TY - GEN
T1 - Thermodynamic and transport properties of hydroxylammonium nitrate-based electric solid propellant vapor
AU - Glascock, Matthew S.
AU - Drew, Patrick D.
AU - Rovey, Joshua L.
N1 - Funding Information:
M.S. Glascock is extremely grateful for the NASA Space Technology Research Fellows program, which funded this research under grant number NNX15AP31H. The authors thank Dr. John Yim at NASA Glenn Research Center for assistance with the CEA program and fruitful discussion on the work. The authors also thank Dr. Kurt Polzin of NASA Marshall Space Flight Center for his advice and discussion. The authors thank Digital Solid State Propulsion, LLC for HIPEP samples for TGA, as well as previous thermochemical modeling work on the material. Finally, the authors wish to thank Lou Ann Miller and Tim Spila at the University of Illinois for their assistance with the TGA.
Funding Information:
M.S. Glascock is extremely grateful for the NASA Space Technology Research Fellows program, which funded this research under grant number NNX15AP31H. The authors thank Dr. John Yim at NASAGlenn Research Center for assistance with the CEA program and fruitful discussion on the work. The authors also thank Dr. Kurt Polzin of NASA Marshall Space Flight Center for his advice and discussion. The authors thank Digital Solid State Propulsion, LLC for HIPEP samples for TGA, as well as previous thermochemical modeling work on the material. Finally, the authors wish to thank Lou Ann Miller and Tim Spila at the University of Illinois for their assistance with the TGA.
Publisher Copyright:
© 2019 by Matthew S. Glascock. Published by the American Institute of Aeronautics and Astronautics, Inc.
PY - 2019
Y1 - 2019
N2 - Electric solid propellants are advanced solid chemical rocket propellants controlled by electric current. Electric solid propellants may also be used in an electric propulsion system, specifically, an ablative pulsed plasma thruster. Previous experiments with the electric solid propellant HIPEP suggest its ablation processes are similar to traditional propellant polytetrafluoroethylene (C2F4). Better understanding of the ablation and resulting propulsion performance of HIPEP requires a model of its vapor composition and transport properties. This paper reports on the development of such a model. The model was validated by comparing results for C2F4 with literature, which showed agreement with multiple models described. Transport property results matched within an order of magnitude for temperatures less than 15,000 K and equilibrium composition densities matched to within an order of magnitude. The electric solid propellant vapor composition was predicted in the temperature range of 500-40,000 Kelvin at 1 bar pressure. Low temperatures (<2,000 K) are dominated by H2O, CO2 and N2, and results at 700 K match within 10% of previous combustion model predictions. At high temperatures (>25,000 K) the vapor is strongly ionized and dominated by C2+, O2+, N2+, and H+ ions. The viscosity of the electric solid propellant vapor is on the order of 10-4 kg/m/s and thermal conductivity is on the order of 10 W/m/K.
AB - Electric solid propellants are advanced solid chemical rocket propellants controlled by electric current. Electric solid propellants may also be used in an electric propulsion system, specifically, an ablative pulsed plasma thruster. Previous experiments with the electric solid propellant HIPEP suggest its ablation processes are similar to traditional propellant polytetrafluoroethylene (C2F4). Better understanding of the ablation and resulting propulsion performance of HIPEP requires a model of its vapor composition and transport properties. This paper reports on the development of such a model. The model was validated by comparing results for C2F4 with literature, which showed agreement with multiple models described. Transport property results matched within an order of magnitude for temperatures less than 15,000 K and equilibrium composition densities matched to within an order of magnitude. The electric solid propellant vapor composition was predicted in the temperature range of 500-40,000 Kelvin at 1 bar pressure. Low temperatures (<2,000 K) are dominated by H2O, CO2 and N2, and results at 700 K match within 10% of previous combustion model predictions. At high temperatures (>25,000 K) the vapor is strongly ionized and dominated by C2+, O2+, N2+, and H+ ions. The viscosity of the electric solid propellant vapor is on the order of 10-4 kg/m/s and thermal conductivity is on the order of 10 W/m/K.
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U2 - 10.2514/6.2019-2070
DO - 10.2514/6.2019-2070
M3 - Conference contribution
AN - SCOPUS:85083941826
SN - 9781624105784
T3 - AIAA Scitech 2019 Forum
BT - AIAA Scitech 2019 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2019
Y2 - 7 January 2019 through 11 January 2019
ER -