Multiple Launch Rocket System (MLRS) Fuze.
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 18, 1982
- Accession Number
- ADA117395
Entities
People
- John J. Bertin
- Richard L. Goodyear
Organizations
- United States Military Academy