Dane Batema John Tapee

Audrey Serra Patricia Roman

Kyle Ryan Carlos Vergara

Benoit Blier Drew Capps

Team 1:

Lessons Learned and Vehicle Summary

Team “Canard”

December 7th, 2006

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Overview

Aircraft Summary:

- Aircraft Properties

- Aerodynamic Constants

- Propulsion Constants

Aircraft Details:

- Propulsion

- Aerodynamics

- Controls

- Structures

Lessons Learned:

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Aircraft Properties

Length (in) 48.2

Wingspan (in) 60.5

Weight (lbf) (w/o payload) 4.4

Weight (lbf) (w/ payload) 5.4

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Aerodynamic PropertiesWing Airfoil MH 43

Wing AR 5.87

Wing Area (ft2) 4.33

Horizontal Tail Airfoil NACA 0006

Horizontal Tail AR 4.92

Horizontal Tail Area (ft2) 0.81

Vertical Tail Airfoil NACA 0006

Vertical Tail Area (ft2) 0.31

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Propulsion Constants

Propeller Dimensions 11x10

Gear Ratio 4.44

Motor Kv (RPM/Volt) 1700

Motor R (Ohms) 0.017

Motor I0 (Amps) 1.9

Battery Nominal Voltage 22.2 V

Battery Peak Current 24.0 A

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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

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Propulsion on Demonstration Day-Lost power during flight

-Reason: Pinion came off motor shaft

-Locktite failed

-Retested on Tuesday (Dec. 5th) – same problem

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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

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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

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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

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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

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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

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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

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Tailwheel

-Tailwheel solution worked very well

-Effective

-Simple

-Cheap

-Low drag

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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

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Lessons Learned

-Measure EVERYTHING!!-Had we checked the manufacturer’s shaft length specification, we would have been able to use the original gearbox

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Lessons LearnedWood construction requires LOTS of sanding

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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

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Benoit is ALWAYS Right

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Quack Quack