System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 1 System Definition Review Robert Aungst Chris Chown Matthew Gray Adrian Mazzarella Brian

System Definition Review - AAE 451 - Team 5

March 27, 2007Slide 1

System Definition Review

Robert AungstChris ChownMatthew GrayAdrian Mazzarella

Brian BoyerNick GohnCharley HancockMatt Schmitt

Team 5



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




• 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




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-Screen Machine Wing Screen

1-Screen Wonder Cessna with Banner

2 LED Screens on Fuselage

1 LED Screen on Fuselage

2 LED Screens

Under Wings

1 Banner



Pugh’s Method – Close Competition

2 Screen Machine 1 Screen Wonder Wing Screen Banner Tow Cessna

Flight Endurance + + +Autonomous Flight + + +Low Fuel Consumption - - -Ground Control + + +Display Dynamacism + + +Stability S - -Visibility of Messages + + -WOW Effect + + +Loiter Time + + +Size of display + + +Cruise Velocity - - -Loiter Velocity - - -Cruise Range + + +Turn Radius S S S

========== ========= ========= ==========Total + 9 9 8Total S 2 1 1Total - 3 3 5

DATUM



Modified Pugh’s Method – Justifying the 2-Screen Concept

Importance 2 Screen Machine 1 Screen Wonder Wing Screen Banner Tow Cessna

Flight Endurance 8 4 4 4 1Autonomous Flight 14 4 4 4 1Low Fuel Consumption 9 2 2 2 4Ground Control 5 4 4 4 1Display Dynamacism 6 4 4 4 1Stability 2 3 2 1 3Visibility of Messages 12 4 3 1 2WOW Effect 1 4 4 3 1Loiter Time 7 4 4 3 1Size of display 11 4 4 4 3Cruise Velocity 3 2 2 2 4Loiter Velocity 10 2 2 2 4Cruise Range 4 3 3 3 2Turn Radius 13 2 2 2 2

========== ========= ========= ==========Total 46 44 39 30Weighted 344 330 296 226



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



• 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

Engine and Propeller Considerations



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:

max

21.15landing Ld C gW

S

ρ μβ

=

21 1 1

ReoDSL o

oo p

CP V q n W dh dVWW A q S V dt g dtS

β βα η β π

⎧ ⎫⎡ ⎤⎪ ⎪⎢ ⎥⎛ ⎞ ⎛ ⎞= + + +⎨ ⎬⎜ ⎟⎢ ⎥⎜ ⎟

⎝ ⎠⎝ ⎠⎪ ⎪⎢ ⎥⎣ ⎦⎩ ⎭

max

3

21.32 psl o

o to L

P W

W g d C S

η βα ρ

⎛ ⎞= ⎜ ⎟⎜ ⎟

⎝ ⎠

max

21

2 stall L

WV C

Sρ=



Constraint Analysis

• Aircraft Data Assumptions for Constraint Diagram Construction:

Standard Atmosphere 30°F

Fuel Weight Fraction 1

Airspeed 135 kts (Cruise)60 kts

(Loiter)

Maximum Lift Coefficient (CLmax)

1.2

Parasite Drag Coefficient (Cd0)

0.03

Oswald’s Efficiency Factor 0.8

Aspect Ratio 14

Propeller Efficiency .85 / .75

Landing and Takeoff Ground Roll

2,500 ft.

Braking Friction Coefficient 0.3



Constraint DiagramConstraint Diagram

0

0.05

0.1

0.15

0.2

0.25

0.3

0.35

0.4

0 10 20 30 40 50 60

Wing Loading (W/S) [lbs/ft^2]

Power-to-Weight (P/W) [hp/lb]

Service Ceiling: Steady, Level Flight @ h =15,000 ft.

Rate of Climb: 1,500' per Minute Climb @Sea Level

Maximum Acceleration: Acceleration of 15' persecond per second in Level Flight @ h =10,000 ft.

Maneuverability: 1.5g Maneuver @ h =10,000 ft.

Takeoff Ground Roll: 2500 ft. Takeoff GroundRoll @ Sea Level

Landing Ground Roll: 2500 ft. LandingGround Roll @ Sea Level

Loiter: Steady, Level Flight @ h = 10,000 ft.and V = 60 kts.

Stall Velocity: 30% lower than Loiter Velocity@ Sea Level

Design Area:Wing Loading: 8Power-to-Weight: .18



Constraint Diagram - Relevant Region

Constraint Diagram

0.1

0.12

0.14

0.16

0.18

0.2

0.22

0.24

0.26

0.28

0.3

4 5 6 7 8 9 10

Wing Loading (W/S) [lbs/ft^2]

Power-to-Weight (P/W) [hp/lb]

= Service Ceiling : Steady , Level Flight @ h.ft 15,000

@Rate of Climb : 1,500 ' per Minute ClimbSea Level

'Maximum Acceleration : Acceleration of 15 = per second per second in Level Flight @ h.ft 10,000

= Maneuverability : 1.5 g Maneuver @ h.ft 10,000

Stall Velocity : 30% lower than Loiter VelocitySea Level @

Design Area:Wing Loading: 8Power-to-Weight: .18



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

7.42’ x

30’

advertisin

g 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



Internal Layout Drawing

Fuel Fuel

Rear

Landing

gear

Nose

Landing

gear

Screen

Screen

Engine

Generator

Avionics

Nose Camera

Tail Camera

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.



Design Requirements Compliance

Requirement Current Target Initial

Screen Dimensions (each)

7.42’ x 30’

7.42’ x 30’

8’ x 45’

Loiter Velocity 60 kts < 65 kts < 55 kts

Loiter Time 6 hrs > 6 hrs > 8 hrs

Cruise Range 400 nm > 400 nm > 400 nm

Loiter L/D (clean)

16.6 > 16 > 22

Specific Fuel Consumption

0. 5 lb/BHP/hr

< 0.5 lb/BHP/hr

< 0.5 lb/BHP/hr

Cruise Velocity 135 kts > 80 kts > 135 kts



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!

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Documents

System Definition Review - AAE 451 - Team 5 March 27, 2007 Slide 1 System Definition Review Robert Aungst Chris Chown Matthew Gray Adrian Mazzarella Brian