hypergolic propellant的例句大全

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。

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

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。