Electric Commuter Transport Concept Enabled by Combustion ...
Transcript of Electric Commuter Transport Concept Enabled by Combustion ...
Electric Commuter Transport Concept Enabled by Combustion Engine
Range Extender
Georgi Atanasov, Jasper van Wensveen, Fabian Peter, Thomas Zill
DLRK 2019 • Chart 1
Outlines
DLRK 2019 • Chart 2 Electric 19-Seater Aircraft with Range Extenders
Background and Objectives.
Conceptual-Level Aircraft Sizing of a Hybrid-Electric 19-Seater
Results and Assessment
Conclusions and Outlook
Background and Objectives
A collaborative project between the DLR and Bauhaus Luftfahrt:
� Re-introduction of small regional aircraft with up to 19 passengers.
Approach:
� 19-seater market analysis
� 19-seater aircraft data base for support
� Assessment of feasible concepts
Objectives of this study:
� A conceptual aircraft design that answers the market analysis results
DLRK 2019 • Chart 3 Electric 19-Seater Aircraft with Range Extenders
Design Goals
Market research data:
• Extremely short utilization distances of
19-seater aircraft
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19
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Trip Distance from x km up to y km
Design aim:
• 19-seater aircraft with fully electric flight
capability.
• State-of-the-art electric components at
prototype level.
• Certification under CS 23
• Competitive payload-range characteristics
� Market suitable for fully electric flight Cu
mu
lative
sh
are
of
flig
hts
Trip Distance [km]
Propulsion Architecture
DLRK 2019 • Chart 5 Electric 19-Seater Aircraft with Range Extenders
Con
Con
Kero
sene
Tank
Gas
Turbine
eMotor Battery
• Classical twin propeller configuration:
o Low-risk, dependable conceptual-level results.
• E-Motors:
o Sized for take-off & all-electric operation.
• Range extender:
o In parallel to e-motors, with a coupling / decoupling device.
o For full IFR mission reserves with kerosene.
o For range flexibility with kerosene.
o Sized for loiter speeds @ 10000ft.
• Batteries:
o Sized for all-electric operation.
o Must not consider mission reserves.
Configurational Aspects
DLRK 2019 • Chart 6 Electric 19-Seater Aircraft with Range Extenders
co
n
Propulsion mass directly
supported by the landing gear
2t 2t4t
Favourable mass distribution
for the wing in flight
0%
100%
Po
we
r
Altitude
E-Motor PowerGas Turbine Power
Pressurized cabin complementing
the e-motors‘ lack of power lapse.
Landing gear to wing root due
to space allocation
wikipedia.com
Designation - E19
Conceptual Design Model Calibration
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• Refined troughout previous studies
• Dependable for similar configurations
� Used as a base for this study
Aircraft Sizing Model Based on Do228
Uncertainty: E19 configuration is different
BAe Jetstream 31
B1900D
Model Validation and Calibration on Similar to E19 Configurations
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B1900D
B1900D ref. data
BAe JS31
Bae JS31 ref. data
Top-Level Aircraft Requirements (TLARs) & Assumptions
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TLAR Value Unit Remarks
MTOM Limit 8618 Kg CS23 Limit
Max Payload 1805 Kg Same as BAe JS31
Min Cruise Altitude 10000 Ft
Ceiling Altitude 25000 Ft Same as BAe JS31
Diversion Mission 100 Nm For IFR flight rules
Approach Speed 109 Kts Similar to BAe JS31
Takeoff Field Length 1440 m Same as BAe JS31
Same technology as the Bae JS31:
• Airframe structure
• Systems
• Gas turbine
• Furnishings & Operator Items
Segment Time [min] Energy [kWh]
Taxi out 3.0 0.8
Take-off 1.1 24.7
Approach & Landing 2.0 6.1
Taxi in 3.0 0.8
Total 9.1 32.4
Allowances
Sizing Results
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El. Power TrainTot. Mass Tot. Power Eff.
[kg] [kW] [-]
E-Motors 253 1251 95.0%
Controllers 12 1321 98.0%
Cooling 44 89 -
Power Distr. 66 1321 99.7%
Battery 2018 1352 -
Sizing Model Results Value Unit
Max. Takeoff Mass (MTOM) 8618 kg
Design Fuel (IFR Reserves Only) 192 kg
Maxi. Zero-Fuel Mass 8426 kg
Max. Payload 1805 kg
Operating Empty Mass (OEM) 6621 kg
Operator's Items 475 kg
Manufacturer's Empty Mass 6146 kg
Furnishings 270 kg
Systems 650 kg
Propellers + Range Ext. (incl
Systems)388 kg
Airframe Structure 2446 kg
El. Power Train Budget 2329 kg
State of the Art Technology Assumptions @ Prototype Level
5kW/kg @ 1680rpm
115kW/kg (Siemens)
1 kW/kg (losses)
• 230 Wh/kg
• 690 W/kg
� Effective: 160 Wh/kg
• 90% State of Charge (start of Mission)
• 20% State of Charge (end of Mission)
Battery Pack
E19 Geometry Overview
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Parameter Wing HTP VTP
Area [m2] 33.2 8.2 6.1
Aspect Ratio [-] 12.0 5.2 1.5
MAC [m] 1.77 1.27 2.17
¼-Chord Sweep [°] 1.8 3.0 36.0
Rel. thickness [-] 16% / 12% 13% / 12% 13% / 12%
E19 Payload-Range Characteristics
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Range [km]
50%
50% 25%
75%10%
90%
6%
94%
• Mostly electric operation in the typical utilization range
• Extended range capability for airline flexibility
88% of
Missions
E19 Power Profile
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Altitude
Electric Mission (190km)
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GT* + E-Mot Power
E-Motor Power
Altitude
Hybrid Mission (340km)
• 10000ft cruise – too short for higher altitude.
• No pressurization offtakes at this altitude.• Climbs higher and faster to improve time
performance at the bigger distances
Payload-Range Comparison
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Range [km]
B1900D
BAe JS31
Do228
E19Typical
Utiliza-
tion
Parameter Unit Do228 BAe JS31 B1900D E19
MTOM kg 6400 6950 7766 8618
Sref m2 32 25.2 28.8 33
Span m 17 15.9 17.75 20
cLcruise - 0.3 0.55 0.45 0.75
L/Dcruise - 10.0 14.6 12.1 19.4
psfcGT,cruise kg/kWh 0.34 0.32 0.33 0.35
� High MTOM is mitigated by improved L/D
Mission Performance
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B1900D
E19
Cruise Points
• E19 � velocity traded for efficiency.
• Penalty most prominent at the longer missions.
• Less affected at the typical utilization range.
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E19
JS31
B1900D
Do228
88% of the
missions
DLRK 2019 • Chart 15
Sizing Requirements for the Hybrid Chain
Electric 19-Seater Aircraft with Range Extenders
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[email protected] Payload - LRC
[email protected] Payload - MC
[email protected] Payload
~88% of the
operations
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Trip Distance from x km up to y km
Emmissions if all 2018 flights were operated by E19
Emmissions if all 2018 flights were operated by the
Do228 at efficient cruise speed
• With renewable energy for recharging, ~70% emissions reduction potential at the 19-seater market
• If current electric mix in Germany is used � a potential of ~45% emissions reduction remains
DLRK 2019 • Chart 16
Conclusions
The conceptual design study conclusions:
• State-of-the-art electric power technology is potetially suitable for the 19-seater market.
• > 70% fuel savings on average are potentially feasible on this market.
• > 40% CO2 emission reduction possible, if battery charging with the German electric mix of today is assumed.
Further efforts needed:
• Operational assessment, including charging during turnaround and life-cycle assessment.
Electric 19-Seater Aircraft with Range Extenders
DLRK 2019 • Chart 17
Outlook
Electric 19-Seater Aircraft with Range Extenders
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Fully Electric
50% Electric Power
25% Electric Power
10% Electric Power
6% Electric Power
E19 Payload-Range
2x Better
Batteries
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50% Electric Power
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Payload-Range
10
0%
PE
• New battery technology could improve performance without redesigning the aircraft.
• The approach is scalable to bigger aircraft for similar range performance.
DLRK 2019 • Chart 18
Thank you for your attention!
Electric 19-Seater Aircraft with Range Extenders