Team 5 Final Design Review Trent Lobdell Ross May Maria Mullins Christian Naylor Eamonn Needler Charles Reyzer James Roesch Charles Stangle Nick White

Outline Mission Requirements Team Design Aerodynamics Dynamics & Control Propulsion Necessary / Predicted Necessity Structures / Landing Gear Manufacturing Vehicle Performance / Predictions Lessons Learned Proof of Flight April 28, 2005 AAE 451 – Team 5

Requirements Design Requirements & Objectives Take-Off and landing distance: 100 ft* Take-Off with minimum climb angle: 20° Endurance: 15 min* Typical descent angle of: 5.5° Stall Speed: 20 ft/s Loiter Speed: 28 ft/s* Minimum Turn speed: 23.33 ft/s* Turn Radius: 35 ft* Operating Altitude: 18 ft* Operational Airspace: 360x150 ft *Changed Requirements from Mission Specification April 28, 2005 AAE 451 – Team 5

Design Features / Unique Aspects Stealth Theme Multi-Sweep Wing Twin Booms Pusher Prop Sweet “Paint” Job April 28, 2005 AAE 451 – Team 5

Sizing and Constraints Weight Estimation Using Historical Data Constraint Diagram Power Loading [lbf/Bhp] W-WE [lbf] Takeoff Weight [lbf] Wing Loading [lbf/ft2] Initial Weight : 0.84 pounds Final Weight : 1.88 pounds April 28, 2005 AAE 451 – Team 5

Design Properties Wing Horizontal Tail Overall Aircraft Vertical Tail Fuselage April 28, 2005 AAE 451 – Team 5

Design - Dimensions April 28, 2005 AAE 451 – Team 5

Aerodynamics - Airfoils Low Re Number 91903 (Stall) - 128660 (Cruise) Wing Eppler E212 Tail Eppler E169 Horizontal Tail NACA 0010 Vertical Tail NASG: http://www.nasg.com/afdb/search-airfoil-e.phtml UIUC: http://www.aae.uiuc.edu/m-selig/ads/coord_database.html April 28, 2005 AAE 451 – Team 5

Aerodynamics – Geometry Defined Sweep Angles (Λ) Defined taper ratio (λ) of 1st segment Defined Span Ratio of 2 segments Adjust to balance Style Aspect Ratio Tip Chord feasibility April 28, 2005 AAE 451 – Team 5

Aerodynamics - Lift Sweep Corrected Hembold Equation1 Lift Coefficients vs. α Prandtl Lifting Line Theory1 CL and Cl CLmax (Hembold) : 0.74 Max Lift (Hembold) : 1.10 lbf α (deg) 1 Anderson, J.D., Fundamentals of Aerodynamics, New York, 2001, pp 351-416 April 28, 2005 AAE 451 – Team 5

Aerodynamics - Drag Parasite Drag Buildup Sref = reference area [ft2] Cf = skin friction coefficient K = form factor Q = interference factor April 28, 2005 AAE 451 – Team 5

Aerodynamics – L/D L/Dmax=13.21 Loiter at α = 0.71°,4.46° L/D vs. α L/Dmax=13.21 Loiter at α = 0.71°,4.46° Loiter at 0.866*L/Dmax2 Wing Incidence: 0° Tail Incidence: -3° L/D=4.7 L/D α (deg) 2 Raymer, D.P., Aircraft Design: A Conceptual Approach, Virginia, 1999, pp 27 April 28, 2005 AAE 451 – Team 5

Class 2 Tail Sizing (X-plot) Static Margin: 17° Final Xn: 0.77 ft Tail Area: 0.24 ft2 April 28, 2005 AAE 451 – Team 5

Trim Diagram δe Trim Diagram for Cf/C = 0.5 αplane Cmcg CLtotal April 28, 2005 AAE 451 – Team 5

Control Surface Sizing Aileron size / dimension: Area:0.18 ft2 (each) Length: 1.06 ft Root Chord: 0.24 ft Tip Chord: 0.10 ft Elevator size / dimension: Area: 0.10 ft2 Span: 0.50 ft Chord: 0.21 ft Rudder size / dimension: Area: 0.07 ft2 (each) Base 1: 0.25 ft Base 2: 0.12 ft Height: 0.35 ft April 28, 2005 AAE 451 – Team 5

Class 2 Vertical Tail Sizing (X-plot) 0.218 ft2 April 28, 2005 AAE 451 – Team 5

Feedback Controller Pitch Rate Feedback to Elevator April 28, 2005 AAE 451 – Team 5

Feedback Controller April 28, 2005 AAE 451 – Team 5 Damping Ratio w/o Feedback = 0.72 Desired Damping Ratio = 0.35 – 1.3 We chose a Damping Ratio = 0.99 Feedback Gain Required = 0.091 April 28, 2005 AAE 451 – Team 5

Propeller Take-Off Characteristics Type 2-Bladed 3-Bladed Propeller Diameter 6 in 5 in Pitch 4 in 3 in Operating RPM 14300 RPM 16400 RPM Efficiency 0.43 0.60 April 28, 2005 AAE 451 – Team 5

