1. March 3, 20051 Structures and Weights 2 PDR Michael Caldwell Jeff Haddin Asif Hossain James Kobyra John McKinnis Kathleen Mondino Andrew Rodenbeck Jason Tang Joe Taylor Tyler Wilhelm AAE 451: Team 2

2. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 2 Overview Landing Gear Center of Gravity Weight and Cost Estimation V-n Diagram Structures  Wing  Fuselage  Tail Wing Loading Analysis

3. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 3 Aircraft 3-View Mission Requirements 15 min. endurance Take-off distance ≤ 60 ft. V stall ≤ 15 ft/s V loiter ≤ 25 ft/s 35 ft. turn radius

4. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 4 Landing Gear Wire mounting  Rigid  Lightweight  Inexpensive  Easy to construct Interchangeable Smooth takeoff and landing on AstroTurf ® Pictures courtesy of http://www.dubro.com

5. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 5 Location  2 front gears by canard  2 back gears by wing Configuration  Wire strut attached to bottom stringer of outer fuselage with mounting bracket  Interchangeable with wheels, skis, floats attached to mounting blocks Gear Configuration Pictures courtesy of http://www.dubro.com Fuselage Attachment Wheel/Ski/Float Attachment

6. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 6 Center of Gravity X cg = 1.708 ft X np = 1.856 ft Static Margin = 14.8%

7. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 7 Weight Estimation

8. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 8 Cost Estimation * Costs of 11 lb f /ft 3 balsa estimated for wing, fuselages, tails, and canard

9. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 9 V-n Diagram Level Flight Turning Flight Max Load Factor V dive ~ 50% higher than V cruise n max =2.7778-g @ V loiter = 25 ft/sec Typical limit load factors for general aviation (n positive = 3.0-g, n negative = -1.5-g) from Raymer, Daniel P., Aircraft Design: A Conceptual Approach p.407

10. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 10 Properties of Wing Box Shear Web  1.6 in. x 0.125 in. (0.1333 ft. x 0.0104 ft.)  Two stringers: 0.25 in. x 0.25 in. (0.0208 ft. x 0.0208 ft.) Wing Spar  Central I beam located at maximum wing thickness  With shear web and two stringers Ribs  20 ribs spaced approximately every 3 inches Stringers  0.375 in. x 0.375 in. (0.03125 ft. x 0.03125 ft.) leading edge stringer  0.375 in. x 0.75 in. (0.03125 ft. x 0.0625 ft.) trailing edge stringer for mounting aileron

11. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 11 Material Properties Density (lb f /ft 3 )Young’s Modulus (ksi)Yield Stress (psi) Balsa116251725 Spruce3415008600 EPS Foam1.5320-36072.5 EPP Foam1.310004000 Epoxy0.0625 lb/ft 2 50014500 Ultrakote0.0156 lb/ft 2 N/A Values from Fall ’04 AAE 451 projects and http://www.matweb.com

12. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 12 Balsa construction  Lightweight  Simple, quick construction Ultrakote wing covering All parts: 11 lb f /ft 3 balsa High safety factor (oversized web/stringers) Structural Geometry

13. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 13 Wing – Fuselage Attachment

14. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 14 Fuselage Structure Formers  Outer Fuselage (each): Six - 1” radius  Main Fuselage: Four - 2” radius One - 1” radius Stringers  Outer Fuselage (each): Seven – 1/8” x 1/8” x 36” One – 1/8” x 1/2” x 36” (for landing gear mounts)  Main Fuselage: Eight – 1/8” x 1/8” x 20”  Balsa sticks

15. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 15 Tail Structure Flat Plate  Non-Lifting Surface  No Volume Needed  Ease of Construction  1/8” Balsa - Lightweight

16. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 16 Wing Loading Analysis Moments and Products of Inertia Constraints Analysis  Load Distribution at Maximum Wing Loading  Maximum Wing Root Bending Moment  Maximum Torsional Moment  Maximum Wing Tip Deflection

17. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 17 Moments and Products of Inertia Volume Moments of Inertia about World Coordinate Axes Ix: 27479.593 (+/- 0.022) Iy: 21915.62 (+/- 0.088) Iz: 49144.3 (+/- 0.11) Volume Radii of Gyration about World Coordinate Axes Rx: 12.69069 (+/- 1.7e-005) Ry: 11.33331 (+/- 3.3e-005) Rz: 16.97136 (+/- 3.5e-005) Volume Moments of Inertia about Centroid Coordinate Axes Ix: 27466.027 (+/- 0.024) Iy: 13719.2 (+/- 0.28) Iz: 40961.48 (+/- 0.3) Volume Radii of Gyration about Centroid Coordinate Axes Rx: 12.68756 (+/- 1.7e-005) Ry: 8.96695 (+/- 9.9e-005) Rz: 15.49415 (+/- 7e-005) Volume = 170.6239 (+/- 0.00032) cubic millimeters Volume Centroid = 6.925188,6e-011,0.281978 (+/- 2.9e-005,9.3e-006,4.5e-006) Volume Moments: First Moments x: 1181.603 (+/- 0.0027) y: 1e-008 (+/- 0.0016) z: 48.1122 (+/- 0.00068) Second Moments xx: 21790.16 (+/- 0.087) yy: 27354.139 (+/- 0.022) zz: 125.4547 (+/- 0.00065) Product Moments xy: 8e-008 (+/- 0.015) yz: -6e-009 (+/- 0.001) zx: 489.802 (+/- 0.0079) Calculated from CAD Model Can be easily recalculated with model updates

18. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 18 Bending Worst case simplification  cantilevered beam  uniform load distribution  negligible outer fuselage mass/support

19. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 19 Twisting Moment due to lift found from moment coefficient

20. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 20 Constraints Twisting: less than one degree of twist Bending: bending stress less than balsa yield stress (w/ safety factor of 2)

21. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 21 Analysis Maximum wing load:  1.97 lbs of lift, assuming uniform distribution and span Maximum bending moment (at root):  1.308 ft-lbs Maximum torsional moment (from C m ):  0.194 ft-lbs

22. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 22 Maximum Wing Tip Vertical Deflection Wing loading updated from uniform load to an elliptical distribution Load assumed concentrated on central I beam section Maximum tip deflection: 0.3605 in.

23. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 23 Summary Landing Gear Center of Gravity Weight and Cost Estimation V-n Diagram Structures  Wing  Fuselage  Tail Wing Loading Analysis Questions?

24. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 24 Appendix

25. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 25 Airfoil Selection: Wing Wortmann FX 63-137 Wortmann FX 63-137: M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS” – Wind Tunnel

26. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 26 Airfoil Selection: Canard NACA 0012

27. [ Overview | 3-View | Landing Gear 1 2 | CG | Weight | Cost | V-n Diagram | Structures 1 2 3 4 5 6 | Wing Loading Analysis 1 2 3 4 5 6 7 ]Overview3-View12CGWeightCostV-n Diagram1234561234567 March 3, 2005 27 Geometric Layout