Accession Number:

AD0384237

Title:

COMBUSTION MECHANISM OF HIGH BURNING RATE SOLID PROPELLANTS.

Descriptive Note:

Quarterly technical rept. no. 3, 1 Jun-31 Aug 67,

Corporate Author:

THIOKOL CHEMICAL CORP HUNTSVILLE ALA HUNTSVILLE DIV

Personal Author(s):

Report Date:

1967-09-01

Pagination or Media Count:

63.0

Abstract:

Thiokols program to tailor the burning rate of a propellant predictably and controllably to any desired level in the range from 1 to 10 inches per second is divided into three phases Phase I - Synthesis of Burning Rate Catalysts, Phase II - Decomposition Studies and Evaluation of Catalysts and Phase III - Decomposition of Advanced Oxidizers, Fuels, and Binders. Experiments will be performed to synthesize more efficient burn rate catalysts by maximizing already determined guideline properties toward development of an ideal catalyst under Phases I and II. Following catalyst synthesis, each compound showing potential will be subjected to comprehensive decomposition studies and combustion mechanism evaluation with propellant ingredients. Thermogravimetric analyses of catalysts mixed with HC polymer show that none of the catalysts tested appear to catalyze the decomposition of HC polymer. Propellants formulated with the copper I complex, the copper II complex and the cobalt II complex of beta-ferrocenyl-beta-oxo-propionaldehyde demonstrated burning rates higher than that of similar propellant containing n-butyl-ferrocene PLASTISCAT-IVR at the 2 percent level. An analysis to relate subsurface heating to changes in ammonium perchlorate crystal structure was conducted. It was shown that if the concept of a constant surface temperature is valid and if the extrapolated value of thermal diffusivity is accurate to within 10 percent, the surface temperature of burning ammonium perchlorate is 440 or - 30 C. Author

Subject Categories:

  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE