The application of airbreathing propulsion systems to winged launchers is examined. The characteristics of ramjet based, LH2 fueled, powerplants are analyzed. The main ramjet design parameters are highlighted. Options (rockets, turboengines) for the boost phase from takeoff to ramjet mode transition are described, and their potential applicability to Single Stage to Orbit (SSTO) and Two Stage to Orbit (TSTO) launcher is discussed.
Airbreathing Propulsion for Transatmospheric Flight
1990
11 pages
Report
Keine Angabe
Englisch
Jet & Gas Turbine Engines , Aircraft , Manned Spacecraft , Air breathing engines , Launch vehicle configurations , Ramjet engines , Transatmospheric vehicles , Propulsion system performance , Cost analysis , Design analysis , Engine design , Hydrogen fuels , Liquid hydrogen , Single stage to orbit vehicles , Thrust-weight ratio , Two stage turbines , Foreign technology
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