sport aviation of the future. possible concepts for future sport aircraft using different...
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Sport Aviation of the Future.Possible Concepts for Future Sport Aircraft Using
Different Environmental Friendly Propulsion Concepts
Patrick Berry
Fluid and Mechatronic Systems
Introduction
A new generation of sport aircraft will require radical changes to the propulsion system
Why?
In the future fossile fuel will be scarce or at least limited and too expensive
Fossile fuel is bad for the environment and might also be prohibited to use in the future because of its environmental impact
So what are the options?!
1) Use bio fuels
2) Go electric
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Introduction
This study will focus on electric propulsion and what this means for the design and use of such aircraft
Different power sources like the sun, batteries and fuel cells will be covered
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Solar powered aircraft
Sources of inspiration:
Human powered aircraft
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Gossamer Albatross
Daedalus (MIT)
Solar powered aircraft
Sources of inspiration:
Solar powered aircraft
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Powered configuration
Configured as a glider
Solair 2
Questions
Is it possible to design something like this which is commercially viable?
…. and to which category do we certify it?
Is there a market?
Will the market accept it?
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Solar powered aircraft
The Sun peaks at 1000 W/m2 (in summertime, at noon on a clear day)
An average of 800 W/m2 can be expected (in southern Europe)
This indicates flight times around 7 hrs on pure solar power
But the aircraft won´t be able to take-off and climb on solar power, so it needs to be a hybrid using batteries to assist
Batteries are an additional dead weight which needs to be minimised, so we are looking for a battery with high energy density (Wh/kg)
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Battery trends in energy density
Quinetic Zephyr using Li-S (350 Wh/kg)Endurance: 2 weeks
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Solar powered aircraft
Affordable solar cells are in the range of 15-20% in efficiency. We need to work with the most efficient ones in order to reduce size, weight and stay reasonable in cost
Essential to minimise losses in the overall power chain
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Solar powered aircraft
How would you use such a plane?
Due to its low power-to-weight ratio it´s more suitable as a powered glider, i.e. a glider with self launch capability
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Specification for a solar powered aircraft
Average solar radiation = 800 W/m2
Max. sink rate in glider configuration: less than 0.7 m/s
Cruise speed in solar powered mode: 20% higher than stall speed
The aircraft shall be a hybrid, i.e. battery power for take-off and climb, solar power for cruise
Min. climb speed: 2m/s
Single seater or two seater
Pilot or passenger weight: 90 kg (+7 kg for parachute)
Certification: CS 22, motorgliders
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Typical sizing diagram for solar powered flight
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Solar constraints
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0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000 5500 6000 6500 7000 7500 8000
Altitude (ft)
(W
/S)o
(k
g/m
2)
Stall margin
Minimum sinkrate
Solar powered cruise
Initial cruise altitude
Design point solar powered a/c
Solar powered aircraft
Two configurations are presented:
1. Conventional layout
2. Canard configuration
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Conventional Single-seater Two seater
Overall length (m) 7.1 7.5
Span (m) 21.2 18.7 26.8 26.5
A 23 23
S (m2) 19.6 15.3 31.2 30.4
Empty weight (kg) 135 122 270 251
Battery weight (kg) 36 (Li-ion) 25 (Li-S) 66 (Li-ion) 42 (Li-S)
Pilot+parachute (kg) 90+7 194
MTOW (kg) 268 244 530 487
Max shaft power (kW)(T-off, climb)
8 16
Solar shaft power (kW)(cruise)
2.2 2 4.1 4
Propeller dia. (m) 2 2
Cruise speed (km/h) 77 76 77
(L/D)max 33 33
Endurance (h) 6.9 6.9
Climb rate (m/s) 1.8 2.1 1.7 1.9
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Canard Single-seater Two seater
Overall length (m) 7.4 8
Span (m) 16.7 15.8 21.8 20.5
A 18 18
S (m2) 15.4 13.9 26.5 23.4
Empty weight (kg) 114 101 218 189
Battery weight (kg) 36 (Li-ion) 24 (Li-S) 66 (Li-ion) 39 (Li-S)
Pilot+parachute (kg) 90+7 194
MTOW (kg) 247 222 478 422
Max shaft power (kW)(T-off, climb)
8 16
Solar shaft power (kW)(Cruise)
2.2 2 3.7 3.3
Propeller dia. (m) 2 2
Cruise speed (km/h) 80 76
(L/D)max 33 35
Endurance (h) 6.9 6.9
Climb rate (m/s) 2 2.2 1.8 2.1
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Typical V-n diagram for a solar powered aircraft
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Problem areas
Requires skilled pilot due to lack of excess power
Solar cell integration on wing and stabilizer
Solar cell integration requires stiff surfaces (brittle cells)
Solar cells need to be embedded for low drag (without too much energy losses)
Aircraft limited in use as to where and when you can operate it
Big question= Maintenance of solar cells!!
