Accession Number : AD0379500

Title :   MAIN TANK INJECTION FOR PACKAGED LIQUID MISSILES PHASE I REPORT. VOLUME II. SYSTEMS FEASIBILITY TESTING.

Descriptive Note : Rept. for 21 Feb 66-10 Feb 67,

Corporate Author : MARTIN CO DENVER COLO

Personal Author(s) : Howell,J. Carney ; Fester,Dale A. ; Bingham,Paul E.

Report Date : MAR 1967

Pagination or Media Count : 137

Abstract : A two-phase program is being conducted to establish feasibility and demonstrate practicality of using main tank injection (MTI) for pressurization of packaged liquid missile (PLM) propellant tanks. The propellants for this short-range, air-to-ground weapon system are MHF-5 fuel and Compound A oxidizer. An analysis of various simplified MTI pressure control techniques is also included. Two half-scale, screen-type propellant retention devices were designed, fabricated, and tested under the projected vibration/slosh and acceleration environments of PLM. These devices, required to ensure gas-free propellant expulsion, were the propellant reservoir and lined dome segment configurations previously selected during systems analysis. The environmental testing, performed with propellant simulants, demonstrated that both configurations could retain propellant without leakage at acceleration and vibration levels in excess of those required for PLM. Based on cost projections and versatility of the devices for PLM, the propellant reservoir was selected over the lined dome segment for the full-scale Phase II demonstration tests. The feasibility of employing MTI pressurization for MHF-5 fuel and Compound A oxidizer was investigated with a specially constructed test system.

Descriptors :   (*STORABLE ROCKET PROPELLANTS, *PROPELLANT TANKS), (*PRESSURE VESSELS, PROPELLANT TANKS), (*LIQUID PROPELLANT ROCKET ENGINES, PRESSURE VESSELS), PRESSURIZATION, PHYSICAL PROPERTIES, VIBRATION, SLOSHING, ACCELERATION, LIQUID ROCKET PROPELLANTS, INJECTION, HYPERGOLIC ROCKET PROPELLANTS, FUELS, OXIDIZERS, FEASIBILITY STUDIES, SIMULATION, AIR TO SURFACE MISSILES, FUEL SYSTEMS(U) HYDRAZINE, NITRIC ACID

Subject Categories : Liquid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE