solid rocket的例句大全

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

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The Analysis of Test Failure of Solid Rocket Engine

固体火箭发动机试验故障分析

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The tentative design of constant altitude flight solid rocket composed of the sustainer, the booster and its simple control method is presented.

介绍了主发动机加助推器和简易控制方法实现固体火箭等高飞行的设计方案。

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Engineering Analysis of Large Solid Rocket Motor Head Area Heat Shield in Ground Spinning Test Firing

大型固体发动机旋转试车头部热防护工程分析

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Constant Temperature Remote Control System for Solid Rocket Engine Pushing Core Model

固体火箭发动机插芯恒温远程控制系统

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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

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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

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Three-dimensional stress analysis in solid rocket motor chamber under overload

固体火箭发动机燃烧室过载下的三维应力分析

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In this paper, a simple method for analysis of ground test data of the solid rocket motor with reversal nozzles is presented based on solving the reverse thrust at an altitude from ground test data.

文中介绍了根据地面实验数据分析反喷管在高空提供的反推力，为带反喷管发动机地面实验数据处理提供了简便的分析方法。

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The characteristic velocity, area of nozzle throat and other parameters are calculated by using the static test results of solid rocket motor ( SRM) and introducing generalized pressure coefficient and thrust coefficient.

利用发动机地面试验结果，引入广义的压强系数和推力系数，计算了发动机的特征速度、喷管喉部面积等参数。

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Analysis on thrust measurement deviation and lateral force interference for a certain type of solid rocket motor

某型号固体发动机推力测试偏差与侧向力干扰问题分析与试验

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The methods for predicting thrust performance deviation and evaluating reliability for solid rocket motors are given by using the error analysis theory and single factor test results.

应用误差分析理论并根据单因素试验结果给出了预示发动机推力性能偏差及可靠度综合评定方法。

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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。

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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

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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。

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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。

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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

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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

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Simulation and Experiment of Thrust Performance for Solid Rocket Motor with Angle-cut Nozzle

斜切喷管固体火箭发动机推力特性仿真与试验

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It's verified that a series of intense pressure impulses can occur in the combustion chamber after the thrust reversal nozzles of the solid rocket motor are suddenly opened.

实验表明，突然打开固体火箭发动机反向喷管后，燃烧室中可能出现强烈的压力冲击，这种压力冲击来自喷管喉部节流和形成准稳态流动之前的非定常过程。

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