Team 5
System Definition Review
Robert Aungst
Chris Chown
Matthew Gray
Adrian Mazzarella
System Definition Review - AAE 451 - Team 5
Brian Boyer
Nick Gohn
Charley Hancock
Matt Schmitt
March 27, 2007 Slide 1
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, 2007 Slide 2
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, 2007 Slide 3
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, 2007 Slide 4
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, 2007 Slide 5
Concept of Operations
•
Schedule Generation Application
–
–
–
13 destination choices within 175 nm
Sort schedule by Time, Destination, Plane, & Action
Allows detailed operations planning
System Definition Review - AAE 451 - Team 5
March 27, 2007 Slide 6
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, 2007 Slide 7
4 Concepts Must Be Evaluated
2-Screen Machine
2 LED Screens on Fuselage
1-Screen Wonder
Wing Screen
2 LED Screens
Under Wings
Cessna with Banner
1 Banner
1 LED Screen on Fuselage
System Definition Review - AAE 451 - Team 5
March 27, 2007 Slide 8
Pugh’s Method – Close Competition
Flight Endurance
Autonomous Flight
Low Fuel Consumption
Ground Control
Display Dynamacism
Stability
Visibility of Messages
WOW Effect
Loiter Time
Size of display
Cruise Velocity
Loiter Velocity
Cruise Range
Turn Radius
Total +
Total S
Total System Definition Review - AAE 451 - Team 5
2 Screen Machine
+
+
+
+
S
+
+
+
+
+
S
==========
9
2
3
1 Screen Wonder
+
+
+
+
+
+
+
+
+
S
=========
9
1
3
Wing Screen
+
+
+
+
+
+
+
+
S
=========
8
1
5
Banner Tow Cessna
DATUM
==========
March 27, 2007 Slide 9
Modified Pugh’s Method – Justifying the 2-Screen Concept
Flight Endurance
Autonomous Flight
Low Fuel Consumption
Ground Control
Display Dynamacism
Stability
Visibility of Messages
WOW Effect
Loiter Time
Size of display
Cruise Velocity
Loiter Velocity
Cruise Range
Turn Radius
Importance
8
14
9
5
6
2
12
1
7
11
3
10
4
13
Total
Weighted
System Definition Review - AAE 451 - Team 5
2 Screen Machine
4
4
2
4
4
3
4
4
4
4
2
2
3
2
==========
46
344
1 Screen Wonder
4
4
2
4
4
2
3
4
4
4
2
2
3
2
=========
44
330
Wing Screen
4
4
2
4
4
1
1
3
3
4
2
2
3
2
=========
39
296
Banner Tow Cessna
1
1
4
1
1
3
2
1
1
3
4
4
2
2
==========
30
226
March 27, 2007 Slide 10
Payload
• Component Selection and Sizing
–
–
–
–
–
Screen
Engine
Generator
Camera
Parachute
System Definition Review - AAE 451 - Team 5
March 27, 2007 Slide 11
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, 2007 Slide 12
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
System Definition Review - AAE 451 - Team 5
March 27, 2007 Slide 13
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, 2007 Slide 14
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, 2007 Slide 15
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, 2007 Slide 16
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, 2007 Slide 17
Constraint Analysis
• Equations for Constraint Diagram:
– Excess Power:
PSL  V

Wo   p

q






2
 CDo
1  n   Wo  1 dh 1 dV 
 W   A Re  q   S   V dt  g dt 

  

 o
 S


– Stall Velocity:
W 1
 Vstall 2CLmax
S 2
– Takeoff Ground Roll:
3
Psl 1.32 p   Wo  2



