Comparison of Electrified Aircraft Propulsion Drive Systems with Different Electric Motor Topologies

Sirimanna, Samith; Balachandran, Thanatheepan; Lee, Dong Su; Agrawal, Shivang; Yu, Yangxue; Wang, Yuyao; Anderson, Aaron; Banerjee, Arijit; Haran, Kiruba S.

doi:10.2514/1.b38195

Cited by 20 publications

(5 citation statements)

References 26 publications

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“…The efficiencies of the electrical components are estimated as the average of the mostly adopted ones for power electronics and electrical machines, as found in the literature [79]. These values may vary depending on the design requirements, such as the type of the machine and its specific power [80]. However, for the model in this study, some of the efficiency values were chosen based on experience.…”

Section: Propulsion System Model and Assumptionsmentioning

confidence: 99%

Application of Probabilistic Set-Based Design Exploration on the Energy Management of a Hybrid-Electric Aircraft

et al. 2022

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The energy management strategy of a hybrid-electric aircraft is coupled with the design of the propulsion system itself. A new design space exploration methodology based on Set-Based Design is introduced to analyse the effects of different strategies on the fuel consumption, NOx and take-off mass. Probabilities are used to evaluate and discard areas of the design space not capable of satisfying the constraints and requirements, saving computational time corresponding to an average of 75%. The study is carried on a 50-seater regional turboprop with a parallel hybrid-electric architecture. The strategies are modelled as piecewise linear functions of the degree of hybridisation and are applied to different mission phases to explore how the strategy complexity and the number of hybridised segments can influence the behaviour of the system. The results indicate that the complexity of the parametrisation does not affect the trade-off between fuel consumption and NOx emissions. On the contrary, a significant trade-off is identified on which phases are hybridised. That is, the least fuel consumption is obtained only by hybridising the longest mission phase, while less NOx emissions are generated if more phases are hybridised. Finally, the maximum take-off mass was investigated as a parameter, and the impact to the trade-off between the objectives was analysed. Three energy management strategies were suggested from these findings, which achieved a reduction to the fuel consumption of up to 10% and a reduction to NOx emissions of up to 15%.

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Section: Propulsion System Model and Assumptionsmentioning

confidence: 99%

Application of Probabilistic Set-Based Design Exploration on the Energy Management of a Hybrid-Electric Aircraft

et al. 2022

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“…Currently, for most of the electrified propulsion, the effort has been on exploring Permanent Magnet Synchronous Machines (PMSM). A study conducted by Samith in [13], showed the comparison of various motors that are available and assessed eight different types of motor topologies, the study concluded that PMSM and BLDC are better candidates for aerospace applications due to their specific power, compared to other topologies investigated. Xie in [11] proposed a sizing procedure for Surface Mounted Permanent Magnet Machines (SMPMM), the procedure is for either the outer rotor or inner rotor machine.…”

Section: Introductionmentioning

confidence: 99%

The Impact of Electric Machine and Propeller Coupling Design on Electrified Aircraft Noise and Performance

Zaghari

Kiran

Sinnige

et al. 2023

AIAA SCITECH 2023 Forum

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Novel propulsion systems have been studied in literature to reduce aircraft emissions with hydrogen or other electrical energy sources. Hybrid Electric Propulsion (HEP) system consists of electric machines as an alternative way to provide power for propulsion resulting in the reduction of aircraft fuel consumption. While reduction of emission is the main driver of new HEP designs, aircraft noise reduction and performance improvement will also need to be investigated. Much quieter electrified aircraft than conventional aircraft is explored with considering the benefits of coupled design between the propeller and electric machines. In this study, several electric machine designs have been explored and coupled with the propeller design to study the trade-off between the aerodynamic and acoustic performance of the propeller. Aerodynamic optimization is used as a baseline to minimize the energy consumption to find the aerodynamics optimum subject to constraints on the thrust levels during the mission. The propeller aerodynamic optimizer considers the electric machine efficiency map, which is a function of propeller torque and rotational speed, to find the optimum combination of propeller and electric machine designs. The objective function of the acoustic optimizations is to reduce the cumulative noise level over the entire mission. It is shown that a wider envelope of peak motor efficiency in the efficiency map provides acoustics and aerodynamic performance benefits. The trade-offs between reducing noise or increasing aerodynamic efficiency to reduce energy consumption are demonstrated.

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“…Several studies [1], [2] have provided the broader academic and industrial community power-density and efficiency targets in order to enable a new class of electrified transportation. To meet these targets, machine designs are moving towards higher speed operation to increase the motor power density [3]. Additionally, new, high-performance machines may forgo high-permeability and dense iron [4], thus reducing the machine filtering inductance.…”

Section: Introductionmentioning

confidence: 99%

A Segmented Electric Aircraft Drivetrain Employing 10-Level Flying Capacitor Multi-Level Dual- Interleaved Power Modules

Bayliss

Iyer

Liou

et al. 2023

2023 IEEE Applied Power Electronics Conference and Exposition (APEC)

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Electric aircraft require power dense and efficient powertrains to become practical and break out of the laboratory and into the air. This work describes a full electric drivetrain, comprising six interleaved 10-level flying capacitor multi-level (FCML) dc-ac converters with high (38.4 kW/kg) specific power density and efficiency (98.95%). A global controller implements field-oriented control, and communicates through digital optical links to a local FPGA controller on each dual-interleaved FCML module (each module comprising two dc-ac converters). Successful demonstration on a full dynamometer test-bed with twin 250 kW electric aircraft machines is demonstrated, along with an active feedforward cancellation technique to reduce higher order harmonics.

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Comparison of Electrified Aircraft Propulsion Drive Systems with Different Electric Motor Topologies

Cited by 20 publications

References 26 publications

Application of Probabilistic Set-Based Design Exploration on the Energy Management of a Hybrid-Electric Aircraft

Application of Probabilistic Set-Based Design Exploration on the Energy Management of a Hybrid-Electric Aircraft

The Impact of Electric Machine and Propeller Coupling Design on Electrified Aircraft Noise and Performance

A Segmented Electric Aircraft Drivetrain Employing 10-Level Flying Capacitor Multi-Level Dual- Interleaved Power Modules

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