液体推进剂火箭

本文介绍了基于GPIB总线接口和PC计算机的液体推进剂火箭爆炸污染参数测试系统，叙述了该系统的硬件组成和软件方案。

This paper introduced a test system developed for the research on the explosion pollution of liquid propellant rocket . This system is based on the GPIB bus interface and PC computer .

数值计算方法在液体推进剂火箭发动机瞬变过程计算中的若干应用

Some Applications of the Numerical Computation Method to the Transient Calculation of Liquid Propellant Rocket Engine

这个结果通常也应适用于液体推进剂火箭。

It is reasonable that this result should be generally applicable also to liquid-propellant rockets .

双元液体推进剂火箭发动机

Bipropellant liquid rocket motor

针对采用液体推进剂火箭发动机的空间推进系统，推导了系统液路和气路的通用积分形式方程。

The general integral equations are derived for liquid and gas components of space propulsion systems with liquid propellant rocket engine .

作者以液体推进剂火箭发动机为研究对象，建立了一个发动机构型分析与评价软件IRE/CAA。

A configuration analysis and assessment software for liquid propellant rocket engine LRE / CAA has been set up by author .

提出了一种模糊方向神经网络分类器，并应用于液体推进剂火箭发动机故障检测与分离。

A fuzzy direction neural network classifier used for fault detection and isolation ( FDI ) in a liquid propellant rocket engine is proposed .

为了实现液体推进剂火箭发动机的多次可靠起动，将气动谐振点火技术应用于气氧煤油的点火。

In order to realize the multiple ignitions of liquid rocket engines reliably , gas dynamic resonance ignition was applied to ignite kerosene / oxygen .

为了分析液体推进剂火箭发动机燃烧室中存在的非稳态环境，必须很好地了解稳态状态。

To appreciate the unsteady environment existing in liquid propellant rocket chambers it is necessary that the steady state be well understood . ( of non-living objects ) the state of being free of pathogenic organisms .

液体推进剂运载火箭爆炸热过程特性试验研究

An experimental study on heat processes propertes of liquid propellant rocket explosion

HAN基液体推进剂是一种新型绿色高能液体推进剂，是液体火箭发动机的理想燃料之一，其燃烧特性的优劣直接影响到发动机的工作性能。

HAN-based liquid propellant is a new type of green high-energy liquid propellant , whose combustion behaviors will directly affect the performance of the engine , as an ideal fuel for the liquid rocket engine .

利用液体火箭发动机作动力装置的火箭，又称液体推进剂火箭。

Steady state fault detection and diagnosis of liquid propellant rocket engines based on decision tree method ;