THE DEVELOPMENT AND EVALUATION OF A HYDROCARBON BINDER FOR HIGH ENERGY SOLID PROPELLANTS.
Abstract
The investigation and characterization of a saturated hydrocarbon binder for use in solid rocket propellant were continued. The molecular weight and functionality distributions were determined for the saturated hydrocarbon perpolymer and found to be independent of each other. Analytical data were obtained for saturated and unsaturated prepolymers with hydroxy or carboxy terminal groups. While NH4C104 and Al were compatible with the isocyanate curing agents, many plasticizers were not. Of the plasticizers, the hydrocarbon oils were most compatible. The difficulties with the plasticizers were the presence of impurities and an effect (not the result of impurities) on the cure of binders. The pressure exponent for burning rate was 0.7 for these propellants (88 wt% solids). The relative viscosity of NH4C104-Oronite 6 slurries was at a minimum for an oxidizer blend of 35.80%, 32.10% and 32.10% by weight of particles averaging 6, 148, and 419 microns, respectively. This blend was used to prepare a high solids loaded propellant with 79% NH4ClO4, 12% aluminum, and 9% Telagen S binder at 60-lb scale. Small motors of this propellant, which had a burning rate-pressure exponent of about 0.8, were fired. The specific impulse at standard conditions for large motors was 250 lbf-sec/lbm. The compatibility of the prepolymer and model compounds with beryllium. LMH-1 and LMH-2 was determined.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1967
- Accession Number
- AD0382431
Entities
People
- Anthony J. Di Milo
- Duane E. Johnson
- Rodney H. Quacchia
Organizations
- Aerojet Rocketdyne Holdings