China has undertaken to research and develop composite solid propellant rocket motors since 1958.
中国从1958年开始复合固体推进剂火箭发动机的探索和研制工作。
A conception of adjustable solid propellant rocket motor was proposed.
本文提出了一种推力可调的固体火箭发动机的设想方案。
A new method of the solid propellant rocket nozzle design is presented.
本文介绍一种设计固体火箭喷管的新方法。
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。
The 300mm diameter solid propellant rocket motor employs a composite propellant end burning grain.
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。
This paper discusses operating principles and technology challenges of the integral solid propellant rocket ramjet.
研讨了整体式固体冲压火箭发动机的工作原理及技术难点；
The ablation mechanism and the performance of carbon-phenolic material of solid propellant rocket nozzles are studied.
本文研究了碳-酚醛材料在固体火箭发动机喷管中的烧蚀机理及性能。
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。
Overload acceleration is one of those important factors which influence the performance of solid propellant rocket motor.
过载加速度是影响固体火箭发动机性能的重要因素之一。
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。
In this paper, one-dimensional two-phase constant lag flow in combustion chamber of solid propellant rocket motors is described.
本文论述了固体火箭发动机燃烧室一维两相常滞后流动。
Interface bond quality of solid propellant rocket motor can be tested by Lamb waves, but the modes of Lamb waves need to be selected.
用兰姆波可对固体火箭发动机进行胶接质量的检测，但需要对其模式进行选择。
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。
To appreciate the unsteady environment existing in liquid propellant rocket chambers it is necessary that the steady state be well understood.
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。
According to the entire design requirements and restraints of a certain solid propellant rocket motor, design method of nozzle contour is put forward.
根据某型号固体火箭发动机总体设计要求及限制条件，给出了喷管型面设计方法。
The plume temperature is an important parameter, for solid propellant rocket engines and it is useful for determining the combustion process of the engine.
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 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。
High speed rotation solid propellant rocket motor recording apparatus which we designed is going to resolve pressure testing of rocket motor in high speed rotation.
本文设计的高速旋转固体火箭发动机内置动态参数记录仪，着重解决火箭发动机在高速旋转状态下压力测试问题。
This paper attempts to analyse the tendency to develop liquid propellant rocket propulsion technology according to the requirements o launch vehicles and spacecrafts.
本文试图根据运载火箭和航天器的需要来分析液体火箭推进技术的发展趋势。
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。
To overcome the difficulties on acquiring enough fault modes from ground and flight test data, the failure process for liquid propellant rocket propulsion systems was modeled.
为克服由于试验或飞行数据不足而无法获取系统足够故障模式的问题，开展了液体火箭推进系统故障过程建模与计算机仿真研究工作。
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 studies the problem of tradeoff optimization between damage of reusable liquid propellant rocket engine's turbine blade and control input sequences during the start-up process.
针对可重复使用液体火箭发动机起动过程，研究了系统控制输入序列的变化对以涡轮叶片为代表的关键部件累积损伤的影响。
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。
The modeling of priming process of Liquid Propellant Rocket Engines (LPRE) was studied.
研究了常温推进剂液体火箭发动机充填过程的建模问题。
Lacking of fault samples is a knotty problem in the fault detection of complex systems such as Liquid-propellant Rocket Engines (LRE).
在对类似于液体火箭发动机这种复杂系统的故障检测过程中，一个非常棘手的问题是缺乏故障类样本。
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