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CEAS Aeronautical Journal

, Volume 11, Issue 1, pp 263–275 | Cite as

Performance analysis of a hybrid-electric retrofit of a RUAG Dornier Do 228NG

  • P. G. Juretzko
  • M. ImmerEmail author
  • J. Wildi
Original Paper
  • 45 Downloads

Abstract

The research in this paper provides an analysis of the payload-range capabilities of a retrofitted CS-23, 19-passenger class aircraft, specifically the RUAG Do 228NG. The aircraft is retrofitted with a serial-hybrid electric propulsion system having current technology-level components. The analysis in this paper finds the design points of the propulsion system (battery mass and generator size) with regard to specific operational requirements by performing mission simulations with different flight profiles (operating scenarios). With the requirement of pure electric take-off and initial climb, it was found that two operational parameters, the top-of-climb altitude and the generator-activation altitude, are significant drivers for the battery mass. The generator size is mainly driven by the design’s speed. The mission performance results show that operational decisions affect the sizing of a retrofitted serial-hybrid propulsion system. The results suggest that once a system is sized, the airplane cannot easily be operated under different conditions. The calculated payload-range chart shows that the retrofit cannot match the payload-range capabilities of the baseline aircraft, showing a range reduced by 37% at a payload of 50% (1020 kg).

Keywords

Electric propulsion Hybrid Noise Mission performance Generator sizing Retrofit Do 228NG 

Notes

Acknowledgements

Valuable discussions with Stelio Iotti (ETH Zurich) during his Master’s Thesis provided the groundwork for the activation altitude calculations. The support by Christian Induni (ALR) with the APP calculations is greatly appreciated. The critical review by Curdin Bapst (ETH Zurich) during his Master’s Thesis was a valuable contribution to the quality of the presented results.

