Solid Propellant Combustion Mechanism Research 1975-1980.
Abstract
The multi-task research conducted during the five years of the contract was aimed at furthering the scientific understanding of propellant combustion processes. The low pressure deflagrations of nitramines were interpreted by a physical model that accounts for the interactions among the condensed phase, surface, and near field flame zones. The model demonstrated the importance of considering both primary and secondary gas phase processes. Chamber flow interactions with propellants having extended flame zones elucidated contributions to erosive burning and sustained acoustic oscillations. The analysis points to the existence of an additional source of acoustic energy produced by couplings with heat addition from residual reactions in the chamber gases. Droplet burning was analyzed in terms of a reduced boundary condition at the surface and the quasi-steady heat feedback assumption. A formalism is offered for experimentally evaluating the boundary conditions for nonsteady conditions. Direct measurements of solid propellant acoustic admittance were made using laser doppler velocimetry coupled with an optical technique for tracking the burning surface. This report contains abstracts of the detailed publications on each topic. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1980
- Accession Number
- ADA094618
Entities
People
- Josette Bellan
- Leonard H. Caveny
- Martin Summerfield
- Moshe Benreuven
Organizations
- Princeton University