Distributed Electric Propulsion Aircraft PDF
Distributed Electric Propulsion Aircraft PDF
Distributed Electric Propulsion Aircraft PDF
Mark D. Moore
NASA Langley Research Center
mark.d.moore@NASA.gov 1
Near-Term Electric Propulsion Evolution Strategy
Can electric propulsion impact aviation over the next decade, or is battery
specific energy too constraining?
What value does electric propulsion offer aviation in the near-term in terms of
carbon emissions, and how can low carbon solutions be incentivized in the
aviation market without dependency on carbon taxing?
GL-10 UAS DEP Tilt-Wing Tilt-Tail Vertical Takeoff and Landing (VTOL) Flight Demonstrator
Fully Redundant Digitally Controlled Vehicle Thrust
Robust Control Throughout Forward Flight to Hover (>20 Flight Transitions)
4x Cruise Efficiency (Lift/Drag Ratio) Compared to Helicopters
5
Vibrant EP Flight Demonstrations at Smaller Scale
Pipistrel Watts Up
Slovenia
(Ready for Production)
E-Fan DA-36 E-Star E-Genius
Airbus Airbus Airbus 6
NASA DEP LEAPTech Testing
7
DEP Aero-Propulsion Highlift Integration
Li)
Coecient
at
61
Knots
(with
and
without
220
kW)
No
Flap
(STAR-CCM+)
40
Flap,
No
Power
(STAR-CCM+)
40
Flap
with
Power
(STAR-CCM+)
40
Flap
with
Power
(EecGve,
STAR-CCM+)
40
Flap
with
Power
(FUN3D)
40
Flap
with
Power
(EecGve,
FUN3D)
Tecnam P2006T Light Twin General Aviation Aircraft NASA Distributed Electric Propulsion (DEP) X-Plane
$15 million, 3-year research project to achieve the first DEP manned flight demonstrator in 2017
Instead of focusing on low speed efficiency, SCEPTOR focuses on how DEP technologies
enables cruise efficiency at higher speeds.
9
SCEPTOR DEP X-Plane
Cirrus
SR-22
General
AviaZon
Aircra)
500
nm
range
+
reserves
3400
lb
13
EP Early Adopter Opportunities
Pathfinder markets are already feasible to establish renewable based, ultra low
carbon aviation solutions; while establishing early certification and technology experience.
14000
Cape Air Northeast Hyannis Airport, MA
Cape Air Commuter Trip Range Distribution Operations 1.4 MW solar farm
12000
Number
of
2000
Trips
0
20
23
27
34
39
40
48
59
66
79
82
90
97
104
110
129
135
139
159
163
168
169
172
183
210
16
Current NASA Cost-Emission Trade Studies
Q400 Regional
Turbo-Prop
100% Electric
(No Hybrid Engine)
Research focusing on rapid, spiral development of EP technologies can achieve early success
in reducing in-flight carbon emissions for shorter range aircraft relatively quickly.
Shorter range aircraft designed to achieve low operating costs will almost certainly be
designed as large battery, series hybrid with small range extenders for operations flexibility.
High utilization is a key ingredient for the economics of electric vehicles to make sense, with
rapid/efficient/high life cycle battery charging systems a critical operational element.
Incentivizing low carbon aviation through dramatic improvements through natural market
economic forces has a higher probability of success than being dependent on carbon taxing.
18
Current SCEPTOR Configuration
19
Comparison to Baseline Tecnam P2006T
20
SCEPTOR Characteristics
22
SCEPTOR Mass Breakdown
1% 2%
10%
fuselage 136.7 kg
2% tail 31.5 kg
wing 166.7 kg
26%
crew 100 kg
12%
accomodations 51 kg
landing gear 54 kg
avionics 37.8 kg
systems 75.6 kg
instrumentation 81.82 kg
cruise motors 70 kg
7%
high-lift motors 64.8 kg
3% electrical system 13.48 kg
nacelles 36.36 kg
4% 3%
margin 39.22 kg
< 1%
4% batteries 358.3 kg
5%
3%
cruise props 30 kg
6%
5% high lift props 16.36 kg
6%
23
SCEPTOR Primary Objective Metric
h, ft
h, ft
3.6
3.7
3.8 3.8 3.8
3.9
44.1
43.9
4.1
4.2 3.7 4.3
4.2
4.4
4.5 4.4
3.6 4.3
2 3.8
3.9
4 3.4 2 44.1
4.2
4.3
4.4
4.5 4.1
4.1
4.2 5.5
3.9
4.1
4.2
4.3 4.6 4.1
4.3 5.3 3.8
4 4.2
4.7 4.4
4.5 5.2
1.5 3.6
3.7
3.8
3.9
4 4.8 1.5 3.8
3.9
4
4.1
4.2
4.4
4.5 3.6
4.1 4.3
4.6
4.2 5.4
3.6
3.7
3.8 3.8
3.9
4
4.1
1 43.9
4.1
4.2
4.4
4.5
4.3
4.24.7
1 4.4
4.5
4.9
3.9
4 4.3 4.2
4.4
4.5
4.1 5.5
4.1 4.3 5.1
54.9
4.1
4.2 4 4.6
3.53.33.1 4.5 4.24
0.5 0.5
3.7
3.8
3.9
44.1
4.2 3.2 32.92.8 3.9
4
4.1
4.3
4.24.6 3.9 3.73.5
2.72.6 3.4 3.2
3.33.1
2.52.4
2.32.2 4.4
4.5 3 2.9
2.8 2.6
4.3
2.1
2
2.2
2.3
2.4
2.5
2.6
2.7
2.8
2.9
33.1
3.2
3.3
3.5
44.1
4.3 2.12 2.7 2.52.4
22.4
2.5
2.6
2.7
2.8
2.9
3
3.1
3.2
3.3
3.4
3.5
3.7
3.9
4
4.2
.2
4.5
4.6
0 0
80 100 120 140 160 180 200 220 80 100 120 140 160 180 200 220
V, KTAS V, KTAS
24