system definition review - aae 451 - team 5 march 27, 2007 slide 1 system definition review robert...
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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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 2
Outline of Presentation
• Concept of Operations• Design Requirements• Concept Selection• Payload Analysis• Constraint Analysis• Sizing Studies• Final Concept
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 3
Mission Statement
• Our mission is to provide an innovative advertising medium through the use of an Unmanned Aerial System (UAS)
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 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:
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 6
• Schedule Generation Application– 13 destination choices within 175 nm– Sort schedule by Time, Destination, Plane, & Action– Allows detailed operations planning
Concept of Operations
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 8
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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 9
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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 10
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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 11
Payload
• Component Selection and Sizing– Screen– Engine– Generator– Camera– Parachute
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 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– ηp ≈ 0.77
• Cessna Caravan 208
Engine and Propeller Considerations
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 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/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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 18
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=
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 19
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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 20
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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 21
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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 22
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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 25
Aircraft Concept
• Isometric Drawing• “Walkaround” Drawing• Internal Layout Drawing• Requirements Compliance
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 26
Isometric and 3-View Drawing
CONCEPTUAL
DRAWING ONLY
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 27
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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 28
Internal Layout Drawing
Fuel Fuel
Rear
Landing
gear
Nose
Landing
gear
Screen
Screen
Engine
Generator
Avionics
Nose Camera
Tail Camera
Ballistic Recovery System
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 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.
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 30
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
System Definition Review - AAE 451 - Team 5
March 27, 2007Slide 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.