Accession Number : AD0710854

Title :   COMBUSTION INSTABILITY AND THE DESIGN OF SOLID PROPELLANT ROCKET MOTORS,

Corporate Author : DEFENCE RESEARCH ESTABLISHMENT VALCARTIER QUEBEC

Personal Author(s) : Roberts,A. K. ; Brownlee,W. G. ; Jackson,F.

Report Date : JAN 1970

Pagination or Media Count : 7

Abstract : The design of a solid propellant rocket motor is generally constrained to meet specific ballistic requirements which are, in turn, imposed by vehicle trajectory considerations. Since the abnormalities associated with combustion instability are characterized by rapid and often severe fluctuations of motor pressure and thrust, unstable operation cannot usually be tolerated in flight vehicles. Consequently, care must be taken during the development phase to design towards stable operation and to dynamically test prototype motors. The nonlinear longitudinal mode of combustion instability is often encountered in motors containing aluminized propellants and has had an important influence on a number of Canadian development programs. The present paper is based on extensive experimental studies of this phenomenon carried out at the Defence Research Establishment Valcartier. This work has yielded a good phenomenological description of the instability, design criteria and guidelines and evaluation techniques which can be of considerable utility to the motor designer. These are described with the aid of typical data. (Author)

Descriptors :   (*SOLID PROPELLANT ROCKET ENGINES, COMBUSTION), STABILITY, INTERIOR BALLISTICS, BURNING RATE, SOLID ROCKET PROPELLANTS, DESIGN, ROCKET NOZZLES, SOLID ROCKET PROPELLANT BINDERS, CONFIGURATION, CANADA

Subject Categories : Combustion and Ignition
      Solid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE