高性能高可靠氢氧发动机方案探讨  

Discussion on the High Performance and Reliability LOX/LH_2 Rocket Engine

作　　者：郑大勇[1,2] 颜勇[2] 胡骏[1] Zheng Da-yong;Yan Yong;Hu Jun(Nanjing University of Aeronautics and Astronautics, Nanjing, 210016;Beijing Aerospace Propulsion Institute, Beijing, 100076)

机构地区：[1]南京航空航天大学,南京210016 [2]北京航天动力研究所,北京100076

出　　处：《导弹与航天运载技术》2016年第6期10-13,54,共5页Missiles and Space Vehicles

摘　　要：根据未来运载器对动力装置的任务需求及氢氧发动机技术发展趋势,基于50吨级氢氧发动机,以产品性能提高、功能拓展和可靠性增长为设计目标,开展了发动机衍生产品优化设计研究。衍生型发动机基于现有燃气发生器循环或开式膨胀循环,充分继承和借鉴了现有产品的技术基础和成熟组件,产品功能有所拓展,产品性能和可靠性有所提高,丰富了中国氢氧发动机产品库,有利于未来运载火箭构型优化和运载能力提升。According to future requirement of engine for the next-generation launch vehicle, a new derivative LOX/LH2 rocketengine is brought forward based on 50-ton-thrust Oxygen/Hydrogen engine aiming at enhancing performance, function and reliability.The derivative engine utilizes a gas generator cycle or expander bleed cycle with high performance, which can significantly lift capability of the vehicle and realise configuration optimization.

关 键 词：氢氧火箭发动机 运载火箭 优化设计 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]