An integrated conceptual design software system for solid rocket motors SRMCAD is developed.
研制了一种固体火箭发动机集成方案设计系统软件SRMCAD。
This paper presents a method of optimum design for single-chamber double-thrust solid rocket motors.
本文讨论了单室双推力星形装药固体火箭发动机的结构优化方法。
Based on the exhaust flame characteristics of solid rocket motors, a multiple target multi-spectral pyrometer was developed.
根据固体火箭发动机羽焰特征研制了多目标多光谱高温仪。
In addition, this achievement provides the basis of integrative performance calculation for all kinds of solid rocket motors.
而且，这一成果为整个固体火箭发动机领域流场的一体化计算打下了基础。
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。
The condensed phase particle size distribution affects the combustion chamber and nozzle efficiency of solid rocket motors to some extent.
凝聚相微粒尺寸分布对固体火箭发动机燃烧室效率和喷管效率有影响。
Owing to the dissimilar combustion mode, their working process is different form that of solid rocket motors and the liquid rocket engines.
由于氧化剂和燃料的燃烧方式不同，固液火箭发动机工作过程和液体火箭发动机及固体火箭发动机有很大的区别。
A new seal structure suited to solid rocket motors (SRM) is introduced, and threaded joint structures and sealing glue compound are studied.
提出了一种适用于固体火箭发动机(SRM)的新型密封结构，并对应用于特定尺寸的螺纹联接结构方式、胶种选择进行了研究。
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.
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。
This dissertation integrates theoretical analysis and numerical simulation method to investigate the ignition transient process of large aspect ratio solid rocket motors.
本文采用理论分析和数值仿真方法对大长径比固体火箭发动机点火瞬态过程进行了系统研究。
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.
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。
During the ground test of solid rocket motors, after the reversal nozzles are opened, the shock wave enters the primary nozzle. This phenomenon makes tested data processing difficult.
带反喷管固体火箭发动机地面实验时，在其反向喷管打开后，激波进入主喷管情况下，会给数据处理带来困难。
China has undertaken to research and develop composite solid propellant rocket motors since 1958.
中国从1958年开始复合固体推进剂火箭发动机的探索和研制工作。
In this paper, one-dimensional two-phase constant lag flow in combustion chamber of solid propellant rocket motors is described.
本文论述了固体火箭发动机燃烧室一维两相常滞后流动。
In this paper, is developed a physical model with the ignition process taken into account, for the internal ballistics calculation of solid propellant rocket motors.
本文根据提出的考虑点火过程的内弹道计算的物理模型，建立了数学方程。
In this paper, is developed a physical model with the ignition process taken into account, for the internal ballistics calculation of solid propellant rocket motors.
本文根据提出的考虑点火过程的内弹道计算的物理模型，建立了数学方程。
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