References

  1. 1.
    Darecki, M. et al.: Flightpath 2050 Europe’s vision for aviation, report of the high-level group on aviation research, Publications Office of the European Union, 2011,  https://doi.org/10.2777/50266
  2. 2.
    Bradley, M., Droney, C.: Subsonic ultra green aircraft research: phase I final report, NASA CR-2011-216847, April 2011Google Scholar
  3. 3.
    Armstrong, M., Ross, C., Blackwelder, M., Rajashekara, K.: Trade studies for NASA N3-X turboelectric distributed propulsion system electrical power system architecture. SAE Int J Aerosp (2012).  https://doi.org/10.4271/2012-01-2163 CrossRefGoogle Scholar
  4. 4.
    Kim, Hyun Dae, Felder, James L., Tong, Michael T., Berton, Jeffrey J., Haller, William J.: Turboelectric distributed propulsion benefits on the N3-X vehicle. Aircr Eng Aerosp Technol 86(6), 558–561 (2014).  https://doi.org/10.1108/AEAT-04-2014-0037 CrossRefGoogle Scholar
  5. 5.
    Isikveren, A.T., Seitz, A., Vratny, P.C., Pornet, C., Plötner, K.O., Hornung, M.: Conceptual studies of universally-electric systems architectures suitable for transport aircraft. Deutscher Luft- und Raumfahrt Kongress, DLRK, Berlin (2012)Google Scholar
  6. 6.
    Schiltgen, B.T., Gibson, A.R., Keith, J.D.: Mission performance comparisons of subsonic airliners with current and future propulsion technologies, 48th AIAA Aerospace Sciences Meeting, Orlando, FL (2010).  https://doi.org/10.2514/6.2010-279
  7. 7.
    Antcliff, K. R., Capristan, F. M.: Conceptual design of the parallel electric-gas architecture with synergistic utilization scheme (PEGASUS) concept, 18th AIAA/ISSMO multidisciplinary analysis and optimization conference, pp. 1–15, Denver, CO, USA, 5–9 June 2017Google Scholar
  8. 8.
    Perullo, C., Mavris, D.: A review of hybrid-electric energy management and its inclusion in vehicle sizing. Aircr Eng Aerosp Technol Int J 86(6), 550–557 (2014)CrossRefGoogle Scholar
  9. 9.
    Pornet, C., Isikveren, A.T.: Conceptual design of hybrid-electric transport aircraft. Prog Aerosp Sci 79, 114–135 (2015).  https://doi.org/10.1016/j.paerosci.2015.09.002 CrossRefGoogle Scholar
  10. 10.
    Donateo, T., Spedicato, L.: Fuel economy of hybrid electric flight. Appl Energy 206, 723–738 (2017)CrossRefGoogle Scholar
  11. 11.
    Wall, T.J., Meyer, R. : A survey of hybrid electric propulsion for aircraft, 53rd AIAA/SAE/ASEE joint propulsion conference, pp. 1–15, Atlanta, GA, 2017,  https://doi.org/10.2514/6.2017-4700
  12. 12.
    Kreimeier, M., Stumpf, E.: Benefit evaluation of hybrid electric propulsion concepts for CS-23 aircraft. CEAS Aeronaut J 8(4), 691–704 (2017).  https://doi.org/10.1007/s13272-017-0269-9 CrossRefGoogle Scholar
  13. 13.
    Voskuijl, M., van Bogaert, J., Rao, A.G.: Analysis and design of hybrid electric regional turboprop aircraft. CEAS Aeronaut J 9, 15–25 (2018).  https://doi.org/10.1007/s13272-017-0272-1 CrossRefGoogle Scholar
  14. 14.
    Brelje, B. J., Martins, J. R.: Development of a conceptual design model for aircraft electric propulsion with efficient gradients, 2018 AIAA/IEEE electric aircraft technologies symposium (EATS), Cincinnati, OH, USA, 12–14 July 2018Google Scholar
  15. 15.
    Xie, Y., Savvaris, A., Tsourdos, A.: Sizing of hybrid electric propulsion system for retrofitting a mid-scale aircraft using non-dominated sorting genetic algorithm. Aerosp Sci Technol 82–83, 323–333 (2018)CrossRefGoogle Scholar
  16. 16.
    Antcliff, K. R., Guynn, M. D., Marien, T., Wells, D. P., Schneider, S. J., Tong, M. J.: “Mission analysis and aircraft sizing of a hybrid-electric regional aircraft,” 54th AIAA aerospace sciences meeting, American Institute of Aeronautics and Astronautics, January 2016,  https://doi.org/10.2514/6.2016-1028
  17. 17.
    Pornet, C., Gologan, C., Vratny, P., Seitz, A., Schmitz, O., Isikveren, A., Hornung, M.: Methodology for sizing and performance assessment of hybrid energy aircraft. J Aircr 52(1), 341–352 (2015)CrossRefGoogle Scholar
  18. 18.
    Hepperle, M.: Electric flight—potential and limitations, AVT-209 workshop on energy efficient technologies and concepts of operation, Lisbon, October 2012Google Scholar
  19. 19.
    Immer, M., Juretzko, P.: Advanced aircraft performance analysis. Aircr Eng Aerosp Technol 90(4), 627–638 (2018).  https://doi.org/10.1108/AEAT-11-2016-0205 CrossRefGoogle Scholar
  20. 20.
    ALR aerospace: APP 7.0 user manual, Zurich (2019)Google Scholar
  21. 21.
    ALR aerospace: APP 7.0 technical reference Manual, Zurich (2019)Google Scholar
  22. 22.
    Equations for calculation of international standard atmosphere and associated off-standard atmospheres, ESDU 77022 (1977)Google Scholar
  23. 23.
    Python software foundation: python 2.7, https://www.python.org/ (2017). Accessed 31 Aug 2017
  24. 24.
    RUAG aerospace services GmbH: Dornier 228 advanced commuter (AC) facts & figures (2017)Google Scholar
  25. 25.
    Pipistrel.: pipistrel alpha electro technical data. http://www.pipistrel.si/plane/alpha-electro/overview (2017). Accessed 31 Aug 2017
  26. 26.
    Air energy GmbH: reference projects. http://www.airenergy.de/en/referenzprojekte/solar-impulse-i/ (2017). Accessed 31 Aug 2017
  27. 27.
    Siemens, A.G.: aerobatic airplane “Extra 330LE”, https://www.siemens.com/press/pool/de/events/2016/corporate/2016-12-innovation/inno2016-aerobatic-airplane-e.pdf. Press release (2016). Accessed 31 Aug 2017
  28. 28.
    Petermaier, K.: Electric propulsion components with high power densities for aviation, transformative vertical flight workshop, 08 March 2015Google Scholar
  29. 29.
    Raymer, D.: Aircraft design: a conceptual approach, 5th edn. AIAA Educational Series, AIAA, Virginia (2012)CrossRefGoogle Scholar

Copyright information

© Deutsches Zentrum für Luft- und Raumfahrt e.V. 2019

Authors and Affiliations

  1. 1.ALR Arbeitsgruppe für Luft- und RaumfahrtZurichSwitzerland
  2. 2.RUAG AviationEmmenSwitzerland

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