aae 451 team 6 system requirements review
DESCRIPTION
AAE 451 Team 6 System Requirements Review. Farah Abdullah Stephen Adams Noor Emir Anuar Paul Davis Zherui Guo Steve McCabe Zack Means Mizuki Wada Askar Yessirkepov. Mission Statement. - PowerPoint PPT PresentationTRANSCRIPT
1
AAE 451 Team 6System Requirements Review
Farah AbdullahStephen Adams
Noor Emir AnuarPaul DavisZherui Guo
Steve McCabeZack MeansMizuki Wada
Askar Yessirkepov
2
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.
3
Customers
6
Regional Market
Similarities in market predictions
7
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
8
Competitors
9
CompetitorsB787-8Replace B767-200ER, B767-300ER and
possibly B757-200 (on shorter routes)
* indicating aircraft will need replacement
10
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.
11
Concept of Operations
12
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
13
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
Climb
Cruise
Land and taxi
Missed approach
2nd Climb
Divert to alternate
Loiter(25min.) Loiter
(25 min.)
Land and taxi
1 2
34
5
6 7
8
910
11
12
Designed Range
6000nm
Dubai New York
200nm
13
1-7 : Basic Mission7-13: Reserve Segment
•Satisfy FAA requirement of min. 45 min additional cruise for night time flights
14
Alternate Mission
Mission Range: 2400nm Max capacity : 300 passengers Max cruise Mach : 0.85 Cruise Altitude : 30000ft
14
Taxi and take off
Climb
Cruise
Land and taxi
Missed approach
2nd Climb
Divert to alternate
Loiter(25min.) Loiter
(25 min.)
Land and taxi
1 2
34
5
6 7
8
910
11
12
Designed Range
2400nm
Seattle
Miami 100nm
13
1-7 : Basic Mission7-13: Reserve Segment
•High Capacity Medium Haul Aircraft
15
System Design Requirements
16
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
17
House Of Quality
18
RequirementsImportant Attributes
•Airport Compatibility•Reliability•Safety•NASA Competition ERA N+2 Requirements
19
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
20
Technologies / Advanced Concepts
21
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…
22
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
0.060
0
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
L ARD
Current Sizing ToolsFuel Weight Prediction
Use Breguet range equation and endurance equation
Total Fuel
Add 1% for trapped fuel
1ln i
i
WV LRC D W
11 ln i
i
WLEC D W
31 2
0 0 1 2 1
1 ... 1.01f f
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
http://www.boeing.com/commercial/airports/767.htm
More Published Data
http://www.boeing.com/commercial/airports/767.htm
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
31
Summary & Next Steps
32
Next StepsRefine sizing codePowerplants
Thrust-to-weight improvementsAerodynamic designs
Airfoil design / Finite wing designFuselage
CAD Model of aircraftEstimation of new technologies on
specifications