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

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

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

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

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

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

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

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

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

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

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

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

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

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

15. complex aeroelastic system discrete element model
Modelling Philosophy
complex aeroelastic system
discrete element model
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. Step Response Experiments
Measured deflection
base plate
Driver plate
Background >> Method >> Results >> Conclusions

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

20. Step Response Experiments
Measured deflection
base plate
Driver plate
-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 experimental & finite element data
discrete element model
experimental & finite element data
mass & stiffness properties
Background >> Method >> Results >> Conclusions

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

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

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

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

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

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

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

30. Background >> Method >> Results >> 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