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LIMIT CYCLE OSCILLATION PREDICTION AND CONTROL DESIGN METHOD FOR AEROELASTIC SYSTEM BASED ON NEW NONLINEAR REDUCED ORDER MODEL

MOE Key Laboratory for Strength & Vibration, College of Aerospace, Xi'an Jiaotong University, Xi'an, PRC, 710049, P. R. China

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YUE-MING LI

MOE Key Laboratory for Strength & Vibration, College of Aerospace, Xi'an Jiaotong University, Xi'an, PRC, 710049, P. R. China

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GUI-RONG YAN

MOE Key Laboratory for Strength & Vibration, College of Aerospace, Xi'an Jiaotong University, Xi'an, PRC, 710049, P. R. China

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https://doi.org/10.1142/S0219876211002435Cited by:9 (Source: Crossref)

Abstract

When the amplitude of the oscillation of the unsteady flow is large or there is large perturbation relative to the mean background flow, the traditional proper orthogonal decomposition/reduced order model (POD/ROM) based on linearized time or frequency domain small disturbance solvers cannot capture the main nonlinear features well such as limit cycle oscillation (LCO), which is very dangerous for the structure. Therefore, the traditional linear ROMs are not good enough for limit cycles prediction and active control law design. A new nonlinear ROM based on dynamically nonlinear flow equation NPOD/ROM was investigated. The nonlinear second-order snapshot equation in time domain for POD basis construction is obtained from the Taylor series expansion of the flow solver. The simulation results indicate that the NPOD/ROM can capture LCO very well and is also very convenient for active control law design, while the traditional POD/ROM lose effectiveness.

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References

K. J. Badcock and M. A. Woodgate, AIAA J. 45(6), 1370 (2007). Google Scholar
Chen, G., Li, Y. M. and Patrick, H. [2010] Design of Active Control Law for Aeroelastic System Based on Proper Orthogonal Decomposition Reduced Order Model, AIAA-2010-2624 . Google Scholar
G. Dietz, G. Schewe and H. Mai, J. Fluids Structures 19(1), 1 (2004), DOI: 10.1016/j.jfluidstructs.2003.07.019. Crossref, Web of Science, Google Scholar
E. Dowell, J. Edwards and T. Strganac, J. Aircraft 40(5), 857 (2003), DOI: 10.2514/2.6876. Crossref, Web of Science, Google Scholar
E. H. Dowell, J. P. Thomas and K. C. Hall, J. Fluids Structures 19(1), 17 (2004), DOI: 10.1016/j.jfluidstructs.2003.07.018. Crossref, Web of Science, Google Scholar
G. Hu and E. H. Dowell , Physics-based identification, modeling and management infrastructure for aeroelastic limit-cycle oscillations , US Air Force Annual Structural Dynamics Conference ( 2008 ) . Google Scholar
Lai, K. L. and Tsai, H. M. [2008] Reduced-order based flutter analysis for complex aeroelastic systems, AIAA-2008-6240 . Google Scholar
T. Lieu, C. Farhat and M. Lesoinne, Comp. Methods Appl. Mech. Eng. 195, 5730 (2006). Crossref, Web of Science, Google Scholar
D. J. Lucia, P. S. Beran and W. A. Silva, Prog. Aerospace Sci. 40(1), 51 (2004), DOI: 10.1016/j.paerosci.2003.12.001. Crossref, Web of Science, Google Scholar
M. Riccardo and T. Patrizio , Nonlinear Control Design: Geometric, Adaptive and Robust , 1st edn. ( Pearson Education Limited , Italy , 1996 ) . Google Scholar
J. P. Thomas, E. H. Dowell and K. C. Hall, J. Aircraft 40(3), 544 (2003), DOI: 10.2514/2.3128. Crossref, Web of Science, Google Scholar
J. P. Thomas, E. H. Dowell and K. C. Hall, J. Aircraft 41(6), 1266 (2004), DOI: 10.2514/1.9839. Crossref, Web of Science, Google Scholar
J. P. Thomas, E. H. Dowell and K. C. Hall, J. Aircraft 41(6), 1266 (2004), DOI: 10.2514/1.9839. Crossref, Web of Science, Google Scholar
Thomas, J. P. and Dowell, E. H. and Hall, K. C. [2008] Using automatic differentiation to create a nonlinear reduced order model of a computational fluid dynamic solver, AIAA-2008-2322 . Google Scholar