自燃推进剂

自燃推进剂组元液滴的高压平衡蒸发计算模型

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

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。

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 .

自燃推进剂火箭发动机稳态燃烧过程的数值模拟

Numerical simulation of stable combustion process in earth storable bipropellant rocket engine

绿色过氧化氢双组元自燃推进剂

Green Hypergolic Bipropellant Using Hydrogen Peroxide as an Oxidant

较轻的推进器采用液态氢，较重的采用自燃推进剂。

The lighter version used liquid hydrogen , the heavier used hypergolic propellants .

用于双组元自燃推进剂变推力火箭发动机的可变增益电磁阀控制系统

Variable Gain Solenoid Valve Control System Used for Hypergolic Bipropellant Variable Thrust Rocket Engine

数值仿真模型中考虑了自燃推进剂雾化机理、高压分解燃烧和预混反应流湍流燃烧等。

The atomization mechanism of hypergolic rocket propellant and decomposition combustion at high pressure and turbulence burning of premixed reactant flow field are considered .

本文提出了一个高压液体双组元自燃推进剂火箭发动机燃烧室计算模型。

A mathematical model describing combustion in a high pressure liquid hypergolic bipropellant ( UDMH / H2O4 ) rocket engine combustor has been developed .

本文对混合比为09、10、11三种状态下工作的双组元自燃推进剂（肼/四氧化二氮）姿控发动机喷管内化学反应流动进行了数值模拟。

The chemical reacting flow in the bipropellant altitude controlling thruster nozzle with the mixture ratio of 0 9,1 0 and 1 1 was simulated by using loosely coupled point implicit scheme .