Accession Number:

AD0835639

Title:

APOLLO SERVICE PROPULSION SYSTEM INJECTOR COLD FLOW TEST

Descriptive Note:

Final rept. 15 Dec 1967-2 Feb 1968

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

• Ridings, T. L.
• Southerlan, R. E.

Report Date:

1968-07-01

Pagination or Media Count:

43.0

Abstract:

A full-scale production Apollo service propulsion system injector was modified to accommodate detailed instrumentation and visual observation capability during a series of propellant rapid expansions to high vacuum conditions to determine the venting characteristics of the injector. It had been suspected that after short burns of the engine at altitude, evaporative freezing of the residual propellants in the injector might result in clogged passages which could prevent safe restarts for extended time periods. Test results indicate that 5 min of venting between engine firing is adequate if propellant and injector temperatures are maintained above 55 degrees F.

Descriptors:

• *LIQUID ROCKET PROPELLANTS
• COLD FLOW
• CONTROLLABLE THRUST ROCKET ENGINES
• FREEZING
• FUEL INJECTORS
• ICE PREVENTION
• INSTRUMENTATION
• LIQUID ROCKET OXIDIZERS
• MANIFOLDS(ENGINES)
• MANNED SPACECRAFT
• MODEL TESTS
• MODIFICATION KITS
• PHOTOGRAPHY
• SPACE SIMULATION CHAMBERS
• SUBLIMATION
• TEMPERATURE
• TEST FACILITIES
• TEST METHODS
• VACUUM
• VENTING

Subject Categories:

• Liquid Rocket Propellants
• Manned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE