Abstract
Energetic nano-sized particles have been shown to have a great potential for use in the aerospace propulsion applications. Some of the unique combustion properties of nano-particles such as very rapid ignition and short combustion times make them particularly valuable for propulsion systems; they can be included in solid fuels, solid propellants, or even as energetic gellant in liquid systems. However, due to the novelty of the application and rapid development of production techniques, there is no comprehensive understanding of what characteristics of a nano-sized particle are important in contributing to desirable performance and ease of processing into a final usable form. Previous studies have shown that HTPB-based solid fuels containing various types of nano-sized particles showed differing performance results when tested in the same hybrid rocket motor under identical conditions. Many of these particles have data available only on the basic composition (aluminum, boron, boron carbide, etc.), average diameter, and/or BET surface area. In order to better understand and correlate observed combustion behavior with intrinsic material properties, the particles of interest need to be better characterized. A variety of standard particle characterization techniques were applied to the fifteen types of particles examined in this study and the results tabulated. Some of the parameters measured were average particle diameter, specific surface area, amount of active content, and oxide layer thickness. Trends in propulsion performance measured using a parameter of great interest to the hybrid rocket community (fuel mass burning rate) in general matched trends in particle characteristics (i.e. active content, surface area), but there were some noticeable exceptions. This study indicates that there is still much more to learn about the correlation between physical and chemical properties and measured combustion performance. Other parameters that should be examined in the future include particle size distribution, degree of agglomeration, reactivity and thermal effects (oxidation rate, onset temperature for oxidation exotherm, heat release associated with any excess stored energy), etc.
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Acknowledgments
The authors would like to thank U.S. Navy NAVSEA-Indian Head and Dr. Richard Bowen at NAVSEA for sponsoring the research work presented in this paper. The donation of nanoparticles from Mr. Fred Tepper (Argonide Corporation), Dr. May Chan (NAWC-China Lake), Dr. Gary Pozarnsky (Aveka, Inc.), Dr. David Pesiri (Technanogy), Mr. Randy Cramer (NAVSEA-Indian Head), and Dr. Denny Hamill (Nanotechnologies) are greatly appreciated. The authors would also like to acknowledge Dr. Curtis E. Johnson of NAWC-China Lake for his effort in determining the active aluminum content in different nano-sized particles using a wet chemistry technique.
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Risha, G.A., Boyer, E., Evans, B. et al. Characterization of Nano-Sized Particles for Propulsion Applications. MRS Online Proceedings Library 800, 240–251 (2003). https://doi.org/10.1557/PROC-800-AA6.6
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DOI: https://doi.org/10.1557/PROC-800-AA6.6