Prabha Srinivasan, Ashok Joshi, Hemalatha E
DOI Number: N/A
Conference number: IFASD-2015-001
The present study focuses on the use of optimization methods for finite element model updation, with the specific objective of achieving improved servoelastic response predictions. Test-analysis deviations of the frequency and mode shapes are generally minimized based on the frequency difference and the modal assurance criterion values. To minimize the differences between analytical and test frequency responses, multiple objective functions are set up based on the frequency domain assurance criterion. Model updation is carried out using genetic algorithms and the approach is illustrated on a generic flexible airvehicle. Fitness functions are set up to improve the test analysis correlations of direct longitudinal transfer functions arising from a symmetric wing control surface excitation, namely pitch rate response and normal acceleration response. The improvement in the analytical predictions of important modal responses associated with symmetric bending of wing and fuselage and symmetric pitching of external stores are shown for two different aircraft configurations.