Accession Number : AD0829264

Title :   1-3A PROPELLANT UTILIZATION SYSTEM TESTS NO. 1 THROUGH NO. 6.

Descriptive Note : Test rept.

Corporate Author : GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

Report Date : 08 MAY 1958

Pagination or Media Count : 51

Abstract : The propellant utilization test program had the following objectives: Determine the ability of the servo controller to hold the Propellant Utilization Valve in the proper position during engine firing; Determine the dynamic response of the Propellant Utilization Valve under engine firing conditions; Determine the interaction of the Propellant Utilization Valve and the Sustainer Head Suppression Valve; Determine the effects of pressurization surges in the propellant tanks on the Propellant Utilization System; and Determine the ability of the Propellant Utilization System to control the residual propellant ratio on a long duration engine firing using a shrouded valve with plus or minus 15% mixture ratio capabilities. (Author)

Descriptors :   *SERVOMECHANISMS), (*SURFACE TO SURFACE MISSILES, LIQUID ROCKET PROPELLANTS), (*PROPELLANT CONTROL, HYDRAULIC VALVES, LIQUID PROPELLANT ROCKET ENGINES, CAPTIVE TESTS, SUSTAINER ENGINES, PRESSURIZATION, PROPELLANT TANKS, CONTROL SYSTEMS, MANOMETERS, FAILURE, LIQUID LEVEL CONTROL.

Subject Categories : Surface-launched Guided Missiles
      Liquid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE