Analysis of dynamic response and flutter suppression system effectiveness of a long-haul aircraft in transonic flight mode

Aeronautical and Space-Rocket Engineering

Strength and thermal conditions of flying vehicles


DOI: 10.34759/vst-2020-1-108-121

Аuthors

Kuz’mina S. I.*, Ishmuratov F. Z.**, Popovskii V. N.***, Karas’ O. V.****

Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia

*e-mail: kuzmina@tsagi.ru
**e-mail: fanil.ishmuratov@tsagi.ru
***e-mail: stataer@tsagi.ru
****e-mail: skomorokhov@tsagi.ru

Abstract

The work is devoted to the study of aircraft aeroservoelasticity problems in transonic flight mode. Review of the state-of-the-art methods and computational algorithms used to obtain aeroservoelasticity characteristics was performed.

An agreed usage of the following approaches for the set problems solving is applied in the presented article:

– a method for unsteady aerodynamic forces computation in transonic flow using Euler equations with account for the flow viscosity,

– an algorithm for aircraft aeroelasticity characteristics computing based on the Ritz polynomial method,

– mathematical models of control systems and techniques for aeroservoelasticity problems solving in the frequency, time and root domains.

The developed methodology application has been demonstrated while the developing and studying the flutter suppression system (FSS) for medium-range aircraft with transonic cruise flight mode M=0.82 Numerical results were obtained for the airplane of conventional layout with a high aspect ratio wing and two engines located on pylons under the wing. The results of computational studies of the aircraft dynamic response were obtained employing various aerodynamic models, i.e. transonic and linear ones. The numerical studies revealed that the aircraft does not possess sufficient margins on flutter speed in transonic flight mode. For the given aircraft version the possibilities for flutter speed increase by active control system, which employed symmetrical ailerons deflection were studied. Signals from deflection sensors, located on the wingtips, were are used while FSS developing.

Gain dependence on the speed for optimal flutter 6. suppression was performed based on the frequency characteristics analysis of the open loop in the form of Nyquist locus. For each speed, the gain was selected in in such a way as ensure approximately double stability margin on amplitude. Comparison of damping and frequencies of elastic vibrations dependence on the flight speed for both open and closed loop was performed. Parametric calculations revealed that the developed FSS ensured the flutter speed increase by 45% for the first flutter form, and by 10% for the second one. Stability problem studies of the “aircraft + FSS” closed loop under the external impact. The problem was being solved in time domain.

It was demonstrated that for ensuring the closed loop stability sufficiently higher speed of aileron deflection is required.

The obtained results of the study allowed conclude that two important factors, affecting aero elasticity characteristics, exist at the transonic flow-around:

– basic stationary flow field effeect on the aerodynamic derivatives. Besides the Mach number and density, the basic flow field is determined by the angle of attack, profiles curvature and sections twisting.

– viscosity effect on the aerodynamic derivatives. These two factors are missing from the linear

methods for aerodynamic forces determining, but their regard affects significantly dynamic response of modern aircraft. Application experience of the developed approach demonstrates the possibility for effective solution of the aeroelasticity problems at transonic flight modes.

Keywords:

aeroelasticity, flutter, dynamic response, transonic flow, flutter suppression system

References

  1. Roger K.L., Hodges G.E., Felt L. Active flutter suppression – A flight test demonstration. Journal of Aircraft, 1975, vol. 12, no. 6, pp. 551–556. DOI: 10.2514/3.59833

  2. Nissim E. Active Flutter Suppression Using Trailing- Edge and Tab Control Surfaces. AIAA Journal, 1976, vol. 14, no. 6, pp. 757-762. DOI: 10.2514/3.61416

  3. Sensburg O., Honlinger H., Noll T. and Huttsell L. Active Flutter Suppression on an F-4F Aircraft. Journal of Aircraft, 1982, vol. 19, no. 5, pp. 354-359. DOI: 10.2514/3.57404

  4. Chen G., Sun J., and Li Y.-M. Adaptive Reduced- Order-Model-Based Control-Law Design for Active Flutter Suppression, Journal of Aircraft, 2012, vol. 49, no. 4, pp. 973-980. DOI: 10.2514/1.C031236

  5. Livne Eli. Aircraft Active Flutter Suppression: State of the Art and Technology Maturation Needs. Journal of Aircraft, 2018, vol. 55, no. 1. DOI: 10.2514/1.C034442

  6. Tewari A. Aeroservoelasticity: Modeling and Control. Springer-Verlag New York, 2015, 318 p. DOI: 10.1007/ 978-1-4939-2368-7

  7. Zhang Z., Chen P.C., Yang S., Wang Z., Wang Q. Unsteady Aerostructure Coupled Adjoint Method for Flutter Suppression. AIAA Journal, 2015, vol. 53, no. 8, pp. 2121-2129. DOI: 10.2514/1.j053495

  8. Moulin B. Robust Controller Design for Active Flutter Suppression. AIAA Guidance, Navigation, and Control Conference and Exhibit (16-19 August 2004, Providence, Rhode Island). AIAA Paper 2004-5115. DOI: 10.2514/6.2004-5115

  9. Bykov A.V., Parafes’ S.G., Smyslov V.I. Hardware and software tools for computational and experimental investigations of aircraft aeroelastic stability. Aerospace MAI Journal, 2009, vol. 16, no. 5, pp. 56-63.

