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Company LOGO System Definition Review Akshay Ashok, Nithin Kolencherry, Steve Skare, Michael...
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Transcript of Company LOGO System Definition Review Akshay Ashok, Nithin Kolencherry, Steve Skare, Michael...
Company LOGO
www.company.com
System Definition ReviewAkshay Ashok, Nithin Kolencherry, Steve Skare,
Michael McPeake, Muhammad Azmi, Richard Wang, Mintae Kim, Dodiet Wiraatmaja, Nixon Lange
Company LOGO
www.company.com
Outline
• Re-cap Market Forecasts • Key Design Goals• Progress Update• Constraint Analysis• Concept development process and result• Advanced Technology Concepts• Cabin Layout• Sizing Studies• Overview of Concept
– Walk around chart• Conclusion
Company LOGO
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Opportunity Description
Create a supersonic transport aircraft that meets the following characteristics:
• Mach 1.6-1.8 Cruise Speed • 4000 nm Design range• 35-70 Passengers (Mixed Class)• 3 Pax-mi/lb Fuel Efficiency• Takeoff Field Length < 10000 ft
Company LOGO
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Mission
A cost-effective, advanced, high-speed commercial air transport that connects major worldwide hubs
Key Design Goals:• Supersonic flights over land (Overpressure <
0.3psf)• IOC in 2020• Manufacturing capabilities exist• 60 passengers• 4000nm ground range
Company LOGO
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Market Summary• Three regions of focus
– Trans-Atlantic– Trans-continental– Inter-Asia
• Worldwide Hubs– Los Angeles (LAX)– New York (JFK)– London (LHR)– Dubai (DXB)– Beijing (PEK)
• Hub and Spoke Structure
• Design Mission
Company LOGO
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Constraint Analysis
• Performance Constraints– 1-g steady flight
• M=1.8, H=50000ft, VS=100fpm
– Subsonic 2-g maneuver• V=250Kts, H=10000ft
– Takeoff and Landing operations from JFK and DXB
• Short runway length at JFK• Hot climate at DXB
– 2nd segment climb• 3% with 4 engines
Key AssumptionsCd0 0.016Thrust Lapse Rate 0.35Maximum fuselage diameter 13 ftOswald efficiency factor 0.8CLmax subsonic flight 1Δ T 25 / 43 RCLmax land 2eTO 0.6CLmax TO 1.5Number of engines 3Ewd 1.9Cruise climb capability 100 fpm
SENSITIVITY
Company LOGO
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Constraint Analysis
40 60 80 100 120 140 160
-0.8
-0.6
-0.4
-0.2
0
0.2
0.4
0.6
0.8 constraint diagram
1g steady, level flight, M =1.8 @ h=50000ft subsonic 2g manuever, V =422ft/s @ h=10000ft
takeoff ground roll 10000ft @ h = 34ft,43° hot day[DXB] landing ground roll 4374ft @ h = 34ft,43° hot day[DXB]
second segment climb gradient of 2.7% above 34ft,43° hot day takeoff ground roll 8000ft @ h = 13ft,25° hot day[JFK]
landing ground roll 2800ft @ h = 13ft,25° hot day[JFK]
W0/S
Ts
l/W0
3
Company LOGO
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CONCEPT SELECTION PROCESS
CONCEPT SELECTION PROCESS
BRAINSTORMING
PUGH’s MATRIX (1ST RUN)
3 BASELINE CONCEPTS SELECTED
HYBRID CONCEPTS GENERATED
FURTHER RESEARCH
PUGH’s MATRIX (2ND RUN)
FINAL DESIGN
Company LOGO
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1st run CONCORDE 1 2 3 4 5 6 7 8
D A T U M
SONIC BOOM + + s + + s + +
SUBSONIC NOISE s s s s + + s +
TURN AROUND TIME s s s s s + + s
AIRPORT COMPATIBLE s - - s - - - -
SAFETY s s s s + s s +
EASE OF MANUFACTURE + + - + + + - s
CABIN VOLUME + + s s s s s +
COST + + - + s + - s
MOVING PARTS + - - + + + - -
AESTHETICS s - - s s s - s
+ 5 4 0 4 5 5 2 4
- 0 3 5 0 1 1 5 2
s 5 3 4 5 4 4 3 4
Pugh’s Matrix
Company LOGO
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Engine Location:- Under wing
Wing: - Delta- Mid fuselage (height)
- AnhedralControl surface:
- on wingSonic boom mitigation:
- Hybrid nose design (weak compression waves)
Hybrid Concept 1
Company LOGO
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Engine Location:- Over wing
Wing: - Delta-Mid Fuselage- No dihedral/ anhedral
Control surface: - Canards- Upper fuselage- Dihedral
Sonic boom mitigation: - Nose shaping
(F-5 shaped sonic boom demostrator)
Hybrid Concept 2
Company LOGO
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Engine Location:- Under wing inlet- Over wing outlet (similar to YF-23)
Wing: - Delta- Bottom fuselage- Dihedral
Control surface: - Canards- Top fuselage- Anhedral
Sonic boom mitigation: - Gulfstream / NASA Quiet Spike™
