AAE 451 Team 3 Critical Design Review Jon

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AAE 451 Team 3 Critical Design Review Jon Amback Melissa Doan Stacie Pedersen Kevin

AAE 451 Team 3 Critical Design Review Jon Amback Melissa Doan Stacie Pedersen Kevin Badger Jason Hargraves Colleen Rainbolt Greg Davidson Etan Karni Lazo Trkulja March 24, 2005 Purdue University School of Aeronautics and Astronautics

Mission Specifications • • • 8 Minute Endurance Vstall ≤ 20 fps Vloiter ≤

Mission Specifications • • • 8 Minute Endurance Vstall ≤ 20 fps Vloiter ≤ 30 fps Climb ≥ 20 descent ≤ -5. 5 Stylish Purdue University School of Aeronautics and Astronautics

Style Features • • • Canard pusher configuration Blended wing-body design Retractable landing gear

Style Features • • • Canard pusher configuration Blended wing-body design Retractable landing gear LED lighting Ventral fins Winglets Purdue University School of Aeronautics and Astronautics

Vehicle 3 -View Length 4. 21 ft. Wingspan 4. 63 ft. Wing Area 3.

Vehicle 3 -View Length 4. 21 ft. Wingspan 4. 63 ft. Wing Area 3. 58 ft. 2 Takeoff Weight 1. 95 lbs. Purdue University School of Aeronautics and Astronautics

Dimensions Main Wing Canard Vert. Stab. USNPS-4 Flat Plate Sref 3. 58 ft 2

Dimensions Main Wing Canard Vert. Stab. USNPS-4 Flat Plate Sref 3. 58 ft 2 0. 31 ft 2 0. 63 ft 2 AR 6. 0 4. 0 1. 5 Taper Ratio 0. 6 0. 5 0. 4 Sweep 0 deg. 25 deg. Dihedral 3 deg. 0 deg. --- Airfoil Purdue University School of Aeronautics and Astronautics

Constraint Diagram Purdue University School of Aeronautics and Astronautics 6

Constraint Diagram Purdue University School of Aeronautics and Astronautics 6

Master Design Code • Automates sizing iteration process » Constraint diagram generation » Propeller

Master Design Code • Automates sizing iteration process » Constraint diagram generation » Propeller analysis using Goldstein’s blade-element method » Motor analysis / comparison using Prop ’ 02 functions and Moto. Calc database » Battery capacity computation from mission model » Sizing of Wing, Canard, and Vertical Stabilizer » Weight estimation based on construction techniques and known systems weights; CG computation » Automatic generation of Flat. Earth input deck • Single code approach ensures all disciplines “design the same aircraft” • 1200+ lines of team code » Also leverages 450+ lines of existing propulsion analysis codes and 3700+ lines in Flat. Earth aeroprediction code Purdue University School of Aeronautics and Astronautics

Propulsion Purdue University School of Aeronautics and Astronautics 8

Propulsion Purdue University School of Aeronautics and Astronautics 8

Selected Propulsion System • Kokam 3 Cell 640 m. Ah Li-Poly Battery Pack •

Selected Propulsion System • Kokam 3 Cell 640 m. Ah Li-Poly Battery Pack • Kokam Super 20 Electronic Speed Controller Purdue University School of Aeronautics and Astronautics 9

Selected Propulsion System • Graupner Speed 480 Brushed Motor » 0. 12 Hp at

Selected Propulsion System • Graupner Speed 480 Brushed Motor » 0. 12 Hp at 11. 1 V and 10 Amps • MPJet 4. 1: 1 Offset Gearbox • APC 11” x 4. 7” Slo-Flyer Propeller Purdue University School of Aeronautics and Astronautics

Graupner Speed 480 Properties Purdue University School of Aeronautics and Astronautics

Graupner Speed 480 Properties Purdue University School of Aeronautics and Astronautics

