An system design was conducted on the HOPE (H-2 Orbiting Plane), focusing on the following technical problems which are deemed to have great effects on the specifications of the airframe: (1) the feasibility of the tip fin; (2) trade-off of main airframe structure materials; and (3) trade-off of the orbit injection systems. The feasibility of HOPE was confirmed. The following items of the system and each subsystem were straightend up: (1) detail of the design requirements and their feasibility; (2) standard specifications of the airframe and its alternatives; and (3) design studies. In a development concept study, it was confirmed that the HOPE first launch in FY (Fiscal Year) 2000 will be possible by advancing the development systematically.
Heisei 3 Nendo HOPE Gainen Sekkei (Concept Study of the Space Transportation System HOPE in FY 1991)
1993
102 pages
Report
Keine Angabe
Englisch
Manned Spacecraft , Aerospace planes , Japanese spacecraft , Recoverable launch vehicles , Reusable launch vehicles , Reusable spacecraft , Spacecraft design , Aerodynamic characteristics , Equipment specifications , Space rendezvous , Spacecraft communication , Spacecraft configurations , Spacecraft control , Spacecraft docking , Spacecraft equipment , Spacecraft guidance , Spacecraft instruments , Spacecraft landing , Spacecraft propulsion , Spacecraft reentry , Spacecraft structures , Thermal resistance , Foreign technology
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