April 28, Summary Project Presentation Michael Caldwell Jeff Haddin Asif Hossain James Kobyra John McKinnis Kathleen Mondino Andrew Rodenbeck Jason Tang Joe Taylor Tyler Wilhelm AAE 451: Team 2

April 28, Overview Aircraft Overview Aerodynamics Dynamics & Controls Structures Propulsion Construction Troubleshooting Flight Testing Cost & Weight Economic Plan Lessons Learned As Designed vs. As Built

April 28, Walkaround

April 28, ft 3.00 ft Aircraft 3-View Mission Requirements 15 min. endurance Take-off distance ≤ 60 ft. V stall ≤ 15 ft/s V loiter ≤ 25 ft/s 35 ft. turn radius Weight1.96 lbs Wingspan5.24 ft Length3.00 ft Height1.50 ft Aspect Ratio5.24 Cruise Speed23 ft/s Max Thrust1.00 lb

April 28, Constraint Diagram Design Space Design Point Wing Loading:  lbf/ft2 Power Loading:  lbf/hp LiPoly Weight: 1.97lb f Wing Area: 5.24 ft 2 Power: hp Takeoff

April 28, Airfoil Selections Wing: Wortmann FX Wortmann FX : M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel Canard  NACA ° incidence Volume for Gyro and Battery Vertical Tails  Flat Plate Non-Lifting Surface No Volume Needed

April 28, Mathematical Model From Prandtl’s Classical Lifting-Line Theory Re=147,820 Root: 1 o Tip: -7 o

April 28, Mathematical Model Re=147,820

April 28, Mathematical Model C Mo calculated using Roskam Vol. VI and C Mα calculated from flatearth.m

April 28, L/D MAX L/D MAX =10.75 α L/Dmax =0.60 o Re=147,820

April 28, Canard, Tail & Control Surface Sizing Class 1 SizingClass 2 Sizing Canard Area S ht 1.43 ft ft 2 Vertical Tail Area S vt (each) 0.92 ft ft 2 Span (ft)Chord (ft)Area (ft 2 ) Aileron (each) Elevator Rudder (each)

April 28, Theoretical Static Margin X cg = 1.70 ft X np = 1.85 ft Static Margin = 14.80%

April 28, C L Max Trimmed Maximum C L (x ref = x cg ) α CL Max α = 0 o Trim Diagram

April 28, Outer Panel Dihedral Wing EVD: 3.36 deg outer panel dihedral Canard EVD: deg outer panel dihedral Dihedral Angle

April 28, Block Diagram H e (s) q(s)/  e (s) H (s)K  Pilot Input Elevator Servo Aircraft  e (s ) q(s) + _ Pitch Rate Gyro Feedback Gain

April 28, Aircraft TF / Natural Frequency and Damping Ratio Aircraft Transfer Function (Flat Earth Predator) Undamped Natural Frequency (Short Period) Damping Ratio (Short Period)

April 28, Gain Calculation, k Gain Calculation: - Flat Earth Predator - SISOTOOL k = Root Locus Plot For k = 0 For k =

April 28, Root Locus

April 28, Gyro and Servo Selection Futaba GYA350 gyro  Weight: 0.92 ounces  Remote gain function JR S241 sub micro servos  Weight: 0.32 ounces  Torque: 17 oz/in

April 28, Material Properties Density (lb f /ft 3 )Young’s Modulus (ksi)Yield Stress (psi) Balsa Spruce EPS Foam EPP Foam Epoxy lb/ft Ultrakote lb/ft 2 N/A Values from Fall ’04 AAE 451 projects and

April 28, Structural Geometry Primarily EPP Foam Balsa fuselage structures

April 28, Wing – Fuselage Attachment

April 28, Fuselage Structure Formers  Outer Fuselage (each): Three - 1” radius  Main Fuselage: Five - 2” radius Stringers  Outer Fuselage (each): Six – 1/8” x 1/8” x 7”  One – 1/4” x 1/8” x 7” One – 3/4” x 1/2” x 36” (for landing gear mounts)  Main Fuselage: Eight – 1/4” x 1/4” x 20”

April 28, V-n Diagram Level Flight Turning Flight Max Load Factor V dive ~ 50% higher than V cruise n max V loiter = 25 ft/sec Typical limit load factors for general aviation (n positive = 3.0-g, n negative = -1.5-g) from Raymer, Daniel P., Aircraft Design: A Conceptual Approach p.407

