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.
本文讨论了单室双推力星形装药固体火箭发动机的结构优化方法。
This paper presents a method of optimum design for single-chamber double-thrust solid rocket motors.
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