Wo g d to   CLmax S 
– Landing Ground Roll:
W d landing  CLmax g 

S
1.152 
System Definition Review - AAE 451 - Team 5
March 27, 2007 Slide 18
Constraint Analysis
• Aircraft Data Assumptions for Constraint Diagram
Construction:
Standard Atmosphere
Fuel Weight Fraction
Airspeed
Maximum Lift Coefficient (CLmax)
Parasite Drag Coefficient (Cd0)
1
135 kts (Cruise)
60 kts (Loiter)
1.2
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
System Definition Review - AAE 451 - Team 5
30°F
0.3
March 27, 2007 Slide 19
Constraint Diagram
Constraint Diagram
0.4
0.35
Service Ceiling: Steady, Level Flight @ h =
15,000 ft.
Power-to-Weight (P/W) [hp/lb]
0.3
Rate of Climb: 1,500' per Minute Climb @
Sea Level
Maximum Acceleration: Acceleration of 15' per
second per second in Level Flight @ h =
10,000 ft.
Maneuverability: 1.5g Maneuver @ h =
10,000 ft.
0.25
Design Area:
Wing Loading: 8
Power-to-Weight: .18
0.2
Takeoff Ground Roll: 2500 ft. Takeoff Ground
Roll @ Sea Level
Landing Ground Roll: 2500 ft. Landing
Ground Roll @ Sea Level
0.15
Loiter: Steady, Level Flight @ h = 10,000 ft.
and V = 60 kts.
0.1
Stall Velocity: 30% lower than Loiter Velocity
@ Sea Level
0.05
0
0
10
System Definition Review - AAE 451 - Team 5
20
30
40
Wing Loading (W/S) [lbs/ft^2]
50
60
March 27, 2007 Slide 20
Constraint Diagram - Relevant Region
Constraint Diagram
0.3
0.28
Power-to-Weight (P/W) [hp/lb]
0.26
= Service Ceiling: Steady, Level Flight @ h
.ft 15,000
0.24
0.22
@ Rate of Climb: 1,500' per Minute Climb
Sea Level
Design Area:
Wing Loading: 8
Power-to-Weight: .18
0.2
'Maximum Acceleration: Acceleration of 15
= per second per second in Level Flight @ h
.ft 10,000
= Maneuverability: 1.5g Maneuver @ h
.ft 10,000
0.18
Stall Velocity: 30% lower than Loiter Velocity
Sea Level @
0.16
0.14
0.12
0.1
4
5
System Definition Review - AAE 451 - Team 5
6
7
8
Wing Loading (W/S) [lbs/ft^2]
9
10
March 27, 2007 Slide 21
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, 2007 Slide 22
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, 2007 Slide 23
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, 2007 Slide 24
Aircraft Concept
• Isometric Drawing
• “Walkaround” Drawing
• Internal Layout Drawing
• Requirements Compliance
System Definition Review - AAE 451 - Team 5
March 27, 2007 Slide 25
Isometric and 3-View Drawing
System Definition Review - AAE 451 - Team 5
CONCEPTUAL
DRAWING
ONLY
March 27, 2007 Slide 26
Aircraft Concept – Walk Around Chart
High wing
configuration
Single 550-750 hp
piston engine
with propeller
T-tail
empennage
configuration
High aspect
ratio, zero
sweep wing
System Definition Review - AAE 451 - Team 5
Retractable
tricycle
landing gear
configuration
7.42’ x 30’
advertising
screen
CONCEPTUAL
DRAWING
ONLY
March 27, 2007 Slide 27
Internal Layout Drawing
Tail Camera
Screen
Avionics
Engine
Nose
Landing
gear
Fuel
Rear
Landing
gear
Fuel
Generator
Nose Camera
Screen
Ballistic Recovery System
System Definition Review - AAE 451 - Team 5
March 27, 2007 Slide 28
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, 2007 Slide 29
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
400 nm
> 400 nm
> 400 nm
16.6
> 16
> 22
0. 5
lb/BHP/hr
135 kts
< 0.5
lb/BHP/hr
> 80 kts
< 0.5
lb/BHP/hr
> 135 kts
Cruise Range
Loiter L/D (clean)
Specific Fuel
Consumption
Cruise Velocity
System Definition Review - AAE 451 - Team 5
March 27, 2007 Slide 30
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.
System Definition Review - AAE 451 - Team 5
March 27, 2007 Slide 31
Questions?
Thank you for your time!
Comments and Questions?
System Definition Review - AAE 451 - Team 5
March 27, 2007 Slide 32