火箭发动机

Finally the sealing reliability is analyzed while the effect of creep-relaxation of each component of flanged connection system for rocket motors is considered.

然后考虑蠕变-松弛作用，提出了在预紧和操作情况下火箭发动机法兰连接系统载荷与变形计算的新方法。

On the basis of the study on the shaping law to process the cowled integral impeller with ECCEM, the data depict the blade surface of the cowled integral impeller were processed, so that the tool-cathode was devised and its path in the process was obtained. Then the shape of the tool-cathode and its path were adjust according to the simulation of the computer.

由于带冠整体叶轮是整体叶轮结构设计的发展方向之一，特别在火箭发动机中，论文在研究展成电解加工带冠整体叶轮成型规律的基础上，分析处理带冠整体叶轮的型面数据，计算加工轨迹，设计工具阴极，并依据计算机仿真对加工轨迹和工具阴极的形状进行修正。

A method was developed to measure the gas temperature in the chamber of solid rocket motor by using the double line of atomic emission spectroscopy. The measurement system had been designed.

发展了一种利用原子发射双谱线法，测试固体火箭发动机燃烧室內燃气温度的方法，设计了相应的测试系统。

Liquid propellant rocket engine ; Thermodynamic cycle ; Energy conversion efficiency ; System analysis

液体推进剂火箭发动机；热力学循环；能量转换效率；系统分析

This method of estimating a rocket motor performance will be covered in greater detail in a future web page.

这个估计方法一火箭发动机的性能将包括更详细的，在未来的网页。

How to reduce the energy consume so that the quality of the interceptor would be reduced and enhanced the final velocity and average velocity are the key technology of the system scheme for LRADI. Aimed at the character of the LRADI, analysis and study the questions of adoption"interval time can be changed double pulse Solid Rocket Motor"and"double high cast virtual target composition guidance trajectory".

因此如何降低能量的消耗、减轻拦截器的重量，提高末速度和平均速度成为远程反空气动力目标拦截器总体方案的一个重要关键技术，本文针对远程反空气动力目标拦截器的特点，提出和论证了采用"间隔时间可调的双脉冲固体火箭发动机"和"双高抛虚拟目标复合导引飞行弹道"两条新技术途径相关的各种问题。

Liquid propellant rocket engines ; combustion chambers ; partition model ; finite elements ; state variable model

液体火箭发动机；燃烧室；分区模型；有限元；状态变量模型

A simplified model for the disign of hypergolic liquid propellant rocket engine combustors is presented.

本文提出了一个自燃推进剂液体火箭发动机燃烧室设计简化模型。

The practical applications of this control system to the hypergolic bipropellant attitude control rocket engines at 30kg and 100kg thrust levels respectively are stated.

说明了该控制系统在30公斤级与100公斤级的双组元燃料变推力姿控火箭发动机中的具体应用情况。

The effort of spray characteristic on rocket engine combustion stability for hypergolic propellant was studied.

用数值方法研究了一甲基肼/四氧化二氮自燃推进剂喷雾液滴直径对火箭发动机燃烧稳定性的影响。

But we don't care about Battlegrounds.

但我们并不在乎沙场中的显露。

Ah! don't mention it, the butcher's shop is a horror.

啊！不用提了。提到肉，真是糟透了。