PROPRIETARY
James BearmanAJ BrinkerDean BrysonBrian GershkoffKuo GuoJoseph HenrichAaron Smith
Daedalus AviationConceptual Design Review:“The Daedalus One”
PROPRIETARYApril 17, 2008 2
Current ConfigurationMission and RequirementsAdvanced TechnologiesCarpet Plots and SizingDesign Trade-OffsStructural ConsiderationsAerodynamicsPerformanceCostLogistics
PROPRIETARYApril 17, 2008 3
Advanced Avionics
Geared Turbofans
Lifting Canard
Supercritical Airfoil
Upper Surface Blown Flaps
Composite Structure
PROPRIETARYApril 17, 2008 4
PROPRIETARYApril 17, 2008 5
Provide a versatile aircraft with medium range and capacity to meet the needs of a commercial aircraft market still expanding in the year 2058
Incorporate the latest in technology to provide reliability, efficiency, while fulfilling the need for an environmentally friendly transportation system
Possess the ability to operate at nearly any airfield
5
PROPRIETARYApril 17, 2008 6
•Mission One•Schaumburg to North Las Vegas•1300 nmi
•Mission Two•South Bend to Burbank•1580 nmi
•Mission Three•West Lafayette to Urbana-Champaign to Cancun•1200 nmi
•Mission Four•Minneapolis to LAX•1330 nmi
6
PROPRIETARYApril 17, 2008 7
PROPRIETARYApril 17, 2008 8
Composites Stronger, lighter aircraft
Artificial Intelligence/Automated Pilot Reduction in flight crew Automatic flight control, collision
avoidanceFly by Light
Weight savings over copper wire Faster response
PROPRIETARYApril 17, 2008 9
Capability to increase CLmax to 7Wing CLmax (clean) ≈ 1.54Takeoff CL (w/ upper surface blowing)
≈ 4
--Nicolai, Fundamentals of Aircraft Design, 1976
PROPRIETARYApril 17, 2008 10http://www.flug-revue.rotor.com/FRHeft/FRHeft07/FRH0702/FR0702c1.JPG
The Geared Turbofan Current predictions say: “The Geared Turbofan engine will deliver a 12
percent reduction in fuel burn, 50 percent reduction in noise and emissions, and 40 percent reduction in
maintenance costs over today's commercial engines.” –
www.pw.utc.com
By 2038 we believe it will achieve over current technology:▪ 30% reduction in fuel burn ▪ 75% reduction in noise and emissions▪ 50% reduction in maintenance costs
PROPRIETARYApril 17, 2008 11
http://www.flug-revue.rotor.com/FRHeft/FRHeft07/FRH0702/FR0702c1.JPG
Thrust per engine - 25,000 lbsSFC per engine - 0.42/hourFan Diameter - 8 ft.Bypass Ratio - 8
PROPRIETARYApril 17, 2008 12
Geared Turbofans reduce CO2 produced by more than 12% compared to today’s engines
Reduce cumulative noise levels about 20dB below the current Stage 4 regulations
PROPRIETARYApril 17, 2008 13
Low wing with Geared Turbofans mounted at the leading edge Easy location for engine maintenance
▪ Geared Turbofan engines reduce maintenance costs by 40% over today's commercial engine
No complicated powered lift devices
PROPRIETARYApril 17, 2008 14
Generation Takeoff weight generated through RDS Initial starting point
▪ T/W=.23▪ W/S=84
Carpet Plot Range▪ T/W=0.23 - 0.414▪ W/S=84 - 160
Varied Wing Sweep (and saved 5,000 lbs)
PROPRIETARYApril 17, 2008 15
Constraints Used Fuel Burn per Seat-Mile Field Length with OEI Cruise Speed 0.75M
Constraints Not Used Takeoff Ground Roll Field Length All Engines Operational Landing Ground Roll
PROPRIETARYApril 17, 2008 16
PROPRIETARYApril 17, 2008 17
Carpet Plots Approximated Design Point
RDS Primary Method of Sizing MATLAB Code for Component Weight
Breakdown
PROPRIETARYApril 17, 2008 18
Taxi
Take
off &
Clim
b
Step CruiseFor Best Range
Descend & Hold
Land & Taxi
Climb- M
iss
Approach
CruiseDescend & Hold
Land & Taxi
Maximum Range Mission (1,800 nmi) Typical Commercial Mission Profile Maximizes Aircraft Range
Fuel Reserves (200 nmi) Extended Loiter Time Flight Diversion to Another Airport
PROPRIETARYApril 17, 2008 19
Input Parameters W/S – 120 T/W – 0.32 AR – 14 Λwing – 10°
λwing – 0.4
(CL)TO – 4
Weights GTOW – 87,100 lbs We – 34,700 lbs
Wf – 24,600 lbs Payload – 27,800 lbs We / Wo – 0.40
Wf/ Wo – 0.28
PROPRIETARYApril 17, 2008 20
Structures ~ 20,000 lbs Wing ~ 8,300 lbs Fuselage ~ 7,200
lbs Canard ~ 600 lbs Vert. Tail ~ 600 lbs Landing Gear ~
3,300 lbs
Propulsion ~ 8,100 lbs Engines ~ 7,000 lbs Fuel System ~ 900
lbs Systems ~ 200 lbs
Equipment ~ 7,000 lbs Controls ~ 2,800 lbs Avionics ~ 2,100 lbs
PROPRIETARYApril 17, 2008 21
Gross TO weight vs. Pax.
