CEAS Aeronautical Journal

, Volume 4, Issue 3, pp 327–343 | Cite as

Propulsion system integration and thrust vectoring aspects for scaled jet UAVs

  • L. Bougas
  • M. Hornung
Original Paper


Scaled UAV configurations of planned aircraft is well suited for the trial of new aeronautical technologies in flight. These systems offer a significant potential for minimizing costs and complexity. For these reasons project Sagitta has been started with the support of the company Cassidian, namely, to build a scaled demonstrator of a full-scale configuration in order to prove the concept of those technologies. Among others, new technologies with respect to the propulsion system of the demonstrator shall be examined. The demonstrator has a flying wing configuration without vertical stabilizers and is powered by two jet engines. Due to the requirements for a low radar cross section for the full-scale configuration, the propulsion system shall have an adequate integration, leading to a curved propulsion duct, in order to integrate the engines as good as possible in the wing. In order to support lateral stability of the scaled configuration, thrust vectoring functionalities shall be implemented into the nozzle system. These aspects induce difficulties with respect to the integration and challenges with the scaling effects regarding the full-scale configuration. Other important issues of such propulsion integration are the total pressure losses in the inlet and nozzle duct, the thermal loads induced by the engine and the required power for the thrust vectoring concept. For the thrust vectoring system, fluidic concepts have been considered due to their potential for weight, complexity and maintenance effort reduction. Such systems have been mostly tested under laboratory conditions; therefore, a flying demonstrator would suit well for a flight trial of the technology. The presented paper will concentrate on the overall integration aspects of the propulsion system and the initial assessment of promising thrust vectoring solutions.


Propulsion integration Thrust vectoring Low observable UAV 


  1. 1.
    Banazadeh, A., Saghafi, F., Ghoreyshi, M., Pilidis, P.: Multi-directional co-flow fluidic thrust vectoring intended for small gas turbine. AIAA 2007-2940. CA, USA (2007)Google Scholar
  2. 2.
    Baranski, J., Hoke, J.: Preliminary characterization of bio-fuels using a small scale gas turbine engine. AIAA 2011 0694. AIAA, Florida, USA (2011)Google Scholar
  3. 3.
    Berens, D.: Ermittlung der Stromaufwärtswirkung des Triebwerks in stark gekrümmten Einläufen (2009)Google Scholar
  4. 4.
    Berens, T., Bissinger, N.C.: Thrust vector behavior of highly integrated asymmetric nozzles for advances fighter aircraft. AIAA 1998, 0948. AIAA, Reno, NV, USA (1998)Google Scholar
  5. 5.
    Deree, K.: Summary of fluidic thrust vectoring research conducted at NASA Langley research center. AIAA 2003-3800. AIAA, Hampton, VA, USA (2003)Google Scholar
  6. 6.
    Deree, K., Berrier, B., Flamm, J., Johnson, S.: A computational study of a new dual throat fluidic thrust vectoring nozzle concept. AIAA 2005-3502 AIAA, USA, p. 5 (2005)Google Scholar
  7. 7.
    Dores, D., Santos, M., Krothapalli, A., Lourenco, L., Collins Jr., E., Alvi, F., et al.: Characterization of a counterflow thrust vectoring scheme on a gas turbine engine exhaust jet. AIAA 2006-3516. AIAA, CA, USA (2006)Google Scholar
  8. 8.
    Flamm, J.: Experimental study of a nozzle using fluidic counterflow for thrust vectoring. AIAA 1998-3255. NASA Langley Research Center, AIAA, Hampton, VA (1998)Google Scholar
  9. 9.
    Flamm, J., Deere, K., Mason, M., Berrier, B., Johnson, K.: Design enhancements of the two-dimensional, dual throat fluidic thrust vectoring nozzle concept. 2006-3701. AIAA, San Francisco, USA (2006)Google Scholar
  10. 10.
    Flamm, J.D., Deere, K.: Experimental study of an axisymmetric dual thrust fluidic thrust vectoring for supersonic aircraft application. AIAA 2007-5084. Hampton, VA, USA (2007)Google Scholar
  11. 11.
    Kirk, A., Kumar, A., Gargoloff, J., Rediniotis, O., Cizmas, P.: Numerical and experimental investigation of a serpentine inlet duct. Reno, NV, USAGoogle Scholar
  12. 12.
    Nicolai, L., Carichner, G.: Fundamentals of aircraft and airship design. Vol I—aircraft design. AIAA Education Series (2010)Google Scholar
  13. 13.
    Raymer, D.: Aircraft design: A conceptual approach. AIAA (2006)Google Scholar
  14. 14.
    Wilde, P., Gill, K., Michie, S., Crowther, W.: Integrated design of fluidic flight controls for a flapless aircraft. 2008-164. AIAA, Nevada, USA (2008)Google Scholar

Copyright information

© Deutsches Zentrum für Luft- und Raumfahrt e.V. 2013

Authors and Affiliations

  1. 1.Institute of Aircraft DesignGarching by MunichGermany

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