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