System Requirements Review

Transcription

1 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

2 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

3 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

4 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

5 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 NM such as from Chicago to New York at a Mach number of about.85. 3) Meet all NASA N+2 criteria 5

6 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 This figure scales down to 11,600 deliveries between 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

7 Competitors Plane Units Cost per Unit Bombardier Challenger 300 USD mil, typically 245 delivered equipped Bombardier Challenger 600 USD mil, typically series 795 delivered equipped Cessna 680 Citation Sovereign 287 delivered USD mil, typically equipped Cessna 750 Citation X USD mil, typically 301 delivered equipped Cessna Citation series 225 expected to sell in 2010 Dassault Falcon produced USD mil (2000DX, 2000LX) Dassault Falcon 50, 50EX 352 delivered USD 20.6 mil (yr. 2004) Gulfstream 350/ delivered USD mil (G350), USD mil (G450) Hawker ordered USD mil, typically equipped 7

8 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

9 Customer Needs For Private Noise Reduction Safety Large Cabin Area For Charter Company Lower Operating Cost Long Max Range Fast Cruise Speed 9

10 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

11 Passenger Capacity / Payload 1 pilot, 1 co-pilot 8 to 12 passengers (depending on customer requirement) 1 flight attendant for transatlantic flight (FAR Section ) Maximum Payload = 4000 lb 11

12 Mission Sketch 12

13 Aircraft Design Missions 13

14 Asia & Europe Airports City Airport Runway Length (ft) Elevation (ft) Seoul Incheon (ICN) Tokyo Narita (NRT) Haneda (HND) Shanghai Hongqiao (SHA) Pudong (PVG) Dubai Dubai (DXB) New Delhi Delhi (DEL) Paris Paris-Charles de Gaulle (CDG) Paris-Orly (ORY) London London Heathrow (LHR) London City (LCY)

15 American Airports City Airport Runway Length (ft) Elevation (ft) John F. Kennedy (JFK) New York Newark Liberty (EWR) LaGuardia (LGA) Chicago O Hare (ORD) Chicago Midway (MDW) LA Los Angeles (LAX) Las Vegas McCarran (LAS) Miami Miami (MIA) Seattle Seattle-Tacoma (SEA)

16 City-Pairs Operations New York Flight Departure Arrival Airport Code Range (nmi) LHR LAX JFK SEA LAS MIA ORD

17 City-Pairs Operations International Flight Departure Arrival Airport Code Range (nmi) DEL SHA NRT ICN DXB CDG CIA LHR

18 CONSTRAINT DIAGRAM 0.6 Thrust to Weight Ratio 0.34 Wing Loading 88 lb/ft 2 Top of climb (1g steady, level flight, M = h=45k, service ceiling) Subsonic 2g manuever, h =10K Takeoff ground roll 4000 h = 5K, +15 hot day Landing ground roll 2500 h = 5K, +15 hot day Second segment climb gradient above h = 5K, +15 hot day T SL /W W 0 /S [lb/ft 2 ] 18

19 Estimated Lift to Drag Ratio and Specific Fuel Consumption Lift to Drag Ratio Subsonic (L/D) max 19.7 Subsonic (L/D) cruise 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

20 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,

21 Equation - Technology Factor - Results We TSL Wo b( Wo) ( AR) ( ) ( ) ( MMAX ) Wf Wo S C C C C C Used MATLAB to obtain the coefficient values Technology factor = 0.95 We Wf Wo = lb = lb = lb 21

22 Design QFD The What Performance Design Practical Comfort 22

23 Design QFD NASA Subsonic Transport Research Goals 23

24 Design QFD The How Noise Fuel Consumption Take off Distance LTO Nox Emissions Speed Size Weight Initial costs Long term costs Range 24

25 Design QFD 25

26 Airplane Cabin Layouts 26

27 27

28 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 ,628 31, ,258 4,000 2,500 Bombardier Challenger ,500 38, ,568 4,810 2,600 Cessna Citation Sovereign ,720 30, mph 3,276 3,640 2,650 Cessna Citation X ,700 36, mph 3,533 5,140 3,400 Dassault Falcon 2000DX ,360 41, ,250 5,300 2,640 Gulfstream G ,750 39, , Hawker ,800 39, ,119 5,169 2,995 28

29 Benchmarking Comparable range, weight, and passenger count to G250 Will implement advanced concepts to achieve N+2 goals for 2020 launch 29

30 Design Requirements Compliance Matrix Requirement Target Threshold Current Estimate Compliant Maximum Mach Number 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) No Seats Yes Volume Per Passenger (ft^3) Yes TSFC (% of avg) Yes N0X Emissions (% of avg.) 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

31 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

32 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

33 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

34 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

35 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

36 Appendix 36

37 Citation Aviation Week & Space Technology: Aerospace Source Book Feb Project Opportunity Description Crossley, William Aircraft initial sizing Excel file, In-class QFD example file, Constraint diagram Excel file 1 Feb Del Rosario, R., and Wahls, R., Subsonic Transport Research at NASA, presented as the School of Aeronautics and Astronautics Colloquium, Nov. 5,