Download presentation
Presentation is loading. Please wait.
1
Team 5 Dynamics & Control PDR 2 Presented By: Trent Lobdell Eamonn Needler Charles Reyzer
2
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
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
4 AAE 451 – Team 5 March 10, 2005 Flight Performance Take-off Distance: 16.29 ft Landing Distance: 22.48 ft
5
5 AAE 451 – Team 5 March 10, 2005 Flight Performance Maximum Climb Angle = 26.77°
6
6 AAE 451 – Team 5 March 10, 2005 Flight Performance
7
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: 10.92 ft (Limit) Bank Angle: 65.85° Turn Rate: 2.57 deg/s
8
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
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 ® $ 89.90 Ikarus R/C Gyros
10
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
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
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
13 AAE 451 – Team 5 March 10, 2005 Detailed Specifications Vertical Tail (each) Horizontal Tail Misc. Area0.11 ft 2 0.25 ft 2 SM = 0.15 Height/Span0.73 ft0.583 ftXcg = 0.62 ft Chord0.4 ft0.429 ftXn = 0.728 ft AR4.841.360Total Weight = 0.88 lbf Weight0.01 lbf0.019 lbf
14
14 AAE 451 – Team 5 March 10, 2005 Trim Diagram Raymer Equations and Tables, p. 490- 501 Made Assumptions to find C mcg Plain flapped surface changes zero-lift angle of attack 00 00 1
15
15 AAE 451 – Team 5 March 10, 2005 Trim Diagram
16
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 = 0.171 ft 2
17
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
18 AAE 451 – Team 5 March 10, 2005 Block Diagrams
19
19 AAE 451 – Team 5 March 10, 2005 Root Locus Damping Ratio without Feedback = 0.21 Desired Damping Ratio = 0.35 - 1.3 Damping Ratio with Feedback = 0.70 (k= 1.67)
20
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
Similar presentations
© 2025 SlidePlayer.com. Inc.
All rights reserved.