Accession Number : ADA117395
Title : Multiple Launch Rocket System (MLRS) Fuze.
Descriptive Note : Conference paper,
Corporate Author : MILITARY ACADEMY WEST POINT NY
Personal Author(s) : Bertin,John J ; Goodyear,Richard L
PDF Url : ADA117395
Report Date : 18 Jun 1982
Pagination or Media Count : 12
Abstract : This analysis showed that pressures measured at the inlet hole to the fluidic generator are in close agreement with those given by normal shock relations. Over the external surface of the ogive, the ratio of local static pressure to stagnation pressure measured at the nose, p/p(t2) decreased as the free stream Mach numbers increased. Within this trend existed regions of expansion and compression which were a result of the ogive's geometry and the injection of the air exhausted from the fluidic generator. Theoretical models predicted reasonably well the dependence on Mach numbers of p/p(t2) as well as the relative values of p/p(t2) at different points on the ogive. Pressures measured at the entrance and exit of the region occupied by the generator permitted calculation of the mass flow rate through the fuze. This analysis verified that the key factors that should be duplicated in laboratory tests were the pressures at the generator's entrance and at the exhaust ports in the ogive; but the most significant result was the accumulation of a data base of the actual pressures to be associated with desired combinations of Mach number and altitude. Consequently, the high altitude chamber proposed to test MLRS fuzes has been incorporated into the product specification and used with confidence in the quality assurance program of the contractor.
Descriptors : *Rocket fuzes, *Air flow, Artillery rockets, Control systems, Fluidic control, Generators, Rocket noses, Ogives, Dynamic pressure, Surfaces, Ports(Openings), Altitude chambers, Wind tunnel tests
Subject Categories : Fluidics and Fluerics
Ammunition and Explosives
Distribution Statement : APPROVED FOR PUBLIC RELEASE