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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29

ISSN Print: 2150-766X
ISSN Online: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2012004978
pages 241-257

HYDROXYLAMMONIUM NITRATE AS GREEN PROPELLANT: DECOMPOSITION AND STABILITY

Rachid Amrousse
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA), 3-1-1 Yoshinodai, Chuo-Ku, Sagamihara, Kanagawa 252-5210, Japan
Toshiyuki Katsumi
Department of Mechanical Engineering, Nagaoka University of Technology, Japan
T. Sulaiman
JAXA, Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-Ku, Sagamihara, Kanagawa 252-5210, Japan
B. R. Das
JAXA, Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-Ku, Sagamihara, Kanagawa 252-5210, Japan
H. Kumagai
Department of Chemical System Engineering, University of Tokyo, 7-3-1 Hongo, Bunkyo-Ku, Tokyo 113-8656, Japan
K. Maeda
Department of Chemical System Engineering, University of Tokyo, 7-3-1 Hongo, Bunkyo-Ku, Tokyo 113-8656, Japan; Precursory Research for Embryonic Science and Technology, Japan Science and Technology Agency, 4-1-8 Honcho Kawaguchi, Saitama 332-0012, Japan
Keiichi Hori
Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA), 3-1-1 Yoshinodai, Chuo-Ku, Sagamihara, Kanagawa 252-5210, Japan

ABSTRACT

Binary hydroxyl ammonium nitrate (HAN) aqueous mixtures have been prepared. Four series of ternary mixtures have been synthesized with methanol and ethanol as fuels: two series with HAN excess and two other series with stoichiometric fuel contents. Thermal and catalytic decomposition of the prepared solutions have been analyzed. For binary HAN solutions, the thermal decomposition starts only once water has been fully vaporized and the oxidizer is in the liquid state. The influence of the fuel depends strongly on the oxidizer. Methanol and ethanol are vaporized before the decomposition, leading to results close to those observed for binary mixtures. HAN and HAN-fuel-based solutions display the highest catalytic effect with a temperature decrease of about 100° C.

REFERENCES

  1. Amrousse, R., Brahmi, R., Batonneau, Y., and Kappenstein, C. , Thermal and catalytic decomposition of H2O2–ionic liquid monopropellant mixtures on monolith-based catalysts.

  2. Courth'eoux, L., Amariei, D., Rossignol, S., and Kappenstein, C. , Facile catalytic decomposition at low temperature of energetic ionic liquid as hydrazine substitute.

  3. Courth'eoux, L., Amariei, D., Rossignol, S., Kappenstein, C., Pillet, N., and Ford, M. , Thermal and catalytic decomposition of HNF and HAN-based propellants.

  4. Courth'eoux, L., Popa, F., Gautron, E., Rossignol, S., and Kappenstein, C. , Platinum supported on doped alumina catalysts for propulsion applications.

  5. Fortini, A. J. and Babcock, J. R. , High temperature catalyst beds for advanced monopropellants.

  6. Hisatsune, K., Izumi, J., Tsutaya, H., and Furukawa, K., Development of HAN-based liquid propellant thruster.

  7. Morgan, O. and Meinhardt, D. , Monopropellant selection criteria—hydrazine and other options.

  8. Van Dijk, C. A. and Priest, R. G. , Thermal decomposition of hydroxylammonium nitrate at kilobar pressures.

  9. Zube, D., Christofferson, S., W¨ucherer, E., and Reed, B., Evaluation of HAN-based propellant blends.


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