System Requirements Review presented by: XG International Gihun Bae - Joe Blake - Jung Hoon Choi - Jack Geerer - Jean Gong - Hwan Song - Daniel Kim - Mike McCarthy - Nick Oschman - Bryce Petersen - Lawrence Raoux 1
Outline Mission Statement Market and Customer Overview Potential Competitors Concept of Operations System Design Requirements Advanced Technologies Initial Design Parameters Summary and Next Steps 2
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 Needs 1) Speed 2) Comfort 3) Reliability 4) Convenience 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 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 300 USD 20.97 mil, typically 245 delivered equipped Bombardier Challenger 600 USD 28.08 mil, typically series 795 delivered equipped Cessna 680 Citation Sovereign 287 delivered USD 17.469 mil, typically equipped Cessna 750 Citation X USD 21.721 mil, typically 301 delivered equipped Cessna Citation series 225 expected to sell in 2010 Dassault Falcon 2000 417 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 delivered USD 31.955 mil (G350), USD 36.955 mil (G450) Hawker 4000 130 ordered USD 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 Tokyo Narita (NRT) 13123 135 Haneda (HND) 9843 21 Shanghai Hongqiao (SHA) 11154 10 Pudong (PVG) 13123 13 Dubai Dubai (DXB) 13123 62 New Delhi Delhi (DEL) 14534 777 Paris Paris-Charles de Gaulle (CDG) 13780 392 Paris-Orly (ORY) 11975 291 London London Heathrow (LHR) 12799 83 London City (LCY) 4948 19 14
American Airports City Airport Runway Length (ft) Elevation (ft) John F. Kennedy (JFK) 14572 13 New York Newark Liberty (EWR) 11000 18 LaGuardia (LGA) 7000 21 Chicago O 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 New York Flight Departure Arrival Airport Code Range (nmi) LHR 3016.22 LAX 2129.86 JFK SEA 2092.49 LAS 1939.55 MIA 946.32 ORD 619.58 16
City-Pairs Operations International Flight Departure Arrival Airport Code Range (nmi) DEL 2297.57 SHA NRT 992.37 ICN 452.74 DXB 2831.99 CDG CIA 605.68 LHR 187.70 17
CONSTRAINT DIAGRAM 0.6 Thrust to Weight Ratio 0.34 Wing Loading 88 lb/ft 2 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 0.5 0.4 T SL /W 0 0.3 0.2 0.1 0 40 60 80 100 120 140 160 W 0 /S [lb/ft 2 ] 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 SFC cruise 0.5 SFC loiter 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 We TSL Wo b( Wo) ( AR) ( ) ( ) ( MMAX ) Wf Wo S C C C C C 1 2 3 4 5 Used MATLAB to obtain the coefficient values Technology factor = 0.95 We Wf Wo =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
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Benchmarking Plane Number of Seats W e (lb) W 0 (lb) M cruise Max. Range with Reserve (mi) FAA Takeoff 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 2,995 28
Benchmarking Comparable range, weight, and passenger count to G250 Will implement advanced concepts to achieve N+2 goals for 2020 launch 29
Design Requirements Compliance 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 analysis 34
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-activevibration-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