A General Approach to the Conceptual Design of All-Electric and Hybrid-Electric Aircraft
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(2) Outline. 1) Introduction. 3) Numerical Implementation. •. Hybrid architectures. •. Hyperion program procedure. •. Future trends. •. Simulation strategies. •. Program validation. 2) Sizing Approach •. Preliminary aircraft sizing. •. Working assumptions. •. General aviation case study. •. Motors and Battery sizing. •. Micro feeder case study. 4) Results. 5) Conclusions. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 2.
(3) Introduction: hybrid architectures. Available architectures. • All Electric • Series Hybrid • Parallel Hybrid • Series/parallel Hybrid. Source: Commercial Aircraft Propulsion and Energy Systems Research: Reducing Global. Carbon Emissions, National Academies Press.. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 3.
(4) Introduction: future trends. Trend of applications • Non propulsive energy. • Electrically assisted gas turbines • Parallel hybrid propulsion. • Series hybrid or Turboelectric • Full-Electric Source: Long-term Hybrid-Electric propulsion architecture options for transport aircraft, A.T. Isikveren, Y.. Fefermann, C. Maury , 2016.. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 4.
(5) Outline. 1) Introduction. 3) Numerical Implementation. •. Hybrid architectures. •. Hyperion program procedure. •. Future trends. •. Simulation strategies. •. Program validation. 2) Sizing Approach •. Preliminary aircraft sizing. •. Working assumptions. •. General aviation case study. •. Motors and Battery sizing. •. Micro feeder case study. 4) Results. 5) Conclusions. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 5.
(6) Sizing Approach: aircraft preliminary sizing Airplane conceptual design •. Computation of aircraft takeoff, empty and payload mass. •. Estimation of aircraft aerodynamic characteristics and performance. •. Determination of required power and mission energy. •. Computation of motor and generator power and fuel and battery mass Engines Regression. Flight profile definition Z. 400. climb. cruise. Mass [kg]. takeoff. descent loiter. Thermal. 300. Electric. 200. Data. 100 0 0. 100 200 300 400 500 600 700 800 900 1000. t. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. Power [kW]. 6.
(7) Sizing Approach: working assumptions Power-train •. Use of propellers driven by electric motors. •. Power provided by batteries. •. Motor power not depending on altitude. •. Windmilling allowed in descent phase. •. Generator: turboshaft or reciprocating engine with alternator. Source: hypstair.eu. Generator model •. Simulation of the thermodynamic cycle at every altitude with estimation of real efficiency through experimental parameters. •. Fuel flow rate obtained from needed power from flight mechanics. •. Selection of a transition altitude for generator operation. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 7.
(8) Sizing Approach: motors and battery sizing •. Aircraft empty mass and aerodynamic characteristics from statistical regression. •. Analysis of needed power, estimated duration and overall energy for each phase. •. Motor and Generator sizing based on maximum and cruise power respectively. •. Battery and fuel mass from required energy and power needs. Guess Weight Empty Weight. max [ Pi ]. Statistical Regression. Aerodynamics Clean and Flapped Polar curves. Flight Mission. Motor. PMOT. ∑ PiTi. Battery Energy. Power Thermal Eng.. ηGEN. Fuel. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 8.
(9) Outline. 1) Introduction. 3) Numerical Implementation. •. Hybrid architectures. •. Hyperion program procedure. •. Future trends. •. Simulation strategies. •. Program validation. 2) Sizing Approach •. Preliminary aircraft sizing. •. Working assumptions. •. General aviation case study. •. Motors and Battery sizing. •. Micro feeder case study. 4) Results. 5) Conclusions. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 9.
(10) Numerical Implementation: Hyperion program. Hyperion: HYbrid PERformance simulatION •. Program initialization through input file. •. Simulation settings selected by user. •. Preliminary aircraft sizing. •. Step-by-step simulation of each flight phase. •. Check on final fuel and SoC levels. •. Battery/Fuel mass correction and reiteration until convergence. •. Visual postprocess and file writing. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 10.
(11) Numerical Implementation: simulation strategies Battery charging Strategy •. Based on battery state of charge, returns generator throttle for subsequent time step. •. Evolution through PID controller: more realistic throttle characteristics. •. Generator turned off during takeoff and first climb segment. •. Divided in steady charging and cyclic charging strategies. Steady charging strategy. Cyclic charging strategy 100%. 100% 80%. 60%. Battery. 80%. Battery. Fuel. 60%. Fuel. 40%. 40%. Throttle. 20%. 0%. Throttle. 20%. 0% 0. 20. 40. 60. 80. 100. 120. 0. 20. Time [min]. 40. 60. 80. 100. 120. Time [min] 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 11.
