2. SAE Aero East 2017 MAE 434W

3. Graduate Advisor Brian Duvall Advisor Dr. Drew Landman
Group Members
Andrew Hellmann
Mark Michielsen
Jordan Roque
Aaron Calkins
Sarah Arms
Stacey LeGrand
David Ewing
Tonya White
Graduate Advisor Brian Duvall
Advisor Dr. Drew Landman

4. The aero east competition
Sponsored by the Society of Automotive Engineers
International competition, limited to 75 teams
To compete successfully requires:
Working in a team environment
Time management and meeting deadlines
The submission of a technical report prior to competing
All the above provide exposure to the real world design and manufacturing process

5. Odu’s 4th year fielding a team All teams have been very competitive
Last year finished 6th out of 35 teams
Previous years placed 12th and 13th
This year we expect to improve on last year’s placing

6. Aircraft Design Process
For 2017 intermediate class rules changed
Payload
A/C dimensions
Scoring
Propulsion limitations unchanged

7. Aircraft Design Process
Required an original design Increased payload volume
Removal of dimension constraints
Takeoff distance limited
Landing distance limited
“Passengers” required to be accompanied by a mass of luggage

8. Aircraft Design Process
Several design configurations considered
Blended wing
Flying wing
Promising, but require design validation and testing
Due to time limitations, a conventional monoplane design was selected.
Large amount of design work completed over summer by previous team members

9. Previous Design – Truss Current Proposition – Semi-monocoque
Fuselage Design
Previous Design – Truss
Current Proposition – Semi-monocoque
Easy to design
Easy to fix
Common with model aircraft
Improved aerodynamics
Simple to manufacture
Used on most full size aircraft.

10. Semi-monocoque Load bearing shell with integral frames
Stringers and longerons run forward and aft connecting formers
Formers define overall shape of aircraft
Stringers add strength and aid in contouring the aircraft skin
Allows for easier configuration of internal layout

11. Repaired upper stringer View of fuselage interior looking aft

12. Spar Design Designed using MSC Nastran/Patran
Finite Element analysis method
Tested for internal stress and deflection

13. Overall 2017 Aircraft layout

14. Wing testing reason and methodology
Testing for single spaced ribs vs double spaced ribs
Testing for covering on vs covering off
Measured deflection in a bending test
Measured deflection in a torsional test

15. Wing testing overview Using the previous competition wing design
Mounting is shown in the far left of the picture
Testing for strength to avoid over engineering
Picture is representative of bending test

16. Wing testing results
Bending test of double spaced wing went to failure after sufficient data was gathered
Held a total of lbs of sand
Failure may have been due to shifting sand bags

17. Luggage Compartment Requirements
Compartment Size
Nothing dictated in rules
Limiting factor: airplane design
Working Area: approx. 7” x 7” x 3”
Weight
Minimum:
½ lbf per passenger
Weight for 60 passengers = 30 lbf
Maximum:
¾ lbf per passenger
Weight for 60 passengers = 40 lbf

18. Luggage Compartment Design
Compartment Size
7” x 7” x 3”
Snug fit to restrict movement
Materials
Steel
High density
Approved in rules
Tack Welded
Design Weight
Empty Weight: Approx lbf
Maximum Capacity: Approx lbf

19. Covering Material Test
Rational
Testing suggests overbuilt wing design
Covering material was previously ignored in calculations
No literature on mechanical properties of Coverlite

20. Covering Material Test
Method
Test designed to determine adhesive and tensile strength
Material loaded with incrementally increasing tension

21. Results
Modulus of Elasticity
Ultimate Tensile Strength
Failure due to excessive creeping.

22. Landing Gear Landing gear design finalized
Bicycle type gear with outriggers
Minimal drag penalty
Main gear attached directly to payload bay
Steerable rear wheel for ground handling

23. Landing Gear Conceptual Design
Made of aluminum
Notched 4 spoke
design to save weight
O-ring used for tire
and simplicity
Shock absorption
from plastic cylinder
Tab bolted to fuselage
with pivot point for trailing
Arm
Rejected in favor of a simpler
system

24. Landing Gear Commercial Radio Control Landing gear strut
48 lb/in spring to absorb bumps on runway
Modified roller-skate wheel
Mounted directly to payload bay for most direct load transfer

25. Timetable

26. Frank Batten College of Engineering