Flow in injector passages of a variable thrust liquid propellant rocket engine was studied.
本文对变推力液体火箭发动机喷注器通道内介质流动进行求解。
A neural network classifier that utilizes fuzzy sets as failure classes of a liquid propellant rocket engine is studied.
研究了一种用模糊集表示火箭发动机故障模式的神经网络分类器。
Noise in the raw acquired data of liquid propellant rocket engine test can reduce accuracy and creditability of the data.
液体火箭发动机试验的原始测量数据中存在着噪声，影响了数据的准确性和可信性。
The general integral equations are derived for liquid and gas components of space propulsion systems with liquid propellant rocket engine.
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。
This paper established the mathematical models of the whole operation process of gelled propellant rocket engine based on system disassembly.
基于系统分解方式，建立凝胶推进剂火箭发动机工作过程的数学模型，并采用液流试验数据对其进行修正。
The principle of coriolis force mass flowmeter and its application in gelled propellant rocket engine test are introduced, results of the test are also analyzed.
介绍了科氏力质量流量计的原理及其在凝胶发动机试车中的应用，并对热试车的测量数据进行了分析。
This paper presents the development of the liquid propellant rocket engine technology from the viewpoint of combustion chamber pressure, thrust level and power cycle.
本文从燃烧室压力、系统工作循环方式以及最大推力三个方面叙述了世界各国液体火箭发动机的技术水平。
According to the requirement of the pasty propellant rocket engine design and pasty propellant pipe flow experiment, a new type of pasty propellant supply system is proposed.
依据膏体推进剂火箭发动机设计和膏体推进剂管道流动实验需求，提出了一种新型膏体推进剂供给系统方案。
The temperature of a high temperature, high pressure plume solid propellant rocket engine is difficult to measure but is useful for determining the combustion status of the engine.
对于固体火箭发动机羽焰温度的测量是困难的，了解其温度分布对于研究发动机内燃烧流场的特性有重要价值。
A calculation of the wall temperature distribution in liquid propellant rocket engine chamber with milled grooves was completed by the aid of three-dimensional finite element method.
采用三维有限元模型对液体火箭发动机铣槽推力室进行了壁温分布计算。边界条件按一维经验公式处理。计算中比较了不同冷却剂流量。
This paper presents computation and analysis of tangential mode of high frequency combustion instability in FY-20 liquid propellant rocket engine by means of the annular instability model.
本文用环形不稳定性计算模型计算、分析了FY -20液体火箭发动机的切向高频燃烧不稳定性。
The structural candidates of centrifugal impeller were designed respectively from single-objective and multi-objective optimization based on the system design of liquid propellant rocket engine.
根据液体火箭发动机系统设计确定的离心泵的性能参数，对泵叶轮的几何参数分别进行了单目标和多目标优化设计。
Firstly, the static and dynamic mathematic model of the Liquid Propellant Rocket Engine of pressure-fed providing system was established in centralized parameter method.
首先采用集中参数法，建立了挤压式供应系统的液体火箭发动机各部件的静态及动态数学模型。
Firstly, the static and dynamic mathematic model of the Liquid Propellant Rocket Engine of pressure-fed providing system was established in centralized parameter method.
首先采用集中参数法，建立了挤压式供应系统的液体火箭发动机各部件的静态及动态数学模型。
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