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Combustion, Explosion, and Shock Waves

, Volume 53, Issue 3, pp 293–297 | Cite as

Study of a hybrid gas generator for a ducted rocket

  • D. KomornikEmail author
  • A. Gany
Article

Abstract

A performance analysis and experimental study of a hybrid gas generator to be used in a ducted rocket are presented. Such a system exhibits potential advantages with regard to safety, performance, costs, availability of the fuel components, storability, and thrust control. A combination of a paraffin wax fuel and oxygen in the gas generator ensures a high regression rate and reveals oxidizer-to-fuel ratios as low as 0.14 in the gas generator (compared to the stoichiometric ratio of 3.4). A fuel regression rate correlation versus the oxidizer mass flux is derived, presenting a major advantage for the fuel flow rate management in comparison to control of the solid propellant gas generator burning rate through the pressure exponent, which requires mechanical interference with the hot nozzle flow to ensure a change in the combustor pressure and a corresponding change in the burning rate. Evaluation of the ducted rocket (with different oxidizers) versus pure ramjet performance shows a higher specific thrust for the former, though the latter exhibits a higher specific impulse.

Keywords

ducted rocket hybrid motor gas generator ramjet 

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References

  1. 1.
    R. S. Fry, “A Century of Ramjet Technology Propulsion Evolution,” J. Propul. Power 20 (1), 27–58 (2004).MathSciNetCrossRefGoogle Scholar
  2. 2.
    J. L. Leingang and D. P. Petters, “Ducted Rockets,” in Progress in Astronautic and Aeronautic, Vol. 170: Tactical Missile Propulsion, Ed. by G. E. Jensen, D.W. Netzer (1996), pp. 447–468.Google Scholar
  3. 3.
    A. Russo Sorge, “Hybrid Propellants Gas Generator,” in 14th Int. Symp. Air Breathing Engines, Florence, Italy, 1999, ISABE Paper No. 99-7247 (1999).Google Scholar
  4. 4.
    G. P. Sutton and O. Biblarz, Rocket Propulsion Elements, (John Wiley and Sons, New York, 2001).Google Scholar
  5. 5.
    D. R. Cruise, “Theoretical Computations of Equilibrium Composition, Thermodynamics Properties and Performance Characteristics of Propellant Systems (PEP Code),” NWC-TP-6037 (Naval Weapons Center, China Lake, 1979).Google Scholar
  6. 6.
    S. Gordon and B. McBride, “Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications,” NASA-RP-1311 Report (NASA Lewis Research Center, Cleveland, 1996).Google Scholar
  7. 7.
    D. A. Vnuchkov, V. I. Zvegintsev, D. G. Nalivaichenko, and S. I. Shpak, “Operation of a Gas Generator Controlled by Supplying a Gaseous Oxidizer,” Fiz. Goreniya Vzryva 44 (8), 18–25 (2008) [Combust., Expl., Shock Waves 44 (6), 432–438 (2008)].Google Scholar

Copyright information

© Pleiades Publishing, Ltd. 2017

Authors and Affiliations

  1. 1.Faculty of Aerospace EngineeringTechnion—Israel Institute of TechnologyHaifaIsrael

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