Review of hybrid-electric aircraft technologies and designs: Critical analysis and novel solutions

Abu Salem, Karim; Palaia, Giuseppe; Quarta, Alessandro A.

doi:10.1016/j.paerosci.2023.100924

Cited by 24 publications

(25 citation statements)

References 158 publications

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“…A wide discussion on electric and hybrid-electric powertrains and aircraft is proposed in refs. [23,24]. Electric propulsion represents a new opportunity for the application of DP, and this recently regained huge scientific interest.…”

Section: Distributed Propulsionmentioning

confidence: 99%

“…In this context, specific attention is being devoted to research into non-conventional solutions for the integration of the propulsion system, involving two different interconnected technological threads. From a general point of view, new types of propulsion systems are under investigation, and technologies involving new fuels, such as hydrogen [11][12][13][14][15][16][17][18] or sustainable aviation fuels [19][20][21][22], or electric and hybrid-electric powertrains [23][24][25][26][27][28][29][30][31][32], are under development to provide breakthrough forward advancements in the field. In addition to these important innovations, and in a way that is generally complementary, non-conventional powertrain/airframe integrations are increasingly being investigated since, either as standalone or in combination with previous new power supply concepts, they can contribute to general improvements in aircraft performance, with significant implications for reducing environmental impact.…”

Section: Introductionmentioning

confidence: 99%

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A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

Abu Salem,

Palaia,

Bravo-Mosquera

et al. 2024

Designs

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The aim of this review paper is to collect and discuss the most relevant and updated contributions in the literature regarding studies on new or non-conventional technologies for propulsion–airframe integration. Specifically, the focus is given to both evolutionary technologies, such as ultra-high bypass ratio turbofan engines, and breakthrough propulsive concepts, represented in this frame by boundary layer ingestion engines and distributed propulsion architectures. The discussion focuses mainly on the integration effects of these propulsion technologies, with the aim of defining performance interactions with the overall aircraft, in terms of aerodynamic, propulsive, operating and mission performance. Hence, this work aims to analyse these technologies from a general perspective, related to the effects they have on overall aircraft design and performance, primarily considering the fuel consumption as a main metric. Potential advantages but also possible drawbacks or detected showstoppers are proposed and discussed with the aim of providing as broad a framework as possible for the aircraft design development roadmap for these emerging propulsive technologies.

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Section: Distributed Propulsionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

Abu Salem,

Palaia,

Bravo-Mosquera

et al. 2024

Designs

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“…The Lead-acid and Nicad (nickel-cadmium)-based battery solutions are conventionally preferred in aircraft battery systems. However, within the scope of the concept of more electric aircraft, there are innovative studies on the use of lithium ion-based batteries instead of such battery structures [26]. The use of lithium ion-based battery types in aircraft instead of conventional battery structures has several advantages, including weight advantages and the ability to meet instantaneous high current demand.…”

Section: More Electric Aircraftmentioning

confidence: 99%

Multilevel Aircraft-Inverter Design Based on Wavelet PWM for More Electric Aircraft

Catalbas,

Pakfiliz,

Soysal

2024

Energies

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This paper proposes a comprehensive power system designed for the use of a more electric aircraft power distribution system. Instead of traditional Nicad battery solutions as the energy source of the aircraft power system, lithium battery structures, which are a recent and promising solution in the field of aviation power systems, are modeled and analyzed. In this study, a WPWM-based, single-phase, multi-level pure sine wave static aircraft-inverter system is designed and integrated to improve the performance of conventional aircraft power systems. In the designed power system, a boost converter structure is proposed that boosts 28 VDC-to-270 VDC voltage coming from the lithium–ion battery pack and can reach a steady state in 0.032 s. The performance of the modeled WPWM-based aircraft-inverter system, compared to SPWM Bipolar and Unipolar switching techniques commonly used in single-phase inverter designs, reveals a THD reduction of approximately 27% with WPWM, resulting in a THD value below 2% for both load current and load voltage. As a result of the study, a power system that will enable the aircraft avionics, ventilation, and navigation systems to perform better than conventional power systems and comply with aircraft electric-power characteristic standards has been designed and detailed.

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“…The miniaturization and reduction in cost of the relevant control components in aircraft, as well as the development and progress of computer and sensing and measurement technologies, have improved the stability of flight control systems and greatly facilitated the development of quadrotors [1]. The high operability, strong mobility and flexibility of quadrotors allow them to meet the specific needs of many projects, generally used in military, industrial and other fields [2,3]. A quadrotor system is multivariable, nonlinear and strongly coupled, and quadrotors will also be disturbed by the surrounding environment during flight [4].…”

Section: Introductionmentioning

confidence: 99%

Robust Approximate Optimal Trajectory Tracking Control for Quadrotors

Li,

Yang,

Yan

et al. 2024

Aerospace

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This paper uses the adaptive dynamic programming (ADP) method to achieve optimal trajectory tracking control for quadrotors. Relying on an established mathematical model of a quadrotor, the approximate optimal trajectory tracking control, which consists of the steady-state control input and the approximate optimal feedback control input, is designed for a nominal system. Considering the compound disturbances in position and attitude dynamic models, disturbance observers are introduced. The estimated values are used to design robust compensation inputs to suppress the effect of the compound disturbances for good trajectory tracking performance. Theoretically, the Lyapunov theorem demonstrates the stability of a closed-loop system. The robustness and effectiveness of the proposed controller are confirmed by the simulation results.

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Review of hybrid-electric aircraft technologies and designs: Critical analysis and novel solutions

Cited by 24 publications

References 158 publications

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

Multilevel Aircraft-Inverter Design Based on Wavelet PWM for More Electric Aircraft

Robust Approximate Optimal Trajectory Tracking Control for Quadrotors

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