固体推进剂火箭发动机

固体推进剂火箭发动机贮存性能规律研究

A study on performance variation of solid propellant rocket engines in storage

固体推进剂火箭发动机羽焰温度诊断的遗传算法研究

Research on Genetic Algorithm for Plume Temperature of Solid Propellant Rocket Engine

直径300毫米的固体推进剂火箭发动机采用了复合推进剂端燃药柱。

The300mm diameter solid Propellant rocket motor employs a composite propellant end burning grain .

某些非金属材料在端燃药柱固体推进剂火箭发动机中的应用与试验分析

The Use and Testing Analysis of Some Nonmetal Materials in the End Burning Grain Solid Propellant Rocket Motor

推进剂的羽焰温度是固体推进剂火箭发动机的重要参数，对于研究发动机内的燃烧过程具有重要价值。

The plume temperature is an important parameter , for solid propellant rocket engines and it is useful for determining the combustion process of the engine .

根据航天技术发展的需求，促使复合固体推进剂火箭发动机从小到大逐步发展起来。

At the request of the diveloopment of spare technology , composite solid propellant rocket motor has developed from small to large , step by stop .

本实验研究中使用了小型固体推进剂火箭发动机及不同结构参数的喉部组件，用于研究喷管结构因素对喷管喉部沉积的影响。

The small experimental solid propellant rocket motor and the throat units with different structural parameters are used in this experimental analysis in order to study the effect of the nozzle structural factors on the nozzle throat deposition .

随着高能固体推进剂及其固体火箭发动机技术的发展和应用，对其安全性和安全使用的重视程度不断提升。

With the development and application of high-energy solid propellant and solid rocket motor , more attention is paid to the sensitivity and safer processes .

固体推进剂吸气式涡轮火箭发动机的气动热力循环分析（英文）冲压式空气喷气发动机

Thermodynamic cycle analysis on solid propellant air-turbo-rocket