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This paper presents a Mach 23 staged two stage-to-orbit launch vehicle candidate. Previously, two stage-to-orbit launch vehicles considered subsonic, supersonic and hypersonic staging options. Studies have shown that performance optimized two stage launch vehicles have first stage performance capabilities that vary widely depending on the propulsion and type of fuel used in the first and second stage. A Mach 23 performance capable first stage could fly around the world and return from the takeoff site using a boost-glide-skip trajectory profile. A Mach 23 staged first stage would be significantly less difficult to develop compared to a single stage-to-orbit launch vehicle. The usable propellant fraction for the Mach 23 rocket-based combined cycle engine powered first stage presented in this paper is 0.614 and the payload fraction is 0.033.

This paper presents the design evolution of a military transatmospheric aerospace plane, considerations of options, and the formulation of a single transatmospheric aerospace plane. The design concept started with requirements, an operational concept, a set of design choices, a technology base, and a close look at the factors that determine orbital closure performance requirements. Several unique factors are considered in the design formulation. The baseline mission is a once around and return to the base from which the takeoff occurred. The flight profile to minimize energy requirements is a boost-glide-skip-glide trajectory. The configuration is based on recent work at the University of Maryland on waverider optization across a range of Mach numbers. Engine selection is based on both specific impulse and engine thrust to weight for a rocket-based combined cycle engine. The Aerojet “strut rocket” combined-cycle engine is baselined.