Team 2
AAE451 System Requirements Review
Chad Carmack
Aaron Martin
Ryan Mayer
Jake Schaefer
Abhi Murty
Shane Mooney
Ben Goldman
Russell Hammer
Donnie Goepper
Phil Mazurek
John Tegah
Chris Simpson
Outline
1
• Brief Market Overview Customer needs, benefits ,market size and competitors.
• Concept of Operations Customer satisfaction
Flight ranges, runway lengths
Aircraft Payload and passenger capability
Mission Sketch
Segment descriptions
• System Design Requirements Quality Function Deployment(QFD)
NASA N+2 goals
New technology adopted
• Initial Estimations Lift to Drag ratio, Specific Fuel Consumption(SFC)
Empty weight fraction prediction
• Future Progress Project goals and deadlines.
Mission Statement
Designed to maximize productivity and
minimize travel time.
Design an environmentally sensitive business jet
with a wide range of capabilities.
An elite ownership experience awaits
2
Benefits
Time saving capability
Long range
Comfort and Luxury
3
Primary Customers
Multinational Corporations
Celebrities
Governments
Fractional Air Services
4
“Now more than ever, a business aircraft is
an essential tool for capturing new
opportunities, for compacting two- to three-
week trips into two to three days. ”
-Jeff Habib, Senior Vice President of U.S. and
Canadian Sales, Dassault Falcon Jet
Projected Market
5
*Source – Honeywell Aviation Forecast
The graph indicates that the Long Range market will continue to
grow in the next decade.
Jet Purchases
6
Big Cabin Jets Captured 40% of Mentions and ~70% of $Value*
*Source – Honeywell Aviation Forecast
Purchase Expectations by Region
7
Source – Honeywell Aviation Forecast
Meeting Our Customer’s Needs
Travel Fast
◦ Mach 0.85 Long Range Cruise
◦ An Initial Cruise Altitude of 42,000 ft. helps evade
commercial traffic
Travel Far
◦ Maximum Range of 6350 nm
◦ LA to Hong Kong, Chicago to Tokyo, non-stop.
Travel Productively
◦ Spacious and comfortable cabin provides a generous
place to both work and relax
8
Proposed Fuselage
9
Amenities Dimensions
Recliners (10x) – 10 Seats L: 35”, W: 33”
Sofas (2x) – 6 Seats L: 90”, W: 35”
Tables (3x) L: 24”, W: 35”
ConferenceTable L: 36”, W: 60”
Lavatories (2x) L: 62”
Bar L:62”, W:40”
Flight Attendant Seating (2x) – 2 Seats L: 30”, W:30”
10
Aircraft Amenities
Amenity Amenity Length Current Total Length
1 Lavatory 62” x 1 Lavatories 5’ 2”
4 Recliners 35” x 4 Recliners 16’ 10”
1 Tables 24” x 1 Table 18’ 10”
1 Conference Table 38” x 1 Conference Table 22’
2 Sofas 90” x 2 Sofas 37’
1 Bar/Kitchenette 72” x 1 Bar/Kitchenette 43’
Miscellaneous Spacing 84” 50’
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Approximating Cabin Length
Amenity Dimensions
Cabin Layout and Dimensions
Fuselage Cross-Section
13
Total Aircraft Length = (50’ Cabin) + (14’ 2” Nose) + (23’ 10” Tail)
= 88’
Cabin Diameter = 8’ 10”
Fineness Ratio = 9.96
14
Aircraft Characteristics
Volume per passenger (Max. Capacity) = 81.5 cubic feet
Representative City Pairs
Non-stop possibilities:
◦ LA to Seoul
(5209 nm)
◦ Dallas to Moscow
(5035 nm)
◦ LA to Beijing
(5432 nm)
◦ New York to Dubai
(5949 nm)
◦ Chicago to Tokyo
(5452 nm)
◦ LA to Hong Kong
(6309 nm)
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Design Mission
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0-1: Take off to 50 ft. 5-6: Climb to 5000 ft. (Best Rate)
1-2: Climb to 42000 ft. (Best Rate) 6-7: Divert to Alternate 200 nm
2-3: Cruise at Mach 0.85 7-8: 45 minute Holding Pattern
3-4: Decent to Land (No Range Credit) 8-9: Land
4-5: Missed Approach (Go Around)
3
0 1
2
4 5
6 7
8 9Takeoff
Climb
Cruise
6350 nm 200 nm
Los Angeles Hong Kong Alternate
Operating Missions
New York to Los Angeles◦ Mach 0.9*
◦ 2146 nm
◦ 16 passengers
Chicago to Houston◦ Mach 0.9*
◦ 804 nm
◦ 4 passengers
*Maximum operating Mach dependent on engine selection
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Benchmark Aircraft
Gulfstream G550
Gulfstream G650
Bombardier Global Express
XRS
Bombardier Global 5000
Gulfstream G500
Citation X
Bombardier Challenger 300
Bombardier Challenger 850
Bombardier Learjet 60 XR
Bombardier Learjet 85
Cessna Citation Sovereign
Gulfstream G150
Hawker 4000
Hawker 750
Hawker 850XP
Hawker 900XP
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Fuel Consumption Benchmark
6.31 lbs/nm (Jane’s All The World’s Aircraft) for
the Gulfstream G650
3.78 lbs/nm As 40% Reduction Design Goal
Currently the G150 Burns approximately 3.49
lbs/nm
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NASA Subsonic Fixed Wing Project
