International Journal of Aerospace System Engineering

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Design Optimization of Single-Stage Launch Vehicle Using Hybrid Rocket Engine

  • Kanazaki, Masahiro (Graduate School of System Design, Tokyo Metropolitan University) ;
  • Ariyairt, Atthaphon (Graduate School of System Design, Tokyo Metropolitan University) ;
  • Yoda, Hideyuki (Graduate School of System Design, Tokyo Metropolitan University) ;
  • Ito, Kazuma (Graduate School of System Design, Tokyo Metropolitan University) ;
  • Chiba, Kazuhisa (Graduate School of Informatics and Engineering, The University of Electro-Communications) ;
  • Kitagawa, Koki (Graduate School of System Design, Japan Aerospace Exploration Agency) ;
  • Shimada, Toru (Graduate School of System Design, Japan Aerospace Exploration Agency)
  • Received : 2015.07.10
  • Accepted : 2015.08.15
  • Published : 2015.12.30
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Abstract

The multidisciplinary design optimization (MDO) of a launch vehicle (LV) with a hybrid rocket engine (HRE) was carried out to investigate the ability of an HRE for a single-stage LV. The non-dominated sorting genetic algorithm-II (NSGA-II) was employed to solve two design problems. The design problems were formulated as two-objective cases involving maximization of the downrange distance over the target flight altitude and minimization of the gross weight, for two target altitudes: 50.0 km and 100.0 km. Each objective function was empirically estimated. Several non-dominated solutions were obtained using the NSGA-II for each design problem, and in each case, a trade-off was observed between the two objective functions. The results for the two design problem indicate that economical performance of the LV is limited with the HRE in terms of the maximum downrange distances achievable. The LV geometries determined from the non-dominated solutions were examined.

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References

  1. G. P. Sutton and O. Biblarz, Rocket Propulsion Elements JOHN WILEY & SONS, INC. A Wiley-lnterscience Publication, 2000.
  2. Z. Thicksten, "Handling considerations of nitrous oxide in hybrid rocket motor testing," in 44th. AIAA/ASME/SAE/ASEE. Joint. Propulsion. Conference and Exhibit, AIAA Paper 2008-4830, 2008.
  3. S. Yuasa, "Fuel regression rate behavior in swirling-oxidizer-flow-type hybrid rocket engines," in Proceedings of 8th International Symposium on Special Topics in Chemical Propulsion, 2009.
  4. S. Hikone, "Regression rate characteristics and combustion mechanism of some hybrid rocket fuels," 2010.
  5. K. Kosugi, A. Oyama, K. Fujii, and M. Kanazaki, "Multidiscipli-nary and multi-objective design exploration methodology for conceptual design of a hybrid rocket," 2011.
  6. Y. Kitagawa, K. Kitagawa, M. Nakamiya, M. Kanazaki, and T. Shimada, "Multi-stage hybrid rocket conceptual design for micro-satellites launch using genetic algorithm," Transactions of the Japan Society for Aeronautical and Space Sciences, vol. 55, no. 4, pp. 229-236, 2012. https://doi.org/10.2322/tjsass.55.229
  7. "NASA glenn research center chemical equilibrium with applications," http://www.grc.nasa.gov/WWW/CEAWeb/, 2010.
  8. K. Deb, "A fast and elitist multiobjective genetic algorithm: NSGA-II," IEEE Transactions on Evolutionary Computation, no. 2, pp. 182-197, 2002.
  9. L. J. Eshelman and J. D. Schaffer, "Real-coded genetic algorithms and interval-schemata," in Foundations of Genetic Algorithms 2. Morgan Kaufmann Publishers, San Mateo, 1993, pp. 187-202.