Hybrid Concept 3
Company LOGO
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APPLICATION OF SONIC-BOOM MINIMIZATION CONCEPTS IN SUPERSONIC TRANSPORT DESIGN
by Harry W, Carlson, Rdymond L. Barger,and Robert J. Muck, Lungley Research Center, Hdmptolz, Vd. 23665
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. JUNE 1973
Engine Location:- Under wing inlet
- Over wing outlet
(similar to YF-23)
Wing:
- Delta
- Bottom fuselage
- Dihedral
Control surface:
- Canards
- Mid fuselage
Sonic boom mitigation: - aircraft geometry
Aft Arrow Wing Concept
Company LOGO
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2nd runAFT ARROW
WING CONCEPT HYBRID CONCEPT 1 HYBRID CONCEPT 2 HYBRID CONCEPT 3
D A T U M
SONIC BOOM - - -
SUBSONIC NOISE s + sCONTROL SURFACES - s sTURN AROUND TIME s + +
AIRPORT COMPATIBLE + + -SAFETY s + -
EASE OF MANUFACTURE - s -EMPTY WEIGHT + + s
COST - - -
+ 2 5 1 - 4 2 5 s 3 2 2
Pugh’s Matrix : 2nd Run
Company LOGO
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DESIGN CRITERIA DETAILED DESCRIPTION
SONIC BOOM geometry altitude weight wetted area aspect ratio frontal area induced dragcontrol surface
effects
SUBSONIC NOISE engine placement noise mitigation type of engine
CONTROL SURFACES
types of control surfaces static stability number
location of control sufaces
airport compatibility complexity
size of control surfaces weight
TURN AROUND TIME
# of passenger doors # of service doors preflight checks
AIRPORT COMPATIBLE
location of control sufaces location of doors geometry fuel bay location
engine placement
SAFETY engine placement fuel bay location landing gearvertical stabilizer
osciallationsemergency
exits stability debris preflight
EASE OF MANUFACTURE moving parts materials used geometry costs
EMPTY WEIGHT # of engines materials used # of landing gear wing size# of moving
parts
COST procurement operation manufacture maintenance crew
Detailed Considerations
Company LOGO
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Further Work:
- Engine placement (over/ under wing)
- Vertical tail selection
- Dihedral/ Anhedral effects (wing/ canard)
- Location of doors
Supersonix Concept
Company LOGO
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Boom Shaping : Dihedral
• Increase Effective Length– Multi-plane lifting surface– Mitigates Boom overpressure
• Potential Issues– Wash out
• subsonic lateral instabilities
– Low planform area• Lift is reduced
– Structural Considerations
Company LOGO
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Boom Shaping :Effective Area Distribution
• Smooth area distribution– Gradual lift development
• Long chord of wing root
– Fuselage diameter morphing– Aircraft length
• Engine Nacelle Placement– Area rule
• Canards– High dihedral
Company LOGO
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Boom Shaping : Nose Design
• Blunt nose– Create strong bow shock
• Mitigate subsequent shocks, overpressure
– Supersonic Area rule– High wave drag
• Nose keel– Alternate option– Unverified results– Material Problems
Company LOGO
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Efficient Supersonic Cruise
• Wing Characteristics– High AR, low sweep for efficient supersonic
• Laminar flow supersonic wing
– Low AR, high sweep for shock mitigation– Need to achieve acceptable trade-off
• Active flow management– Attached flow on wing– “Phantom Body”
• Artificial area
Company LOGO
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1975 1980 1985 1990 1995 2000 2005 2010 20150
1
2
3
4
5
6
7
8
T/Wen vs. Manufactured Year
T/We
Samara NK-25
Aviadvigatel D-30F6
GE F101-102
Samara NK-321
GE F136
P&W F135
P&W 1000G
Engines
Company LOGO
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Engines
Engines– 107724 lb thrust is needed– Samara NK-321
• Produced by Kuznetsov Design Bureau
• Entered service in 1987• Used on Tupolev Tu-144LL• Noise problem
Company LOGO
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Engine Noise : Solutions
– Adaptive Cycle Engine (ACE)• extra bypass duct on the outside of the engine • quiet on take off and landing • Significant improvement in subsonic flight
– Eccentric Exhaust Configuration• Decrease the effective perceived noise by 10.5 dB
Company LOGO
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Cabin Layout / Fuselage Design
• 7 rows of 2 first class seats, 15 rows of 3 coach class seats
• Passenger total: 59 • Crew: 4 (Captain, First Officer, 2 Attendants).
