火箭发动机试验的立场，施加武力对负载细胞。
介绍一种固体火箭发动机试验用综合软件系统。
A multifunctional software system for solid motor test is introduced, which consists of independent modules with Shared data bases.
介绍了一种固体火箭发动机试验数据分析处理及管理系统。
A software system for solid rocket motor test data analysis and management is introduced.
在此基础上，建立了火箭发动机试验台液氢供应系统的健康评价体系。
Base on these, the health condition evaluation system of the liquid hydrogen supplying system of a rocket engine testing platform was set up.
液体火箭发动机试验的原始测量数据中存在着噪声，影响了数据的准确性和可信性。
Noise in the raw acquired data of liquid propellant rocket engine test can reduce accuracy and creditability of the data.
从工程研制角度出发，探讨了分析固体火箭发动机试验失败原因的一般方法和过程。
The general method and process to analyze the failure reason of solid rocket engine from the engineering research are discussed in this paper.
周日的飞行明确了宇宙飞船建造商s caledComposites将要在明年开启装有火箭发动机的飞行计划，在太空中的试验飞行将在2011年底或2012年初进行。
Sunday's flight clears spaceship builder Scaled Composites to begin rocket-powered flights next year, and test flights in space in late 2011 or early 2012.
这个网页介绍了测试报告，详细说明第一静力试验(kdx- 001)上进行了河童的dx火箭发动机，以及后的测试分析。
This web page presents the test report detailing the first static test (KDX-001) conducted on the Kappa-DX rocket motor, as well as post-test analysis.
在低温液体火箭发动机的试验中，对液体密度的测量是很重要的。
It is very important to measure liquid density in cryogenic liquid rocket engine test.
基于系统分解方式，建立凝胶推进剂火箭发动机工作过程的数学模型，并采用液流试验数据对其进行修正。
This paper established the mathematical models of the whole operation process of gelled propellant rocket engine based on system disassembly.
本文介绍了固体火箭发动机水下推力矢量特性试验。
The thrust vector control(TVC) performance test of solid rocket motor is presented in this paper.
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。
Finite element method is used in the study of nozzle damping of instable combustion in a solid rocket motor. Wave decline method is used in the experimental research.
研究了火箭发动机高速旋转试验台高速轴在工作激振频率内的振型。
The mode shapes of the high-speed shaft in rotating test-bed for rocket engine within working excited frequencies were studied.
本文建立了火箭发动机在管内点燃情况下，串联结构的高低压无后座力发射器的内弹道方程，并对试验弹进行了数值计算。
This paper established the internal ballistics equation for the high-low pressure launcher with tandem construction when the rocket motor is ignited in the launch tube.
并介绍了试验测试系统和试验结果。该试验可为固体火箭发动机燃烧不稳定性预估提供原始数据。
Also the measurement system for testing and test results are presented This test can provide original data for estimation of combustion instability in solid rocket motors.
然后，利用某型号固体火箭发动机进行喷管分离流试验，测得了喷管壁面上沿轴向的压强分布数据。
Then, the experiment of flow separation in the nozzle was done with a solid rocket motor, and the inside pressure data along the axis of the nozzle was gotten.
对液体火箭发动机主涡轮的性能试验进行了介绍。
The performance tests of the main turbine of a liquid rocket engine are introduced in this paper.
通过数值模拟和试验研究，分析了喷口遮挡对姿控火箭发动机性能的影响。
The effect of the blocked spouts on the performance of an attitude control rocket motor was analyzed by using numerical simulation and test.
通过转子试验平台实时数据和液体火箭发动机历史试车数据，验证了TP-FDS。
Then, with the help of historical data from LRE test as well as real-time data from rotor test platform, the TP-FDS was validated.
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。
Finite element method is used in the study of nozzle damping of instable combustion in a solid rocket motor.
提出了一种带有中间喷管的新型双脉冲固体火箭发动机技术方案，设计了一台结构参数可调的试验发动机；
A new type of dual-pulse solid rocket motor concept with an intermediate nozzle is presented and a test motor with changeable structural parameters was designed.
将电磁悬浮技术用于火箭发动机推力测试试验台是一次新的尝试。
It is a new experience to apply magnetic levitation technique to thrust measurement for rocket engine.
针对固体火箭发动机(srm)地面试验图像受烟雾干扰严重，在SRM地面试验图像预处理中，烟雾去除研究非常重要。
According to the case that the smog severely disturbs the SRM ground test image, the smog removing is very important in the SRM ground test image preprocessing.
文中讨论了橡胶制品的自然老化与加速老化的特点，介绍了固体火箭发动机用橡胶制品加速老化试验的方法和步骤，并给出了试验结果与结论。
In this paper, the characteristics of natural and accelerated aging of rubber product is discussed. Also, the method and procedure of accelerated ageing tests and the test results are presented.
压力-时间痕量从kdx- 002静力试验的河童的DX火箭发动机将被用来估计推进剂燃烧率，与结果相比，钢绞线燃烧器的数据 。
The pressure-time trace from the KDX-002 static test of the Kappa-DX rocket motor will be used to estimate the propellant burn rate, with the results compared to Strand Burner data .
本文用最大误差方法，对固体火箭发动机六分力立式试验台的静态误差进行了分析。
By using the method of maximum error, the paper deals with the analysis of the static error of the six-component force test stand of solid rocket motors.
介绍了固体火箭发动机喷管硬质泡沫塑料堵盖的设计方法与试验过程。
Design methods and test process of nozzle closure made of hard foamed plastics for SRM are introduced.
通过压力、高低温循环等大量的试验和理论分析表明：采用填充密封胶的螺纹联接密封结构具有优异的密封性，适宜在固体火箭发动机环境中应用。
Based on pressure and high low temperature cycling tests and theoretic analysis, the threaded joint parts filled with sealing glue compound show excellent seal ability, and can be applied to SRM.
该火箭发动机和试验台是如图3所示。
该火箭发动机和试验台是如图3所示。
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