1 / 31

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.

kyrie
Download Presentation

Simulating an Insect-Scale Flapping Wing Air Vehicle

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript


  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

More Related