to add the projectile firing range.

在建立的模型的基础上，深入研究了炮弹的射角、火箭发动机的点火时间、火箭发动机的助推时间、滑翔段的飞行姿态以及末段制导律等对炮弹的射程及性能的影响。

互联网摘选

Deep space exploration gives a higher request to the performance of the rocket motor.

深空探测对火箭发动机的性能提出了更高的要求。

互联网摘选

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

互联网摘选

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

互联网摘选

The research of thermal protection system for the ramjet combustor of the integral solid ducted rocket motor is an important component of the development of the solid ducted rocket motor.

补燃室热防护系统研究是飞航导弹固冲发动机研究的一项重要内容。

互联网摘选

By studied the physics and mathematics model of the test-bed of thrust misalignment testing system for solid-propellant rocket motor, the data-processing software for six-component testing system is developed, and then the special parameters of the six-component data are extracted;

在对固体火箭发动机推力偏心测试台架进行物理与数学模型深入分析的基础上，开发了六分力测试系统的数据处理软件，对采集到的六分力数据进行特征提取；

互联网摘选

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。

互联网摘选

Simple reacting flow simulation of hybrid rocket motor

固液混合火箭发动机简单反应流模拟

互联网摘选

The Study of Error Source of Influencing Solid Rocket Motor Thrust Misalignment Characteristics

影响固体火箭发动机推力偏心特性的误差源研究

互联网摘选

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.

互联网摘选

Moreover infrared characteristics of a rocket motor nozzl was calculated, and effective and net radiative heat flux of the nozzle in mid-wave infrared band 2~ 6 μ m, long-wave infrared band 8~ 14 μ m and full wave band were analyzed.

还计算了一火箭发动机尾喷管的辐射特性，分析了该喷管在中波红外波带2~6μm和长波红外波带8~14μm及全波长的有效辐射和净辐射热流。

互联网摘选

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

互联网摘选

A hybrid rocket motor using this igniter was tested. The experiment results demonstrated that this new igniter can successfully start the N2O/ PMMA hybrid motor.

试验表明，在催化剂被加热到400~600℃左右后，该点火器可以成功启动N2O/有机玻璃（PMMA）混合火箭发动机。

互联网摘选