1. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 1 System Definition Review Robert Aungst Chris Chown Matthew Gray Adrian Mazzarella Brian Boyer Nick Gohn Charley Hancock Matt Schmitt Team 5

2. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 2 Outline of Presentation Concept of Operations Design Requirements Concept Selection Payload Analysis Constraint Analysis Sizing Studies Final Concept

3. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 3 Mission Statement Our mission is to provide an innovative advertising medium through the use of an Unmanned Aerial System (UAS)

4. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 4 Concept of Operations Continuous area coverage of South Florida metropolitan areas and beaches for advertising purposes Advertisements change based on location and circumstance –Targeted advertising for specific areas –e.g. advertising Best Buy near Circuit City locations Large, fuselage mounted LED screens will deliver adverts Business will be developed around this new technology

5. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 5 Concept of Operations Operations based at Sebring Regional Airport, serving 3 high population areas Continuous area coverage of city for 18 hrs (6am to 12am) –3 missions total with 6 hour loiter each Seven planes needed for 3 city operations with 1 spare Coverage area map:

6. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 6 Schedule Generation Application –13 destination choices within 175 nm –Sort schedule by Time, Destination, Plane, & Action –Allows detailed operations planning Concept of Operations

7. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 7 Major Design Requirements Customer Attributes –Advertisement visibility is paramount in order to meet customer’s needs –Must maintain a loiter speed which allows the public to retain the content of advertisements –For a successful venture, these two requirements must be clearly met in order to provide a superior service to the customer Engineering Requirements –Screen dimensions: 7.42’ x 30’ (each) –Loiter Speed: 60 kts –Loiter Endurance: 6 hrs

8. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 8 4 Concepts Must Be Evaluated 2-Screen MachineWing Screen 1-Screen WonderCessna with Banner 2 LED Screens on Fuselage 1 LED Screen on Fuselage 2 LED Screens Under Wings 1 Banner

9. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 9 Pugh’s Method – Close Competition

10. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 10 Modified Pugh’s Method – Justifying the 2-Screen Concept

11. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 11 Payload Component Selection and Sizing –Screen –Engine –Generator –Camera –Parachute

12. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 12 Screen Two High Intensity LED Screens –7.42 ft X 30 ft Viewable up to 1500 ft –500 lbs installed (each) –$120k cost (each) –Power Consumption 3.9 kw/5.2 hp, each –Daytime Viewable Brightness: 6500 cd/m² –Dynamic Display 60 fps video/text –Weatherproof

13. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 13 Honeywell TPE-331 Turboprop –Over 14,000 Manufactured –20+ Variants –HP ≈ 500-1700 –SFC ≈ 0.55 –Weight ≈ 350-400 lbs P&W PT6A Turboprop –Over 36,000 Manufactured –50+ Variants –HP ≈ 500–1900 –SFC ≈ 0.60 –Weight ≈ 300-400 lbs –Many 4000–8000 lb GTOW Single Engine Applications Propellers –Hartzell 3,4 Blade –McCauley 3,4,5 Blade –Diameter ≈ 82-110 in –Weight ≈ 50-150 lbs –Variable Pitch –Aluminum –η p ≈ 0.77 Cessna Caravan 208 Engine and Propeller Considerations

14. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 14 Generator Used to power screens, avionics, etc Screen requirements: –12.89 kW (17.3 hp) AC –30% efficiency AC-DC-DC conversion. –12.89 kW/screen X 2 screens X 30% = 7.7 kW DC (10.3 hp) Options: –Gas-powered APU + Generates excess power, provides emergency backup power - Uses considerable fuel, heavy –External propeller-powered APU + Provides emergency backup power - Increases drag, adds complexity –Electric generator driven by accessory gearbox + Simple, supplied and designed by engine manufacturer - Increases engine cost, no emergency power

15. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 15 Camera Micropilot MP-Dayview –High resolution CCD camera –Designed for UAV applications –Roll and elevation control via joystick –Two-axis gimbal for image stabilization –25x optical zoom –Weight: 2 lb

16. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 16 Parachute Recovery System Ballistic Recovery Systems –Largest current application: Cessna 182 (3100 lb GTOW) Cost: $17,445 System Weight: 85 lbs –Extrapolated specifications: Cost: $32,053 System Weight: 177.5 lbs Used in the event of catastrophic failure

17. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 17 Constraint Analysis Major performance constraints: – Service Ceiling: Steady, level flight @ h = 15,000 ft and V = 135 kts – Rate of Climb: 1,500 ft/min climb rate @ sea level and V = 135 kts – Maximum Acceleration: Acceleration of 15 ft/s 2 in level flight @ h = 10,000 ft and V = 60 kts – Maneuverability: 1.5g maneuver @ h = 10,000 ft and V = 135 kts – Loiter: Steady, level flight @ h = 1,000 ft and V = 60 kts – Stall Velocity: 30% lower than loiter velocity @ sea level – Takeoff Ground Roll: 2500 ft takeoff ground roll @ sea level – Landing Ground Roll: 2500 ft landing ground roll @ sea level

18. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 18 Constraint Analysis Equations for Constraint Diagram: –Excess Power: –Stall Velocity: –Takeoff Ground Roll: –Landing Ground Roll:

19. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 19 Constraint Analysis Aircraft Data Assumptions for Constraint Diagram Construction: Standard Atmosphere 30°F Fuel Weight Fraction1 Airspeed135 kts (Cruise) 60 kts (Loiter) Maximum Lift Coefficient (CLmax)1.2 Parasite Drag Coefficient (Cd0)0.03 Oswald’s Efficiency Factor0.8 Aspect Ratio14 Propeller Efficiency.85 /.75 Landing and Takeoff Ground Roll 2,500 ft. Braking Friction Coefficient0.3

20. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 20 Constraint Diagram

21. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 21 Constraint Diagram - Relevant Region

22. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 22 Constraint Diagram From the Constraint Diagram: –Estimate for ideal starting design for current sizing estimates: Wing Loading: 8 lbs/ft 2 Power-to-Weight Ratio:.18 hp/lb –Using these values as a starting point, the next step is to create carpet plots

23. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 23 Screen Trade Study Primary Driver: –Can the screen be seen clearly? Screen size Loiter velocity Loiter altitude Initial Reference: –Billboard advertising - 15 ft X 45 ft –Current LED billboards visible from 2000 ft Normalized target parameters: –Angular diameter of screen > 0.4° /sec –Angular velocity of aircraft < 1.0°/sec 10 ft 1000 ft

24. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 24 Sizing Approach Design Mission –Sizing done with MATLAB script using empty weight fraction regression from existing UAVs –Future studies to use FLOPS/ACS Basic assumptions –L/D: 17 –AR: 14 –Propeller Efficiency: 0.8 –Cbhp: 0.55

25. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 25 Aircraft Concept Isometric Drawing “Walkaround” Drawing Internal Layout Drawing Requirements Compliance

26. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 26 Isometric and 3-View Drawing CONCEPTUAL DRAWING ONLY

27. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 27 Aircraft Concept – Walk Around Chart 7.42’ x 30’ advertising screen T-tail empennage configuration High wing configuration High aspect ratio, zero sweep wing Single 550-750 hp piston engine with propeller Retractable tricycle landing gear configuration CONCEPTUAL DRAWING ONLY

28. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 28 Internal Layout Drawing Fuel Rear Landing gear Nose Landing gear Screen Engine Generator Avionics Nose Camera Tail Camera Ballistic Recovery System

29. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 29 Design Requirements Review Design requirements review was carried out to verify design requirements. Further research of requirements led to alteration of design requirements for the mission profile based on the “voice of the customer.” Design requirements compliance shows the current, target, and initial values. Initial values changed to target values as a result of the design requirements review.

30. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 30 Design Requirements Compliance RequirementCurrentTargetInitial Screen Dimensions (each) 7.42’ x 30’ 8’ x 45’ Loiter Velocity60 kts< 65 kts< 55 kts Loiter Time6 hrs> 6 hrs> 8 hrs Cruise Range400 nm> 400 nm Loiter L/D (clean)16.6> 16> 22 Specific Fuel Consumption 0. 5 lb/BHP/hr < 0.5 lb/BHP/hr Cruise Velocity135 kts> 80 kts> 135 kts

31. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 31 Next Steps Detailed design in specific disciplines: –Aerodynamics –Structures –Propulsion –Flight Mechanics and Performance Detailed aerodynamic sizing. Finalize internal layout and component weights. Select structural materials. Internal structural component design. Landing gear design. Compile necessary carpet plots. Select an engine and finalize propeller dimensions. Investigate the fuselage color that gives optimized screen visibility.

32. System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 32 Questions? Thank you for your time! Comments and Questions?