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Simulating an Insect-Scale Flapping Wing Air Vehicle

Simulating an Insect-Scale Flapping Wing Air Vehicle. Ben Parslew, Bill Crowther & Antonio Filippone Aerospace Engineering · The University of Manchester, UK benparslew@hotmail.com. Design Functionality. Background >> Method >> Results >> Conclusions. Design Functionality.

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Simulating an Insect-Scale Flapping Wing Air Vehicle

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  1. Simulating an Insect-Scale Flapping Wing Air Vehicle Ben Parslew, Bill Crowther & Antonio Filippone Aerospace Engineering · The University of Manchester, UK benparslew@hotmail.com

  2. Design Functionality Background >> Method >> Results >> Conclusions

  3. Design Functionality Background >> Method >> Results >> Conclusions

  4. Design Functionality Background >> Method >> Results >> Conclusions

  5. Design Functionality Background >> Method >> Results >> Conclusions

  6. Design Functionality Background >> Method >> Results >> Conclusions

  7. Design Functionality Background >> Method >> Results >> Conclusions

  8. Thrust Generation flexural centre wing Background >> Method >> Results >> Conclusions

  9. Thrust Generation flexural centre wing aerodynamic force passive rotation Background >> Method >> Results >> Conclusions

  10. Thrust Generation flexural centre wing aerodynamic force passive rotation Background >> Method >> Results >> Conclusions

  11. Thrust Generation flexural centre wing aerodynamic force passive rotation net thrust Background >> Method >> Results >> Conclusions

  12. Thrust Generation flexural centre wing aerodynamic force passive rotation net thrust net thrust Background >> Method >> Results >> Conclusions

  13. Aim • Construct a robust theorerical model • Simulate structural dynamics and aerodynamic loads • Identify design changes to increase efficiency & effectiveness Background >> Method >> Results >> Conclusions

  14. Simulation Method Background>> Method >> Results >> Conclusions

  15. Modelling Philosophy discrete element model complex aeroelastic system Background>> Method >> Results >> Conclusions

  16. System Identification experimental measurements discrete element model finite element modelling Background>> Method >> Results >> Conclusions

  17. System Identification experimental measurements discrete element model mass & stiffness properties finite element modelling Background>> Method >> Results >> Conclusions

  18. Measured deflection base plate Driver plate Step Response Experiments Background>> Method >> Results >> Conclusions

  19. Measured deflection base plate Driver plate Step Response Experiments -natural frequency -damping ratio Background>> Method >> Results >> Conclusions

  20. Measured deflection base plate Driver plate Step Response Experiments -natural frequency -damping ratio highly underdamped response Background>> Method >> Results >> Conclusions

  21. Eigenfrequency Analysis -natural frequency -amplitude ratio Background>> Method >> Results >> Conclusions

  22. System Identification discrete element model mass & stiffness properties experimental & finite element data Background>> Method >> Results >> Conclusions

  23. θ System Identification discrete element model wing models -Binary -Elastic mass & stiffness properties experimental & finite element data Background>> Method >> Results >> Conclusions

  24. θ System Identification discrete element model wing models -Binary -Elastic -Quasi-steady “blade-element” theory -Lift and drag: functions of angle of attack; obtained from experimental data mass & stiffness properties experimental & finite element data Background>> Method >> Results >> Conclusions

  25. System Dynamics discrete element model Background>> Method >> Results >> Conclusions

  26. Results Background>> Method >> Results >> Conclusions

  27. Force Time Histories Wing rotation, θ (deg.) Thrust, T (mN) T θ Background>> Method >> Results >> Conclusions

  28. Hovering Flight Background>> Method >> Results >> Conclusions

  29. Frequency Response Background>> Method >> Results >> Conclusions

  30. Conclusions • Low system damping • structure & wings can be design independently • large number of cycles to reach steady state oscillation • Binary wing is more robust than the elastic wing – • yields maximum thrust over broad range of frequencies Background>> Method >> Results >> Conclusions

  31. Simulating an Insect-Scale Flapping Wing Air Vehicle Ben Parslew, Bill Crowther & Antonio Filippone Aerospace Engineering · The University of Manchester, UK benparslew@hotmail.com

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