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Aeroelastic Response Estimation of Airplane's Aileron Input

Verify the classical analytical approach for estimating an airplane's aeroelastic response to aileron input by investigating the effects of structural flexibility. Manipulate the solution using time-proven graphs and formulas that are limited to a certain group of aeronautical designs neglecting structural flexibility effects. Use finite element method (FEM) to determine the time history of the aeroelastic response. Consider both a flexible aircraft beam and a complex 3D aircraft in the analysis.

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Aeroelastic Response Estimation of Airplane's Aileron Input

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Presentation Transcript

  1. Objective ESTIMATION OF AIRPLANE’S AEROELASTIC RESPONSE TO AILERON INPUT VERIFICATION OF CLASSICAL ANALYTICAL APPROACH EFFECTS OF STRUCTURAL FLEXIBILITY

  2. Analytical Solution MANIPULATION WITH TIME PROVEN GRAPHS AND FORMULAS LIMITED TO A CERTAIN GROUP OF AERONAUTICAL DESIGNS NEGLECTING STRUCTURAL FLEXIBILITY EFFECTS

  3. Using FEM TIME HISTORY OF AEE RESPONSE ARBITRARY DEFINITION OF INPUT PROPERTIES FLEXIBLE AIRCRAFT

  4. Beam vs. Complex 3D

  5. Aircraft Dimensions: Weights: Performance: Span 16.2 m Max. Take-Off Max. Allowed Length 8.4 m Weight: 680 kg Speed: 245 km.h-1

  6. Aircraft

  7. FEM Model

  8. FEM Model

  9. FEM Model

  10. FEM Model

  11. FEM Model

  12. Modal Analysis

  13. Modal Analysis

  14. Modal Analysis

  15. STRUCTURAL MODEL AERO PANELING Aeroelastic Model

  16. Aileron Response

  17. Aileron Response Input Profile Definition

  18. Aileron Response

  19. Results

  20. Results Rolling Due to Aileron Deflection

  21. Results Rolling Due to Aileron Deflection

  22. Type of solution Roll Rate Stability Derivative Ratio Analytical 0.8214 -0.6237 Dynamic 0.8204 -0.6256 Results Comparing Results

  23. Explanation ENCOUNTERING LITTLE INERTIA RESISTANCE SUFFICIET STRUCTURAL RIGIDITY OF THE SYSTEM

  24. Results

  25. Results

  26. Thank you for your attention

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