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Beta 2: A near term, fully reusable, horizontal takeoff and landing two-stage-to-orbit launch vehicle conceptA recent study has confirmed the feasibility of a near term, fully reusable, horizontal takeoff and landing two-stage-to-orbit (TSTO) launch vehicle concept. The vehicle stages at Mach 6.5. The first stage is powered by a turboramjet propulsion system with the turbojets being fueled by JP and the ramjet by LH2. The second stage is powered by a space shuttle main engine (SSME) rocket engine. For about the same gross weight as growth versions of the 747, the vehicle can place 10,000 lbm. in low polar orbit or 16,000 lbm. to Space Station Freedom.
Document ID
19920012293
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Burkardt, Leo A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1992
Publication Information
Publication: Rocket-Based Combined-Cycle (RBCC) Propulsion Technology Workshop. Tutorial Session
Subject Category
Spacecraft Propulsion And Power
Accession Number
92N21536
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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