燃烧消耗量
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。
Study on Software of Solid Propellant Burning Rate Prediction Based on one-dimensional Steady-state Reaction Gas Flow
基于一维气相稳态反应流的燃速预估软件研究
To know more altitude compensation and base characteristics of plug nozzle, cold-flow tests on 1-cell 2D linear plug nozzle, which utilize high pressure air as propellant were conducted.
为研究塞式喷管的高度特性和底部特性,采用高压空气为工作介质对单元直排塞式喷管进行实验。
Modeling and Simulation of Pasty Propellant Flow in Hot Pipe
膏体推进剂在热管道内流动的建模与仿真
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