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Interim Design Review

herne avatar
herne
21 diapositives · 432 Views · Sep 01, 2014

Interim Design Review. Group 13 – Flapping Wing MAV NASA Parker Cook George Heller Joshua Nguyen Brittney Theis. The Customer. Dr. Shih Funding to be provided by the NASA Ames facility. The Problem.

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Interim Design Review
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  1. Interim Design Review Group 13 – Flapping Wing MAV NASA Parker Cook George Heller Joshua Nguyen Brittney Theis

  2. The Customer • Dr. Shih • Funding to be provided by the NASA Ames facility

  3. The Problem • We are tasked with designing and building a micro aerial vehicle (MAV) that is competition legal for the European Micro Air Vehicle Conference and Flight Competition.

  4. Project Scope and Needs

  5. Design Inspiration The Delfly inspired design was chosen as our flapping wing MAV because of its ability to meet our customers needs and has the highest probability to fulfill our design criteria and complete all necessary functions.

  6. Gear Train and Wing Mechanism

  7. Dimensions • Includes • Drivetrain • Wings • Fuselage • Connection rods

  8. Wing Calculations Wingtip speed vs. body mass Wing length vs. body mass Wing loading vs. mass of man made objects

  9. Stiffness effect on wing lift performance Lift and thrust as a function of wing area U=forward flight speed Φ=total flapping angle f=flapping frequency b=wing span

  10. Tiny Pager Motor by Solarbotics Diameter = 4mm (0.158”) Length = 16.4mm (0.65”) Shaft Diameter = 0.66mm (0.026”) Weight = 1g (.035oz) Motor Selection

  11. Gear Size Calculation • Nylon Gears will be used to minimize weight • Frequency will need to be 35Hz • Gear Ratio taken to be 4.81:1

  12. Component Selection Great Planes ElectriFly 4Ch FM Rx 72MHz Hitec Eclipse 7 7-Channel FM/4 Futaba FM Receiver Crystal Short R114F 72MHz High

  13. Component Selection • Servos: • The servos for the control surfaces of the MAV would need to be very tiny, and are not commercially available. • Piezo-electrics were researched, but would require more power than we could supply. Battery: 110mAh 1S 3.7V LiPo: BMCX

  14. Wing Material Selection • McMaster Polyester (PET) Film • Thickness: .001“ • Width: 40“ • Length: 10' • Tensile Strength: 28,000 psi • Clear, No Tint, Weather Resistant

  15. “Bones” Material Selection • McMaster Rigid Carbon Fiber Shape Round Tube • OD: .125“ • ID: .074" • Length: 48" • Tensile Strength: 120,000 psi

  16. Cost Analysis

  17. Conclusion

  18. Bill of Materials

  19. Future Plans • Purchase Materials • Finalize research • Find Torque on the Shaft • Resizing • Find appropriate Servos • Finalize Design Calculations • Finalize Manufacturing Plans

  20. Questions?