1. SAE Aero 2017
Midterm Presentation Joe Zongolowicz, Nick Montana, Frank Dixon, Kevin Scheventer, Kathy Hansen, Marquis Ward, Gerald Short, Zhangsiwen Xiao, Thomas Houck, Coleman Gordon,

2. Project Criteria Design, Build, and Fly a Remote Control Aircraft
Aircraft must Take Off in 200 ft and Land in 400 ft
Aircraft must be powered by a 1000w power supply
Aircraft cannot exceed 55 lbs Gross Weight
Aircraft must carry as many Passengers and Luggage as Possible
Flight Conditions
25 mph Cruise
45 lbs Gross Weight

3. Terminology

4. Aircraft Design Tool Purpose: Design Aid and Performance Analysis
Created using MS Excel
Input: Mission Profile, Target Payload, Motor Data, Atmospheric Conditions
Output: Size and shape of wing & tail; performance predictions

5. Aircraft Configuration
Long, Thin Wing
20 ft span, in Mean Chord
Large Area, High Efficiency
1.35 lbs Cruise
Maximize Roll Stability
Eppler 423 Hi-lift Foil
Small pitching moment
Cruise
0.27 ft-lb torque nose down
Optimized Tail Boom
Maximize Pitch/Yaw Control
Minimum Wetted Area

6. Wing Structure Testing
2 Test wings: 3 in airfoil spacing vs. 6 in airfoil spacing
Deflection testing (uncovered and covered)
Loads
Load 1 (lb)
Load 2 (lb)
Load 3 (lb)
Load 4 (lb)
Load 5 (lb)
Load 6 (lb)
Load 7 (lb)
Total Load (lb)
Trial 1
0.5
0.45
0.3875
0.2625
0.0125 →
2.6125
Trial 2 1
0.9
0.775
0.525
0.025
5.225

7. Wing Structure Testing

8. Tail Design Conventional Tail with Single Vertical Stabilizer
Vertical Tail
Height: 6.98 in
Mean Chord: 3.49 in
Horizontal Tail
Span: in
Mean Chord: in
Structural Test of Representative Horizontal Tail
Increase Stiffness
Minimize Weight

9. Fuselage Design Removed unnecessary vertical supports Pratt Truss
Increased Cross Sectional Area
Accommodate Passengers and Luggage
Tail boom stress testing: 6 lbs
Warren Truss
Compare with MAE434W Design
Semi-Monocoque Fuselage

10. Motor & Propeller Specification
▶ Theoretical Analysis
▶ eCalc and XROTOR
▶ Experimental testing
▶ ODU Low Speed Wind tunnel
▶ On-going Analysis
▶ Previous Propeller: 13 x 5.5
▶ Current Best: 15 x 6
▶ Static Thrust Increase of 0.5 lb or 7.5%

11. Landing Gear: Design
Primary Concerns: shock absorption, weight, and drag
Chosen Design: Hinged Trailing Arm with rubber spring
Simple assembly
Independent wheels
Better handling

12. Landing Gear FEA: Results
Load Scenario
Max Stress (ksi)
Yield Stress (ksi)
FoS
Vertical Bending
22.95
31.18
1.36
Side Load
30.6
1.02

14. Remaining Work Aircraft Design Develop Weight Budget
Finalize outer mold lines in CAD
Design internal structure in CAD
Finish Flight Performance Predictions
Structural Testing
Payload bay stress testing
Wing & Tail Torsion Testing (with and without covering)
Manufacture Airplane
Begin Flight Testing (Design Validation)

15. QUESTIONS?