Previous studies have shown that Single‐State‐to‐Orbit (SSTO) vehicle propellant can be reduced by Magnets‐Hydro‐Dynamic (MHD) processes that minimize airbreathing propulsion losses and propellant consumption during atmospheric flight. Similarly additional reduction in SSTO propellant is enabled by Inertial Electrostatic Confinement (IEC) fusion, whose more energetic reactions reduce rocket propellant needs. MHD airbreathing propulsion during an SSTO vehicle’s initial atmospheric flight phase and IEC fusion propulsion during its final exo‐atmospheric flight phase is therefore being explored. Accomplished work is not yet sufficient for claiming such a vehicle’s feasibility. But takeoff and propellant mass for an MHD airbreathing and IEC fusion vehicle could be as much as 25 and 40 percent less than one with ordinary airbreathing and IEC fusion; and as much as 50 and 70 percent less than SSTO takeoff and propellant mass with MHD airbreathing and chemical rocket propulsion. Thus this unusual combined cycle engine shows great promise for performance gains beyond contemporary combined‐cycle airbreathing engines.
Combining MHD Airbreathing and Fusion Rocket Propulsion for Earth‐to‐Orbit Flight
SPACE TECHNOLOGY AND APPLICATIONS INT.FORUM-STAIF 2005: Conf.Thermophys in Micrograv;Conf Comm/Civil Next Gen.Space Transp; 22nd Symp Space Nucl.Powr Propuls.;Conf.Human/Robotic Techn.Nat'l Vision Space Expl.; 3rd Symp Space Colon.; 2nd Symp.New Frontiers ; 2005 ; Albuquerque, New Mexico (USA)
AIP Conference Proceedings ; 746 , 1 ; 1339-1344
06.02.2005
6 pages
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Combining MHD Airbreathing and Fusion Rocket Propulsion for Earth-to-Orbit Flight
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