Characterization of solid fuel mass-burning enhancement utilizing an X-ray translucent hybrid rocket motor

Brian Evans, Nicholas A. Favorito, J. Eric Boyer, Kenneth K. Kuo

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

    2 Citations (Scopus)

    Abstract

    The addition of nano-sized energetic materials, such as aluminum and boron, has been shown to increase the mass-burning rates of solid fuels. Previous results showed that the addition of 13 wt% Silberline® aluminum flakes to HTPB-based solid fuels increased linear regression rates by as much as 60%. When similar fuel formulations were tested in a larger (~3 times the port diameter) hybrid rocket motor the measured regression rates were nearly identical to those of pure HTPB solid fuels. SEM/EDS analysis was conducted to indicate the reason behind this phenomenon. In contrast, the addition of the same wt% of Silberline® flakes to paraffin-based solid fuels does show a significant increase (~30%) over baseline paraffin solid fuels. The differences in particle entrainment mechanisms for these two types of fuels were attributed to the trend of burning-rate augmentation. Waterfall analyses of pressure-time signals were utilized to study the inherent low-frequency instability of hybrid rockets. Comparisons are made to a universal frequency-scaling formula proposed in the literature, showing agreement to within 25%. To understand the instantaneous mass-burning behavior, a real-time X-ray radiography system is utilized to image the solid fuel surface during combustion testing. Results for both HTPB-based and paraffin-based solid fuel formulations are described. Traditionally, average solid fuel regression rates are correlated to the average oxidizer mass flux by a power-law curve fit. However, instantaneous fuel surface burning behavior does not exhibit the power-law behavior when correlated to the instantaneous oxidizer mass flux.

    Original languageEnglish (US)
    Title of host publicationAdvancements in Energetic Materials and Chemical Propulsion
    Pages705-724
    Number of pages20
    StatePublished - Dec 1 2005
    Event6th International Symposium on Special Topics in Chemical Propulsion: Advancements in Energetic Materials and Chemical Propulsion, ISICP 2006 - Santiago, Chile
    Duration: Mar 8 2005Mar 11 2005

    Publication series

    NameAdvancements in Energetic Materials and Chemical Propulsion

    Other

    Other6th International Symposium on Special Topics in Chemical Propulsion: Advancements in Energetic Materials and Chemical Propulsion, ISICP 2006
    CountryChile
    CitySantiago
    Period3/8/053/11/05

    Fingerprint

    Rocket engines
    X rays
    Paraffin
    Paraffins
    Aluminum
    Mass transfer
    X ray radiography
    Boron
    Rockets
    Linear regression
    Energy dispersive spectroscopy
    Scanning electron microscopy

    All Science Journal Classification (ASJC) codes

    • Materials Chemistry

    Cite this

    Evans, B., Favorito, N. A., Boyer, J. E., & Kuo, K. K. (2005). Characterization of solid fuel mass-burning enhancement utilizing an X-ray translucent hybrid rocket motor. In Advancements in Energetic Materials and Chemical Propulsion (pp. 705-724). (Advancements in Energetic Materials and Chemical Propulsion).
    Evans, Brian ; Favorito, Nicholas A. ; Boyer, J. Eric ; Kuo, Kenneth K. / Characterization of solid fuel mass-burning enhancement utilizing an X-ray translucent hybrid rocket motor. Advancements in Energetic Materials and Chemical Propulsion. 2005. pp. 705-724 (Advancements in Energetic Materials and Chemical Propulsion).
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    title = "Characterization of solid fuel mass-burning enhancement utilizing an X-ray translucent hybrid rocket motor",
    abstract = "The addition of nano-sized energetic materials, such as aluminum and boron, has been shown to increase the mass-burning rates of solid fuels. Previous results showed that the addition of 13 wt{\%} Silberline{\circledR} aluminum flakes to HTPB-based solid fuels increased linear regression rates by as much as 60{\%}. When similar fuel formulations were tested in a larger (~3 times the port diameter) hybrid rocket motor the measured regression rates were nearly identical to those of pure HTPB solid fuels. SEM/EDS analysis was conducted to indicate the reason behind this phenomenon. In contrast, the addition of the same wt{\%} of Silberline{\circledR} flakes to paraffin-based solid fuels does show a significant increase (~30{\%}) over baseline paraffin solid fuels. The differences in particle entrainment mechanisms for these two types of fuels were attributed to the trend of burning-rate augmentation. Waterfall analyses of pressure-time signals were utilized to study the inherent low-frequency instability of hybrid rockets. Comparisons are made to a universal frequency-scaling formula proposed in the literature, showing agreement to within 25{\%}. To understand the instantaneous mass-burning behavior, a real-time X-ray radiography system is utilized to image the solid fuel surface during combustion testing. Results for both HTPB-based and paraffin-based solid fuel formulations are described. Traditionally, average solid fuel regression rates are correlated to the average oxidizer mass flux by a power-law curve fit. However, instantaneous fuel surface burning behavior does not exhibit the power-law behavior when correlated to the instantaneous oxidizer mass flux.",
    author = "Brian Evans and Favorito, {Nicholas A.} and Boyer, {J. Eric} and Kuo, {Kenneth K.}",
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    Evans, B, Favorito, NA, Boyer, JE & Kuo, KK 2005, Characterization of solid fuel mass-burning enhancement utilizing an X-ray translucent hybrid rocket motor. in Advancements in Energetic Materials and Chemical Propulsion. Advancements in Energetic Materials and Chemical Propulsion, pp. 705-724, 6th International Symposium on Special Topics in Chemical Propulsion: Advancements in Energetic Materials and Chemical Propulsion, ISICP 2006, Santiago, Chile, 3/8/05.

