1. Dane Batema John Tapee Audrey Serra Patricia Roman Kyle RyanCarlos Vergara Benoit BlierDrew Capps Team 1: Lessons Learned and Vehicle Summary Team “Canard” December 7th, 2006

2. AAE 451 Team 1 2 Overview Aircraft Summary: - Aircraft Properties - Aerodynamic Constants - Propulsion Constants Aircraft Details: - Propulsion - Aerodynamics - Controls - Structures Lessons Learned:

3. AAE 451 Team 1 3 Aircraft Properties Length (in) 48.2 Wingspan (in) 60.5 Weight (lbf) (w/o payload) 4.4 Weight (lbf) (w/ payload) 5.4

4. AAE 451 Team 1 4 Aerodynamic Properties Wing Airfoil MH 43 Wing AR 5.87 Wing Area (ft 2 ) 4.33 Horizontal Tail Airfoil NACA 0006 Horizontal Tail AR 4.92 Horizontal Tail Area (ft 2 ) 0.81 Vertical Tail Airfoil NACA 0006 Vertical Tail Area (ft 2 ) 0.31

5. AAE 451 Team 1 5 Propulsion Constants Propeller Dimensions 11x10 Gear Ratio 4.44 Motor Kv (RPM/Volt) 1700 Motor R (Ohms) 0.017 Motor I 0 (Amps) 1.9 Battery Nominal Voltage 22.2 V Battery Peak Current 24.0 A

6. AAE 451 Team 1 6 Propulsion -Improper gearbox dimensions from manufacturer lead to motor stripping gearbox (and extra gearbox) -Backup planetary gearbox provided by Sean; original MEGA motor was modified to fit it -New gearbox caused several aircraft-level changes, chiefly new motor/gearbox mounting scheme -Gearbox issues caused last minute problem solving (and panic) -11x10 propeller used instead of 11x11 (11x11 only available for gas engines) Stripped Gearbox Teeth

7. AAE 451 Team 1 7 Propulsion on Demonstration Day -Lost power during flight -Reason: Pinion came off motor shaft -Locktite failed -Retested on Tuesday (Dec. 5 th ) – same problem

8. AAE 451 Team 1 8 Cooling Intake Cooling Outtake Aerodynamics -Aerodynamic design largely unchanged -Small changes to wetted area of some parts -Drag from cooling intake/outtake for propulsion system difficult to predict and ignored

9. AAE 451 Team 1 9 Dynamics and Controls Vertical Tail Horizontal Tail -D&C remained mostly unchanged -Increased the elevator and flaperon size slightly -Change was made due to experience, and the designed sizes looked small

10. AAE 451 Team 1 10 Wing Structure Main Carbon Spar Fwd -Wing structure remained unchanged from design except the addition of a carbon spar -Spar was removed after the preliminary concept once calculations showed it wasn’t needed -However, spar gives wing some redundancy and added stiffness without adding too much weight

11. AAE 451 Team 1 11 Carbon Robs Fwd Front Main Rib Landing Gear Plate Rear Main Rib Internal Fuselage Structure -Design details of the fuselage ribs were done as part of the build process -Fuselage contains 2 main ribs, both with cutouts to allow access to internal components -Ribs also serve as wing attachment points -Carbon rods shifted below chord line to allow flush fit with fuselage -Ribs were balsa/plywood/balsa laminates, but could have been thinner -An aft balsa rib with holes allowed control rods and wires to pass through and be secured

12. AAE 451 Team 1 12 Replacement Gearbox Aluminum Spacer Mounting Plate Motor Mounting -Originally, there was a rib in the nose that the motor/gearbox mounted to -With the use of a different gearbox, that rib had to be removed -New motor/gearbox assembly mounted to a plywood plate epoxied directly to nose -Access hatch made to access new motor/gearbox assembly -Aluminum spacer needed to position motor pinion correctly Original Mount

13. AAE 451 Team 1 13 Stiffening Wire Landing Gear 4 Mounting Bolts Intake Vent Main Landing Gear -Plywood plate used as landing gear attachment to carry the brunt of the impact load -Aluminum gear initially were attached by 3 bolts, but aircraft oscillated, so 4 bolts were used to stabilize it -Thin wire added to reduce bending and deflection of the struts

14. AAE 451 Team 1 14 Tailwheel -Tailwheel solution worked very well -Effective -Simple -Cheap -Low drag

15. AAE 451 Team 1 15 CG Payload Speed Cntr. Main Batts Receiver Batt Receiver Rate Gyro Component Layout Rate Gyro Rudder Servo Elevator Servo On/Off Switch -Internal components arranged to place CG at the spot selected by the D&C team -CG location gives aircraft a static margin of 17% -Internal component layout closely matched CATIA model -Payload’s CG was positioned very close to empty aircraft’s CG, allowing for payload to be added or removed without excessive rearranging of components

16. AAE 451 Team 1 16 Lessons Learned -Measure EVERYTHING!! -Had we checked the manufacturer’s shaft length specification, we would have been able to use the original gearbox

17. AAE 451 Team 1 17 Lessons Learned Wood construction requires LOTS of sanding

18. AAE 451 Team 1 18 Lessons Learned Not all balsa and plywood are the same, and structural properties change with orientation –This lesson might lead to a lighter aircraft design International makeup of the team had pros and cons –Team members enjoyed learning about other cultures –Three spoken languages made technical communication difficult at times

19. AAE 451 Team 1 19 Benoit is ALWAYS Right

20. AAE 451 Team 1 20 Quack