Accession Number : ADA623831


Title :   Refinement of Propellant Strand Burning Method to Suit Aluminised Composite Rocket Propellant


Descriptive Note : Technical note


Corporate Author : DEFENCE SCIENCE AND TECHNOLOGY ORGANISATION EDINBURGH (AUSTRALIA) WEAPONS SYSTEMS DIV


Personal Author(s) : Smith, Paul C ; Hale, Garry ; Pietrobon, Raoul A


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a623831.pdf


Report Date : Dec 2014


Pagination or Media Count : 37


Abstract : An epoxy coating was trialled as an inhibitor for composite rocket propellant strands burned in a Crawford-style bomb. The epoxy coating performed at least as well as the traditional paint coating and produced a virtually identical burn rate law. Burn rate results for epoxy coated strands were insensitive to strand preparation technique such as bevelling of the strand and de-dusting, thus demonstrating a robust inhibitor system. Acceptable robustness of the epoxy coating was demonstrated when applied to aluminised composite rocket propellant with no spurious results recorded. Accuracy and precision of results for all four batches of aluminised composite propellant were acceptable and at least as precise as historical results obtained with non-aluminised propellant inhibited with paint. A couple of methods for reducing effort while maintaining sufficient accuracy of burn rate data were demonstrated. A single coating of epoxy as opposed to two provided sufficient inhibition and could almost halve combined preparation and coating time. Burning as little as 6 strands, one at each pressure across the range of interest, can provide a sufficiently accurate burn rate law during the early stages of propellant development.


Descriptors :   *COMPOSITE PROPELLANTS , *EPOXY COATINGS , *INHIBITION , *STRANDS , ACCURACY , BURNING RATE , COMBUSTION , HYDROXY TERMINATED POLYBUTADIENE , INHIBITORS , PRECISION


Subject Categories : Physical Chemistry
      Coatings, Colorants and Finishes
      Rocket Propellants


Distribution Statement : APPROVED FOR PUBLIC RELEASE