Combustion Tailoring Criteria for Solid Propellants.
Abstract
The objective of this research program is to develop an analytical model describing the steady-state combustion of solid propellants. The model will be developed and implemented from experimental data acquired from a dual experimental program. Tests with small samples of propellants will provide experimental data for modeling the propellant combustion process for different ingredient variations, e.g., oxidizer size, concentration, and metals. Additional tests in apparatus simulating the environment of a rocket motor will provide experimental data showing the effect of rocket motor environment upon the combustion process. During Phase 4, analytical work was directed towards modeling the gaseous reaction zones above the surface of an ammonium perchlorate oxidized propellant. Experimental work was directed towards testing a series of propellants containing four different oxidizers.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1968
- Accession Number
- AD0393555
Entities
People
- Merrill W. Beckstead
- Ronald L. Derr
Organizations
- Lockheed Propulsion Company