    Characterization of solid fuel mass-burning enhancement utilizing an X-ray translucent hybrid rocket motor. / Evans, Brian; Favorito, Nicholas A.; Boyer, J. Eric; Kuo, Kenneth K.

    Advancements in Energetic Materials and Chemical Propulsion. 2005. p. 705-724 (Advancements in Energetic Materials and Chemical Propulsion).

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

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    N2 - The addition of nano-sized energetic materials, such as aluminum and boron, has been shown to increase the mass-burning rates of solid fuels. Previous results showed that the addition of 13 wt% Silberline® aluminum flakes to HTPB-based solid fuels increased linear regression rates by as much as 60%. When similar fuel formulations were tested in a larger (~3 times the port diameter) hybrid rocket motor the measured regression rates were nearly identical to those of pure HTPB solid fuels. SEM/EDS analysis was conducted to indicate the reason behind this phenomenon. In contrast, the addition of the same wt% of Silberline® flakes to paraffin-based solid fuels does show a significant increase (~30%) over baseline paraffin solid fuels. The differences in particle entrainment mechanisms for these two types of fuels were attributed to the trend of burning-rate augmentation. Waterfall analyses of pressure-time signals were utilized to study the inherent low-frequency instability of hybrid rockets. Comparisons are made to a universal frequency-scaling formula proposed in the literature, showing agreement to within 25%. To understand the instantaneous mass-burning behavior, a real-time X-ray radiography system is utilized to image the solid fuel surface during combustion testing. Results for both HTPB-based and paraffin-based solid fuel formulations are described. Traditionally, average solid fuel regression rates are correlated to the average oxidizer mass flux by a power-law curve fit. However, instantaneous fuel surface burning behavior does not exhibit the power-law behavior when correlated to the instantaneous oxidizer mass flux.

    AB - The addition of nano-sized energetic materials, such as aluminum and boron, has been shown to increase the mass-burning rates of solid fuels. Previous results showed that the addition of 13 wt% Silberline® aluminum flakes to HTPB-based solid fuels increased linear regression rates by as much as 60%. When similar fuel formulations were tested in a larger (~3 times the port diameter) hybrid rocket motor the measured regression rates were nearly identical to those of pure HTPB solid fuels. SEM/EDS analysis was conducted to indicate the reason behind this phenomenon. In contrast, the addition of the same wt% of Silberline® flakes to paraffin-based solid fuels does show a significant increase (~30%) over baseline paraffin solid fuels. The differences in particle entrainment mechanisms for these two types of fuels were attributed to the trend of burning-rate augmentation. Waterfall analyses of pressure-time signals were utilized to study the inherent low-frequency instability of hybrid rockets. Comparisons are made to a universal frequency-scaling formula proposed in the literature, showing agreement to within 25%. To understand the instantaneous mass-burning behavior, a real-time X-ray radiography system is utilized to image the solid fuel surface during combustion testing. Results for both HTPB-based and paraffin-based solid fuel formulations are described. Traditionally, average solid fuel regression rates are correlated to the average oxidizer mass flux by a power-law curve fit. However, instantaneous fuel surface burning behavior does not exhibit the power-law behavior when correlated to the instantaneous oxidizer mass flux.

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    Evans B, Favorito NA, Boyer JE, Kuo KK. Characterization of solid fuel mass-burning enhancement utilizing an X-ray translucent hybrid rocket motor. In Advancements in Energetic Materials and Chemical Propulsion. 2005. p. 705-724. (Advancements in Energetic Materials and Chemical Propulsion).