Investigation of aluminum agglomeration in AP/HTPB composite propellants

J. C. Mullen, M. Q. Brewster

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Aluminum flame conditions, burning surface structure, and surface regression rate of composite propellant laminates of aluminum powder, fine and coarse ammonium perchlorate (AP), and hydroxyl-terminated polybutadiene (HTPB) are experimentally investigated. An aluminum matrix consisting of 15 μm Al powder mixed with fine-AP/HTPB (76:24) is sandwiched between two AP slabs. The Al matrix, or fuel, thickness ranges from 0.5 mm to 1.2 mm. The laminate sandwiches are burned in a combustion chamber with a nitrogen shroud at pressures of approximately 4 atm and 21 atm. Observation of aluminum agglomerates including separation from the burning propellant surface is conducted using a high-speed, digital video camera. Once separated from the surface, the burning agglomerates suggest the location and structure of the stoichiometric flame. A backlight is used to provide clear definition of the propellant surface profile. Preliminary results indicate a merged (premixed) flame at low pressures transitioning to a split (diffusion) flame at higher pressures.

Original languageEnglish (US)
Title of host publicationCollection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
Pages3372-3377
Number of pages6
ISBN (Print)1563478072, 9781563478079
DOIs
StatePublished - Jan 1 2006
Event44th AIAA Aerospace Sciences Meeting 2006 - Reno, NV, United States
Duration: Jan 9 2006Jan 12 2006

Publication series

NameCollection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
Volume5

Other

Other44th AIAA Aerospace Sciences Meeting 2006
CountryUnited States
CityReno, NV
Period1/9/061/12/06

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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  • Cite this

    Mullen, J. C., & Brewster, M. Q. (2006). Investigation of aluminum agglomeration in AP/HTPB composite propellants. In Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting (pp. 3372-3377). (Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting; Vol. 5). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2006-280