Company LOGO
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Cabin Layout / Fuselage Design
• 7 rows First Class x 40” Seat Pitch = 280”15 rows Coach x 36” Seat Pitch = 540”2 Galleys/Restrooms (exits) x 104” = 208”
1028”
90 ft170 ft
(~90 ft)
Company LOGO
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Cabin Layout / Fuselage Design
• Cabin Diameter: 9 feet, Aisle Height: 78” • “Jump seats” for attendants • 4 exits: 2 between FC and coach, 2 overwing
Cockpit
Exits
Exits
Crew Seats
Company LOGO
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Attributes ValuesW0 Design 284000 lb
We Design 124000 lb
Wf Design 143000 lb
Tsl Required 108000 lbf
Wing Area 3340 ft2 Design Range 4700 nm
AR 2.1W0/S 85 lbf/ft2
Tsl/W0 0.38
Cruise Mach # 1.8Maximum Mach # 2.0
SFC cruise 0.94 1/hrSupersonic (L/D)max 9.2
Supersonic (L/D)cruise 7.9
Subsonic (L/D)max 10
Subsonic (L/D)loiter 10
Company LOGO
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Component Weights
• Used database of 16 existing commercial aircraft
• Some differences between our aircraft and those in the database– Horizontal Tail– Delta Wing
• Average mass fraction values were corrected based on these differences
Company LOGO
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Center of Gravity
• Utilized Derived Component Weights• Includes All Major Component Weights, Most Minor Weights
– Includes: Fuel, Wing, Tail, Canard, Engines, Fuselage, Furnishings, Passengers, etc.
– Does Not Include: Baggage, Air Conditioning, Anti-Icing System• Placement was not accurate enough at this stage
Company LOGO
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• Center of Gravity Location (at MTOW) ≈ 97 ft– Roughly 57% of the total length of the aircraft– Estimation includes 87% of the take off gross weight of the aircraft
• Likely to change, but not significantly
Company LOGO
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Blunt Nose
Top-mounted Canards
Arrow-wing Design
Rear mounted Engines
Dihedral Wing
Area-ruled fuselage for minimum wave drag
Aerodynamically Contoured Skin
Company LOGO
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Compliance MatrixRequirements Target Threshold Revised on 3/3 Requirement Units
Take off field length 8400 10000 8000 ftLanding field length 8400 10000 2800 ft
Door height above ground 8 10 ftTurnaround time 0.5 1 hr
Still air range 5000 4000 4000 nmNumber of passenger 60 50 59 peopleCruise Mach number 2 1.6 1.8 MachCabin volume per pax 65 50 43.13033982 pax/[ft^3/pax]
Operating cost $/ASMCruise Altitude 50000 40000 50000 ft
Cruise Efficiency 0.3 0.6 lb fuel/pax miSonic boom overpressure 0.3 0.3 0.8 lb/ft^2
Cumulative certification noise 60 80 dBStall Speed kts
COTs 80 50 %
Second Segment climb gradient 2.6 2.4 3 %
Company LOGO
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References• http://www.nasa.gov/vision/earth/improvingflight/supersonic_jousting.html • Carlson, H.W, Muck, J.R, APPLICATION OF SONIC-BOOM MINIMIZATION
CONCEPTS IN SUPERSONIC TRANSPORT DESIGN, June 1973• F-5 Shaped Sonic Boom Demonstrator’s Persistence of• Boom Shaping Reduction through Turbulence• John M. Morgenstern*, Alan Arslan†, Victor Lyman‡ and Joseph Vadyak§• Lockheed Martin Aeronautics Company, Palmdale, CA 93599• AIAA-2005-0012; 43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV• http://www.enemyforces.net/aircraft/mig31.htm• http://www.fighter-planes.com/info/mig31_foxhound.htm • http://www.jet-engine.net/• Papamoschou, D. Debiasi, M. Conceptual Development of Quiet Turbofan
Engines• for Supersonic Aircraft, April 2003