变推力液体火箭发动机 variable thrust liquid rocket engine
在研制变推力火箭发动机的过程中，低工况时遇到了燃烧振荡问题，我们采用横向挡流板很好地解决了这个问题。
On the development process of the variable thrust rocket engine combustion vibra ions are encountered in the low working conditions, we solved this problem finely by lateral baffle.
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。
The practical applications of this control system to the hypergolic bipropellant attitude control rocket engines at 30kg and 100kg thrust levels respectively are stated.
本文对变推力液体火箭发动机喷注器通道内介质流动进行求解。
Flow in injector passages of a variable thrust liquid propellant rocket engine was studied.
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