通过提出一个“Y假设”，本文求得了一个固体火箭发动机线性声振荡燃烧的三维理论模型。
On the assumption of "Y", a three-dimensional model is obtained for the linear acoustic combustion in a rocket motor.
建立了任意斜交曲线坐标系下液体火箭发动机(LRE)内部工作过程的气液两相湍流化学反应流模型。
Two-phase turbulent reacting flow model of the internal operating processes in Liquid Rocket Engine (LRE) is set up in non-orthogonal curvilinear coordinates.
最后，基于模型数据，应用神经网络识别了液体火箭发动机的几种故障模式。
Finally, based on the model data, the neural networks are applied to recognize several fault patterns of the liquid rocket engine.
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。
This paper established the mathematical models of the whole operation process of gelled propellant rocket engine based on system disassembly.
以轴对称非定常欧拉方程为基础，建立了激光推进火箭发动机吸收室内纯气相单组分、以激光等离子体为内热源的流场模型。
A gas flow model with laser plasma as heat source was developed based on axial symmetric Euler equations in the laser propulsion rocket engine absorption chamber.
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。
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.
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.
结果表明，该模型精度较高，在固体火箭发动机研究方面具有较好的工程应用价值。
The results show that the model with high precision will find promising engineering application in research of solid rocket motors.
模型的8个火箭发动机，每个都有250磅的推力。
The model had eight working rocket engines with 250pounds of thrust each.
建立了液体火箭发动机切向不稳定燃烧数值分析模型并进行了初步分析。
A numerical model was employed to analyze the tangential combustion instability in liquid rocket engine.
研究表明，九分力模型和九分力推力矢量试车台提高了推力矢量测量的精度，适合用于测量大型固体火箭发动机的推力矢量。
The study shows that the nine-component model and nine-component thrust vector stand can improve the precision of thrust vector measurement greatly.
根据固体火箭发动机绝热防护模型，提出了一种嵌金属丝端燃装药绝热层设计方法。
According to the thermal shielding model of solid rocket motor, an approach of ablation heat shield design of end-burning grain with embedded wire was put forward in this paper.
对某大型液体火箭发动机的热试车数据及通过发动机模型仿真得到的故障数据进行动态时间弯曲分析，得到弯曲路径集，然后结合决策树方法进行了故障检测和诊断。
Through dynamic time warping analysis to the hot-fire test data and simulated fault data of a certain liquid rocket engine, the warped path sets were obtained.
分析了液体火箭发动机中所用涡轮的各种损失因素，并建立了相应的数学模型，给出了计算方法。
The loss factors in liquid rocket turbine are analysed in detail and a related mathematical model and calculation method is proposed.
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。
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.
基于粘弹性随机有限元法（VSFEM）和多项式回归模型，分析了固体火箭发动机药柱结构的随机参数灵敏度。
Stochastic parameter sensitivity of SRM grain structure was analyzed based on viscoelastic stochastic finite element method(VSFEM) and polynomial regression model.
基于粘弹性随机有限元法（VSFEM）和多项式回归模型，分析了固体火箭发动机药柱结构的随机参数灵敏度。
Stochastic parameter sensitivity of SRM grain structure was analyzed based on viscoelastic stochastic finite element method(VSFEM) and polynomial regression model.
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