A rapid method for optimization of the rocket propulsion system for single-stage-to-orbit vehicles
Charles H. Eldred, Sabina V. Gordon, Langley Research Center, United States. National Aeronautics and Space Administration
National Aeronautics and Space Administration, 1976 - Technology & Engineering - 31 pages
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angle of attack ascent mass ratio ascent propellant mass ascent propellant requirements ascent trajectory baseline vehicle calibration vehicle Component category conventional bell nozzles dynamic pressure engine system mass Entry mass equation fixed expansion ratio flight performance horizontal landing in-flight constraints Is,vac Langley Research Center lift-off thrust-to-weight ratio linearized sizing program liquid hydrogen liquid oxygen LOX-LH2 main engine mass or minimum mass plus categories method minimum dry mass minimum gross mass mixture ratio mp,a mp,r mp,sd mp,sv mpay nozzle expansion ratio ODIN optimum orbital maneuvering system payload percent for vehicle point-design vehicle propellant mass ratio propulsion system characteristics propulsion system mass propulsion system variations ratio and lift-off RCS entry propellants RCS propellant reaction control system rocket engine rocket propulsion systems shown in figure single-stage-to-orbit space shuttle specific impulse SSME system mass coefficient tankage systems mass trajectory analysis trajectory optimization trajectory performance vehicle system vertical take-off