Develop improved prediction methods and
technologies for lower noise, lower emissions,
and higher performance for subsonic aircraft
Analyzing Research and Testing Methods to
make major improvements by 2020
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Advanced Technology
Unducted Fan shows promise to reduce emissions and fuel
consumption
“ERA is focused on the goals of NASA’s N+2, a notional
aircraft with technology primed for development in the 2020
time frame as part of the agency’s subsonic fixed wing
program”
◦ Aviation Week Dec 14, 2009
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Benefits of UDF
Relative to 1998 levels, NASA plans to reduce
cumulative noise levels to 42 dB below stage 4, 75%
lower NOx emissions, and reduce fuel burn by 40%
◦ Aviation Week
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House of Quality
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Requirements Compliance Matrix
Part 1
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Performance
Characteristics
Target Threshold Current
Range 6300 nm 6000 nm 6300 nm
Takeoff Distance 6000 ft 7000 ft 6000 ft
Max. Pax. 17 8 16
Cruise Mach 0.85 0.8 0.85
Cruise Altitude 45000 ft 40000 ft 45000 ft
Requirements Compliance Matrix
Part 2
25
Performance
Characteristics
Target Threshold Current
Cabin Noise 60 dB 70 dB 65 dB
LTO NOx
Emissions
CAEP 6-75% CAEP 6-60% CAEP 6-70%
Cumulative
certification
noise limits
232 dB 274 dB 274 dB
Requirements Compliance Matrix
Part 3
26
Performance
Characteristics
Target Threshold Current
Fuel cost per
mile
3.8 lb/mile 4 lb/mile 6.23 lb/mile
Loading Door
Still height
4 ft 5 ft 4 ft
Variable Costs $4100/hr $4300/hr $4100/hr
Constraint Diagram
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Constraint Diagram Analysis
T/W limited by Second Segment Climb
◦ Current min. is ~0.33
W/S limited by Landing Ground Roll
(3500ft)
◦ Current max. is ~100
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Aircraft Database
Database Includes two classes
◦ Class 1: Larger Business Jets
Gulfstream G500
Gulfstream G550
Gulfstream G650
Bombardier Global 5000
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Aircraft Database
Database Includes two classes
◦ Class 2: Smaller Business Jets
Cessna Citation X
Cessna Citation Sovereign
Bombardier Challenger 300, 850
Bombardier Learjet 60XR, 85
Gulfstream G150
Hawker 750, 850XP, 900XP, 4000
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Aircraft Database
31
y = 1.378x-0.08
0.45
0.47
0.49
0.51
0.53
0.55
0.57
0.59
0.61
0.63
0.65
0 20000 40000 60000 80000 100000 120000
We/W
o
Wo
Team 2 Aircraft Database
Class 2: Smaller Planes
Class 1: Larger Planes
Performance Estimates
Aspect Ratio
◦ AR = 8.0
◦ Estimated from existing Business Jets
Lift to Drag Ratio at Cruise
◦ L/D = 0.85[1.4(AR)+7.1] = 15.56
◦ Source: Raymer and Carte
Specific Fuel Consumptions
◦ SFCcruise = 0.5
◦ SFCloiter = 0.6
◦ Estimated from existing Business Jet engine data
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Weight Estimates
Least Squares Regression: 108,000 lbs
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0.154 0.016 0.394 0.089 0.934 0.032
0 0
0
3.08 ( / ) ( / )eSL cruise
WW AR T W W S M Range
W
1 2 3 4 5 6
0 0
0
( / ) ( / )c c c c c ceSL cruise
WbW AR T W W S M Range
W
Weight Estimates
Curve Fit with Similar Planes: 92,000 lbs
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y = 67.69x-0.42
0.5
0.51
0.52
0.53
0.54
0.55
0.56
0.57
84000 86000 88000 90000 92000 94000 96000 98000 100000 102000
We/W
o
Wo
Similarly Sized Planes
0.422
0 0
0
67.69ceWaW W
W
Performance Prediction
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0.7 0.72 0.74 0.76 0.78 0.8 0.82 0.84 0.86 0.88 0.9
5600
5800
6000
6200
6400
6600
6800
7000
7200
Mach Number
Range (
nm
i)
Range vs. Mach for Various Loadings
08 Passengers
12 Passengers
16 Passengers
Technology Factors
Currently none are being used
◦ Predicts “worst case” in early design stage
◦ Should make it easier to meet initial design
goals once technology factors are included
Anticipated Technology Factors
◦ Empty Weight (composites)
◦ Engine Efficiency (unducted turbofan)
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Next Steps
More accurate L/D equations
Inclusion of technology factors in sizing
Development of aircraft performance code
Acquiring engine configurations and performance data
Choosing wing type and analyzing aerodynamic data to minimize drag
Completing aircraft Catia model
37
Questions?
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