Accession Number:

AD0738615

Title:

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

Descriptive Note:

Corporate Author:

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

Personal Author(s):

Report Date:

1970-01-01

Pagination or Media Count:

18.0

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

Subject Categories:

  • Jet and Gas Turbine Engines
  • Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE