Accession Number : ADP007959

Title :   Highly Integrated Ducted Rocket Propulsion Modules for Future Hypersonic Tactical Missiles,

Corporate Author : MESSERSCHMITT-BOELKOW-BLOHM G M B H OTTOBRUNN (GERMANY F R)

Personal Author(s) : Weinreich, Herman L.

Report Date : DEC 1990

Pagination or Media Count : 13

Abstract : Integrated airbreathing propulsion systems for future hypersonic tactical missiles have been studied under funding of the German MOD. A 30 km range-Mach 5-antiradiation mission was selected for more detailed investigations. Main aspects for the missile/propulsion design are: simple design with no or minimum geometrical variability, no ejecta during boost/sustain transition, high average velocity (transition Mach number well above 3) To minimize the mass fraction of the required booster propellant an optimum, common (non ejectable) boost/sustain nozzle must be adopted; the booster pressure should be optimized to use the strength potential of the ramcombustor structure; the intake must be closed during boost to reduce drag and to avoid dangerous buzz.

Descriptors :   *ANTIRADIATION MISSILES, *ROCKET PROPULSION, *DUCTED ROCKETS, *HYPERSONIC FLIGHT, DRAG, EJECTA, MACH NUMBER, MASS, MISSIONS, NOZZLES, NUMBERS, PRESSURE, PROPELLANTS, PROPULSION SYSTEMS, STRUCTURES, TRANSITIONS, VELOCITY.

Subject Categories : Rocket Engines
      Guided Missiles

Distribution Statement : APPROVED FOR PUBLIC RELEASE