Conceptual Investigation for a LOX/Methane/H2 Dual Fuel Dual Mode Rocket Engine

摘要：

A LOX/methane/H2 dual fuel dual mode rocket engine uses LOX/methane propellant, which density is higher,at low altitude and uses LOX/H2 propellant,which specific impulse is higher, at high altitude. The influence of using LOX/methane/H2 dual fuel dual mode rocket engine as a HTHL SSTO vehicle power on the vehicle performance is evaluated through trajectory computation. The viability of the engine is analyzed with the rocket engine static characteristics emulation program.

关键词： Single-stage-to-orbit Horizontal Take-off Horizontal Landing Dual Fuel Dual Mode Rocket Engine

作者: Chen Tao Zhu Senyuan Liu Yu

作者单位: School of Astronautics, Beihang University, 100083 Beijing, China Beijing Aerospace propulsion institute, 100076 Beijing, China School of Astronautics,Beihang University, 100083 Beijing,China

会议类型: 国际会议

会议名称: The 11th International Space Conference of Pacific-basin Societies(第11届环太平洋国际航天会议)

会议地点: 北京

会议语种:英文

页码: 537-544

在线出版日期: 2007-05-16（万方平台首次上网日期，不代表论文的发表时间）