Propeller Properties Purdue University School of Aeronautics and Astronautics

Propeller Properties Purdue University School of Aeronautics and Astronautics

Aerodynamics Purdue University School of Aeronautics and Astronautics 13

Aerodynamics Purdue University School of Aeronautics and Astronautics 13

Selected Airfoil • USNPS – 4 » » Flat lower surface -- easy to

Selected Airfoil • USNPS – 4 » » Flat lower surface -- easy to manufacture Thickness suitable for servos and retracts High Clmax Low pitching moment » Low Cd Purdue University School of Aeronautics and Astronautics

Drag Buildup Parasite Drag Induced Drag Coefficient (ref. Raymer) Total Drag Coefficient Purdue University

Drag Buildup Parasite Drag Induced Drag Coefficient (ref. Raymer) Total Drag Coefficient Purdue University School of Aeronautics and Astronautics 15

Lift Coefficient 3 -D Lift Curve Slope 3 -D CLmax Full Aircraft Zero Degree

Lift Coefficient 3 -D Lift Curve Slope 3 -D CLmax Full Aircraft Zero Degree Ao. A Lift Coefficient -Flat. Earth. m (ref. Roskam) Taking into account: Wing/Body interaction Incidence Angles Downwash Purdue University School of Aeronautics and Astronautics 16

Polars Desired Operating Point CLmax Purdue University School of Aeronautics and Astronautics 17

Polars Desired Operating Point CLmax Purdue University School of Aeronautics and Astronautics 17

Flight Controls and Performance Purdue University School of Aeronautics and Astronautics 18

Flight Controls and Performance Purdue University School of Aeronautics and Astronautics 18

Location of CG and AC CG AC SM=19. 7% (Flat. Earth) Desired ≥ 15%

Location of CG and AC CG AC SM=19. 7% (Flat. Earth) Desired ≥ 15% Purdue University School of Aeronautics and Astronautics 19

Stabilizer Sizing with X-Plots Design Point Static Margin = 19. 7% Purdue University School

Stabilizer Sizing with X-Plots Design Point Static Margin = 19. 7% Purdue University School of Aeronautics and Astronautics

Sizing of Control Surfaces All surfaces deflect +/- 30° 30% of chord Elevator 30%

Sizing of Control Surfaces All surfaces deflect +/- 30° 30% of chord Elevator 30% of 10% of b/2 canard b/2 Rudder 40% of tail chord 20% of chord Aileron 40% of wing b/2 10% of b/2 Purdue University School of Aeronautics and Astronautics

Trim Diagram SM=15% Purdue University School of Aeronautics and Astronautics 22

Trim Diagram SM=15% Purdue University School of Aeronautics and Astronautics 22

Flight Performance - Takeoff • Vtakeoff= 28 ft/s • ttakeoff = 2. 7 s

Flight Performance - Takeoff • Vtakeoff= 28 ft/s • ttakeoff = 2. 7 s • Xtakeoff = 53 ft Purdue University School of Aeronautics and Astronautics 23

Flight Performance - Turning Purdue University School of Aeronautics and Astronautics

Flight Performance - Turning Purdue University School of Aeronautics and Astronautics

Flight Performance • Endurance » Need 489 m. Ah battery for 8 minute endurance

Flight Performance • Endurance » Need 489 m. Ah battery for 8 minute endurance » Battery selected provides 640 m. Ah (best available match to required capacity) • Climb » Motor selected to provide adequate power for design climb angle with selected prop Purdue University School of Aeronautics and Astronautics

Control Strategy • Feedback yaw rate to the rudder » Expected deficiency in lateral-directional

Control Strategy • Feedback yaw rate to the rudder » Expected deficiency in lateral-directional stability due to close coupling of vertical stabilizer and CG » Greater potential for aircraft to enter unrecoverable dive if using pitch feedback • Increase the damping of dutch roll mode from present value of 0. 275 to a recommended maximum value of 0. 4 Purdue University School of Aeronautics and Astronautics

Lateral-Directional Root Locus K = 0. 95 *Negative Transfer Function Purdue University School of

Lateral-Directional Root Locus K = 0. 95 *Negative Transfer Function Purdue University School of Aeronautics and Astronautics 27

Block Diagram Purdue University School of Aeronautics and Astronautics

Block Diagram Purdue University School of Aeronautics and Astronautics

Closed-Loop Pulse Response Rudder deflected 10 deg. Rudder neutralized Purdue University School of Aeronautics

Closed-Loop Pulse Response Rudder deflected 10 deg. Rudder neutralized Purdue University School of Aeronautics and Astronautics 29

Landing Gear, Structures and Weights Purdue University School of Aeronautics and Astronautics 30

Landing Gear, Structures and Weights Purdue University School of Aeronautics and Astronautics 30

Landing Gear Layout • Nose gear carries 8% of weight; remainder on mains •

Landing Gear Layout • Nose gear carries 8% of weight; remainder on mains • Tailstrike at 10. 0 » 20. 0 tipback angle • Wingtip strike at 15. 7° bank » 30. 0 overturn angle » 1. 52 ft. track between main gear 0. 5 ft. 20. 0 2. 15 ft. 10. 0 Purdue University School of Aeronautics and Astronautics

Fuselage Structure Foam Panels (nonstructural) Hollow Balsa Box Structure Balsa Stringers (4) 3/16” sq.

Fuselage Structure Foam Panels (nonstructural) Hollow Balsa Box Structure Balsa Stringers (4) 3/16” sq. 1/16” thick Purdue University School of Aeronautics and Astronautics

Vertical Stabilizer 3/16” x 1/4” Balsa Fin Structure, Solid Rudder 0. 37 ft 0.

Vertical Stabilizer 3/16” x 1/4” Balsa Fin Structure, Solid Rudder 0. 37 ft 0. 93 ft Balsa Tristock Bracing Purdue University School of Aeronautics and Astronautics

Wing Structure Balsa Wing Skin Balsa Leading Edge Spar 0. 03 ft 0. 017

Wing Structure Balsa Wing Skin Balsa Leading Edge Spar 0. 03 ft 0. 017 ft Balsa Subspar 0. 97 ft Blue Foam Core 0. 10 ft Balsa Trailing Edge Foam Wing Saddle Purdue University School of Aeronautics and Astronautics

Bending and Torsion Results • Ultimate Root Bending Moment 31. 83 lbf-ft (tensile failure)

Bending and Torsion Results • Ultimate Root Bending Moment 31. 83 lbf-ft (tensile failure) • Max Root Bending Moment in Turning Flight 9. 73 lbf-ft • Computed Factor of Safety = 3. 3 • Maximum twist angle = -0. 2 (LE down) Purdue University School of Aeronautics and Astronautics

Weight Distribution Purdue University School of Aeronautics and Astronautics

Weight Distribution Purdue University School of Aeronautics and Astronautics

Weight and Balance Weight (lbs. ) Arm (ft. ) Moment (ft. -lbs. ) Airframe

Weight and Balance Weight (lbs. ) Arm (ft. ) Moment (ft. -lbs. ) Airframe 0. 856 -0. 12 -0. 10 Propulsion 0. 666 0. 12 0. 08 Avionics 0. 256 -0. 98 -0. 25 Landing Gear 0. 155 -0. 77 -0. 12 Miscellaneous 0. 063 -0. 16 -0. 01 TOTAL 1. 950 -0. 25 -0. 51 • Origin at wing root c/4 • Nose-up moments are positive Purdue University School of Aeronautics and Astronautics 37

V-n Diagram Ultimate Load Factor Mission Load Factor Purdue University School of Aeronautics and

V-n Diagram Ultimate Load Factor Mission Load Factor Purdue University School of Aeronautics and Astronautics

Construction and Test Plan Purdue University School of Aeronautics and Astronautics 39

Construction and Test Plan Purdue University School of Aeronautics and Astronautics 39

Fabrication Plan • Parallel construction process • Also bench test propulsion and avionics prior

