AN EXPERIMENTAL INVESTIGATION OF POSSIBLE ALUMINUM ADDITIVE CONTRIBUTIONS TO UNSTABLE COMBUSTION IN SOLID ROCKET PROPELLANTS
Abstract
Composite - double base rocket propellant slabs which contained different concentrations and particle sizes of aluminum were burned in a transparent-walled chamber. The chamber was exhausted to the atmosphere. The slabs were ignited in cigarette fashion and burned under ambient nitrogen pressures of 200-800 psi. Experimental runs were made under steady flow conditions and under oscillating conditions with a siren rotating over the exhaust part. Motion pictures were taken of the burning process at high framing rates. Data on droplet burning and concentrations in various regions above the propellant surfaces were obtained from individual frames of the film.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1962
- Accession Number
- AD0282519
Entities
People
- Leland A. Watermeier
- Samuel P. Pfaff
- William P. Aungst
Organizations
- Ballistic Research Laboratory