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

2. 2 AAE 451 – Team 5 March 3, 2005 Outline Landing Gear Weights and CG Wing Geometry Wing Loads Fuselage and Tail Structures

3. 3 AAE 451 – Team 5 March 3, 2005 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

4. 4 AAE 451 – Team 5 March 3, 2005 Landing Gear 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 Parameters θ = 30° Material = Al Ngear = 3 (Gen. Av.)

5. 5 AAE 451 – Team 5 March 3, 2005 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

6. 6 AAE 451 – Team 5 March 3, 2005 Weights/CG Sizing  Actual distances above - specified on next page  Weight : 0.84 lbs AC  CG  Components

7. 7 AAE 451 – Team 5 March 3, 2005 Weights/CG CG 31.3% AC 40.7% Static Margin 9.4% Values are for Micro size components Weight (lbf)Location (ft) Motor0.0901.208 Speed Control0.0630.146 Batteries0.3500.059 Gear Box0.0331.222 Wing0.0800.309 Tails0.0351.981 Booms0.0571.798 Wheels0.0190.393 Radio0.0130.146 Gyro0.0630.146 Wing Servos0.0280.871 H-Tail Servo0.0141.981 V-Tail Servo0.0142.010 CG TOTAL0.8570.551

8. 8 AAE 451 – Team 5 March 3, 2005 Load Analysis Structural loads from code – basic equations used  τ max = 2.40 lbf/ft 2  M root = 0.26 ft-lbf  σ max = 0.0048 lbf/ft 2 Deflections  δ y = 9.1e -11 ft  δ Φ = 1.1e -4 degrees

9. 9 AAE 451 – Team 5 March 3, 2005 Load Analysis Continued… Torsion Loads  T = 0.1 ft-lbf. at high maneuver Failure of wing (most likely due to buckling) occurs at  n cr = 38 or at σ cr = 32lbf.

10. 10 AAE 451 – Team 5 March 3, 2005 V-n Diagram Maximum Loading never reached  (n=5 for homebuilt) q max occurs at around 32 ft/s

11. 11 AAE 451 – Team 5 March 3, 2005 Wing Geometry Section  Eppler E212 Main Elements  W/S = 0.33 lbf/ft 2  b = 3.24 ft  c tip = 0.33 ft  c root = 1.11 ft Construction Elements  CNC from single foam core block  Single layer of bi-directional S-glass Polyester Matrix

12. 12 AAE 451 – Team 5 March 3, 2005 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

13. 13 AAE 451 – Team 5 March 3, 2005 Horizontal Tails Based on Eppler 169 Foam core on CNC Fiberglass skin

14. 14 AAE 451 – Team 5 March 3, 2005 Vertical Tails Based on NACA 0010 Same foam and fiberglass construction

15. 15 AAE 451 – Team 5 March 3, 2005 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

16. 16 AAE 451 – Team 5 March 3, 2005 Questions?