  10. Aleshin B.S., Zhivov Yu.G., Kuvshinov V.M., Ustinov A.S. Aktivnye sistemy upravleniya samoletov (Active control system of the aircraft), Moscow, Nauka, 2016, 215 p.

  11. Redd L.T., Gilman Jr., Cooley D.E., Sevart F.D. Wind-Tunnel Investigation of a B-52 Model Flutter Suppression System. Journal of Aircraft, 1974, vol. 11, no. 11, pp. 659-663. DOI: 10.2514/3.60401

  12. Edwards J.W., Wieseman C.D. Flutter and Divergence Analysis Using the Generalized Aeroelastic Analysis Method. Journal of Aircraft, 2008, vol. 45, no. 3, pp. 906-915. DOI: 10.2514/1.30078

  13. Schuster D.M., Liu D.D., Huttsell L.J. Computational Aeroelasticity: Success, Progress, Challenge. Journal of Aircraft, 2003, vol. 40, no. 5, pp. 843-856. DOI: 10.2514/2.6875

  14. Bendiksen O. Review of unsteady transonic aerodynamics: Theory and application. Progress in Aerospace Sciences, 2011, vol. 47, no. 2, pp. 135-167. DOI: 10.1016/j.paerosci.2010.07.001

  15. Danowsky B.P., Lieu T., Coderre-Chabot A. Control Oriented Aeroservoelastic Modeling of a Small Flexible Aircraft Using Computational Fluid Dynamics and Computational Structural Dynamics. AIAA Paper 2016­1749. DOI: 10.2514/6.2016-1749

  16. Bendiksen O. Energy Approach to Flutter Suppression and Aeroelastic Control. Journal of Guidance, Control, and Dynamics, 2001, vol. 24, no. 1, pp. 176-184. DOI: 10.2514/2.4699

  17. Bragin N.N., Kovalev V.E., Skomorokhov S.I., Slitinskaya A.Y. On evaluation of buffeting of a swept wing with high aspect ratio at transonic speeds. Aerospace MAI Journal, 2018, vol. 25, no. 4, pp. 16-27.

  18. Mukhopadhyay V. Transonic Flutter Suppression Control Law Design and Wind-Tunnel Test Results. Journal of Guidance, Control, and Dynamics, 2000, vol. 23, no. 5, pp. 930-937. DOI: 10.2514/2.4635

  19. Kuzmina S., Zichenkov M., Ishmuratov F., Zichenkov M. Investigation of interaction of shock movement with structural elastic deformations in transonic flow. International Forum on Aeroelasticity and Structural Dynamics IFASD-2013 (Bristol, UK, 24-26 June 2013), vol. 3, pp. 1503-1516.

  20. Gudilin A.V., Evseev D.D., Ishmuratov F.Z. et al. Uchenye zapiski TsAGI, 1991, vol. XXII, no. 5, pp. 89-101.

  21. Ishmuratov F.Z., Chedrik V.V. ARGON Code: Structural Aeroelastic Analysis and Optimization. International Forum on Aeroelasticity and Structural Dynamics IFASD-2003 (Amsterdam, 4-6 June 2003).

  22. Zubakov A.V., Zubakova O.V., Ishmuratov F.Z., Timokhin V.P. Svidetel’stvo o gosudarstvennoi registratsii programm dlya EVM “Programmnyi kompleks rascheta i analiza kharakteristik aeroservouprugosti aviatsionnykh konstruktsii FRECAN” no. 2015610225, 12.01.2015 (Certificate of state registration of computer programs “Software complex for calculation and analysis of aeroservoelasticity characteristics of FRECAN aircraft structures”, no. 2015610225, 20.01.2015).

  23. Kuzmina S., Ishmuratov F., Karas O., Chizhov A. Dynamic response of an airplane elastic structure in transonic flow. 29th Congress of the International Council of the Aeronautical Sciences ICAS2014 (St. Petersburg, Russia, 7-12 September 2014).

  24. Kuzmina S., Ishmuratov F., Chizhov A., Karas O. Investigation of viscosity influence on transonic flutter. Transportation Research Procedia, 2018, no. 29, pp.191-201.

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