Regression rate behavior of hybrid rocket solid fuels

  • Chiaverini M
  • Serin N
  • Johnson D
 et al. 
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Abstract

An exptl. investigation of the regression-rate characteristics of hydroxyl-terminated polybutadiene (HTPB) solid fuel burning with oxygen was conducted by using a windowed, slab-geometry hybrid rocket motor. A real-time, x-ray radiog. system was used to obtain instantaneous solid-fuel regression rate data at many axial locations. Fuel temp. measurements were made by using an array of 25-μm fine-wire embedded thermocouples. The regression rates displayed a strong dependence on axial location near the motor head-end. At lower mass flux levels, thermal radiation significantly influence the regression rates. The regression rates were also affected by the addn. of activated aluminum powder. A 20% by wt. addn. of activated aluminum to HTPB increased the fuel mass flux by 70% over that of pure HTPB. Correlations were developed to relate the regression rate to operating conditions and port geometry for both pure HTPB and for HTPB loaded with certain fractions of activated aluminum. Thermocouple measurements indicated that the fuel surface temps. for pure HTPB were between 930 and 1190 K. The HTPB activation energy was estd. at 11.5 kcal/mol, suggesting that the overall regression process is governed by phys. desorption of high-mol. wt. fragments from the fuel surface. [on SciFinder(R)]

Author-supplied keywords

  • activated aluminum hydroxyl terminated polybutadie
  • hybrid rocket solid fuel regression rate character
  • hydroxyl terminated polybutadiene burning oxygen

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Authors

  • Martin J Chiaverini

  • Nadir Serin

  • David K Johnson

  • Yeu-Cherng Lu

  • Kenneth K Kuo

  • Grant A Risha

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