Accession Number : AD0832704
Title : MSTS TEST REPORT, RUN 95-417-A5-S1, TEST 6.
Corporate Author : GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
Report Date : 1959
Pagination or Media Count : 38
Abstract : This test was performed at low propellant flow rates. The fuel flow rate was 2200 GPM and LO2 was 3500 GPM. Propellant loading was complete 20.06 minutes after fuel load start. LO2 engine tank full was indicated at 19.0 minutes. Helium load start was delayed until three minutes after fuel load start while LN2 flow was initiated at fuel load start. Bottle temperatures thirteen minutes after fuel load start were -298 DGF and -299 DGF, respectively, for the upper and lower temperatures. The characteristic droop in the booster bottle pressure occurred at 2880 PSIG just prior to the PS-80 cutoff point. The pressure recovered to 3000 PSIG within 2.5 minutes. (Author)
Descriptors : (*LIQUID PROPELLANT ROCKET ENGINES, CAPTIVE TESTS), PROPELLANT TRANSFER, CONTROL SYSTEMS, HEAT EXCHANGERS, PRESSURIZATION, GROUND SUPPORT EQUIPMENT, INSTRUMENTATION, FAILURE, SURFACE TO SURFACE MISSILES, PROPELLANT CONTROL.
Subject Categories : Surface-launched Guided Missiles
Liquid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE