Accession Number : ADD012138
Title : Pulsed Integral Rocket.
Descriptive Note : Patent Application,
Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC
Personal Author(s) : Nagy,
Report Date : 21 Oct 1985
Pagination or Media Count : 13
Abstract : The prevention of over-acceleration of air-launched air-breathing missiles which are boosted by a solid fueled rocket is accomplished by replacing the solid refueled rocket with a two-section solid motor arrangement designed for a choice between simultaneous burning and sequential burning. When a host aircraft is flying are relatively low velocities, the two-section motors should be fired simultaneously to boost the ramjet of the air-breathing missile to operational velocities (mach 3 to mach 5). When the host aircraft is flying at relatively high velocities, the two-section motors should be fired sequentially to aviod over-acceleration and extend the operational range of the missile. While the ramjet and the two-section rocket motor may all be housed in the same casing, they must be separated from each other by thermal insulation and must have their own igniter which is controlled separately.
Descriptors : *PATENT APPLICATIONS, *INTEGRAL ROCKET RAMJETS, *SOLID PROPELLANT ROCKET ENGINES, DUAL MODE, GUIDED MISSILES, AIR LAUNCHED, PULSES
Subject Categories : Air- and Space-launched Guided Missiles
Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE