Nitramine Propellant Research.
Abstract
An extended model of the combustion of nitramine propellants is derived to account for multiple particle sizes, mixed oxidizers and active binders. Burning rates of various nitramine propellants are reported over the pressure range from 500 psi to 50,000 psi and show effects of systematic ingredient variations. A high pressure window bomb is utilized to observe the combustion process of these propellants by cinematography to a pressure of 6000 psi. The propellants are also extinguished by rapid decompression, and their surface and subsurface structures are studied with the aid of a scanning electron microscope. A computer program is developed to incorporate the model extensions and is applied to explain the experimental data. Parametric studies are performed with the model to formulate methods to achieve desirable burning rate characteristics in nitramine propellants. It is concluded that the model successfully describes the combustion of nitramine propellants and is a useful tool to evaluate combustion tailoring in association with propellant development efforts. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 15, 1976
- Accession Number
- ADA033034
Entities
People
- L. D. Strand
- N. S. Cohen
Organizations
- Jet Propulsion Laboratory