SAE Aero 2017 Midterm Presentation Joe Zongolowicz, Nick Montana, Frank Dixon, Kevin Scheventer, Kathy Hansen, Marquis Ward, Gerald Short, Zhangsiwen Xiao,

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Presentation transcript:

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,

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

Terminology

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

Aircraft Configuration Long, Thin Wing 20 ft span, 17.10 in Mean Chord Large Area, High Efficiency 1.35 lbs Drag @ Cruise Maximize Roll Stability Eppler 423 Hi-lift Foil Small pitching moment -.005 @ Cruise 0.27 ft-lb torque nose down Optimized Tail Boom Maximize Pitch/Yaw Control Minimum Wetted Area

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

Wing Structure Testing

Tail Design Conventional Tail with Single Vertical Stabilizer Vertical Tail Height: 6.98 in Mean Chord: 3.49 in Horizontal Tail Span: 57.35 in Mean Chord: 12.75 in Structural Test of Representative Horizontal Tail Increase Stiffness Minimize Weight

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

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%

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

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

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)

QUESTIONS?