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 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. 1
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 Now more than ever, a business aircraft is an essential tool for capturing new opportunities, for compacting two- to threeweek trips into two to three days. -Jeff Habib, Senior Vice President of U.S. and Canadian Sales, Dassault Falcon Jet 4
Projected Market The graph indicates that the Long Range market will continue to grow in the next decade. *Source Honeywell Aviation Forecast 5
Jet Purchases Big Cabin Jets Captured 40% of Mentions and ~70% of $Value* *Source Honeywell Aviation Forecast 6
Purchase Expectations by Region Source Honeywell Aviation Forecast 7
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
Aircraft Amenities Amenities Dimensions Recliners (10x) 10 Seats L: 35, W: 33 Sofas (2x) 6 Seats L: 90, W: 35 Tables (3x) L: 24, W: 35 Conference Table L: 36, W: 60 Lavatories (2x) L: 62 Bar L:62, W:40 Flight Attendant Seating (2x) 2 Seats L: 30, W:30 10
Amenity Dimensions Approximating Cabin Length 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 11
Cabin Layout and Dimensions
Fuselage Cross-Section 13
Aircraft Characteristics Total Aircraft Length = (50 Cabin) + (14 2 Nose) + (23 10 Tail) = 88 Cabin Diameter = 8 10 Fineness Ratio = 9.96 Volume per passenger (Max. Capacity) = 81.5 cubic feet 14
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) 15
Design Mission 2 Cruise 3 Climb 6 7 Los Angeles Hong Kong Alternate 0 Takeoff 1 4 5 6350 nm 200 nm 8 9 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) 16
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 17
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 18
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 19
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 20
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 21
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 22
House of Quality 23
Requirements Compliance Matrix Part 1 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 24
Requirements Compliance Matrix Part 2 Performance Characteristics Target Threshold Current Cabin Noise 60 db 70 db 65 db LTO NOx Emissions Cumulative certification noise limits CAEP 6-75% CAEP 6-60% CAEP 6-70% 232 db 274 db 274 db 25
Requirements Compliance Matrix Part 3 Performance Characteristics Fuel cost per mile Loading Door Still height Target Threshold Current 3.8 lb/mile 4 lb/mile 6.23 lb/mile 4 ft 5 ft 4 ft Variable Costs $4100/hr $4300/hr $4100/hr 26
Constraint Diagram 27
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 28
Aircraft Database Database Includes two classes Class 1: Larger Business Jets Gulfstream G500 Gulfstream G550 Gulfstream G650 Bombardier Global 5000 29
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 30
We/Wo Aircraft Database 0.65 Team 2 Aircraft Database y = 1.378x -0.08 0.63 0.61 Class 1: Larger Planes 0.59 0.57 0.55 0.53 0.51 0.49 0.47 Class 2: Smaller Planes 0.45 0 20000 40000 60000 80000 100000 120000 Wo 31
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 SFC cruise = 0.5 SFC loiter = 0.6 Estimated from existing Business Jet engine data 32
Weight Estimates Least Squares Regression: 108,000 lbs We bw AR ( T / W ) ( W / S ) M Range W 0 c1 c2 c3 c4 c5 c6 0 SL 0 cruise W W e 0 3.08 W AR ( T / W ) ( W / S) M Range 0.154 0.016 0.394 0.089 0.934 0.032 0 SL 0 cruise 33
We/Wo Weight Estimates Curve Fit with Similar Planes: 92,000 lbs 0.57 0.56 0.55 We aw 67.69 W W 0 c 0 0 Similarly Sized Planes 0.422 y = 67.69x -0.42 0.54 0.53 0.52 0.51 0.5 84000 86000 88000 90000 92000 94000 96000 98000 100000 102000 Wo 34
Range (nmi) Performance Prediction Range vs. Mach for Various Loadings 7200 7000 08 Passengers 12 Passengers 16 Passengers 6800 6600 6400 6200 6000 5800 5600 0.7 0.72 0.74 0.76 0.78 0.8 0.82 0.84 0.86 0.88 0.9 Mach Number 35
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) 36
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? 38