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Team 5 Structures PDR

Team 5 Structures PDR. Presented By: Ross May James Roesch Charles Stangle. Outline. Landing Gear Weights and CG Wing Geometry Wing Loads Fuselage and Tail Structures. Landing Gear. Solid spring main gear Aluminum struts 1.5 inch diameter wheels 30° angle for lateral stability

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Team 5 Structures PDR

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  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

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