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。
The design and realization of a variable thrust liquid rocket engine control system is present in this paper.
本文讨论了某型变推力液体火箭发动机数字控制系统的设计和实现。
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。
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