Accession Number : AD0853475
Title : Experimental Studies on the Oscillatory Combustion of Solid Propellants.
Descriptive Note : Research rept.
Corporate Author : NAVAL WEAPONS CENTER CHINA LAKE CA
Report Date : MAR 1969
Pagination or Media Count : 114
Abstract : This report describes the results of testing a series of composite and double-base propellants in a T-burner facility. The investigation reveals the unstable combustion behavior that is susceptible of excitation under acoustic pressure-coupled conditions. The degree of instability is quantitatively described in terms of the response function, which is a well-defined characteristic of the propellant. The effect of pressure and frequency has been systematically investigated for the frequency range of 500-10,000 cps and for pressures up to nearly 3,000 psia. Such an extended coverage has permitted the determination of a very general pattern of behavior, including the maximum instability conditions, the isoresponse function contours, and the neutral boundary separating the unstable and stable combustion regimes in the 1.5-inch T-burner. (Author)
Descriptors : (*SOLID PROPELLANT ROCKET ENGINES, SOLID ROCKET PROPELLANTS), (*SOLID ROCKET PROPELLANTS, COMBUSTION), STABILITY, COMPOSITE PROPELLANTS, DOUBLE BASE ROCKET PROPELLANTS, BURNING RATE, COMBUSTION PRODUCTS, INTERACTIONS, ACOUSTICS, SOLID ROCKET PROPELLANT BINDERS, OSCILLATRON, FUEL ADDITIVES.
Subject Categories : Combustion and Ignition
Solid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE