solid rocket的例句大全

Technique of thrust termination with reversal nozzle for solid rocket motors

固体火箭发动机反向喷管推力终止技术

An Exploratory Research of Test Technique for Solid Rocket Motor Thrust Termination

固体火箭发动机推力终止试验技术探讨滚珠式推力终止装置可靠性研究

A cold air experiment on thrust termination of a solid rocket motor with reversal nozzles is described in this paper.

本文介绍一个反向喷管推力终止的冷模拟实验。

Measuring method of opening time and operating synchronism of the reverse nozzle closures of solid rocket motor during thrust termination test was studied.

研究了固体火箭发动机推力终止试验时，反向喷管堵盖打开时间及同步性测量方法。

Dynamic calculation on thrust vector control system for solid rocket motor

固体火箭发动机推力向量控制系统动力学计算

Investigation on secondary gas injection for solid rocket motor based on thrust vector control

基于推力矢量控制的固体火箭发动机气体二次喷射研究

Nozzle is an important part of the thrust vector control system of solid rocket motor and high-performance design of a nozzle plays an important role in the performance of the motor.

喷管是固体火箭发动机推力向量控制系统的重要组成部分，高效能的喷管设计对发动机的性能至关重要。

The effects of the extendible exit cone on stability of the thrust vector control system of largescale solid rocket motor are presented and the measures for improving the system stability are suggested.

介绍了喷管可延伸出口锥对大型固体火箭发动机推力向量控制系统稳定性的影响，并提出了改善其系统稳定性的措施。

Combustion time determination in pressure-time curve of solid rocket motor

固体发动机压强-时间曲线中燃烧时间的确定

Based on the solid propellant burning rate formula, a new method for the combustion time determination during the data treatment in solid rocket motor firing test was studied with a method of numerical integration and interpolation.

以固体推进剂燃速公式为基础，采用计算力学中的数值积分及插值法，并利用计算机技术，研究了用燃烧室药柱的实际肉厚，确定固体火箭发动机试验曲线中燃烧时间的新方法。

As the increase of motor size and the time of motor operation, the spin stabilized solid rocket propelled space vehicles performed the unpredictable nutation instability.

自旋稳定固体火箭发动机飞行器随着发动机尺寸的增大，工作时间的增长，在发动机工作末期出现了不可预见的不稳定性运动。

The chamber-nozzle subsonic-transonic flowfield of solid rocket motor is computed by time-dependent method. The governing equations are numerically solved by MacCormack explicit scheme. The parameters of boundary points are calculated with physical boundary conditions and characteristic equations on the reference plane.

本文用时间相关法计算了固体火箭发动机燃烧室&喷管亚跨声速流场数值解，控制方程用MacCormack二步显格式：边界点参数用物理边界条件和参考平面上的特征方程计算。

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

As one of the key components of solid rocket motor, it is not only to withstand high temperature and pressure, but also to withstand the erosion of the solid particles and thermal chemical erosion of hot gas.

喷管喉衬是固体火箭发动机关键部件之一，要承受高温高压，固体粒子的冲刷以及高温燃气的热化学侵蚀等。

Application of infrared thermal imaging device in temperature measurement of solid rocket motor plume

红外热像仪在固体火箭发动机羽焰测温中的应用

Temperature field of solid rocket motor plume was measured by using a infrared thermal imaging device.

利用红外热像仪测量固体火箭发动机尾焰温度场。

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

According to the thermal shielding model of solid rocket motor, an approach of ablation heat shield design of end-burning grain with embedded wire was put forward in this paper.

根据固体火箭发动机绝热防护模型，提出了一种嵌金属丝端燃装药绝热层设计方法。

Numerical calculation model and method are applicable to analyzing reacting flow field of the solid rocket ramjet with central air-inlet mode.

采用的数值计算模型和方法适用于分析中心进气式固冲发动机反应流场。

Using k-ε turbulence model and one step eddy-dissipation model, numerical studies on the reacting flow field of solid rocket ramjet with secondary air inlets were carried out. Influence of mass flow ratio on combustion efficiency and temperature field was analyzed.

采用k-ε湍流模型及单步涡扩散化学反应模型，对二次进气结构的固体冲压发动机补燃室的反应流场进行数值模拟，分析了二次进气流量比对燃烧效率与温度场分布的影响。