Modification of aerodynamic wing loads by fluidic devices

• Autorzy: Stalewski W. , Sznajder J.

Identyfikatory

DOI

10.5604/12314005.1133229

• Języki publikacji: EN

Abstrakty

EN

Airplane wing load control systems are designed for modification/redistribution of aerodynamic loads in order to decrease risk of structural damage in conditions of excessive loads, to improve passenger comfort in turbulent atmosphere or to act as flight control systems. Classical examples include systems involving symmetric deflections of ailerons reducing wing root bending moments (Lockheed C-5 Galaxy) or deflections of spoilers stabilizing landing approach path (Lockheed TriStar). The fast development of Micro Electromechanical Systems and their application in Flow Control System opens the perspectives of designing practical wing load control systems based on fluidic actuators, modifying local aerodynamic loads by inducing changes to flow, for example, by inducing flow separation in the boundary layer or modifying Kutta condition on the trailing edge. This is the principle of operation of novel concepts of flow control actuators proposed by Institute of Aviation and discussed in the paper. The systems include actuators in the central part of the wing section, reducing local lift similarly to classical spoilers and actuators on the modified trailing edge, acting similarly to ailerons. The potential advantages in comparison to classical devices include potentially shorter reaction time because of avoiding the necessity of moving large surfaces against high dynamic pressure, which is important in conditions of fast-changing loads in turbulent atmosphere.

Słowa kluczowe

EN

transport; aircraft engineering; mechanical engineering

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2014
• Tom: Vol. 21, No. 3
• Strony: 271--278
• Opis fizyczny: Bibliogr. 7 poz., rys.

Twórcy

autor

Stalewski W.

• Institute of Aviation Department of Aerodynamics and Flight Mechanics Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.:[phone] ext. 492, fax: [phone]

autor

Sznajder J.

• Institute of Aviation Department of Aerodynamics and Flight Mechanics Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.:[phone] ext. 492, fax: [phone]

Bibliografia

• [1] Englar, R. J., Overview of Circulation Control Pneumatic Aerodynamics: Blown Force and Moment Augmentation and Modification as Applied Primarily to Fixed-Wing Aircraft, in: Applications of Circulation Control Technologies, Edited by R. D. Joslin, G. S. Jones, Progress In Astronautics And Aeronautics, Vol. 214, pp. 23-45, 2006.
• [2] Englar, R. J., Smith, M. J., Kelley, S. M., Rover, R. C. III, - Application of Circulation Control to Advanced Subsonic Transport Aircraft, part I: Airfoil development, Journal of Aircraft,Vol. 31,No. 5,pp. 1160-1168, 1994.
• [3] Jones, G. S., Pneumatic Flap Performance for a Two-Dimensional Circulation Control Airfoil, Applications of Circulation Control Technologies. Edited by R. D. Joslin, G. S. Jones, Progress in Astronautics and Aeronautics, Vol. 214, AIAA, Chapt. 7, pp. 191-243, Reston, VA 2006.
• [4] Jabbal, M., Liddle, S. C., Crowther, W. J., Active Flow Control Systems Architectures for Civil Transport Aircraft, Journal of Aircraft, Vol. 47, No. 6, pp. 1966-1981, 2011.
• [5] Moulin, B., Karpel, M., Gust Loads Alleviation Using Special Control Surfaces, Journal of Aircraft, Vol. 44, No. 1, pp. 17-25, 2007.
• [6] Yarf-Abbasi, A., Clarke, A., Lawson, C. P., Fielding, J. P., Design and Development of the Eclipse and Demon Demonstrator UAVs, 26th International Congress Of The Aeronautical Sciences, ICAS, 2008.
• [7] Seifert, A., David, S., Fono, I., Stalnov, O., Dayan, I., Roll Control via Active Flow Control: From Concept to Flight, Journal of Aircraft, Vol. 47, No. 3, pp. 864-874, 2010.