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Year 2011, Volume 01, Issue 2, 237 - 253, 01.12.2011

Abstract

References

  • [1] Shubov, M. A., (2004), Mathematical Modeling and Analysis of Flutter in Bending-Torsion Coupled Beams, Rotating Blades and Hard Disk Drives, Journal of Aerospace Engineering, Vol. 17, pp. 256– 269.
  • [2] Shubov, M. A., (2006), Flutter Phenomenon in Aeroelasticity and Its Mathematical Analysis, Journal of Aerospace Engineering, Vol. 19, No. 1.
  • [3] Goura, G., (2001), Time Marching Analysis of Flutter Using Computational Fluid Dynamics, (Phd Thesis), University of Glasgow Department of Aerospace Engineering.
  • [4] Dorf, R. C., Bishop, R. H., (2008), Modern Control Systems, Prentice Hall.
  • [5] Murty, H. S., (1995), Aeroelastic Stability Analysis of an Airfoil with Structural Nonlinearities Using a State Space Unsteady Aerodynamics Model, AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, New Orleans, USA.
  • [6] Borglund, R., (2007), Robust Aeroelastic Analysis in the Laplace Domain: The µ-p Method, International Forum on Aeroelasticity and Structural Dynamics, Stockholm, Sweden.
  • [7] Eller, D., (2009), Aeroelasticity and Flight Mechanics: Stability Analysis Using Laplace-Domain Aerodynamics, International Forum on Aeroelasticity and Structural Dynamics, Seattle, USA.
  • [8] Lee, B. H. K., (1984), A Study of Transonic Flutter of a Two-Dimensional Airfoil Using the U-g and p-k Methods, Canada National Research Council Aeronautical Report.
  • [9] Ju, Q. and Qin, S., (2009), New Improved g Method for Flutter Solution, Journal of Aircraft, Vol. 46, No. 6, pp. 1284-1286.
  • [10] Bisplinghoff, R. L., Ashley, H. and Halfman, R. L., (1955), Aeroelasticity, Addison-Wesley Publishing Company.
  • [11] Dowell, E. H., Crawley, E. F., Curtiss Jr., H. C., Peters, D. A., Scanlan, R. H. and Sisto, F., (1995), A Modern Course in Aeroelasticity, Kluwer Academic Publishers.
  • [12] Yates, E., (1985), Standard Aeroelastic Configurations for Dynamic Response I-Wing 445.6, AGARD Report No.765.
  • [13] Scanlan, R. H. and Rosenbaum, R., (1951), Introduction to the Study of Aircraft Vibration and Flutter, The Macmillan Company.
  • [14] Nikbay, M., Fakkusoglu, N. and Kuru, M. N., (2010), Reliability Based Multi-disciplinary Optimization of Aeroelastic Systems with Structural and Aerodynamic Uncertainties, 13th AIAA/ISSMO Multidisciplinary Analysis and Optimization (MAO) Conference, Fort Worth, Texas, USA.
  • [15] Beaubien, R. J., Nitzsche, F. and Feszty, D., (2005), Time and Frequency Domain Flutter Solutions for the AGARD 445.6 Wing, International Forum on Aeroelasticity and Structural Dynamics, Munich, Germany.
  • [16] Lee-Rausch, E. M. and Batina, J. T., (1993), Calculation of AGARD Wing 445.6 Flutter Using Navier-Stokes Aerodynamics, AIAA 11th Applied Aerodynamics Conference, Monterey, California.
  • [17] Allen, C. B., Jones, D., Taylor, N. V., Badcock, K. J., Woodgate, M. A., Rampurawala, A. M., Cooper, J. E. and Vio, G. A., (2004), A Comparison of Linear and Non-Linear Flutter Prediction Methods: A Summary of PUMA DARP Aeroelastic Results, Royal Aeronautical Society Aerodynamics Conference, London.
  • [18] Kolonay, R. M., (2002), Computational Aeroelasticity, Presented in Technical Course Organized by The Applied Vehicle Technology Panel (AVT) on Application of Adaptive Structures in Active Aeroelastic Control, METU, Ankara, Turkey

INTEGRATING ANALYTICAL AEROELASTIC INSTABILITY ANALYSIS INTO DESIGN OPTIMIZATION OF AIRCRAFT WING STRUCTURES

Year 2011, Volume 01, Issue 2, 237 - 253, 01.12.2011

Abstract

Two analytical flutter solution approaches have been developed to optimize two and three dimensional aircraft wing structures with design criteria based on aeroelastic instabilities. The first approach uses open loop structural dynamics and stability analysis for a two dimensional wing model in order to obtain the critical speeds of flutter, divergence and control reversal for optimization process. The second approach involves a flutter solution for three dimensional wing structures by using assumed mode technique and is applied to aeroelastic optimization based on flutter criterion efficiently. This flutter solution employs energy equations and Theodorsen function for aerodynamic load calculation and is fully-parametric in terms of design variables which are taper ratio, sweep angle, elasticity and shear modulus. Since bending and torsional natural frequencies are required for flutter solution, a free vibration analysis of aircraft wing is developed analytically as well. The analytical results obtained for flutter solution of AGARD 445.6 wing model for Mach number of 0.9011 are found to be compliant with the experimental results from literature. Next, the three dimensional flutter code is coupled with optimization framework to perform flutter based optimization of AGARD 445.6 to maximize the flutter speed.