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Problem areas
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Battery powered aircraft
Source of inspiration:
PC Aero Electra One
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Battery powered aircraft
Battery powered aircraft are based on the sun powered configurations shown previously
Main difference: Wing loading can be increased since sun power is eliminated (saves weight)
Since battery weight will be even more dominant in this case, we need to decrease structure weight as much as possible (wing essentially)
No sun power means no need for non-tapered wings any more, i.e. weight potential
Aspect ratio can be reduced (weight saver), which means somewhat reduced soaring performance,
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Specification for a battery powered aircraft
Maximize range/endurance
Min. cruise speed : 20% higher than stall speed
Min. climb speed: 2m/s
Single seater or two seater
Pilot or passenger weight: 90 kg (+7 kg for parachute)
Certification: CS 22, motorgliders
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Conventional Single-seater Two seater
Overall length (m) 7.6 8
Span (m) 11.7 16.4
A 15 15
S (m2) 9.1 17.9
Empty weight (kg) 101 189
Battery weight (kg) 76 (Li-ion) 76 (Li-S) 155 (Li-ion) 155 (Li-S)
Pilot+parachute (kg) 90+7 194
MTOW (kg) 274 538
Max shaft power (kW) 12 25
Propeller dia. (m) 2 2
Min. cruise speed (km/h) 84 84
(L/D)max 26 27
Endurance (h) 2.7 4.5 2.7 4.4
Climb rate (m/s) 2 1.8
Max cruise speed (km/h) 160 160
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Canard Single-seater Two seater
Overall length (m) 7.6 8
Span (m) 10.8 15.2
A 13 13
S (m2) 9 17.7
Empty weight (kg) 97 183
Battery weight (kg) 76 (Li-ion) 76(Li-S) 155 (Li-ion) 155 (Li-S)
Pilot+parachute (kg) 90+7 194
MTOW (kg) 270 532
Max shaft power (kW) 12 25
Propeller dia. (m) 2 2
Min. cruise speed (km/h) 92 92
(L/D)max 28 30
Endurance (h) 2.9 4.5 2.9 4.4
Climb rate (m/s) 2.7 2.6
Max cruise speed (km/h) 160 160
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Pros and cons
Battery powered aircraft are probably the easiest way to replace current combustion engine types (except for bio fuels)
Battery powered aircraft have power to spare, thus easier to fly, require ”normal skilled pilots”
Might be more interesting for the market since range of speed is greater
Big pro = existing infrastructure!
Limited use in terms of over the year useage
Batteries don´t work that good in a cold environment
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Fuel cell powered aircraft
Source of inspiration:
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DLR Antares
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Fuel cell powered aircraft compared to battery powered
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Fuel cell powered aircraft
The DLR Antares is a derivative of an existing aircraft. It carries two external wing pods. One is the hydrogen tank the other is the fuel cell
In a blank paper design you would probably try to integrate the tank and fuel cell more
One big problem is to house the large pressurised tank (45 MPa), needs to be placed close to the C of G
Suggestion: place it in the main spar!
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Fuel cell powered aircraft
The fuel cell powered aircraft concepts are based on the battery powered concepts previously shown
Same specification
Battery weight exchanged for fuel cell + tank weight
Only differrence is in endurance
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Conventional Single-seater Two seater
Overall length (m) 7.6 8
Span (m) 11.7 16.4
A 15 15
S (m2) 9.1 17.9
Empty weight (kg) 101 189
Battery weight (kg) 76 (Li-ion) (Fuel cell) 155 (Li-ion) (Fuel cell)
Pilot+parachute (kg) 90+7 194
MTOW (kg) 274 538
Max shaft power (kW) 12 25
Propeller dia. (m) 2 2
Min. cruise speed (km/h) 84 84
(L/D)max 26 27
Endurance (h) 2.7 3.5 2.7 3.2
Climb rate (m/s) 2 1.8
Max. cruise speed (km/h) 160 160
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Canard Single-seater Two seater
Overall length (m) 7.6 8
Span (m) 10.8 15.2
A 13 13
S (m2) 9 17.7
Empty weight (kg) 97 183
Battery weight (kg) 76 (Li-ion) (Fuel cell) 155 (Li-ion) (Fuel cell)
Pilot+parachute (kg) 90+7 194
MTOW (kg) 270 532
Max shaft power (kW) 12 25
Propeller dia. (m) 2 2
Min. cruise speed (km/h) 92 92
(L/D)max 28 30
Endurance (h) 2.9 3.5 2.9 3.2
Climb rate (m/s) 2.7 2.6
Max. cruise speed (km/h) 160 160
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Pros and cons
Technology seems promising
Still in early development stage, not mature
Lack of infrastructure!!
Use is limited by the same reason as battery powered aircraft:
Gas performance degrade with lower temperature
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How we prepared the study
We used an in-house design program, which we rearranged
The rearrangement included:
Adding solar power model
Adding electric motor model
Adding battery model
Adding fuel cell model
Rearranged weight equations in weight module
The electric motor model and weight equations were trimmed against published Solair 2 data
We benchmarked against existing aircraft in the category and found good relevence
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Conclusions
This study has shown that it´s quite possible to design electric aircraft with different power sources, even using today´s technology
The ability to design light and with low drag is emphazised more than ever
”Green aircraft” won´t be any high speed machines
Live ”green”= eat ”slow food”
Fly ”green”= fly slowly
Will the market accept slow flight?
Personal view: the market might digest battery powered aircraft in the very near future, but the other variants will probably have to wait for a while
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Questions?
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