Accession Number:

AD0773433

Title:

Solid Strand Burn Rate Technique for Predicting Full-Scale Motor Performance

Descriptive Note:

Final rept. Oct 1972-Oct 1973

Corporate Author:

AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA

Personal Author(s):

Report Date:

1973-10-01

Pagination or Media Count:

41.0

Abstract:

The objective of this program was to perform and evaluate solid strand burn rate measurements on the Titan 3 propellant taken from cartons which were cast during motor manufacture. The results of this evaluation would determine if the solid strand burn rate technique would be an acceptable approach toward re-establishing the correlation between full-scale motor performance, and small ballistic test motors, and liquid strand burn rate tests. The effects of strand preparation, sample selection, burn rate variability within the carton, and particle orientation were briefly investigated. During the program, an improved monitoring system was developed and demonstrated.

Subject Categories:

  • Combustion and Ignition
  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE