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

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

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 AAE 451 – Team 5 March 3, 2005 Landing Gear Main gear trade study  Option 1 Single beam, t = ft Stroke = ft Weight = lbf  Option 2 Single beam, t = ft Stroke = ft Weight = lbf  Option 3 Dual beam, t = ft Stroke = 1.2e -8 ft Weight = lbf Parameters θ = 30° Material = Al Ngear = 3 (Gen. Av.)

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 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 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) Motor Speed Control Batteries Gear Box Wing Tails Booms Wheels Radio Gyro Wing Servos H-Tail Servo V-Tail Servo CG TOTAL

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 = lbf/ft 2 Deflections  δ y = 9.1e -11 ft  δ Φ = 1.1e -4 degrees

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

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

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 AAE 451 – Team 5 March 3, 2005 Questions?