Accession Number:

AD0843084

Title:

Carbides for Solid Propellant Nozzle Systems

Descriptive Note:

Final technical rept. 1 Oct 1967-30 Jun 1968

Corporate Author:

TRW EQUIPMENT LABS CLEVELAND OH MATERIALS TECHNOLOGY DEPT

Personal Author(s):

• Lally, F. T.
• Laverty, D. P.

Report Date:

1968-10-01

Pagination or Media Count:

45.0

Abstract:

The magnitude of reactivity between Al2O3 and carbide composite rocket nozzle throat materials was assessed by means of laboratory tests. A secondary objective of the program was to establish the validity of the laboratory tests in evaluating material performance. The program included a plasma jet test that measured mechanical and chemical erosion and a static reactivity test to separate the purely chemical effects. A prediction of the performance of the carbide composites in a test firing was made, based on the laboratory tests.

Descriptors:

• *NOZZLE INSERTS
• *NOZZLE THROATS
• PERFORMANCE(ENGINEERING)
• HIGH TEMPERATURE
• TEST METHODS
• CARBIDES
• EROSION
• MELTING
• SOLID PROPELLANT ROCKET ENGINES
• THERMAL STRESSES
• PLASMA JETS
• ALUMINATES
• COMPOSITE PROPELLANTS
• METALATION
• NONDESTRUCTIVE TESTING
• DEGRADATION

Subject Categories:

• Solid Propellant Rocket Engines
• Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE