AAE 451 Team 6 System Requirements Review

transcript

AAE 451 Team 6System Requirements Review

Farah AbdullahStephen Adams

Noor Emir AnuarPaul DavisZherui Guo

Steve McCabeZack MeansMizuki Wada

Askar Yessirkepov

Mission StatementImplement 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 dB below stage 4 certification noise

measurements at takeoff, sideline, and approachReduce landing and takeoff NOx by 75% below CAEP6Reduce 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.

Customers

Regional Market

Similarities in market predictions

Regional MarketAfter 3 major domestic markets, many major

international routes with high demandsMajor RoutesUS-West EuropePRC-West EuropeSouth America-West EuropeAsia-West EuropeMiddle East-West EuropeAsia PRCPRC-USAsia-USMiddle East-US

Airbus Market Outlook

Competitors

CompetitorsB787-8Replace B767-200ER, B767-300ER and

possibly B757-200 (on shorter routes)

* indicating aircraft will need replacement

CompetitorsB787-8 will be have no competition for small

twin aisle aircraft carrying 200-250 passengers

Compete against B787-8, 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.

Concept of Operations

Representative city-pairs City Pairs Distance Min. Runway

LengthBeijing - Berlin 3977 nmi 5200 ft

Beijing – Los Angeles 5437 nmi 8925 ft

Beijing – Honolulu 4398 nmi 6952 ftTokyo – Honolulu 3318 nmi 6952 ft

Tokyo – San Francisco 4470 nmi 7500 ftTokyo – Paris 5256 nmi 11811 ft

New York – London 2999 nmi 4984 ft

New York - Munich 3830 nmi 8400 ft

New York - Dubai 5946nmi 8400 ft

Design Mission

Max design range : 6500nm Covers whether issues

Max capacity : 250 passengers Max cruise Mach : 0.85 Cruise Altitude : 35000ft

Taxi and take off

Cruise

Land and taxi

Missed approach

2nd Climb

Divert to alternate

Loiter(25min.) Loiter

(25 min.)

Land and taxi

Designed Range

6000nm

Dubai New York

1-7 : Basic Mission7-13: Reserve Segment

•Satisfy FAA requirement of min. 45 min additional cruise for night time flights

Alternate Mission

Mission Range: 2400nm Max capacity : 300 passengers Max cruise Mach : 0.85 Cruise Altitude : 30000ft

Taxi and take off

Cruise

Land and taxi

Missed approach

2nd Climb

Divert to alternate

Loiter(25min.) Loiter

(25 min.)

Land and taxi

Designed Range

2400nm

Seattle

Miami 100nm

1-7 : Basic Mission7-13: Reserve Segment

•High Capacity Medium Haul Aircraft

System Design Requirements

Requirements

Airline Passengers Authority/PublicAirport CompatibleLow Operations CostLow Maintenance CostReliabilityLow Fuel BurnOperational LifeRange

Safe AircraftAffordable Ticket PriceComfortCargo SpaceFast Travel Time

NASA RequirementsNox EmissionsNoise LevelSafety and AirworthinessCFR

House Of Quality

RequirementsImportant Attributes

•Airport Compatibility•Reliability•Safety•NASA Competition ERA N+2 Requirements

Compliance Matrix

Current Target Threshold Reference Values

Noise Levels 266 dB cum. 230 dB cum. 246 dB (-20 dB) Airbus A321-200

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 A321-200

Field Length* 5000-6000 ft 2500-3000 ft 3500-4500 ft Boeing 757-200

Max Payload Range

6560 nmi 6000 nmi Boeing 757-200

Cruise Mach 0.8 @ 35,000 ft 0.85 @ 35,000 ft 0.75 @ 35,000 ft Boeing 757-200

Passengers 270 >200 Boeing 757-200

* Field length values only for LTO http://www.airbus.com/fileadmin/media_gallery/files/tech_data/AC/AC_A321_01092010.pdf

http://www.airliners.net/a/stats.main?id=103

Technologies / Advanced Concepts

Technologies/Advanced conceptsTechnology Pro(s) Con(s)

Propulsion Airframe Aeroacoustics (Chevron

nozzle)

reduces noise by 1.1 db

weight/fuel penalty

Noise shielding on landing gear and highlift devices

large noise reduction

weight/fuel penalty

Ultra high bypass engine (propfan)

35% better fuel efficiency

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…

Sizing Capabilities

Current Sizing ToolsEmpty Weight Prediction

for Jet Transports

This equation is from Raymer Table 3.1Fuel Weight Prediction

Requires fuel burn prediction and drag prediction

1.02( )eW WW

Current Sizing ToolsDrag Prediction

Use similar existing aircraft AR to estimate (L/D)cruise

for subsonic aircraft

This equation is from Nicolai Figure 5.3

1.4 7.1cruise

Current Sizing ToolsFuel Weight Prediction

Use Breguet range equation and endurance equation

Total Fuel

Add 1% for trapped fuel

WV LRC D W

11 ln i

WLEC D W

0 0 1 2 1

1 ... 1.01f f

W WWW WW W W W W

Sizing Calibration Baseline Aircraft

Boeing 767-200ER

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

More Published Data

Predictions Using Sizing ToolNoncalibrated Weights

Calibrated Weights

TOGW 509940 lbEmpty Weight 236410 lbFuel Weight 228130 lb

Payload Weight 44000 lb

TOGW 382450 lb

Empty Weight 177310 lb

Fuel Weight 250940 lb

Payload Weight 38720 lb

Summary & Next Steps

Next StepsRefine sizing codePowerplants

Thrust-to-weight improvementsAerodynamic designs

Airfoil design / Finite wing designFuselage

CAD Model of aircraftEstimation of new technologies on

specifications

AAE 451 Team 6 System Requirements Review

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