320 likes | 334 Views
Team 5. System Definition Review. Robert Aungst Chris Chown Matthew Gray Adrian Mazzarella. Brian Boyer Nick Gohn Charley Hancock Matt Schmitt. Outline of Presentation. Concept of Operations Design Requirements Concept Selection Payload Analysis Constraint Analysis Sizing Studies
E N D
Team 5 System Definition Review Robert Aungst Chris Chown Matthew Gray Adrian Mazzarella Brian Boyer Nick Gohn Charley Hancock Matt Schmitt
Outline of Presentation • Concept of Operations • Design Requirements • Concept Selection • Payload Analysis • Constraint Analysis • Sizing Studies • Final Concept
Mission Statement • Our mission is to provide an innovative advertising medium through the use of an Unmanned Aerial System (UAS)
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
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:
Schedule Generation Application 13 destination choices within 175 nm Sort schedule by Time, Destination, Plane, & Action Allows detailed operations planning Concept of Operations
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
4 Concepts Must Be Evaluated 2 LED Screens Under Wings 2 LED Screens on Fuselage 1 Banner 1 LED Screen on Fuselage
Payload • Component Selection and Sizing • Screen • Engine • Generator • Camera • Parachute
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
Engine and Propeller Considerations • 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 • ηp ≈ 0.77 • Cessna Caravan 208
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
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
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
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/s2 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
Constraint Analysis • Equations for Constraint Diagram: • Excess Power: • Stall Velocity: • Takeoff Ground Roll: • Landing Ground Roll:
Constraint Analysis • Aircraft Data Assumptions for Constraint Diagram Construction:
Constraint Diagram • From the Constraint Diagram: • Estimate for ideal starting design for current sizing estimates: • Wing Loading: 8 lbs/ft2 • Power-to-Weight Ratio: .18 hp/lb • Using these values as a starting point, the next step is to create carpet plots
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
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
Aircraft Concept • Isometric Drawing • “Walkaround” Drawing • Internal Layout Drawing • Requirements Compliance
Isometric and 3-View Drawing CONCEPTUAL DRAWING ONLY
Aircraft Concept – Walk Around Chart High wing configuration Single 550-750 hp piston engine with propeller T-tail empennage configuration Retractable tricycle landing gear configuration CONCEPTUAL DRAWING ONLY High aspect ratio, zero sweep wing 7.42’ x 30’ advertising screen
Internal Layout Drawing Tail Camera Screen Avionics Engine Rear Landing gear Nose Landing gear Fuel Fuel Generator Nose Camera Screen Ballistic Recovery System
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.
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.
Questions? Thank you for your time! Comments and Questions?