Combustion Mechanism of Composite Propellant During Depressurization.
Abstract
The investigations of the extinguishing by depressurization resulted in a period of low gas temperature after the stop of the steady state flame and before the redevelopment of a second flame. By comparison of the depressurization rate and the time intervals for a 50% pressure decay, the continued gasification of the propellant could be measured. Surface structure analysis by Scanning Electron Microscope enabled the determination of the oxidizer/binder area ration on the extinguished surface, furthermore the burning of local spots to about 0.1 mm propellant thickness during the phase of extinguishing. The measurements included 16 different propellant mixtures at pressure levels of 25 bar, 45 bar, and 95 bar.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1973
- Accession Number
- AD0769445
Entities
People
- Horst Selzer