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System RequirementsReview XG International
presented by:
Gihun Bae - Joe Blake - Jung Hoon Choi - Jack Geerer - Jean Gong - Hwan Song -
Daniel Kim - Mike McCarthy - Nick Oschman - Bryce Petersen - Lawrence Raoux1
Outline
• Mission Statement
• Market and Customer Overview
• Potential Competitors
• Concept of Operations
• System Design Requirements
• Advanced Technologies
• Initial Design Parameters
• Summary and Next Steps2
Mission Statement
• Our environmentally-sensitive aircraft is going to provide the customer with a transportation method that combines speed, comfort, and convenience all while meeting NASA’s N+2 criteria.
3
Environmentally-Sensitive
• Environmentally-sensitive implies demanding the final product have as little environmental impact as possible.
• An aircraft can damage the environment in many ways, from fossil fuel usage to harmful emissions to noise, all of which must be considered.
• Environmentally-sensitive does not imply a lack of performance. 4
Customer•Benefits:1) Lower fuel consumption
and therefore lower operating cost.
2) Services wide range of airports.
3) Quiet, efficient travel option.
•Primary Function:1) Transport business executives.2) Travel a distance of 800-1000 NM
such as from Chicago to New York at a Mach number of about .85 .
3) Meet all NASA N+2 criteria
•Needs1) Speed2) Comfort3) Reliability4) Convenience
5
Market
• The primary market for our aircraft includes partial jet ownership firms and private businesses.
• Rolls-Royce’s 2009 forecast predicts 20,921 business jet deliveries between 2019 -2028. This figure scales down to 11,600 deliveries between 2020-2025.
• If our design meets all performance goals as well as NASA’s N+2 criteria, we think we can sell 5% of these projected deliveries.
• To be conservative we will aim to sell a 3% market share, corresponding to 350 aircraft needed between 2020-2025.
6
Competitors
Plane Units Cost per Unit
Bombardier Challenger 300245 delivered
USD 20.97 mil, typically equipped
Bombardier Challenger 600 series 795 delivered
USD 28.08 mil, typically equipped
Cessna 680 Citation Sovereign 287 deliveredUSD 17.469 mil, typically equipped
Cessna 750 Citation X301 delivered
USD 21.721 mil, typically equipped
Cessna Citation series 225 expected to sell in 2010
Dassault Falcon 2000417 produced
USD 28.55-30.765 mil (2000DX, 2000LX)
Dassault Falcon 50, 50EX 352 delivered USD 20.6 mil (yr. 2004)
Gulfstream 350/450 170 deliveredUSD 31.955 mil (G350), USD 36.955 mil (G450)
Hawker 4000 130 orderedUSD 21.671 mil, typically equipped
7
Competitors
•Besides competition from other aircraft manufacturers, other forms of competition include:
1) Other forms of high speed public transportation, for example bullet trains.
2) A major advancement in the commercial aviation industry.3) Some other form of never before seen futuristic
transportation.
8
Customer Needs
• For Private
– Noise Reduction
– Safety
– Large Cabin Area
• For Charter Company
– Lower Operating Cost
– Long Max Range
– Fast Cruise Speed
9
To Satisfy Needs
• Private
– Low Noise Emission Engine
– Dual Engine, Good Sliding Capability
– Maximum Legroom
• Charter Company’s
– Fuel Efficient Engine
– Transatlantic Capability for more Customers
– Max cruise speed of 0.82M
10
Passenger Capacity / Payload
• 1 pilot, 1 co-pilot
• 8 to 12 passengers (depending on customer requirement)
• 1 flight attendant for transatlantic flight (FAR Section 121.391)
• Maximum Payload = 4000 lb
11
Mission Sketch
12
Aircraft Design Missions
13
Asia & Europe Airports
City Airport Runway Length (ft) Elevation (ft)
Seoul Incheon (ICN) 13123 63
TokyoNarita (NRT) 13123 135
Haneda (HND) 9843 21
ShanghaiHongqiao (SHA) 11154 10
Pudong (PVG) 13123 13
Dubai Dubai (DXB) 13123 62
New Delhi Delhi (DEL) 14534 777
ParisParis-Charles de Gaulle (CDG) 13780 392
Paris-Orly (ORY) 11975 291
LondonLondon Heathrow (LHR) 12799 83
London City (LCY) 4948 19
14
American Airports
City Airport Runway Length (ft) Elevation (ft)
New York
John F. Kennedy (JFK) 14572 13
Newark Liberty (EWR) 11000 18
LaGuardia (LGA) 7000 21
ChicagoO’Hare (ORD) 13000 668
Chicago Midway (MDW) 6522 620
LA Los Angeles (LAX) 12091 126
Las Vegas McCarran (LAS) 14510 2181
Miami Miami (MIA) 13000 8
Seattle Seattle-Tacoma (SEA) 11900 433
15
City-Pairs Operations
Departure Arrival
Airport Code Range (nmi)
JFK
LHR 3016.22
LAX 2129.86
SEA 2092.49
LAS 1939.55
MIA 946.32
ORD 619.58
New York Flight
16
City-Pairs Operations
Departure Arrival
Airport Code Range (nmi)
SHA
DEL 2297.57
NRT 992.37
ICN 452.74
CDG
DXB 2831.99
CIA 605.68
LHR 187.70
International Flight
17
CONSTRAINT DIAGRAM
0
0.1
0.2
0.3
0.4
0.5
0.6
40 60 80 100 120 140 160
TS
L/W
0
W0/S [lb/ft2]
Top of climb (1g steady, level flight, M = 0.85 @ h=45K, service ceiling)
Subsonic 2g manuever, 250kts @ h =10K
Takeoff ground roll 4000 ft @ h = 5K, +15° hot day
Landing ground roll 2500 ft @ h = 5K, +15° hot day
Second segment climb gradient above h = 5K, +15° hot day
Thrust to Weight Ratio ≈ 0.34
Wing Loading ≈ 88 lb/ft2
18
Estimated Lift to Drag Ratio and Specific Fuel Consumption
Lift to Drag Ratio
Subsonic (L/D)max 19.7
Subsonic (L/D)cruise 17.139
Subsonic (L/D)loiter 19.7
•Lift to Drag Ratio varies with Aspect Ratio
Specific Fuel Consumption
SFCcruise 0.5
SFCloiter 0.4
•Specific Fuel Consumption was obtained from various jets
•This will change the thrust of the jets ( )
19
Empty Weight Fraction Predictor
• Used carefully chosen data from 11 existing airplanes of various manufacturers– Technical specifications from…
• Jane’s All the World’s Aircraft• Aviation Week• Each manufacturer’s websites
• Gulfstream: G200, G250• Bombardier: Challenger 850, Learjet 60XR,
Learjet 85• Cessna: Citation Sovereign, Citation XHawker:
750, 850XP, 900XP, 4000 20
Equation - Technology Factor - Results
1 2 3 4 5( ) ( ) ( ) ( ) ( )e SL oC C C C C
o MAX
f o
W T Wb W AR M
W W S
eW
fW
oW
•Used MATLAB to obtain the coefficient values
•Technology factor = 0.95
=19628.83 lb
=10016.57 lb
=31805.40 lb
21
Design QFD
• The ‘What’
– Performance
– Design
– Practical
– Comfort
22
Design QFD
• NASA Subsonic Transport Research Goals
23
Design QFD
• The ‘How’– Noise – Fuel Consumption – Take off Distance– LTO Nox Emissions – Speed– Size – Weight– Initial costs– Long term costs– Range
24
Design QFD
25
Airplane Cabin Layouts
26
27
Benchmarking
PlaneNumber of
SeatsWe
(lb)
W0
(lb)
Mcruise
Max.Range with
Reserve(mi)
FAATakeoff
Field Length
(ft)
FAA Landing
Field Length
(ft)
Endeavour XG 8-12 19,628 31,805 .80 4,258 4,000 2,500
Bombardier Challenger 300 11 23,500 38,850 .80 3,568 4,810 2,600
Cessna Citation Sovereign 9-12 17,720 30,300 472 mph 3,276 3,640 2,650
Cessna Citation X 8-12 21,700 36,100 552 mph 3,533 5,140 3,400
Dassault Falcon 2000DX 8-19 22,360 41,000 .80 3,250 5,300 2,640
Gulfstream G250 10 23,750 39,600 .80 3,906 - -
Hawker 4000 8-10 22,800 39,500 .82 4,119 5,169 2,99528
Benchmarking
• Comparable range, weight, and passenger count to G250
• Will implement advanced concepts to achieve N+2 goals for 2020 launch
29
Design RequirementsCompliance Matrix
Requirement Target Threshold Current Estimate Compliant
Maximum Mach Number 0.85 0.8 0.8 Yes
Empty Weight (lb) 18,500 20,000 19,629 Yes
Gross Weight (lb) 28,000 32,000 31,805 Yes
Takeoff Distance (ft) 2,300 2,800 3,100 No
Maximum Range (nmi) 3,700 3,600 3,700 Yes
Design Mission Range (nmi) 3,700 3,600 3,700 Yes
Noise (dB) 40 50 77 No
Seats 10 8 8 Yes
Volume Per Passenger (ft^3) 65 60 60 Yes
TSFC (% of avg) 55 65 65 Yes
N0X Emissions (% of avg.) 25 50 100 No
* Highlighted Requirements denote NASA N+2 guidelines.
