SAE Aero 2017 Status Update Joe Zongolowicz, Thomas Houck, Kathy Hansen, Gerald Short, Marquis Ward, Zhangsiwen Xiao, Coleman Gordon, Kevin Scheventer,

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Presentation transcript:

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

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 must carry as much Passengers and Luggage as Possible Aircraft cannot exceed 55 lbs All Up Weight Project Criteria

Modifications to 2016 Design Longer Wing Span New Tail Wider & Longer Fuselage New Landing Gear Re-spec’d Propeller Modifications to 2016 Design

Aircraft Configuration Longer Wing Higher Aspect Ratio Longer Tail Boom Same Airfoil, Eppler 423 Aircraft Configuration

Aircraft Configuration Half the Drag 0.041 v. 0.07 Double the Lift 56 lbs v. 28 lbs @ 30 mph Lower Pitching Moment -0.42 v. -0.515 @ 6 deg A.O.A. Aircraft Configuration

Wing & Tail Structural Design Wing Structure to be Lightened Single Vertical Tail Redesigned Spars in Horizontal Tail Wing & Tail Structural Design

Wing & Tail Structure TEST PLAN Single spaced test wing will have ribs spaced at 2 inch intervals as designed. Double spaced test wing will have ribs spaced at 4 inch intervals. Tests on each wing: Deflection testing without skin Deflection testing with skin Torsion testing with skin Wing & Tail Structure TEST PLAN

Fuselage Design Warren Truss Tail Boom v. Pratt Truss Increased Cross Sectional Area Accommodate Passengers and Luggage Test New Design to Failure Compare with MAE434W Design Semi-Monocoque Fuselage Fuselage Design

Landing Gear design Thorough Analysis Completed Spring 2016 Simple Axle Design Chosen Design Modified with Springs and Dampers for Larger Aircraft Landing Gear design

MOTOR & Propeller Specification Motor Selection Validated in Spring 2016 Analyzed using eCalc Fall 2016 will Analyze Multiple Propellers Analysis will use eCalc and Crotor Propellers will Undergo Wind Tunnel Testing to Validate Analysis Goal is to increase Efficiency and Thrust MOTOR & Propeller Specification

QUESTIONS?