Propeller Plots – 6 inch prop Take-Off Loiter CT = 0.076 CP = 0.042 CT = 0.025 CP = 0.023 April 28, 2005 AAE 451 – Team 5

Motor Selection - Graupner Speed 400 6V (Direct Drive) Characteristics Engine Characteristics Propeller Shaft Diameter 0.091 in Engine Diameter 1.08 in Engine Length 1.5 in Weight 2.55 oz Rated Horsepower 0.12 hp Rated Loaded RPM 15500 RPM Operating Conditions Operating RPM (Take Off) 14300 RPM Input Voltage 8.34 Volts  11.1 Volts Input Current 11.7 Amps Output Power 0.078 hp April 28, 2005 AAE 451 – Team 5

Battery & Speed Controller Selection Thunder Power 3 Cell Li-Po Rated for 12-15 Amps 2100 mAh Allows for extended endurance as specified in the DR&O 4.6 oz. JETI 12 Amp Microprocessor Motor Controller For 2-3 Cell LiPo Weight = 0.53 oz. 1x0.75x0.3 in. NiCd 4 Cells 4.8 Volts 300 mAh 2.3 oz. April 28, 2005 AAE 451 – Team 5

Landing Gear Main gear (2) Tail Gear (2) Single beam, t = 0.0052 ft 30° angle for lateral stability 20° in front of CG for longitudinal stability Absorb impact Gear deform instead of break Easy to change Tail Gear (2) Heavy duty control horns Prevent prop and tail strike Parameters θ = 30° Material = Al ngear = 3 (Gen. Av.) April 28, 2005 AAE 451 – Team 5

Structures - CG April 28, 2005 AAE 451 – Team 5

Structures - 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 April 28, 2005 AAE 451 – Team 5

Structures - Load Analysis 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 = 32 psf. April 28, 2005 AAE 451 – Team 5

Predicted Flight Performance Max. Turning Radius: 35 ft (DR&O) Bank Angle: 34.82° Turn Rate: 0.8 rad/s Min. Turning Radius: 10.92 ft (Limit) Bank Angle: 65.85° Turn Rate: 2.57 rad/s Maximum Climb Angle: 26.77° Take-Off Distance: 16.29 ft Landing Distance: 22.48 ft Add Roll Rate Adjust Max Climb angle April 28, 2005 AAE 451 – Team 5

Strength Testing Failure at 26 lbf April 28, 2005 AAE 451 – Team 5

Strength Testing Failure due to buckling April 28, 2005 AAE 451 – Team 5

Manufacturing – Milling Wing/fuselage and tails milled using CNC Wet lay-up with 0.6 oz. bidirectional s-glass April 28, 2005 AAE 451 – Team 5

Manufacturing – “Surgery” Circular holes cut for boom insertion Boom Inserted and bonded with Epoxy Hatch cut and tapped for component placement April 28, 2005 AAE 451 – Team 5

Manufacturing – Component Placement Batteries Soldered Motor Installed Servos Connected all components to radio receiver Connected Batteries Rate Gyro Speed Controller Radio Receiver Motor April 28, 2005 AAE 451 – Team 5

Ground Testing Control Surfaces Servos Static Endurance Pitch-Rate Gyro Two-Foot Drop Test April 28, 2005 AAE 451 – Team 5

Flight Testing Four Days Nine Tests One Flight Repairs Problem Solving More Repairs Accomplishment April 28, 2005 AAE 451 – Team 5

Lessons Learned Weight code was not accurate Historical data needs to be updated with R/C aircraft Lack of understanding of speed controller and battery configuration Weight always goes up CG always goes back Cost always goes up April 28, 2005 AAE 451 – Team 5

COMPONENT PROPERTIES UNITS AS DESIGNED AS FLOWN Weight lbf 0.84 1.88 Horsepower Hp 0.073 0.100 Wing Area ft2 4.95 Horizontal Tail Size (Including Elevator) 0.48 Elevator Area 0.10  Propeller Efficiency Non-Dimensional 43% 40% Propeller Size in 6.00 Vertical Tail Size (Including Rudder) 0.23 Rudder Area 0.07  Aileron Area  0.18 0.18  Horsepower from Voltage Volts 8.4 11.1 Wheel Diameter 1.25 3.00 Horizontal Tail A/C Distance from the Wing Quarter Chord ft 2.29 Vertical Tail A/C Distance from the Wing Quarter Chord 2.31 2.39 Wing Chord 0.72 Distance from Centerline to Inboard Aileron 0.58 Distance from Centerline to Outboard Aileron 0.27 Chord of Aileron 0.18 Maximum Surface Deflection deg 30.00 35.00 Chord of Elevator 0.21 Chord of Rudder CG Distance to Nose 0.65 0.75 CG Distance to Wing Quarter Chord 0.13 0.00

A Success Story of the Ages April 28, 2005 AAE 451 – Team 5

Questions? April 28, 2005 AAE 451 – Team 5