Team 5 Dynamics & Control PDR 2 Presented By: Trent Lobdell Eamonn Needler Charles Reyzer

2 AAE 451 – Team 5 March 10, 2005 Outline Drag Revisited Flight Performance Engine Cooling Sizing X-plots Trim Diagram Elevator Size Feedback Diagram

3 AAE 451 – Team 5 March 10, 2005 Drag Buildup Parasite Drag Buildup S ref = reference area [ft 2 ] C f = skin friction coefficient K = form factor Q = interference factor

4 AAE 451 – Team 5 March 10, 2005 Flight Performance Take-off Distance: ft Landing Distance: ft

5 AAE 451 – Team 5 March 10, 2005 Flight Performance Maximum Climb Angle = 26.77°

6 AAE 451 – Team 5 March 10, 2005 Flight Performance

7 AAE 451 – Team 5 March 10, 2005 Flight Performance Turning Radius: 35 ft (DR&O)  Bank Angle: 34.82°  Turn Rate: 0.8 deg/s Turning Radius: ft (Limit)  Bank Angle: 65.85°  Turn Rate: 2.57 deg/s

8 AAE 451 – Team 5 March 10, 2005 Engine Cooling Mount Holes Shaft Outlet VentRam Scoop Airflow Front ViewSide View Foam Melting Temperature: 194° F

9 AAE 451 – Team 5 March 10, 2005 Gyro Selection  Specifications:  3.5 to 12 volts  0.85 oz  1.6"x1.5"x0.65“  Remote Gain Control  Available at  Hobby-Lobby ®  $ Ikarus R/C Gyros

10 AAE 451 – Team 5 March 10, 2005 Sizing Solidifications Error noticed with original gyro selection  0.85 oz << 3 oz  Original gyro thought to be needed was 3 oz  Alternative found  Plane sized with Lithium Polymer  CG code updated

11 AAE 451 – Team 5 March 10, 2005 Sizing Updated CG code changes made Locations originally done as percentage of plane length Lithium-Polymer Batteries Selected Weights better refined

12 AAE 451 – Team 5 March 10, 2005 H-tail X-plot CG curve found using traditional CG calculations which account for H-tail and V- tail AC curve found using Roskam equation

13 AAE 451 – Team 5 March 10, 2005 Detailed Specifications Vertical Tail (each) Horizontal Tail Misc. Area0.11 ft ft 2 SM = 0.15 Height/Span0.73 ft0.583 ftXcg = 0.62 ft Chord0.4 ft0.429 ftXn = ft AR Total Weight = 0.88 lbf Weight0.01 lbf0.019 lbf

14 AAE 451 – Team 5 March 10, 2005 Trim Diagram Raymer Equations and Tables, p Made Assumptions to find C mcg Plain flapped surface changes zero-lift angle of attack

15 AAE 451 – Team 5 March 10, 2005 Trim Diagram

16 AAE 451 – Team 5 March 10, 2005 Elevator Size Based upon trim diagram, c f /c = 0.5 chosen With 2 inches clearance for uninterrupted deflection, elevator span ~ 0.8 ft Elevator chord = 0.5*h-tail-chord ~ 0.21 ft Elevator area = ft 2

17 AAE 451 – Team 5 March 10, 2005 Feedback Controller Pitch rate feedback to the elevator Damping ratio for the pitch rate is deficient

18 AAE 451 – Team 5 March 10, 2005 Block Diagrams

19 AAE 451 – Team 5 March 10, 2005 Root Locus Damping Ratio without Feedback = 0.21 Desired Damping Ratio = Damping Ratio with Feedback = 0.70 (k= 1.67)

20 AAE 451 – Team 5 March 10, 2005 Summary Drag Revisited Flight Performance Engine Cooling CG Changes X-plots Trim Diagram Elevator Size Feedback Diagram