Targets and Thresholds are based on "Project Opportunity Description" N+2 guidelines, as well as market, client, and company-driven protocols.
Current Estimates were generated using several comparable in-service aircraft including the Cessna Citation and Gulfstream G540
30
Advanced Concepts
• Solar Film– New films are flexible, lightweight, rapidly increasing in
efficiency, declining in price
– Could generate up to 30 watts per square foot, power interior lighting, avionics, high-tech devices
• Propfan– 35% better fuel efficiency than contemporary turbofans
– Integrated AVCS to reduce cabin noise
– Mach .8 achievable
31
Advanced Concepts
• High-Lift Devices– Engine blows direct flow along external downward flaps at
trailing edge (“Cascade effect”)
• Vortex Generators– Delay flow separation
– Increase maximum takeoff weight
• Selective Catalytic Reduction
– Reduces N0X emissions by as much as 90%
– Creates ammonia as a byproduct
32
Advanced Concepts•Composite Material–Large Scale Composite Material via VARTM (Vacuum Assisted Resin Transfer Method)–20%+ reduction of weight–Up to 60% of body made up of Composite material
•Carbon Nanotube–Possible increase of strength–Reduction of weight–High cost to overcome
33
Next Steps
• Demonstrate ability to meet performance targets, customer requirements through benchmarking, proof-of-concept testing
• Further explore possible configurations, technologies
– Place engines, wings, control surfaces
– Analyze effects/trade-offs of integrated systems
• Revisit/Refine QFD, Requirements Compliance Matrix, sizing code, 3-D model
• Begin aerodynamic analysis34
Summary
• 8 Passenger, 3700 mi range N+2 compliant aircraft scheduled for deployment in 2020
• Environmentally-Sensitive manufacturing/operation without sacrificing performance
• Focus on fractional ownership firms, foreign markets
• At least 600 aircraft sold by 2031
• Incorporates hybrid power systems & advanced aerodynamics to reduce fuel consumption, increase mission flexibility
• Serves as a design platform for meeting NASA N+3 guidelines by 2025 35
Appendix
36
Citation
• Aviation Week & Space Technology: Aerospace Source Book 2009 1 Feb. 2010.
• http://greenecon.net/understanding-the-cost-of-solar-energy/energy_economics.html
• http://www.flightglobal.com/articles/2009/02/16/322533/sikorksy-to-test-active-vibration-control-for-s-92-rotor.html
• http://www.aerospaceweb.org/question/propulsion/q0067.shtml
• http://adsabs.harvard.edu/abs/1980aiaa.confR....M
• http://www.arvinmeritor.com/media_room/pdfs/gp0440.pdf
• Project Opportunity Description
• Crossley, William “Aircraft initial sizing Excel file”, “In-class QFD example file”, “Constraint diagram Excel file” 1 Feb. 2010.
• Del Rosario, R., and Wahls, R., “Subsonic Transport Research at NASA”, presented as the School of Aeronautics and Astronautics Colloquium, Nov. 5, 2009.
37