Accession Number : AD0728177

Title :   Depressurization Extinguishment for Various Starting Pressures and Solid Propellant Types,

Corporate Author : DEUTSCHE FORSCHUNGS- UND VERSUCHSANSTALT FUER LUFT- UND RAUMFAHRT E V TRAUEN (WEST GERMANY)

Personal Author(s) : Steinz,J. A. ; Selzer,H.

Report Date : 1971

Pagination or Media Count : 9

Abstract : A detailed experimental program was conducted to support an advanced transient flame model for the depressurization extinguishment of composite propellants. The pressure was varied from 20 atm to 90 atm and the initial depressurization rate from 1000 atm/s to 60.000 atm/s. Generally, the flame ceases within 0,4 ms to 2 ms after initiating the depressurization and recovers for a second flame with a duration up to 150 ms. The relaxation time of the surface and the pyrolysis of the solid material play an important role for the continuation of the combustion. (Author)

Descriptors :   (*COMPOSITE PROPELLANTS, *QUENCHING(INHIBITION)), MODELS(SIMULATIONS), SOLID ROCKET PROPELLANTS, SOLID ROCKET PROPELLANT BINDERS, COMBUSTION, PRESSURE, PYROLYSIS, AMMONIUM PERCHLORATE, WEST GERMANY

Subject Categories : Combustion and Ignition
      Solid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE