Team 5 Structures PDR

1. Team 5Structures PDR Presented By: Ross May James Roesch Charles Stangle

2. Outline • Landing Gear • Weights and CG • Wing Geometry • Wing Loads • Fuselage and Tail Structures AAE 451 – Team 5

3. Landing Gear • Solid spring main gear • Aluminum struts • 1.5 inch diameter wheels • 30° angle for lateral stability • 20° in front of CG for longitudinal stability • Skid/tail dragger gear • Negates propeller and tail strike • 5º slope from horizontal for skid • 18 gauge steel wire AAE 451 – Team 5

4. Landing Gear • Parameters • θ = 30° • Material = Al • Ngear = 3 (Gen. Av.) • Main gear trade study • Option 1 • Single beam, t = 0.0017 ft • Stroke = 0.0215 ft • Weight = 0.0014 lbf • Option 2 • Single beam, t = 0.0034 ft • Stroke = 0.0027 ft • Weight = 0.0029 lbf • Option 3 • Dual beam, t = 0.0017 ft • Stroke = 1.2e-8 ft • Weight = 0.0032 lbf AAE 451 – Team 5

5. Landing Gear • Drop test • h = 3.6 * (wing loading)1/2 -Raymer • Height will be 2 ft • Raised to 4 ft to simulate drop from carrying height AAE 451 – Team 5

6. Weights/CG AC  • Sizing • Actual distances above - specified on next page • Weight : 0.84 lbs CG  Components AAE 451 – Team 5

7. Weights/CG • CG 31.3% • AC 40.7% • Static Margin 9.4% Values are for Micro size components AAE 451 – Team 5

8. Load Analysis • Structural loads from code – basic equations used • τ max = 2.40 lbf/ft2 • Mroot = 0.26 ft-lbf • σmax = 0.0048 lbf/ft2 • Deflections • δy = 9.1e-11 ft • δΦ = 1.1e-4 degrees AAE 451 – Team 5

9. Load Analysis Continued… • Torsion Loads • T = 0.1 ft-lbf. at high maneuver • Failure of wing (most likely due to buckling) occurs at • ncr = 38 or at σcr = 32lbf. AAE 451 – Team 5

10. V-n Diagram • Maximum Loading never reached • (n=5 for homebuilt) • qmax occurs at around 32 ft/s AAE 451 – Team 5

11. Wing Geometry • Section • Eppler E212 • Main Elements • W/S = 0.33 lbf/ft2 • b = 3.24 ft • ctip = 0.33 ft • croot = 1.11 ft • Construction Elements • CNC from single foam core block • Single layer of bi-directional S-glass • Polyester Matrix AAE 451 – Team 5

12. Fuselage • CNC solid shape for blended fuselage • Stronger main section • Easily and precisely created • Fiberglass skin • Provides load bearing structure for wing • Strength VS weight tradeoff very acceptable AAE 451 – Team 5

13. Horizontal Tails • Based on Eppler 169 • Foam core on CNC • Fiberglass skin AAE 451 – Team 5

14. Vertical Tails • Based on NACA 0010 • Same foam and fiberglass construction AAE 451 – Team 5

15. Control Surface Layout • Ailerons as shown • Elevator will be approximately half of horizontal tail area • Rudder will again be approximately half of total surface Vertical Tail AAE 451 – Team 5

16. Questions? AAE 451 – Team 5