model of propellant的例句大全

based on the assumption of geometric burning law, a computational model of propellant burning rate under the effect of plasma was presented.

基于几何燃烧定律的假设，提出了等离于体作用下火药燃速的计算模型。

The High-Pressure Equilibrium Vaporization Model of a Hypergolic Propellant Species Droplet

自燃推进剂组元液滴的高压平衡蒸发计算模型

The effect of initial propellant temperature on rocket engine combustion stability for hypergolic propellant ( MMH/ NTO) is studied. A physics model for initial propellant temperature effecting evaporation rate has been developed in this paper.

对自燃推进剂（MMH/NTO）初始温度对火箭发动机燃烧稳定性的影响进行了研究，从推进剂初始温度对蒸发速率的影响规律出发，发展了初始温度大小影响蒸发速率的物理模型。

A numerical analysis model of tangential combustion instability in liquid propellant engine

液体火箭发动机切向不稳定燃烧数值分析模型

A Model for Erosive Burning of Solid Propellant Based on Statistical Theory of Turbulent Flame

根据紊流火焰统计理论所建立的固体推进剂侵蚀燃烧模型

The mathematic model of turbulent gas-particle flows of remained propellant space emission is established by applying multi-phase fluid model of Euler theory.

应用Euler理论的多相流体模型，建立了剩余推进剂排放气-粒两相湍流流动的数学模型；

Application of annular instability model to FY-20 liquid propellant rocket engine

环形不稳定性计算模型在FY-20液体火箭发动机上的应用

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。

in this paper, a new parameter named slurry combustion effect was induced for applying solid propellant bdp model for prediction of pasty propellant and slurry propellant steady combustion behavior.

在固体推进剂BDP燃烧模型基础上，引入膏体推进剂燃烧热效应这一新参数将模型推广于膏体推进剂和固体推进剂药浆燃烧研究。

In this study, the SST k-ω turbulence model was used to simulate the coupled whole field for the transpiration cooling of a thruster in a liquid O2/ H2 propellant rocket engine.

本文选用SST K-ω湍流模型对采用烧结多孔介质进行发汗冷却的液体O2/H2火箭发动机推力室进行了全场耦合数值模拟研究。

study of emulational model on the deflagration-to-detonation transition of high energy propellant

高能推进剂燃烧转爆炸仿真模型研究

By making numerical calculation of the model, the process and condition for hot-spot formation were discussed, from which it is concluded that friction between crack surfaces slip and crack growth can lead to formation of hot-spot in composite solid propellant.

通过模型数值计算，探讨推进剂裂纹摩擦产生高温热点的过程和条件。分析计算表明裂纹摩擦和扩展可导致推进剂形成高温热点。

Objective To establish model of blast-toxicosis combined injury caused by the explosion of the liquid propellant.

目的复制冲击波和液体火箭推进剂中毒致冲毒复合伤的动物模型.