Fabrication Plan • Parallel construction process • Also bench test propulsion and avionics prior to installation Purdue University School of Aeronautics and Astronautics

Flight Test Plan • • • Low/Hi-speed taxi tests Flight 1 A – 1

Flight Test Plan • • • Low/Hi-speed taxi tests Flight 1 A – 1 x: Unpowered glide test series Flight 2: 1 st Powered Flight (outdoors) Flight 3: Envelope expansion (outdoors) Flight 4 A – 4 x: Final shakedown (indoors / outdoors) • Flight 5: Demonstrate design mission (indoors) Purdue University School of Aeronautics and Astronautics

Budget and Labor • Budget » Team: spent $135. 40 of $150 permitted »

Budget and Labor • Budget » Team: spent $135. 40 of $150 permitted » Purdue: $92. 88, excluding R/C gear » Remaining purchases are foam and sheet balsa • Labor » Team has worked 1323 hours to-date » Extrapolating for remainder of semester results in $57, 900 at $25/hr/person Purdue University School of Aeronautics and Astronautics

Remaining Challenges • Transportation • Compressed construction / testing schedule • Pilot availability Ready

Remaining Challenges • Transportation • Compressed construction / testing schedule • Pilot availability Ready to Build Purdue University School of Aeronautics and Astronautics

Questions? Purdue University School of Aeronautics and Astronautics

Questions? Purdue University School of Aeronautics and Astronautics

Backup charts • Propulsion • Structures • Finance Purdue University School of Aeronautics and

Backup charts • Propulsion • Structures • Finance Purdue University School of Aeronautics and Astronautics

Graupner Speed 480 Rated horsepower 0. 1182 hp @ take-off Motor efficiency 71% Motor

Graupner Speed 480 Rated horsepower 0. 1182 hp @ take-off Motor efficiency 71% Motor constants Kv = 2450 RPM/V Kt = 0. 5520 In-oz/amp R = 0. 241 Ohms Io = 1. 09 Amps Rated number of cells 3 Lithium Rated Amps 10 Amps Rated voltage 8. 4 V Weight 0. 221 lbs Price $25. 90 (Hobby Lobby) Purdue University School of Aeronautics and Astronautics 46

Selected Gearbox Gear Ratio (available) 4. 1: 1 Efficiency 87% Price $13. 90 (Hobby

Selected Gearbox Gear Ratio (available) 4. 1: 1 Efficiency 87% Price $13. 90 (Hobby Lobby) Purdue University School of Aeronautics and Astronautics 47

Selected Propeller Properties Prop (Calculated) 11 in. x 4. 4 in Prop (Available) 11

Selected Propeller Properties Prop (Calculated) 11 in. x 4. 4 in Prop (Available) 11 in x 4. 7 in RPM 5000 RPM Weight 0. 113 lbs Chord 0. 6 in. Airfoil of Propeller Clark-Y Price $3. 09 Reynolds Number ~100, 000 Purdue University School of Aeronautics and Astronautics 48

Other Propeller Options Propeller Option Pitch and Diameter APC Slow-Flyer 10 x 7 APC

Other Propeller Options Propeller Option Pitch and Diameter APC Slow-Flyer 10 x 7 APC Slow-Flyer 10 x 4. 7 APC Slow-Flyer 11 x 6 APC Slow-Flyer 11 x 7 Purdue University School of Aeronautics and Astronautics

Battery Properties Kokam 3 -Cell Continuous Amps Nominal Output Weight 640 m. Ah 9.

