固体火箭

大型高能工业CT在固体火箭发动机检测方面的应用

Application of high Energy Industrial Computed Tomography In Testing Solid Rocket Engine

固体火箭喷管排气中的粒子分布关于｛x／n｝的分布

Distribution of the particle diameters in the jet exhaust of solid rocket motor

固体火箭发动机集成初步设计CAD系统研究

Some Progress in Development of Chinese Integrated Preliminary CAD Design of Solid Rocket Motors

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。

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

基于FBG传感器的固体火箭发动机结构健康监测技术

Health monitoring of solid rocket structure based on fiber grating sensing

介绍一种应用CAT技术确定固体火箭发动机燃烧时间的新方法。

The paper introduces a new method of measuring combustion time with CAT technique for solid rocket engine .

用TotalLagrangian增量有限元法分析固体火箭发动机的应力和变形

The analysis for stress and deformation of solid rocket engine by using the TOTAL-LAGRANGIAN incremental finite element method

基于爆破试验的CFRP固体火箭发动机壳体的可靠性设计

Reliability design of CFRP solid rocket motor vessel based on the burst experiment

固体火箭发动机结构系统可靠性Monte-Carlo数字仿真

System Reliability Digital Simulation with Monte-Carlo Method for Solid Rocket Motor Structure

固体火箭发动机ICT局部重建算法研究

Research on Local Tomography Algorithm of Solid Rocket Engine Based on ICT

基于VXI的固体火箭发动机地面试验柔性自动测试系统设计

The design of flexible automatic test system for SRM ground test based on VXI

提出一种用于评估固体火箭发动机内弹道压强&时间曲线（P-T曲线）的多样本时间序列方法。

A reliability evaluation method for P-T curve based on multi-sample time series analysis is proposed .

在此基础上，将MDF方法应用于固体火箭发动机内弹道计算，通过算例验证了MDF方法的适用性。

Basing research above , the MDF method has been used for SRM internal ballistics calculation , which has been test by two cases .

采用MDO方法，可提高固体火箭助推器的设计质量，大大减少设计迭代次数，从而缩短设计周期。

MDO method can improve design quality for solid rocket booster , and greatly reduce iterative times and shorten design period .

应用二阶隐式TVD格式对固体火箭冲压发动机增程弹丸超音速进气道内部湍流流场进行了数值仿真。

The numerical simulation of supersonic inlet internal turbulent flow of solid rocket ramjet assisted range projectiles was performed by 2-order implicit TVD .

讨论光纤布拉格光栅（FBG）传感技术用于固体火箭发动机结构应变场、温度场和损伤状况健康监测的可行性。

The feasibility of applying fiber gratings sensing on health monitoring of solid rocket motor ( SRM ) is discussed , including the strain measurement , temperature measurement and damage measurement .

针对固体火箭冲压发动机的特点，研制了固体火箭冲压发动机CAD软件，该软件系统包括了燃气发生器设计、助推补燃室设计、进气道设计、发动机性能计算和飞行弹道的计算。

The paper presents a CAD system developed for solid propellant ramjet rocket motor design . It includes gas generator design , booster chamber design , air inlet design , performance evaluation of a ramjet rocket motor and missile trajectory demonstration .

借助于ALE方法的早期程序SALE的基本框架，编写了适用于固体火箭发动机燃烧室流场分析的计算程序，求解气相流动。

Based on the SALE frame , the early code of ALE , compiled has been suitable for the Solid Rocket Motor combustion chamber flow field analysis computational procedure , the solution gas phase flows .

用RTR技术研究固体火箭发动机燃烧室中粒子运动轨迹（I）可行性分析与试验研究

Experimental study of particles trajectory in firing solid rocket motor with RTR TECHNIQUE part ( I ) analysis of feasibility and experimental results

用Fluent计算流体力学软件对固体火箭发动机喷管流场进行了数值计算，研究了喷管收敛半角、喷管喉部上游圆弧曲率半径和喉部圆柱段长度对喷管流场的影响。

Nozzle flow field of SRM was numerically simulated with Fluent software . The effects of nozzle convergent half angle , radius of curvature on upstream of throat section and length of throat cylinder on flow field are investigated .

采用二阶隐式TVD格式，结合区域分解算法对固体火箭冲压发动机增程弹丸超音速进气道内外复杂流场进行了数值模拟。

Applied second-order implicit TVD scheme and zonal method , the numerical simulation of supersonic inlet internal and external complex flow of solid rocket ramjet assisted range projectiles was presented .

采用新型的Flash单片机、信号采集电路与温控电路等构成一个对固体火箭发动机温控系统，满足其固体火药的初始温度设计要求。

The paper states the way of incorporating a new type of flash singlechip , signal acquisition circuits , temperature-control circuits into a temperature-control system for a soild rocket motor , so as to fulfil the settings on the initial temperature of its charge .

用辨识方法确定了带反喷固体火箭发动机推力终止过程中的瞬变参数，视这些参数是服从正态分布的随机变量，用MonteCarlo方法分析了推力终止过程内弹道的散布。

As the transient parameters during thrust termination of SRM with four reverse nozzles are determined by identification techniques and considered as random variables which obey normal distribution , the interior ballistic dispersion during thrust termination can be analyzed by Monte Carlo method .

结果表明，石墨渗铜材料具有较好的抗热震性能，解决了高性能战术导弹和航天飞行器高压强大流量固体火箭发动机（SRM）喉衬材料的关键技术。

Results indicate that copper impregnated graphite has good thermal shock resistance , which solves the critical technique of throat liner material used in high performance tactical missile and space vehicles with high pressure , high flow rate SRM .

C801导弹的助推器和续航发动机均采用固体火箭发动机，大大提高了其战斗性能。

The performance of C801 missile is greatly improved by using sol-id rocket motor both in its booster and sustainer .

固体火箭发动机（SRM）推进剂药柱在立式贮存时要承受两种主要载荷联合作用，即固化降温趋于平衡后的长期温差热载荷以及轴向的重力载荷作用。

Under vertical storage state of solid rocket motor ( SRM ), its propellant grain bears two main associate loads in a long period , that is , the heat load due to the temperature difference after the curing temperature tends to equilibrium state and self axial gravity load .

利用UDF和动网格技术建立了模拟包含燃面退移的固体火箭发动机内流场的计算方法，得到燃面变化下的二维瞬态内流场和相应的内弹道数值仿真结果。

UDF and the dynamic meshes are uesd to established a method which include moving burning surface of solid rocket motor , and get under the burning surface changes in two-dimensional transient flow field and the corresponding numerical simulation results within the trajectory .

本文主要研究了OdysseyXE数据采集系统在固体火箭发动机六分力测试系统的应用，重点解决通用数据采集系统数据采集软件的二次开发问题。

In this paper , the application of the Data Acquisition System of Odyssey XE in the Six-Component Testing System for Solid Rocket Motor is researched , and the most important is to solve the second-develop of data acquisition software of the general purpose data acquisition system .

文中以某上面级固体火箭发动机模态分析为例，利用有限元法、固定界面法和Guyan缩聚法进行自由度缩聚后再进行模态分析，分析结果令人满意。

In this paper , one model of rocket solid engines is analyzed by means of finite element method , fixed interface method and Guyan reduced method to reduce the degree of freedom . The result is satisfactory .

固体火箭喷管烧蚀和传热的基本问题

Some essential problems with ablation and heat-conduction in solid rocket nozzle