Initiation Mechanisms of Solid Rocket Propellant Detonation
Abstract
This study involves the development of a computerized model with which to identify the causes of solid propellant rocket motor detonations during firing. The model treats the problem of suddenly exposing propellant cracks (or flaws or debonds) to chamber gases at higher pressures and temperatures than gases initially in the crack. Simplified analyses are used to compute the transient pressures produced by the gas flows, burning and crack deformations (positive and negative). These predictions are made in terms of a variety of parameters associated with the crack, chamber, motor case and propellant. Two phenomena appear important in producing pronounced pressure rises. These are: (1) partial or complete crack collapse due to stress waves reflected from the motor case and (2) rapid acceleration of the burning during the final stages of crack collapse. The latter is due to the relatively large quantities of heat acquired by the propellant during the relatively long periods of gas filling. Quantification of these effects remains to be accomplished.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 15, 1976
- Accession Number
- ADA031273
Entities
People
- A. H. Wiedermann
- A. N. Takata
Organizations
- IIT Research Institute