最终给出了一台40公斤推力级、低增压比为3.0的单叶轮微涡扇发动机的丰富数据和特性曲线。
Eventually given a 40 kg thrust class, low-pressurized than 3.0 single-turbofan engine micro-impeller rich data and characteristic curves.
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.
此种电机适用于推力为数十公斤的场合。
The motor is fit for use where the thrust needed is dozens of kilograms.
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