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

PDF Url : AD0853475

Report Date : Mar 1969

Pagination or Media Count : 115

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.

Descriptors :   *SOLID PROPELLANT ROCKET ENGINES, COMPOSITE PROPELLANTS, DOUBLE BASE ROCKET PROPELLANTS, OSCILLOSCOPES, STABILITY

Subject Categories : Combustion and Ignition
      Solid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE