Enhanced Method of Conceptual Sizing of Aircraft Electro-Thermal De-icing System
There is a great advancement towards the All-Electric Aircraft (AEA) technology. The AEA concept assumes that all aircraft systems will be integrated into one electrical power source in the future. The principle of the electro-thermal system is to transfer the energy required for anti/de-icing to the protected areas in electrical form. However, powering a large aircraft anti-icing system electrically could be quite excessive in cost and system weight. Hence, maximising the anti/de-icing efficiency of the electro-thermal system in order to minimise its power demand has become crucial to electro-thermal de-icing system sizing. In this work, an enhanced methodology has been developed for conceptual sizing of aircraft electro-thermal de-icing System. The work factored those critical terms overlooked in previous studies which were critical to de-icing energy consumption. A case study of a typical large aircraft wing de-icing was used to test and validate the model. The model was used to optimise the system performance by a trade-off between the de-icing peak power and system energy consumption. The optimum melting surface temperatures and energy flux predicted enabled the reduction in the power required for de-icing. The weight penalty associated with electro-thermal anti-icing/de-icing method could be eliminated using this method without under estimating the de-icing power requirement.
[1] Gent, R. W., Dart, N. P. and Cansdale, J. T. (2000), "Aircraft Icing", The Royal Society, , no. 358, pp. 2873-2911.
[2] SESAR (2012), SESAR Releases: Advancing ATM Modernisation, available at: http://www.sesarju.eu/news-press/news/sesar-releases-advancing-atm-modernisation-1055 (accessed 03/26).
[3] SAE Aerospace (1989), Ice, Rain, Fog, and Frost Protection, AIR1168/4, Society of Automative Engineers, Inc, PA.
[4] Shinkafi, A. and Lawson, C. (2013), "Evaluating Inflight Ice Protection Methods for Applications on Next Generation Aircraft", Journal of Aerospace Engineering and Technology, , no. 2231-038X.
[5] AL-Khalil, K. M., Horvath, C., Miller, D. R. and Wright, B. W. (2001), Validation of NASA Thermal Ice ProtectionComputer Codes, Part 3: The Validation of Antice, NASA/TM-2001-210907, NASA, Washington.
[6] Petrenko, V., (2006), Method for Modifying Friction Between an Object and Ice or Snow (Patent No. US 7,034,257), 219/482 ed., H05B 3/02, Hanover/US.
[7] Moir, I. and Seabridge, A. (2008), Aircraft Systems Mechanical, Electrical, and Avionics Subsystems Integration, 3rd ed, Wiley, New Jersey.
[8] FAA (2007), Pilot Guide: Flight in Icing Conditions, 91-74A, FAA.
[9] Palacios, J. L. (2008), Design, Fabrication, and Testing of an Ultrasonic De-icing System for Helicopter Rotor Blades (PhD thesis), The Pennsyvania State University, PA.
[10] Wright, B. W., Al-Khalil, K. and Miller, D. (1997), Validation of NASA Thermal Ice Protection Computer Codes Part2 - LEWICE/Thermal, AIAA 97-0050, AIAA, Virginia.
[11] Petrenko, V. F., Higa, M. and Starostin, M., Deresh, L. (2003), "Pulse Electrothermal De-icing", in Chung, J.S., Prinsenberg, S. (ed.), Proceedings of The Thirteenth (2003) International Offshore and Polar Engineering Conference, Vol. 1, 25-30 May 2003, Honolulu, Hawii, USA, The International Society of Offshore and Polar Engineers, Honolulu, pp. 435.
[12] Botura, G. C., Sweet, D. and Flosdorf, D. (2005), Development and Demonstration of Low Power Electrothermal De-icing System, AIAA 2005-1460, AIAA, Washington.
[13] Stoner, P., Christy, D.P. and Sweet, D.B., ( 2007), Low Power, Pulsed, Electro-thermal Ice Protection System, 244/134 D ed., B64D 15/4, USA.
[14] GKN (2010), Composite Aircraft Wing Research gets underway at GKN Aerospace, available at: http://www.gknaerospace.com/ newsarticle.aspx?page=S633463542178688750&ArchiveID=5&CategoryID=33&ItemID=313&src= (accessed 05/15).
[15] Habashi, W. G. (2010), Recent Progress in Unifying CFD and In-Flight Icing Simulation, ICFD10-EG-30I11, ICFD, Ain Soukhna, Egypt.
[16] Meier, O. and Scholz, D. (2010), A Handbook Method for the Estimation of Power Requirements for Electrical De-icing Systemms, 161191, Hamburg University of Applied Sciences, Hamburg, Germany.
[17] Petrenko, V. F., Charles, R. S., Kozlyuk, V., Petrenk, F. V. and Veerasamy, V. (2011), "Pulse Electro-thermal De-icer (PETD)", Cold Regions Science and Technology, , no. 65, pp. 70-78.
[18] Qinglin, M. (2010), Aircraft Icing and Thermo-Mechanical Expulsion De-icing Technology (unpublished MSc thesis), Cranfield University, Cranfield.
[19] Bowden, D. T., Gensemer, A. E. and Skeen, C. A. (1964), Engineering Summary of Airframe Icing Technical Data, FAA ADS-4, FAA, Washington, D.C.
[20] Lewis, J.P, Bowden, T. (1952), Preliminary Investigation of Cyclic De-icing of an Airfoil using an External Electric Heater, RM E51J30, NACA, Washington.
[21] Xie, A. (2012), Interactive Heat Transfer Simulations for Everyone, , The Concord Consortium, VA, USA.
[1] Gent, R. W., Dart, N. P. and Cansdale, J. T. (2000), "Aircraft Icing", The Royal Society, , no. 358, pp. 2873-2911.
[2] SESAR (2012), SESAR Releases: Advancing ATM Modernisation, available at: http://www.sesarju.eu/news-press/news/sesar-releases-advancing-atm-modernisation-1055 (accessed 03/26).
[3] SAE Aerospace (1989), Ice, Rain, Fog, and Frost Protection, AIR1168/4, Society of Automative Engineers, Inc, PA.
[4] Shinkafi, A. and Lawson, C. (2013), "Evaluating Inflight Ice Protection Methods for Applications on Next Generation Aircraft", Journal of Aerospace Engineering and Technology, , no. 2231-038X.
[5] AL-Khalil, K. M., Horvath, C., Miller, D. R. and Wright, B. W. (2001), Validation of NASA Thermal Ice ProtectionComputer Codes, Part 3: The Validation of Antice, NASA/TM-2001-210907, NASA, Washington.
[6] Petrenko, V., (2006), Method for Modifying Friction Between an Object and Ice or Snow (Patent No. US 7,034,257), 219/482 ed., H05B 3/02, Hanover/US.
[7] Moir, I. and Seabridge, A. (2008), Aircraft Systems Mechanical, Electrical, and Avionics Subsystems Integration, 3rd ed, Wiley, New Jersey.
[8] FAA (2007), Pilot Guide: Flight in Icing Conditions, 91-74A, FAA.
[9] Palacios, J. L. (2008), Design, Fabrication, and Testing of an Ultrasonic De-icing System for Helicopter Rotor Blades (PhD thesis), The Pennsyvania State University, PA.
[10] Wright, B. W., Al-Khalil, K. and Miller, D. (1997), Validation of NASA Thermal Ice Protection Computer Codes Part2 - LEWICE/Thermal, AIAA 97-0050, AIAA, Virginia.
[11] Petrenko, V. F., Higa, M. and Starostin, M., Deresh, L. (2003), "Pulse Electrothermal De-icing", in Chung, J.S., Prinsenberg, S. (ed.), Proceedings of The Thirteenth (2003) International Offshore and Polar Engineering Conference, Vol. 1, 25-30 May 2003, Honolulu, Hawii, USA, The International Society of Offshore and Polar Engineers, Honolulu, pp. 435.
[12] Botura, G. C., Sweet, D. and Flosdorf, D. (2005), Development and Demonstration of Low Power Electrothermal De-icing System, AIAA 2005-1460, AIAA, Washington.
[13] Stoner, P., Christy, D.P. and Sweet, D.B., ( 2007), Low Power, Pulsed, Electro-thermal Ice Protection System, 244/134 D ed., B64D 15/4, USA.
[14] GKN (2010), Composite Aircraft Wing Research gets underway at GKN Aerospace, available at: http://www.gknaerospace.com/ newsarticle.aspx?page=S633463542178688750&ArchiveID=5&CategoryID=33&ItemID=313&src= (accessed 05/15).
[15] Habashi, W. G. (2010), Recent Progress in Unifying CFD and In-Flight Icing Simulation, ICFD10-EG-30I11, ICFD, Ain Soukhna, Egypt.
[16] Meier, O. and Scholz, D. (2010), A Handbook Method for the Estimation of Power Requirements for Electrical De-icing Systemms, 161191, Hamburg University of Applied Sciences, Hamburg, Germany.
[17] Petrenko, V. F., Charles, R. S., Kozlyuk, V., Petrenk, F. V. and Veerasamy, V. (2011), "Pulse Electro-thermal De-icer (PETD)", Cold Regions Science and Technology, , no. 65, pp. 70-78.
[18] Qinglin, M. (2010), Aircraft Icing and Thermo-Mechanical Expulsion De-icing Technology (unpublished MSc thesis), Cranfield University, Cranfield.
[19] Bowden, D. T., Gensemer, A. E. and Skeen, C. A. (1964), Engineering Summary of Airframe Icing Technical Data, FAA ADS-4, FAA, Washington, D.C.
[20] Lewis, J.P, Bowden, T. (1952), Preliminary Investigation of Cyclic De-icing of an Airfoil using an External Electric Heater, RM E51J30, NACA, Washington.
[21] Xie, A. (2012), Interactive Heat Transfer Simulations for Everyone, , The Concord Consortium, VA, USA.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:67293", author = "Ahmed Shinkafi and Craig Lawson", title = "Enhanced Method of Conceptual Sizing of Aircraft Electro-Thermal De-icing System", abstract = "There is a great advancement towards the All-Electric Aircraft (AEA) technology. The AEA concept assumes that all aircraft systems will be integrated into one electrical power source in the future. The principle of the electro-thermal system is to transfer the energy required for anti/de-icing to the protected areas in electrical form. However, powering a large aircraft anti-icing system electrically could be quite excessive in cost and system weight. Hence, maximising the anti/de-icing efficiency of the electro-thermal system in order to minimise its power demand has become crucial to electro-thermal de-icing system sizing. In this work, an enhanced methodology has been developed for conceptual sizing of aircraft electro-thermal de-icing System. The work factored those critical terms overlooked in previous studies which were critical to de-icing energy consumption. A case study of a typical large aircraft wing de-icing was used to test and validate the model. The model was used to optimise the system performance by a trade-off between the de-icing peak power and system energy consumption. The optimum melting surface temperatures and energy flux predicted enabled the reduction in the power required for de-icing. The weight penalty associated with electro-thermal anti-icing/de-icing method could be eliminated using this method without under estimating the de-icing power requirement.
", keywords = "Aircraft de-icing system, electro-thermal, in-flight icing.", volume = "8", number = "6", pages = "1090-8", }
