1. The practical applications of this control system to the hypergolic bipropellant attitude control rocket engines at 30kg and 100kg thrust levels respectively are stated.
说明了该控制系统在30公斤级与100公斤级的双组元燃料变推力姿控火箭发动机中的具体应用情况。
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2. 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。
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3. The atomization mechanism of hypergolic rocket propellant and decomposition combustion at high pressure and turbulence burning of premixed reactant flow field are considered .
