机译:重复脉冲操作下微波火箭的推力性能
University of Tokyo, Chiba 277-8561, Japan Department of Advanced Energy, 5-1-5 Kashiwa-no-ha,Kashiwa;
University of Tokyo, Chiba 277-8561, Japan Department of Advanced Energy, 5-1-5 Kashiwa-no-ha, Kashiwa;
University of Tokyo, Chiba 277-8561, Japan Department of Advanced Energy, 5-1-5 Kashiwa-no-ha, Kashiwa;
Japan Atomic Energy Agency, Ibaraki 311-0193, Japan Fusion Research and Development Directorate, 801-1 Mukoyama, Naka;
Japan Atomic Energy Agency, Ibaraki 311-0193, Japan Fusion Research and Development Directorate, 801-1 Mukoyama, Naka;
Japan Atomic Energy Agency, Ibaraki 311-0193, Japan Fusion Research and Development Directorate, 801-1 Mukoyama, Naka;
A: area of the thruster; C_m: momentum coupling coefficient; c_p: isobaric specific heat; f: pulse repetition frequency; I: thrust impulse;
机译:重复脉冲操作下微波火箭的推力性能
机译:等离子体结构对气体推进剂的依赖性与微波火箭的推力性能
机译:气体推进剂等离子体结构的依赖性和微波火箭的推力性能
机译:微波束空间传输系统对微波火箭的推力性能和等离子体产生
机译:带有螺旋形燃油口的混合火箭的推力增强喷嘴
机译:可调谐的微波超表面用于高性能操作:色散补偿和动态切换
机译:Сalculation分析了运行与设计因素对氧气低推动火箭发动机参数的影响分析
机译:采用射束微波能量的固体火箭发动机推力增强