Battery Properties Kokam 3 -Cell Continuous Amps Nominal Output Weight 640 m. Ah 9. 6 A 11. 1 V 0. 119 lbs Price $31. 99 Purdue University School of Aeronautics and Astronautics

Speed Controller Kokam Super 20 Amp Auto low voltage cutoff (lvc) Continuous Amps Output

Speed Controller Kokam Super 20 Amp Auto low voltage cutoff (lvc) Continuous Amps Output 20 A Peak output current 200 A Input operating voltage 2. 1 to 18 V DC Weight 0. 0265 lbs Price $33. 99 Purdue University School of Aeronautics and Astronautics

Propulsion Parts List Purdue University School of Aeronautics and Astronautics 52

Propulsion Parts List Purdue University School of Aeronautics and Astronautics 52

Bending Results • Max Allowable Root Bending Moment 31. 83 lbf-ft (tensile failure) •

Bending Results • Max Allowable Root Bending Moment 31. 83 lbf-ft (tensile failure) • Max Allowable Compressive Moment 88. 05 lbf-ft • Max Bending Moment in Loiter 9. 18 lbf-ft • Max Bending Moment in Turning Flight 9. 73 lbf-ft Purdue University School of Aeronautics and Astronautics

USNPS-4 Characteristics Purdue University School of Aeronautics and Astronautics 54

USNPS-4 Characteristics Purdue University School of Aeronautics and Astronautics 54

USNPS-4 Characteristics Purdue University School of Aeronautics and Astronautics

USNPS-4 Characteristics Purdue University School of Aeronautics and Astronautics

USNPS-4 Characteristics Purdue University School of Aeronautics and Astronautics

USNPS-4 Characteristics Purdue University School of Aeronautics and Astronautics

Parasite Drag Buildup , where Fuselage , where Form Factor: Interference Factor: (assumed based

Parasite Drag Buildup , where Fuselage , where Form Factor: Interference Factor: (assumed based on historical data and absence of naceles) Purdue University School of Aeronautics and Astronautics 57

Parasite Drag Buildup Wings/Canards/Winglets (1. 02 accounts for thickness/curvature) Form Factor: Sweep correction: Interference

Parasite Drag Buildup Wings/Canards/Winglets (1. 02 accounts for thickness/curvature) Form Factor: Sweep correction: Interference Factor: (assumed based for mid-body, filleted wings) Miscellaneous Drag Based on historic small propeller aircraft Purdue University School of Aeronautics and Astronautics 58

Total Drag Polar Prediction Induced Drag Coefficient Total Drag Coefficient Purdue University School of

Total Drag Polar Prediction Induced Drag Coefficient Total Drag Coefficient Purdue University School of Aeronautics and Astronautics 59

Lift Coefficient Lift Curve Slope { Purdue University School of Aeronautics and Astronautics 60

Lift Coefficient Lift Curve Slope { Purdue University School of Aeronautics and Astronautics 60

Break Even Point Final Aircraft Price Profit Margin MSRP of R/C Plane Profit Per

Break Even Point Final Aircraft Price Profit Margin MSRP of R/C Plane Profit Per Aircraft Units to Break Even $228. 28 15% $262. 52 $34. 24 1, 691 Purdue University School of Aeronautics and Astronautics

Materials Cost Purdue University School of Aeronautics and Astronautics

Materials Cost Purdue University School of Aeronautics and Astronautics

Avionics • JR 241 Servos for Rudder/Nose Wheel Steering, Elevator, Flaperons (1 ea. )

Avionics • JR 241 Servos for Rudder/Nose Wheel Steering, Elevator, Flaperons (1 ea. ) • JR 331 Servo for Retracts • Futaba GYA 350 Gyro Purdue University School of Aeronautics and Astronautics

Constraint Equations Climb Power Loading Stall Speed Purdue University School of Aeronautics and Astronautics

Constraint Equations Climb Power Loading Stall Speed Purdue University School of Aeronautics and Astronautics

Constraint Equations Climb Power Loading Stall Speed Purdue University School of Aeronautics and Astronautics

Constraint Equations Climb Power Loading Stall Speed Purdue University School of Aeronautics and Astronautics

Constraint Equations Sustained Turning Steady Flight Purdue University School of Aeronautics and Astronautics

Constraint Equations Sustained Turning Steady Flight Purdue University School of Aeronautics and Astronautics