Carbides for Solid Propellant Nozzle Systems
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1968
- Accession Number
- AD0843084
Entities
People
- D. P. Laverty
- F. T. Lally