Flutter Characteristics ofAircraft Wing Considering Control Surface and Actuator Dynamics with Friction Nonlinearity

Lee, Seung-Jun;Lee, In;Shin, Won-Ho

  • Published : 2007.06.30


Whenever the hinge axis of aircraft wing rotates, its stiffness varies. Also, there are nonlinearities in the connection of the actuator and the hinge axis, and it is necessary to inspect the coupled effects between the actuator dynamics and the hinge nonlinearity. Nonlinear aeroelastic characteristics are investigated by using the iterative V-g method. Time domain analyses are also performed by using Karpel's minimum state approximation technique. The doublet hybrid method(DHM) is used to calculate the unsteady aerodynamic forces in subsonic regions. Structural nonlinearity located in the load links of the actuator is assumed to be friction. The friction nonlinearity of an actuator is identified by using the describing function technique. The nonlinear flutter analyses have shown that the flutter characteristics significantly depends on the structural nonlinearity as well as the dynamic stiffness of an actuator. Therefore, the dynamic stiffness of an actuator as well as the nonlinear effect of hinge axis are important factors to determine the flutter stability.


Dynamic Stiffness;Friction;Nonlinearity;Flutter;DHM


  1. Dulger, L. C. and Uyan, S., 1997, 'Modeling, Simulation and Control of a Four-Bar Mechanism with a Brushless Servo Motor', Mechatronics, Vol. 7, No.4, pp. 369-383
  2. Torfs, D. and Schutter, J. D., 1995', Modeling and Control of a Flexible One-Link Robot Driven by a Velocity Controlled Actuator', Mechanical Systems and Signal Processing, Vol. 9, No.1, pp. 15-29
  3. Ebrahimi, M. and Whalley, R., 2000, 'Analysis, Modeling and Simulation of Stiffness in Machine Tool Drives', Computers & Industrial Engineering, Vol. 38, No.1, pp. 93-105
  4. Guesalaga, A., 2004, 'Modelling End-of-roll Dynamics in Positioning Servos,' Control Engineering Practice, Vol. 12, No.2, pp. 217-224
  5. McIntosh, S. C., Reed R. K Jr. and Rodden, W. P., 1981, 'Experimental and Theoretical Study of Nonlinear Flutter', Journal of Aircraft, Vol. 18, No. 12, pp. 1057-1063
  6. Conner, M. D., Tang, D. M., Dowell, E. H. and Virgin, L. N., 1997, 'Nonlinear Behavior of a Typical Airfoil Section with Control Surface Freeplay: A Numerical and Experimental Study', Journal of Fluids and Structures, Vol. 11, No.1, pp. 89-110
  7. Bae, J. S., Yang, S. M. and Lee, I., 2002, 'Linear and Nonlinear Aeroelastic Analysis of a Fighter-type Wing with Control Surface', Journal of Aircraft, Vol. 39, No.4, pp. 697-708
  8. Woolston, D. S., Runyan, H. W. and Andrews, R. E., 1957, 'Some Effects of System Nonlinearities in the Problem of Aircraft Flutter', NACA TN 3539
  9. Laurenson, R. M. and R. M. Trn, 1980, 'Flutter Analysis of Missile Control Surfaces Containg Structural Nonlinearites', AlAA Journal, Vol. 18, No. 10, pp. 1245-1251
  10. Tavakoli, M. S. and Houser, D. R., 1986, 'Optimum Profile Modifications for the Minimization of Static Transmission Errors of Spur Gears', ASME, Journal of Engineering for Industry, Vol. 108, No.1, pp. 86-9
  11. Paek, S. K., and Lee, I, 'Flutter analysis for control surface of launch vehicle with dynamic stiffness', Computers & Structures, Vol. 60, No.4, pp. 593-599
  12. Shin, W. H., 2007, 'Aeroservoelastic Analysis of Missile Fin Considering Structural Nonlinearity', Ph. D. Thesis, Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology
  13. Gelb A. and Vander Velde, W. E., 1968, 'Multiple-input describing functions and nonlinear system design', McGraw-Hill, Inc.
  14. Karpel, M., 1982, 'Design for Active Flutter Suppression and Gust Alleviation Using State-Space Aeroelastic Modeling', Journal of Aircraft, Vol. 19, No.3, pp. 221-227