Accession Number:

ADA050333

Title:

A. An Analytical and Experimental Study of the Erosive Burning of Composite Propellants. B. Modeling of Single Particle Aluminum Combustion

Descriptive Note:

Final rept. 1 Oct 1975-30 Sep 1977

Corporate Author:

ATLANTIC RESEARCH CORP ALEXANDRIA VA COMBUSTION AND PHYSICAL SCIENCE DEPT

Personal Author(s):

Report Date:

1977-11-01

Pagination or Media Count:

142.0

Abstract:

Augmentation of solid propellant burning rate often occurs in the presence of strong product gas flow across the burning surface this phenomenon is referred to as erosive burning. Increasing use of motors with low port-to- throat area ratios including nozzleless motors is leading to increased occurrence and severity of erosive burning. A first generation model based upon bending of columnar diffusion flames by a crossflow, permitting prediction of the effect of high-velocity crossflow on the burning rate of a composite propellant given only the zero-crossflow burning rate characteristics, is briefly summarized and compared with data. A second generation model still under development which does not require even zero-crossflow burning rate data, using only composition and particle size as input, is outlined. In addition, a test device permitting extensive characterization of burning rate-pressure- crossflow velocity relationships for various propellants with direct continuous measurement of instantaneous burning rate by high-speed chematography is described, and results of a series of tests with seven propellants are presented. A model of aluminum particle combustion in CO2 which incorporates measured kinetic data for the gas phase reaction of aluminum with CO2 rather than assuming a flame-sheet infinite gas-phase kinetics as in past models has been developed, programmed and used to parametrically study the effect of various parameters on particle burning rate and burn-time. This model treats aluminum oxide condensation as occurring in an infinitesimally thin shell whose location is determined by specification of a condensation temperature.

Subject Categories:

  • Solid Propellant Rocket Engines
  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE