Combustion Mechanisms of Wide Distribution Propellants
Abstract
The objective of this research is to describe the effects of oxidizer particle size distribution on the burning rate of solid propellants used in rocket motors. Current models over predict the burning rate of wide distribution (wide distribution denotes two oxidizer modes that have extreme differences in mean diameter) formulations by 40 to 200 percent indicating combustion mechanisms unique to this type of propellant. Four sets of AP/HTPB propellants were formulated to control the physical and chemical heterogenities characteristic of the propellant surface using 400 and 20 microns oxidizer particles. The propellants were tested at pressure levels from 0 to 2000 psig. An optical, distance measurement technique was developed and used to measure the local, non-steady surface deflagration of the propellant burning surface. The method uses a laser beam, synchronous detection, and closed-loop tracking to locate the surface in the hostile combustion environment. An acoustic emission technique determined average burning rates. Combustion phenomena were also accessed using high-speed photography and scanning electron microscopy. Keywords: Particle size distribution, Burning rate, Solid propellants, Rocket motors, Combustion mechanisms, AP/HTPB propellants, Laser diagnostics, Acoustic emissions, Scanning electron.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1988
- Accession Number
- ADA199761
Entities
People
- Robert A. Fredrick Jr.
Organizations
- Purdue Research Foundation