High-Fidelity Microstructural Characterization and Performance Modeling of Aluminized Composite Propellant

Kosiba, Graham D.; Wixom, Ryan R.; Oehlschlaeger, Matthew A.

doi:10.1002/prep.201700124

Title: High-Fidelity Microstructural Characterization and Performance Modeling of Aluminized Composite Propellant

Abstract

Abstract Image processing and stereological techniques were used to characterize the heterogeneity of composite propellant and inform a predictive burn rate model. Composite propellant samples made up of ammonium perchlorate (AP), hydroxyl‐terminated polybutadiene (HTPB), and aluminum (Al) were faced with an ion mill and imaged with a scanning electron microscope (SEM) and x‐ray tomography (micro‐CT). Properties of both the bulk and individual components of the composite propellant were determined from a variety of image processing tools. An algebraic model, based on the improved Beckstead‐Derr‐Price model developed by Cohen and Strand, was used to predict the steady‐state burning of the aluminized composite propellant. In the presented model the presence of aluminum particles within the propellant was introduced. The thermal effects of aluminum particles are accounted for at the solid‐gas propellant surface interface and aluminum combustion is considered in the gas phase using a single global reaction. Properties derived from image processing were used directly as model inputs, leading to a sample‐specific predictive combustion model.

Authors:

Kosiba, Graham D. ^[1]; Wixom, Ryan R. ^[2]; Oehlschlaeger, Matthew A. ^[1]

Rensselaer Polytechnic Institute, Troy, NY (United States)
Sandia National Lab. (SNL-NM), Albuquerque, NM (United States)

Publication Date:: Fri Oct 27 00:00:00 EDT 2017

Research Org.:: Sandia National Lab. (SNL-NM), Albuquerque, NM (United States)

Sponsoring Org.:: USDOE National Nuclear Security Administration (NNSA)

OSTI Identifier:: 1411233

Alternate Identifier(s):: OSTI ID: 1405198

Report Number(s):: SAND-2017-12589J
Journal ID: ISSN 0721-3115; 658869; TRN: US1800205

Grant/Contract Number:: AC04-94AL85000; NA0003525

Resource Type:: Accepted Manuscript

Journal Name:: Propellants, Explosives, Pyrotechnics

Additional Journal Information:: Journal Volume: 42; Journal Issue: 12; Journal ID: ISSN 0721-3115

Publisher:: Wiley

Country of Publication:: United States

Language:: English

Subject:: 37 INORGANIC, ORGANIC, PHYSICAL, AND ANALYTICAL CHEMISTRY; Image Processing; Stereology; Point-Sampled Intercept; Composite Solid Propellants; Combustion Modeling

Citation Formats


                    Kosiba, Graham D., Wixom, Ryan R., and Oehlschlaeger, Matthew A. High-Fidelity Microstructural Characterization and Performance Modeling of Aluminized Composite Propellant.  United States: N. p., 2017. 
Web.  doi:10.1002/prep.201700124.

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                    Kosiba, Graham D., Wixom, Ryan R., & Oehlschlaeger, Matthew A. High-Fidelity Microstructural Characterization and Performance Modeling of Aluminized Composite Propellant.  United States.  https://doi.org/10.1002/prep.201700124

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                    Kosiba, Graham D., Wixom, Ryan R., and Oehlschlaeger, Matthew A. Fri .  
"High-Fidelity Microstructural Characterization and Performance Modeling of Aluminized Composite Propellant".  United States.  https://doi.org/10.1002/prep.201700124.  https://www.osti.gov/servlets/purl/1411233.

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@article{osti_1411233,

  title        = {High-Fidelity Microstructural Characterization and Performance Modeling of Aluminized Composite Propellant},

  author       = {Kosiba, Graham D. and Wixom, Ryan R. and Oehlschlaeger, Matthew A.},

  abstractNote = {Abstract Image processing and stereological techniques were used to characterize the heterogeneity of composite propellant and inform a predictive burn rate model. Composite propellant samples made up of ammonium perchlorate (AP), hydroxyl‐terminated polybutadiene (HTPB), and aluminum (Al) were faced with an ion mill and imaged with a scanning electron microscope (SEM) and x‐ray tomography (micro‐CT). Properties of both the bulk and individual components of the composite propellant were determined from a variety of image processing tools. An algebraic model, based on the improved Beckstead‐Derr‐Price model developed by Cohen and Strand, was used to predict the steady‐state burning of the aluminized composite propellant. In the presented model the presence of aluminum particles within the propellant was introduced. The thermal effects of aluminum particles are accounted for at the solid‐gas propellant surface interface and aluminum combustion is considered in the gas phase using a single global reaction. Properties derived from image processing were used directly as model inputs, leading to a sample‐specific predictive combustion model.},

  doi          = {10.1002/prep.201700124},

  journal      = {Propellants, Explosives, Pyrotechnics},

  number       = 12,

  volume       = 42,

  place        = {United States},

  year         = {Fri Oct 27 00:00:00 EDT 2017},

  month        = {Fri Oct 27 00:00:00 EDT 2017}

}

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Works referenced in this record:

BoneJ: Free and extensible bone image analysis in ImageJ
journal, December 2010

Doube, Michael; Kłosowski, Michał M.; Arganda-Carreras, Ignacio
Bone, Vol. 47, Issue 6
DOI: 10.1016/j.bone.2010.08.023

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Title: High-Fidelity Microstructural Characterization and Performance Modeling of Aluminized Composite Propellant

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Citation Formats

BoneJ: Free and extensible bone image analysis in ImageJ journal, December 2010

BoneJ: Free and extensible bone image analysis in ImageJ
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