RESPONSE OF A BURNING SOLID PROPELLANT TO PRESSURE WAVES OF FINITE AMPLITUDE.
Abstract
Shock-tube techniques were utilized to determine the response of a burning solid propellant surface to pressure perturbations of small, but finite amplitudes. This method of obtaining propellant responses is described with emphasis upon the techniques which were developed to remove undesirable temperature gradients. Other experimental techniques utilized to obtain high-frequency response pressure measurements under reproducible pressure, flow, and temperature conditions are described. The propellants include those (both aluminized and nonaluminized) with a wide range of pressure exponents as well as absolute burning rate. All of these experiments were conducted at about 400 psia ambient pressure. A discussion of the treatment of the experimental data to obtain Fourier transforms and the propellant response as a function of frequency is presented, with particular emphasis upon the significance and reproducibility of the data. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1965
- Accession Number
- AD0624944
Entities
People
- A. L. Huebner
- T. A. Coultas
Organizations
- Rocketdyne