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
Distribution Statement : APPROVED FOR PUBLIC RELEASE