Accession Number : ADD009736

Title :   Twostage Hypersonic Ramjet.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : Leingang,John L

Report Date : 13 Jul 1982

Pagination or Media Count : 10

Abstract : A two-stage ramjet engine including an aft end, ejectable, boost-stage-combustor/nozzle assembly for initially accelerating from low-to-mid-supersonic launching speeds to high supersonic speeds, and mounted in a tandem arrangement immediately aft of a separate, forward end-cruise stage-combustor/nozzle assembly positioned directly behind an inlet-diffuser section for subsequently further accelerating from high supersonic to hypersonic speeds after ejecting the entire boost stage.

Descriptors :   *Patents, *Ramjet engines, *Hypersonic velocity, Booster rocket engines, Integral rocket ramjets, Second stage engines, Ramjet engine nozzles, Combustors, Ejection, Separation, Guided missiles, Air breathing

Subject Categories : Guided Missiles
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE