H-2 transfer vehicle, ISS, spacecraft propulsion, propulsion system configuration, propulsion system performance, combustion vibration, reaction control system, firing test
その他のタイトル（英）
The results of propulsion system firing test for HTV
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Office of Space Flight and Operations
Japan Aerospace Exploration Agency Office of Space Flight and Operations
JAXA Special Publication: FY2004 Report of Joint Research Achievements of the Space Division of Institute of Aerospace Technology and Institute of Space and Astronautical Science: Basic Technologies of Space Transportation Systems
巻
JAXA-SP-05-010
ページ
93 - 98
発行年
2006-01-20
抄録（英）
The system firing test for HTV (H-2 Transfer Vehicle) was performed on June thru August, 2004. The result shows that the system provides approximately 50 percent thrust during short impulse RCS firings using four forward thrusters with GHe saturated propellant.
HTV推進システム燃焼試験結果報告
49056019.pdf
(961.77KB)
