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。
Two-phase turbulent reacting flow model of the internal operating processes in Liquid Rocket Engine (LRE) is set up in non-orthogonal curvilinear coordinates.
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。
Finally, based on the model data, the neural networks are applied to recognize several fault patterns of the liquid rocket engine.
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。
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.
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 numerical model was employed to analyze the tangential combustion instability in liquid rocket engine.
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。
The manufacture quality of solid rocket engine is ensured by the constant temperature pushing core model.
恒温插芯可以确保固体火箭发动机的制造质量，远程控制可以避免事故突发带来的人员伤亡。
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。
This paper presents a no-contact temperature measurement for a small rocket engine jet exhaust, for a shock wave on nose cone of a model in a jet exhaust and for a model surface of various materials.
本文叙述了用光学法测量小发动机燃气流火焰温度、燃气流中模型前端的激波温度及不同材料的模型表面温度。
A nonlinear dynamic mathematical model for describing the transient processes of working conditions has been established according to the fault characteristics in a liquid rocket engine.
针对发动机的故障特点，提出了其工作状态过渡的非线性动态数学模型。
A nonlinear dynamic mathematical model for describing the transient processes of working conditions has been established according to the fault characteristics in a liquid rocket engine.
针对发动机的故障特点，提出了其工作状态过渡的非线性动态数学模型。
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