(12) Numerical Implementation: program validation •. Validation on general aviation, micro feeder, commuter and regional aircraft classes. •. Validation based on aircraft weight breakdown and installed power. •. Conventional airplanes simulated as turboelectric. •. Validation on Panthera Hybrid (internal ring) General Aviation – Power 312 22.9%. 250 200. 200. Panthera Hybrid. 178. 100 50 0. Motor [kW]. Generator [kW]. Empty [kg]. 120 9.1%. 150 110 105. General Aviation Weight Breakdown. 121 8.9%. Fuel [kg]. 312 23.7%. Simulated General Aviation. 53 4.0% 61 4.5%. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. Payload [kg]. 830 63.1%. Battery [kg] 868 63.7%. 12.
(13) Numerical Implementation: program validation. MTO [kg]. ME [kg]. MF [kg]. SW [m2]. PM [kW]. Real. 3600. 2250. 275. 25.4. 560. Simulated. 3327. 1927. 304. 24.0. 443. Real. 7764. 4732. 894. 28.8. 1910. Simulated. 7659. 4707. 814. 28.2. 1860. Real. 23000. 13500. 2000. 61.0. 3650. Simulated. 22990. 13450. 1920. 61.8. 3930. Aircraft Micro feeder Tecnam P2012. Commuter Beechcraft Beech-1900D. Large regional ATR 72-600. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 13.
(14) Outline. 1) Introduction. 3) Numerical Implementation. •. Hybrid architectures. •. Hyperion program procedure. •. Future trends. •. Simulation strategies. •. Program validation. 2) Sizing Approach •. Preliminary aircraft sizing. •. Working assumptions. •. General aviation case study. •. Motors and Battery sizing. •. Micro feeder case study. 4) Results. 5) Conclusions. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 14.
(15) Results: general aviation case study. 1800 1600 1400 1200 1000 800 600 400 200 0. •. Study on a single-engine, 4-seater general aviation aircraft with range of 300 km. •. Comparison of an All-Electric (internal ring) and Hybrid-Electric (external ring). •. Battery with 1000 W kg-1 and 500 Wh kg-1 of specific power and energy. •. Final state of charge (SoC) of 25% and 10% fuel reserve. 1775. Aircraft Results 1328. All-Electric. 185 145. MTOM [kg]. 312 23.5%. Motor Power [kW]. Weight Breakdown. 145 10.9%. Empty [kg] 478 26.9%. Fuel [kg] Payload [kg]. 985 55.5%. HybridElectric. 312 17.6% 31 2.3%. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. Battery [kg] 841 63.3%. 15.
(16) Results: micro feeder case study •. Study on a twin-engine, 8-seater micro feeder aircraft with range of 250 km All-Electric and 600 km Hybrid-Electric. •. Comparison of an All-Electric (internal ring) and Hybrid-Electric (external ring). •. Battery with 1000 W kg-1 and 500 Wh kg-1 of specific power and energy. •. Final state of charge (SoC) of 25% and 10% fuel reserve Aircraft Results. 3600. Weight Breakdown. 407 11.3%. 3615 3609. Empty [kg]. 913 25.3%. 3000. Fuel [kg]. 653 18.1%. 2400 All-Electric. 1800 1200 400 400. 600. 600 250. 0 MTOM [kg]. Power [kW]. HybridElectric. 913 25.3% 166 4.6%. Payload [kg] Battery [kg]. 2049 56.7% 2123 58.8%. Range [km] 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 16.
(17) Outline. 1) Introduction. 3) Numerical Implementation. •. Hybrid architectures. •. Hyperion program procedure. •. Future trends. •. Simulation strategies. •. Program validation. 2) Sizing Approach •. Preliminary aircraft sizing. •. Working assumptions. •. General aviation case study. •. Motors and Battery sizing. •. Micro feeder case study. 4) Results. 5) Conclusions. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 17.
(18) Conclusion • Developed a general procedure for All-Electric and serial HybridElectric aircraft conceptual design using turboshaft or reciprocating generator. • Conducted validation on available hybrid aircraft and simulated conventional limit case • Conceptual design of All-Electric and Hybrid-Electric 4-seater general. aviation aircraft and 8-seater micro feeder aircraft. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 18.
(19) Acknowledgements • Research partially funded by the EU’s Horizon 2020 research and innovation programme under Grant Agreement N. 723368. • Develop hybrid electric serial powertrains to enable cleaner, quieter and more efficient aircraft propulsion. • Deliver optimized propulsion components with increased reliability suitable for commercial deployment to small aircraft. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 19.
(20) Thank you for your attention!. 2 3 - 2 5 th O C T O B E R 2 0 1 8 - T O U L O U S E. 20.
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