Initiation Mechanisms of Solid Rocket Propellant Detonation
Abstract
The purpose of this study is to identify mechanisms responsible for several accidental detonation of high-energy solid rocket propellant motors. During the past year a computer model was developed to predict the amount of foam or melt generated in cracks following sudden exposure of the crack to a cavity containing higher temperature/pressure gases than exists within the crack. In addition an experimental design was developed to study deflagration to detonation transitions (DDT). Analytical predictions suggest that DDT can occur as a consequence of burning propellant cracks provided molten propellant is generated within the burning propellant cracks and the cracks are subjected to sufficiently high amplitude stress waves. The stronger the stress waves are, the less the amount of melt needed for DDT. DDT can be initiated by single burning cracks in close proximity to the motor case, or by multiple burning cracks which are similarly oriented by respect to each other and closely spaced.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1979
- Accession Number
- ADA079986
Entities
People
- A. N. Takata
Organizations
- IIT Research Institute