0
20,000
40,000
60,000
80,000
100,000
120,000
140,000
160,000
180,000
200,000
0 20 40 60 80 100 120 140 160 180 200
Passengers
Gro
ss T
O W
eig
ht
(lb
s)
Daedalus One
PROPRIETARYApril 17, 2008 22
PROPRIETARYApril 17, 2008 23
108 Seats, Single Class Seat Pitch: 32 in Seat Width: 20 in Aisle Width: 24 in 2 Galley Areas: 35 and
16 ft2
2 Lavs: ~20 ft2
PROPRIETARYApril 17, 2008 24
Initial design: High Wing Low Canard Current Design: Low Wing High Canard
▪ Reason: Landing gear placement, better accessibility for ground service, easier to maintain with lower wing
Wing Sweep Study: Result 10° Varied Sizing Based on 10° sweep and 20° sweep
▪ Reason: Find the most weight efficient aircraft Upper Surface Blowing
Placed engines above the wings near leading edge▪ Reason: Increase lift especially for takeoff and landing
PROPRIETARYApril 17, 2008 25
Initial Design: Tri-tail Current Design: Single Tail
▪ Reason: Reduced weight, sizing proved 3 Tails not needed
Forward Wing Extension▪ Reason: Allows more fuel, helps move Center
of Gravity forwardElliptical Fuselage
▪ Reason: Allow for more comfortable passenger cabin
PROPRIETARYApril 17, 2008 26
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PROPRIETARYApril 17, 2008 29
Main Wing-Super Critical 20712 Representative (custom airfoil to be developed) Data obtained from analysis in Fluent 12% thick airfoil Allows for high cruise speed via controlling
shock formation
PROPRIETARYApril 17, 2008 30
Zero lift angle of attack ≈ -5° Max Cl ≈ 1.7 Stall Angle ≈ 18°
Cl vs Alpha for SC 20712
y = 0.0985x + 0.4688
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-10 -5 0 5 10 15 20 25
Angle of Attack (degrees)
Co
eff
icie
nt
of
Lif
t (C
l)
SC 20712
Linear of Cl SC 20712
Linear (Linear of Cl SC 20712)
PROPRIETARYApril 17, 2008 31
Canard and Tail-Super Critical 20012 Data obtained from analysis in Fluent Symmetric airfoils are standard for
vertical and horizontal tails
PROPRIETARYApril 17, 2008 32
Zero Lift Angle of Attack ≈ 0 ° Max Cl ≈ 1.18 Stall Angle ≈ 15°
Cl vs Alpha for SC 20012
y = 0.0851x + 0.0604
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
-10 -5 0 5 10 15 20
Angle of Attack (degrees)
Co
effi
cien
t o
f L
ift
(Cl)
SC 20012
Linear of Cl for SC 20012
Linear (Linear of Cl for SC 20012)
PROPRIETARYApril 17, 2008 33
Stall Limit
Absolute Ceiling
Service Ceiling
q Limit
PROPRIETARYApril 17, 2008 34
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Variation of CG Location
20000
30000
40000
50000
60000
70000
80000
90000
100000
40.0 45.0 50.0 55.0 60.0 65.0 70.0 75.0 80.0
C.G. Location From Nose (ft)
Weig
ht
(lb
s)
C.G Location
Flight Conditions
Ground Conditions
Main Gear Location
Neutral Point
GTOW
W0f + reserves
OWE + payload
OWE
We
We + trapped fuel
PROPRIETARYApril 17, 2008 36
Canard Scanard: 300 ft2
Elevator Area Ratio: 1/3 AR: 4 Sweep: 15° Taper Ratio: 0.4
PROPRIETARYApril 17, 2008 37
Vertical Tail Sized for One Engine Out at Takeoff Stail: 310 ft2
Rudder Area Ratio: 1/3 AR: 2 Sweep: 15° Taper Ratio: 0.4
PROPRIETARYApril 17, 2008 38
RDT&E Cost: $24.4B USD (2008)Cost per aircraft: $49M USD Sale Price: $54M USD Break Even Point: 455 AircraftOperating Cost: $11.5M USD/Yr
$0.0616/seat-mile USD Jet A: $2.50/Gal
PROPRIETARYApril 17, 2008 39
Jetway
To
w
Baggage
Fuel
Wa
ter
Baggage
Galley
Electric
Elect
ric
La
v
PROPRIETARY
108 Passenger Capacity
1800 nmi Range 2700 ft Takeoff
Ground Roll Affordable
Acquisition Cost Reasonable
Operational Cost
Opens new markets
Enhances service to existing markets
Improves reliability and ease of air travel
Allows air travel industry to expand beyond current limits
April 17, 2008 40
PROPRIETARY
PROPRIETARYApril 17, 2008 42
Takeoff and Landing Drag Polar
0
0.5
1
1.5
2
2.5
3
3.5
4
4.5
0 0.5 1 1.5 2 2.5
CD
CL
Takeoff
Landing
PROPRIETARYApril 17, 2008 43
Cruise Drag Polar
0
0.1
0.2
0.3
0.4
0.5
0.6
0.00E+00 1.00E-02 2.00E-02 3.00E-02 4.00E-02 5.00E-02 6.00E-02 7.00E-02
CD
CL
Cruise M=.75
Cruise M=.80
Cruise M=.85
PROPRIETARYApril 17, 2008 44
Thrust Available Vs Cruise Drag
0.00
10000.00
20000.00
30000.00
40000.00
50000.00
60000.00
70000.00
80000.00
0 0.2 0.4 0.6 0.8 1 1.2
Mach Number
Fo
rce
(lb
s)
Drag
Thurst