给出了推力室内从推进剂雾化、蒸发、燃烧到传热一整套合理的数学模型。
And a reasonable mathematic model about the spray, evaporation, combustion and heat transfer of the propellant in engine is given.
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 .
为了有效地进行燃烧，推进剂必须雾化。
For proper combustion it is necessary to atomize the propellants.
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