1. 2 Mission Statement Market Competition Concept of Operations Design Requirements Design...
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Transcript of 1. 2 Mission Statement Market Competition Concept of Operations Design Requirements Design...
System Requirements Review
New Environmentally
Responsible DesignNayanapriya Bohidar
Alex FickesAnthony Malito
Keyur PatelDanielle Woehrle
Matt Dienhart
Dean JonesRicardo Mosqueda
Dustin Souza
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Outline
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Mission Statement
Market
Competition
Concept of Operations
Design Requirements
Design Comparison
New Technologies and Advanced Concepts
Sizing Code
Summary
Mission StatementTo design an environmentally responsible aircraft for the twin aisle commercial transport market with a capacity of 300+ passengers, NASA’s N+2 capabilities, and an entry date of 2020-2025.
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NASA’s N+2 technology benefits include: Reducing cumulative noise by 42dB below Stage 4 Reducing take-off and landing NOx emissions to 75% below
CAEP6 levels Reducing fuel burn by 50% relative to “large twin-aisle
performance” (777-200LR) Reducing field length by 50% relative to the
large twin-aisle
Market
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Twin-aisle aircraft represent the fastest-growing market segment
Growth fueled by emerging economies (Asia-Pacific, Latin America, Middle East, etc.)
Image Source: Boeing Market Forecast
Asia-Pacific, Middle East, Latin America
Low Cost Carriers (LCC’s)
Passengers looking for cheap hub-to-hub and nonstop flights
Airliners looking for high capacity aircraft to meet increasing market demand
Customers
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Competition
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High-Speed Rail Systems
Boeing 737, Airbus A319
Image Source:www.hasea.com
Map of proposed high-speed rail
systems in China, along with estimated
travel times from Beijing
Operational City Pairs
Concept of Operations
Runway Length (ft) Flight Time (Min)
Origin Destination Origin DestinationRoute
Distance (nmi)
0.75Mach
0.85Mach
Tokyo, Japan
Sapporo,Japan
8,202 9,843 593.91 101.91 93.45
Seoul, South Korea
Jeju, South Korea
10,499 9,843 323.86 69.21 64.60
Sydney, Australia
Melbourne, Australia
8,301 11,998 509.89 91.73 84.47
Beijing, China
Shanghai,China
10,499 10,827 779.22 124.35 113.25
Hong Kong,China
Taipei, Taiwan
12,467 10,991 580.10 100.24 91.97
Tokyo, Japan
Naha, Japan
8,202 9,843 803.39 127.27 115.83
8Reference: Centre for Asia Pacific Aviation
Design Mission 400 Passengers (Max Payload) 4,000 nmi Range
(Tokyo-NHD to New Delhi-DEL: 3,200nmi)
Runway Length 8,300 ft (Takeoff)
Concept of Operations
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200 nmi4000 nmi
Design Requirements
Requirement Threshold TargetCruise Mach 0.75 0.85
Range 3,000 nmi 4,000 nmi
Field Length 8,300 ft 5,800 ft
Fuel Burn 33% reduction 50% reduction
NOx Emissions 50% below CAEP 6 75% below CAEP 6
Noise Reduction-32 dB
(cum. below Stage 4)-42 dB
(cum. below Stage 4)Pax Capacity 350 400
*Reference Vehicle B737-700
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Design Comparison
Requirement Target Design B767-300 B777-200 B737-700
Cruise Mach 0.85 0.85 0.84 0.785
Range 4,000 nmi 3,780 nmi 5,240 nmi 3,440
Field Length 5,800 ft. 7,907 ft. 8,202 ft. 8,300 ft.
Pax Capacity 400 350 440 149
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Reference: Boeing.com
Geared Turbofan Unducted Fan (UDF) Bio-Diesel
Trailing Edge Brushes Blended Wing Body Spiroid Winglets
New Technologies and Advanced Concepts
PROPULSION
AERODYNAMICS
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Fly By Wireless Morphing Trailing Edge
Composites Bonded Skin Panels
DYNAMICS & CONTROLS
STRUCTURES
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New Technologies and Advanced Concepts
Sizing Code Progress We used three sizing codes:
Simple – Incorporates design mission range, (L/D)max and number of passengers
Initial – Incorporates all of the above in addition to T/W and W0/S ratios.
MATLAB – Incorporates all of the above and the entire design mission (i.e. loiter time, emergency landing etc.)
Sizing codes usedBoeing 767 - 200ER with CF6-80C2B7F engines: Simple Initial MATLAB
Actual Calculated Error Calculated Error Calculated ErrorW0 (Maximum Takeoff Gross Weight) [lb] 395,000 383,375 -2.94% 389,861 -1.30% 546,580 38%We (Empty Weight) [lb] 184,400 195,300 5.91% 202,484 9.81% 252,340 37%
W f (Fuel Weight) [lb] - 122,275 - 121,576 - 243,550 -
Airbus A330 - 200 with CF6-80E1A2 engines: Simple Initial MATLABActual Calculated Error Calculated Error Calculated Error
W0 (Maximum Takeoff Gross Weight) [lb] 507,050 493,299 -2.71% 502,105 -0.98% 563,040 11%We (Empty Weight) [lb] 263,075 241,182 -8.32% 256,006 -2.69% 259,480 -1%W f (Fuel Weight) [lb] - 176,216 - 170,198 - 245,840 -
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Summary
Market forecasts predict a need for higher capacity aircraft to fly heavily trafficked routes
400 passenger, 4000 nmi range, N+2 compliant aircraft scheduled for deployment in 2020-2025
Next Steps Constraint Analysis Sizing code refinement Acquire Propulsion systems data Preliminary wing design
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