April 28, Bending Worst case simplification  Cantilevered beam  Negligible weight, outer fuselage mass/support  Elliptical load distribution

April 28, Analysis Maximum wing load:  1.97 lbs of lift, elliptical loading, load factor of 2.77 yields 5.45 lbs Maximum bending moment (at root):  ft-lbs Maximum torsional moment (from C m ):  ft-lbs

April 28, Results Maximum wing stress: psi Maximum tip deflection: 0.16 in. Maximum rotation: 0.13 degrees

April 28, Moments and Products of Inertia Balsa Components: Volume = (+/ ) cubic inches Volume Centroid = ,2e-007, (+/- 8.6e-006,2.2e- 006,1.2e-005) Volume Moments: Volume Moments of Inertia about World Coordinate Axes Ix: (+/ ) Iy: (+/ ) Iz: (+/ ) Volume Moments of Inertia about Centroid Coordinate Axes Ix: (+/ ) Iy: (+/ ) Iz: (+/ ) Foam Components: Volume = (+/ ) cubic inches Volume Centroid = ,1.1e-005, (+/- 3.5e- 006,2.7e-006,2.4e-006) Volume Moments: Volume Moments of Inertia about World Coordinate Axes Ix: (+/ ) Iy: (+/ ) Iz: (+/ ) Volume Moments of Inertia about Centroid Coordinate Axes Ix: (+/ ) Iy: (+/- 0.11) Iz: (+/ ) Calculated from CAD Model Multiply by material density to determine Mass MOI

April 28, Propeller Selection

April 28, Motor & Battery Selection ComponentsProp 2 Code Calculates near 900mAh necessary to fly mission Fails to include component energy requirements Components need approximately 150mAh across our mission 1050mAh battery necessary Kokam 1200mAh battery chosen on grounds of weight & preferred vendors

April 28, Unique Aspects of the Design Twin Boom Design EPP Foam Robust Interchangeable Landing Gear Brushless Motor 3-Bladed Prop Alternative

April 28, Construction Balsa Components  Cut from 1/8 th inch sheet  CNC machined using 2 axis milling  Assembled using CA glue

April 28, Construction Vertical Tails  Constructed from 1/8 th inch balsa sheet  Fiber glassed for increased stiffness  Removable, mounted to principle stringer

April 28, Construction Foam & balsa sections bonded with epoxy Foam wing sections cut on mitres, achieving dihedral, bonded together with epoxy

April 28, Construction Main fuselage bonded to wings with epoxy UltraKote applied Hardware mounted

April 28, Troubleshooting Landing Gear  Z-bend wire mounted to plywood  Change from skis to wheels

April 28, Troubleshooting Vertical Tails  Fishing line to secure the rotation of vertical tails

April 28, Troubleshooting Wing  Balsa Spar inserted in the inner wing  Aluminum spar (arrow shafts) inserted in the entire wing

April 28, Flight Testing: Day 1 Sunday, April 17th Pickett Park:  Glide Testing CG too far forward

April 28, Flight Testing: Day 2 Monday, April 18th: McAllister Park  “Flight Testing” CG too far forward ?!?! Insufficient Power Repairs Necessary

April 28, Flight Testing: Day 3 Tuesday, April 19 th Mollenkopf Athletic Center: “Flight Testing” CG still too far forward? Elevator chord too short? More Power? FLIGHT Testing Static Longitudinal Instability CG WAY too far aft Elevator chord too long Still in need of more testing Pictures courtesy of WLFI TV

April 28, Weight Estimation

April 28, Weight Comparison

April 28, Cost Estimation

April 28, Cost Comparison

April 28, Total Person-Hours (as of Week 9 - 3/21/05):1700 hours Total Person-Hours (as of Week /27/05):3325 hours Economic Plan Estimated Total Person-Hours at Project Completion:3500 hours

April 28, Lessons Learned Pilot Availability Underpowered Motor / Batteries CNC Issues Aerodynamic Center / Center of Gravity Weight Issues

April 28, Lessons Learned Skis vs. Wheels EPP Foam vs. Balsa Construction Material Property Availability Airfoil Selection Communication is Key

April 28, Aircraft Comparison Each Aileron = 0.35 ft 2 (+0.10 ft 2 )Elevator = 0.38 ft 2 (+0.05 ft 2 ) Each Rudder = 0.10 ft 2 (-0.32 ft 2 )Wing = 6.0 ft 2 (+0.76 ft 2 )

April 28, Longitudinal Static Instability Calculated X cg = 1.70 ft Actual X cg = 1.90 ft Calculated X ac = 1.85 ft Intended static margin  15% Static margin at flight time  -5%

April 28, Aircraft Comparison

April 28, Constraint Diagram Revisited Design Space Current Design Point Weight:  3.13 lb f Wing Area  6 ft 2 Power:  0.01 hp Wing Loading:  0.52 lb f /ft 2 Power Loading:  lb f /hp Desired Design Point Takeoff

April 28, Summary Aircraft Overview Aerodynamics Dynamics & Controls Structures Propulsion Construction Troubleshooting Flight Testing Cost & Weight Economic Plan Lessons Learned As Designed vs. As Built

April 28, Questions?

April 28, Appendix

April 28, SELIG – WORTMANN COMPARISON Selig 1210: M.S.Selig,J.J.Guglielmo,A.P.Broeren and P.Giguere,"Summary of Low-Speed Airfoil Data, Volume 1 – Wind Tunnel Data Wortmann FX : M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel Airfoil Selection: Wing

April 28, Airfoil Selection: Canard NACA 0012

April 28, Wing Twist Distribution Root: 1 o Tip: -7 o

April 28, Mathematical Model Prandtl’s Classical Lifting Line Theory  Elliptical Loading Parasite Drag – Component Buildup Method

April 28, Turning Conditions

April 28, L/D Mathematical Model * Raymer, Daniel P., Aircraft Design: A Conceptual Approach p.493

April 28, L/D MAX L/D MAX Velocity Loiter Straight:  V L/Dmax = ft/s Loiter Turn:  V L/Dmax = ft/s Re=147,820

April 28, Effect of Control Surface Deflection: Lift Roskam,Jan, Airplane Design PartVI: Prelimenary Calculation of Aerodynamic, Thrust, and Power Characteristics, 2000

April 28, Effect of Control Surface Deflection: Pitching Moment Roskam,Jan, Airplane Design PartVI: Prelimenary Calculation of Aerodynamic, Thrust, and Power Characteristics, 2000

April 28, Desired Static Margin Static Margin (Raymer)  Typical Fighter Jet: 0-5%  Typical Transport Aircraft = 5-10%  Model aircraft usually more stable Goal: Static Margin = 15%

April 28, Dihedral Angle EVD of the wing and canard: Wing EVD: Canard EVD:

April 28, Root Locus

April 28, Landing Gear Wire mounting  Rigid  Lightweight  Inexpensive  Easy to construct Interchangeable Smooth takeoff and landing on AstroTurf ® Pictures courtesy of

April 28, Location  Front gear by canard  Back gear by wing Configuration  Wire strut attached to stringer in outer fuselage with mounting bracket  Interchangeable with wheels, skis, and floats attached to mounting blocks Gear Configuration Pictures courtesy of Fuselage Attachment Wheel/Ski/Float Attachment

April 28, Constraints Twisting: less than one degree of twist Bending: bending stress less than EPP foam yield stress (w/ safety factor of 2)

April 28, Prandtl & Goldstein

April 28, Propeller Efficiency and Advance Ratio Operation Range  J =

April 28, Thrust Coefficient and Advance Ratio

April 28, Propeller Efficiency and Advance Ratio

April 28, Component Trade Study Graupner Speed % too powerful, unreliable data Each “Tier” represents a battery / motor combination More selection with Li & Brushless Connectors for brushed motors and Li batteries are not compatible. It would not be wise to have a Li & brushed combination. Our Aircraft needs to weigh less than 32 oz Our Aircraft

April 28, Thrust, Power, and Endurance Airspeed Amps “Sedate” Mission 15min Airspeed Amps “Trainer” Mission 23min

April 28, Tail Sizing (Class 1) Constants  c HT = 0.50  c VT = 0.05  C w = 1 ft  S w = 5.24 ft  L HT = 1.83 ft  L VT = 0.75 ft Horizontal tail (canard)  Area = ft 2 Vertical tail  Area = ft 2 (each)

April 28, Tail Sizing (Class 2) Vertical Tail  Plot C nβ versus S vt  S vt = ft 2

April 28, Tail Sizing (Class 2) Horizontal Tail  Plot X cg and X ac versus S ht  S ht = 1.36 ft 2