Integrated airbreathing propulsion systems for future hypersonic tactical missiles were 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, and 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; and the intake must be closed during boost to reudce drag and to avoid dangerous buzz. A special two position intake concept permits intake closure during boost, strating of the internal shock system, and cruise flight with minimum external drag and high pressure recovery at transition Mach numbers. Based on promising test results of the DLR/Cologne obtained with a comparable intake model a new family of intakes with different internal compression ratio and lip-bluntness was designed. A boron loaded ducted rocket with subsonic self throttling gas generator flow was selected for cruise flight propulsion due to its simple design, excellent combustion stability, and the high level of existing experience. Even at combustor temperatures above the condensation temperature of boron-oxide, the volumetric impulse of boron loaded propellants remains attractive. The ducted rocket gas generator can be integrated within the missile freebody which also contains seeker, warhead, electric compartment, and missile controls. The missile flight control system is based on jet reaction using minirockets during boost and high pressure intake tap air during cruise. C/C material was adopted for the structural design. The superiority of the ducted rocket powered medium range antiradiation missile was demonstrated by comparison with a rocket powered missile having the same diameter and payload. For short range (6 to 12 km) low level missions the solid fuel ramjet with integral boost is an attractive propulsion concept.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Structures for hypersonic airbreathing tactical missiles

    Caywood, W. C. / Rivello, R. M. | NTRS | 1978



    Optimal Mid-Course Guidance of Variable Flow Ducted Rocket Missiles

    Kuroda, T. / Mihara, S. / Matsuda, H. et al. | British Library Conference Proceedings | 1998


    Optimal mid-course guidance of variable flow ducted rocket missiles

    Kuroda, Takeshi / Mihara, Shoichiro / Matsuda, Hiroaki et al. | AIAA | 1998


    Optimal Mid-Course Guidance of Variable Flow Ducted Rocket Missiles

    Kuroda, T. / Mihara, S. / Matsuda, H. et al. | British Library Conference Proceedings | 1998