Accession Number : AD0762841

Title :   Combustion Instability Study of Solid Propellants.

Descriptive Note : Final rept. Sep 71-Mar 73,

Corporate Author : UNITED TECHNOLOGY CENTER SUNNYVALE CALIF

Personal Author(s) : Brown,Robert S. ; Erickson,James E. ; Babcock,Wayne R.

Report Date : JUN 1973

Pagination or Media Count : 44

Abstract : The rotating valve method of measuring the combustion response of solid propellants to small amplitude pressure oscillations were evaluated. The method is based on producing pressure oscillations in a small rocket motor by varying the area of a secondary exhaust nozzle in a periodic manner. This is accomplished by using a rotating value as the secondary orifice. The valve apparatus operates concurrently with a primary nozzle which controls the steady-state pressure. The frequency of the oscillations is determined by the rotational speed of the valve. A theoretical analysis was conducted to relate the combustion response function to measurable ballistic properties of the combustion chamber. (Modified author abstract)

Descriptors :   (*SOLID ROCKET PROPELLANTS, COMBUSTION), STABILITY, PRESSURE, ROCKET NOZZLES, VARIABLE AREA NOZZLES, NOZZLE AREA RATIO, FLOW FIELDS, OSCILLATION, INTERIOR BALLISTICS, COLD FLOW

Subject Categories : Combustion and Ignition
      Solid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE