Cryogenic Size Reduction of Solid Propellant
Abstract
A growing need exists to develop improved methods for the disposal and/or recovery of solid rocket propellants. Laboratory, bench scale, and prototype tests were performed to develop the dry washout concept for size reduction and removal of solid propellants using cryogenic media. Three propellant types were investigated: hazard class 1.1 composite modified double base (CMDB), hazard class 1.1. cross linked double base (XLDB), and hazard class 1.3 hydroxl terminated polybutadiene (HTPB). No propellant initiations were detected. The laboratory tests were established that essentially no change in the sensitivity of the test propellants occurs between ambient and cryogenic temperatures. Impact, friction, low level shock and electrostatic discharge sensitivity tests were conducted. Over 2000 trials were conducted. The bench scale tests demonstrated the safety of liquid nitrogen washout and established parameter ranges for effective propellant removal. Removal rates of greater than 60 lb/hr were achieved for all propellant types. The prototype tests demonstrated cryogenic washout of several reduced scale motors in a semiautomated process. Two motors were processed, one containing 40 lbs of XLDB propellant, the other containing 60 lbs of HTPB propellant. Propellant removal rates ranged from 8.3 lb/hr to 156 lb/hr with liquid nitrogen flow of less than 4 gpm.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1992
- Accession Number
- ADA356182
Entities
People
- Michael H. Spritzer
- Will P. Creedon