Firstly, according to the traits of the variable thrust engine, the hardware of the control system is designed.
首先结合变推力发动机的特点设计了数字控制器的硬件电路。
Flow in injector passages of a variable thrust liquid propellant rocket engine was studied.
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。
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.
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。
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