Accession Number : AD0738615

Title :   Hybridverbrennung in Beschleunigungs-Staustrahl-triebwerken (Hybrid Combustion in Acceleration Ram-Rockets),

Corporate Author : DEUTSCHE FORSCHUNGS- UND VERSUCHSANSTALT FUER LUFT- UND RAUMFAHRT E V BRUNSWICK (WEST GERMANY)

Personal Author(s) : Lutz,Otto ; Riester,Egbert ; Schadow,Klaus

Report Date : 1970

Pagination or Media Count : 18

Abstract : For a definite mission of a missile, advantages of a ram rocket drive over than of a solid propellant rocket may be found. The investigation of this problem is the task of the report. The initial accelerations by a rocket booster are also taken into account. The gas generator of the ram rocket is a rocket combustion chamber including a boron loaded solid propellant in which a liquid oxydizer is injected (hybrid reaction). The very rich exhaust gases leaving the generator are used as fuel for the ramjet combustor. After optimizing the system there is a gain in payload of 24 percent for a constant speed ram rocket compared with a solid propellant rocket. If in addition the ram rocket is used to accelerate the missile, the gain in payload will increase to 43 per cent. (Author)

Descriptors :   (*RAMJET ENGINES, *HYBRID ROCKET PROPELLANTS), (*HYBRID ROCKET ENGINES, RAMJET ENGINES), GAS GENERATING SYSTEMS, BORON, LIQUID ROCKET OXIDIZERS, OXYGEN, THRUST, SPECIFIC IMPULSE, WEST GERMANY

Subject Categories : Jet and Gas Turbine Engines
      Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE