Asgard Aviation (formerly team 2) - PowerPoint Presentation

Asgard Aviation(formerly team 2) Logan Waddell Morgan BuchananErik SusemichelAaron Foster Craig WikertAdam AtaLi TanMatt Haas 1

OutlineMission StatementMarket and Customers Market sizeCustomer Benefits / NeedsCompetitionConcept of OperationsRepresentative City PairsPayload / Capacity Design MissionSystem Design RequirementsDesign RequirementsBenchmarking Technologies / Advanced ConceptsInitial Sizing2

Mission StatementTo design an environmentally responsible aircraft that sufficiently completes the “N+2” requirements for the NASA green aviation challenge. “N+2” Goals Burn 50% less fuel burnCumulative -42 dB noise reduction (Approach, Landing, Taxi)75% reduction in LTO nitrogen oxide emissions3

Customer Needs / BenefitsNASA“N+2” goals AirlinesGeneral Public4 Airport Noise levels

Market / Customers*Boeing 5 Twin Aisle - Value ($B) ~3,600 Twin Aisle – 7,100 new airplanes Boeing projects the worlds fleet to double by 2029

Market / Customers6 *Boeing Steady increase in RPK since 1977, ~ 5% annually Largest Markets: Asia-Pacific, North America, Europe

CompetitionSimilar size aircraft:Boeing 767-300, 757-300, 787Airbus A330-200 High speed railBullet trains7 Boeing 757 and 767

CONOPS - City Pairs Mission design represents popular routes Examples Routes Great Circle Distance Passengers / Year ____________________________(nm)__________________________ Domestic range requirement of 3200 nm based on:MIA to SEA facing 65 kts headwind FAR Reserves London New York 2999 1609337 Miami Seattle 2363 N/A New York San Francisco 2224 909514 Los Angeles New York 2145 1697593 Miami New York 948 955838 Atlanta New York 659 935265 Chicago New York 641 1182326 Las Vegas Los Angeles 205 924732 Boston New York162988976 8

Runway Length *MITAirport Runway lengths (ft) JFK 14572 ORD 13001 LAX 12091 SFO 11870 LHR 12799 LAS 14510 MIA 13000 ATL 11890 BOS 10083 SEA 11900 9

Aircraft Payload / Passenger Capacity 250 Passengers 180 lb/passenger Baggage 50 lb/passenger On board Baggage 15 lb/passenger7 Crew Members 180 lb/crew Baggage 30 lb/crew W payload = 61250 lbs W crew = 1470 lbs 10

Design Mission11

Typical Operating Mission Typical Design Missions Aircraft Qualities Aircraft Limitations Typical Design Mission Range 4,000 nm 750 nm City Pairs Seattle to Miami Chicago to New York Passengers 250 212 Cruise Altitude 35,000 ft 30,000 ft Reserve Segments 200 nm 100 nm Takeoff Weight 268,000 lbs 243,100 lbs Mach Number 0.8 0.8 12

Design RequirementsCompliance Matrix Requirement Unit Target Threshold Current Range naut. miles 4000 3600 - Payload pax 250 230 250 Cruise Mach # - 0.8 0.76 0.8 Runway Length (Takeoff) ft 7000 9000 - Runway Length (Landing) ft 6000 6500 - Emissions g/kN thrust 15 22 - Noise (Cum.) dB -42 -32 - Fuel Burn (SFC)-Cruise lb/(lbs*hr) 0.3 0.45 - 13

Design Requirements Noise(below stage 4)-42 dBLTO NOx Emissions (below CAEP 6)-75%Performance: Aircraft Fuel Burn -50%Performance:Field Length-50% ERA N+2 Requirements Noise prediction/reduction technologies for airframe/propulsion systems Emissions-reduction technologies (mainly NO x ) Alternative Fuel Usage Improved vehicle performance from: Lightweight, durable structures High-lift aerodynamics Higher bypass ratio engines NASA Subsonic Fixed Wing Project Goals: 14

Benchmarking  Max PassengersOEW (lb) Max Takeoff Weight (lb) Max Payload (lb)Usable Fuel (lb) Cruise Mach # Max Field Length (ft) Max Range (nmi) Boeing 757-200PF 279 142,350 270,000 38,200 79,980 0.80 13,500 4,750 Boeing 767-200ER 255 181,610 395,000 78,500 161,738 0.80 13,000 6,385 Boeing 777-200LR 301 320,000 766,000 141,000 320,863 0.84 14,000 9,395 Airbus A321-200 220 103,527 187,39354,00051,3700.7915,0003,200Airbus A330-200380264,845480,607115,01297,5300.8215,0007,250Info on Boeing aircraft from boeing.comInfo on Airbus aircraft from airbus.com15

Technologies/Advanced ConceptsFuel Burn Spiroid wingletsAdvanced engine conceptsNoiseLanding gearEmissionsLess fuel burn 16

Technologies/Advanced conceptsWingletsBlended SpiroidMulti-Winglets17

Geared Turbofan EnginePratt & Whitney currently has a line of geared turbofan engines called the PurePower family. Developing advanced GTF for Airbus and Boeing next gen narrow body replacement aircraft. Geared Turbofan allows fan to operate at lower speeds while compressor and turbine operate at high speeds.Provides 12%-15% improvement in fuel burn range, 50% NOx emissions reduction, and 20 dB decrease from CAEP noise standards 18

Affordable Large Integrated StructuresEliminates structural discontinuities and fastened assembliesReduction in part count Lower manufacturing time and cost 19 Northrop Grumman

Landing Gear FairingsReduces the noise in the mid and high frequency domain compared to the plain landing gear configuration up to 4.5 dBReduces vortex shedding due to bluff-body nature of nose and main landing gear Northrop Grumman 20

Hybrid Laminar Flow Control21 Active drag reduction techniqueDesign of the suction surface Chambers underneath the perforated skin  Applied to the vertical and horizontal tail reduces drag by 1%*Clean Sky

Composite MaterialsLighter weight High strength to weight ratioReduction of overall weight 20% or more Stronger Graphite/epoxy compositeGreater resistance to damage from cyclic loading HybridAddition of fiberglass or kevlar Creates greater fatigue toughnessImpact resistance 22

SizingUsing MATLAB to create a comprehensive sizing code based on first order method from Raymer text Empty weight prediction based off of Raymer database (Table 3.1)Equation Used: We/W0=A*W0C*K vsFuel weight prediction based on drag and fuel burn predictionsClimb, Landing, Warmup and Takeoff fractions used historical data Cruise fraction used Breguet range equation:exp(-R*C/(V*L/D))Loiter fraction used endurance equation: exp(-E*C/(L/D)) L/D prediction Equation Used: L/D = 1.4*AR+7.1 23

Aircraft Database Published Information (from Jane’s All the Worlds Aircraft and Boeing.com) Boeing 767-200ER Airbus A330-200 Range 6,545 [nmi] 6,750 [nmi] Takeoff Gross Weight 395,000 [lb] 507,050 [lb] Empty Weight (OWE) 184,400 [lb] 263,075 [lb] Fuel Weight 159,920 [lb] 186,255 [lb] Total Fuel capacity 23,980 [gal] 36,750 [gal] Boeing 767-200ER Airbus A330-200 24

Sizing Code Predictions ActualPrediction% ErrorGross Takeoff Weight 395,000 [lb]408,264 [lb]3.35 Empty Weight Fraction.46684.4698 0.63 L/D (cruise) 18 18.3 2.22 Actual Prediction % Error Gross Takeoff Weight 507,050 [lb] 365,624 [lb] -27.89 Empty Weight Fraction .51883 .47295 -8.80 L/D (cruise) N/A N/A N/A Boeing 767-200ER Airbus A330-200 The initial sizing calculations prove to be mostly accurate on both of the baseline aircraft 25

Our Design Predictions PredictionGross Takeoff Weight267,365 [lb]Empty Weight128,848 [lb] Empty Weight Fraction.48192 26

Summary and Next StepsFinalizing the sizing codeIncluding the new technologies into the sizingConstructing a preliminary CAD geometry for the aircraft 27

References Boeing http://www.boeing.com Airbus http://www.airbus.com NASA www.aeronautics.nasa.gov/isrp/era/index.htm MIT http://aviationweek.typepad.com/files/mit_n3_final_presentation.pdf Northrop Grumman http://aviationweek.typepad.com/files/northrop_grumman_final.pdf Aviation Week http://www.aviationweek.com/aw/commercial/ Perforated Fairings for Landing Gear Noise Control , N. Molin http://eprints.soton.ac.uk/43011/1/paper_vancouver_noabsolute_small.pdf 28