Abstract
A novel, reusable, Vertical‐Takeoff‐and‐Landing, Single‐Stage‐to‐Orbit (VTOL/SSTO) launch system concept, named HYP‐SSTO, is presented in this paper. This launch vehicle system concept uses a highly coupled, main high performance liquid oxygen/liquid hydrogen (LOX/LH2) propulsion system, that is used only for launch, with a hybrid auxiliary propulsion system which is used during final orbit insertion, major orbit maneuvering, and landing propulsive burn phases of flight. By using a hybrid propulsion system for major orbit maneuver burns and landing, this launch system concept has many advantages over conventional VTOL/SSTO concepts that use LOX/LH2 propulsion system(s) burns for all phases of flight. Because hybrid propulsion systems are relatively simple and inert by their nature, this concept has the potential to support short turnaround times between launches, be economical to develop, and be competitive in terms of overall system life‐cycle cost. This paper provides a technical description of the novel, reusable HYP‐SSTO launch system concept. Launch capability performance, as well as major design and operational system attributes, are identified and discussed.
Published Version
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