AAE 451 Team 6 System Requirements Review Farah

AAE 451 Team 6 System Requirements Review Farah Abdullah Stephen Adams Noor Emir Anuar Paul Davis Zherui Guo Steve Mc. Cabe Zack Means Mizuki Wada Askar Yessirkepov 1

Mission Statement �Implement advanced technologies to design a future large commercial airliner (200 passenger minimum) that simultaneously addresses all of the N+2 goals for noise, emissions and fuel burn as set forth by NASA. �These NASA goals include: � Reduce noise by 42 d. B below stage 4 certification noise measurements at takeoff, sideline, and approach � Reduce landing and takeoff NOx by 75% below CAEP 6 � Reduce fuel burn by 50% relative to a “large twin-aisle reference” � Reduce field length by 50% relative to a “large twin-aisle reference” �Use market driven parameters to design a realistic and desirable aircraft. 2

Customers 3

Regional Market �Similarities in market predictions 6

Regional Market �After 3 major domestic markets, many major international routes with high demands Major Routes US-West Europe PRC-West Europe South America-West Europe Asia-West Europe Middle East-West Europe Asia PRC-US Asia-US Middle East-US Airbus Market Outlook 7

Competitors 8

Competitors �B 787 -8 �Replace B 767 -200 ER, B 767 -300 ER and possibly B 757200 (on shorter routes) * indicating aircraft will need replacement 9

Competitors �B 787 -8 will be have no competition for small twin aisle aircraft carrying 200 -250 passengers �Compete against B 787 -8, assuming the proliferation of point to point model as opposed to hub and spoke distribution �Smaller, long range, efficient aircraft offers economical option to open up markets into low volume city pairs. 10

Concept of Operations 11

Representative city-pairs City Pairs Beijing - Berlin Beijing – Los Angeles Beijing – Honolulu Distance Min. Runway Length 3977 nmi 5437 nmi 5200 ft 8925 ft 4398 nmi 6952 ft Tokyo – Honolulu 3318 nmi 6952 ft Tokyo – San Francisco 4470 nmi 7500 ft Tokyo – Paris 5256 nmi 11811 ft New York – London 2999 nmi 4984 ft New York - Munich 3830 nmi 8400 ft New York - Dubai 5946 nmi 8400 ft 12

Design Mission Cruise 4 3 Divert to alternate 10 Loiter (25 min. ) 9 5 Climb Loiter (25 min. ) 2 nd Climb 11 8 Missed approach 1 2 6 Taxi and take off Dubai 7 Land taxi Designed Range 6000 nm � Max design range : 6500 nm � Covers whether issues � Max capacity : 250 passengers � Max cruise Mach : 0. 85 � Cruise Altitude : 35000 ft New York 13 12 Land taxi 200 nm 1 -7 : Basic Mission 7 -13: Reserve Segment • Satisfy FAA requirement of min. 45 min additional cruise for night time flights 13

Alternate Mission Cruise 4 3 Divert to alternate 10 Loiter (25 min. ) 9 5 Climb Loiter (25 min. ) 2 nd Climb 11 8 Missed approach 1 2 6 Taxi and take off Seattle 7 Land taxi Designed Range 2400 nm � Mission Range: 2400 nm � Max capacity : 300 passengers � Max cruise Mach : 0. 85 � Cruise Altitude : 30000 ft Miami 13 12 Land taxi 100 nm 1 -7 : Basic Mission 7 -13: Reserve Segment • High Capacity Medium Haul Aircraft 14

System Design Requirements 15

Requirements Airline Passengers Authority/Public Airport Compatible Low Operations Cost Low Maintenance Cost Reliability Low Fuel Burn Operational Life Range Safe Aircraft Affordable Ticket Price Comfort Cargo Space Fast Travel Time NASA Requirements Nox Emissions Noise Level Safety and Airworthiness CFR 16

House Of Quality 17

Requirements �Important Attributes • Airport Compatibility • Reliability • Safety • NASA Competition ERA N+2 Requirements 18

Compliance Matrix Current Target Threshold 266 d. B cum. 230 d. B cum. 246 d. B (-20 d. B) Airbus A 321 -200 LTO NOx Emissions 26 kg/LTO 6. 5 kg/LTO (-75%) 13 kg/LTO (-50%) Boeing 757 -200 Fuel Burn 2800 kg/hr cruise 1400 kg/hr (-50%) 1820 kg/hr (-35%) Airbus A 321 -200 5000 -6000 ft 2500 -3000 ft 3500 -4500 ft Boeing 757 -200 6560 nmi 6000 nmi Boeing 757 -200 0. 85 @ 35, 000 ft 0. 75 @ 35, 000 ft Boeing 757 -200 270 >200 Boeing 757 -200 Noise Levels Field Length* Max Payload Range Cruise Mach 0. 8 @ 35, 000 ft Passengers Reference Values * Field length values only for LTO http: //www. airbus. com/fileadmin/media_gallery/files/tech_data/AC/AC_A 321_01092010. pdf http: //www. airliners. net/a/stats. main? id=103 19

Technologies / Advanced Concepts 20

Technologies/Advanced concepts Technology Propulsion Airframe Aeroacoustics (Chevron nozzle) Noise shielding on landing gear and highlift devices Ultra high bypass engine (propfan) Pro(s) Con(s) reduces noise by 1. 1 db large noise reduction 35% better fuel efficiency weight/fuel penalty high noise penalty Electric Aircraft Drive systems, Hybrid turbine-electric engines high fuel and power generation efficiency storage of Hydrogen is problematic Composite body lower weight, better strength higher initial cost, maintenance costs Active Engine Control and Health monitoring better fuel economy and engine lifespan greater electronic complexity And others… 21

Sizing Capabilities 22

Current Sizing Tools �Empty Weight Prediction � for Jet Transports �This equation is from Raymer Table 3. 1 �Fuel Weight Prediction �Requires fuel burn prediction and drag prediction

Current Sizing Tools �Drag Prediction �Use similar existing aircraft AR to estimate (L/D)cruise � for subsonic aircraft �This equation is from Nicolai Figure 5. 3

Current Sizing Tools �Fuel Weight Prediction �Use Breguet range equation and endurance equation � �Total Fuel � Add 1% for trapped fuel

Sizing Calibration �Baseline Aircraft �Boeing 767 -200 ER http: //boeing. mediaroom. com/index. php? s=13&cat=30&item=1126

Payload and Range http: //www. boeing. com/commercial/airports/767. htm

Published Data http: //www. boeing. com/commercial/airports/767. htm

More Published Data http: //www. boeing. com/commercial/airports/767. htm

Predictions Using Sizing Tool �Noncalibrated Weights TOGW 509940 lb Empty Weight 236410 lb Fuel Weight 228130 lb Payload Weight 44000 lb �Calibrated Weights TOGW 382450 lb Empty Weight 177310 lb Fuel Weight 250940 lb Payload Weight 38720 lb

Summary & Next Steps 31

Next Steps �Refine sizing code �Powerplants �Thrust-to-weight improvements �Aerodynamic designs �Airfoil design / Finite wing design �Fuselage �CAD Model of aircraft �Estimation of new technologies on specifications 32