References

  • [1] Shubov, M. A., (2004), Mathematical Modeling and Analysis of Flutter in Bending-Torsion Coupled Beams, Rotating Blades and Hard Disk Drives, Journal of Aerospace Engineering, Vol. 17, pp. 256– 269.
  • [2] Shubov, M. A., (2006), Flutter Phenomenon in Aeroelasticity and Its Mathematical Analysis, Journal of Aerospace Engineering, Vol. 19, No. 1.
  • [3] Goura, G., (2001), Time Marching Analysis of Flutter Using Computational Fluid Dynamics, (Phd Thesis), University of Glasgow Department of Aerospace Engineering.
  • [4] Dorf, R. C., Bishop, R. H., (2008), Modern Control Systems, Prentice Hall.
  • [5] Murty, H. S., (1995), Aeroelastic Stability Analysis of an Airfoil with Structural Nonlinearities Using a State Space Unsteady Aerodynamics Model, AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, New Orleans, USA.
  • [6] Borglund, R., (2007), Robust Aeroelastic Analysis in the Laplace Domain: The µ-p Method, International Forum on Aeroelasticity and Structural Dynamics, Stockholm, Sweden.
  • [7] Eller, D., (2009), Aeroelasticity and Flight Mechanics: Stability Analysis Using Laplace-Domain Aerodynamics, International Forum on Aeroelasticity and Structural Dynamics, Seattle, USA.
  • [8] Lee, B. H. K., (1984), A Study of Transonic Flutter of a Two-Dimensional Airfoil Using the U-g and p-k Methods, Canada National Research Council Aeronautical Report.
  • [9] Ju, Q. and Qin, S., (2009), New Improved g Method for Flutter Solution, Journal of Aircraft, Vol. 46, No. 6, pp. 1284-1286.
  • [10] Bisplinghoff, R. L., Ashley, H. and Halfman, R. L., (1955), Aeroelasticity, Addison-Wesley Publishing Company.
  • [11] Dowell, E. H., Crawley, E. F., Curtiss Jr., H. C., Peters, D. A., Scanlan, R. H. and Sisto, F., (1995), A Modern Course in Aeroelasticity, Kluwer Academic Publishers.
  • [12] Yates, E., (1985), Standard Aeroelastic Configurations for Dynamic Response I-Wing 445.6, AGARD Report No.765.
  • [13] Scanlan, R. H. and Rosenbaum, R., (1951), Introduction to the Study of Aircraft Vibration and Flutter, The Macmillan Company.
  • [14] Nikbay, M., Fakkusoglu, N. and Kuru, M. N., (2010), Reliability Based Multi-disciplinary Optimization of Aeroelastic Systems with Structural and Aerodynamic Uncertainties, 13th AIAA/ISSMO Multidisciplinary Analysis and Optimization (MAO) Conference, Fort Worth, Texas, USA.
  • [15] Beaubien, R. J., Nitzsche, F. and Feszty, D., (2005), Time and Frequency Domain Flutter Solutions for the AGARD 445.6 Wing, International Forum on Aeroelasticity and Structural Dynamics, Munich, Germany.
  • [16] Lee-Rausch, E. M. and Batina, J. T., (1993), Calculation of AGARD Wing 445.6 Flutter Using Navier-Stokes Aerodynamics, AIAA 11th Applied Aerodynamics Conference, Monterey, California.
  • [17] Allen, C. B., Jones, D., Taylor, N. V., Badcock, K. J., Woodgate, M. A., Rampurawala, A. M., Cooper, J. E. and Vio, G. A., (2004), A Comparison of Linear and Non-Linear Flutter Prediction Methods: A Summary of PUMA DARP Aeroelastic Results, Royal Aeronautical Society Aerodynamics Conference, London.
  • [18] Kolonay, R. M., (2002), Computational Aeroelasticity, Presented in Technical Course Organized by The Applied Vehicle Technology Panel (AVT) on Application of Adaptive Structures in Active Aeroelastic Control, METU, Ankara, Turkey

Details

Primary Language English
Journal Section Research Article
Authors

Melike NİKBAY This is me
Istanbul Technical University, Faculty of Aeronautics and Astronautics, Astronautical Engineering Department, Maslak, Istanbul, 34469, Turkey


Pinar ACAR This is me
Istanbul Technical University, Faculty of Aeronautics and Astronautics, Astronautical Engineering Department, Maslak, Istanbul, 34469, Turkey

Publication Date December 1, 2011
Published in Issue Year 2011, Volume 01, Issue 2

Cite

Bibtex @ { twmsjaem761801, journal = {TWMS Journal of Applied and Engineering Mathematics}, issn = {2146-1147}, eissn = {2587-1013}, address = {Işık University ŞİLE KAMPÜSÜ Meşrutiyet Mahallesi, Üniversite Sokak No:2 Şile / İstanbul}, publisher = {Turkic World Mathematical Society}, year = {2011}, volume = {01}, number = {2}, pages = {237 - 253}, title = {INTEGRATING ANALYTICAL AEROELASTIC INSTABILITY ANALYSIS INTO DESIGN OPTIMIZATION OF AIRCRAFT WING STRUCTURES}, key = {cite}, author = {Nikbay, Melike and Acar, Pinar} }