Efficiency Focused Energy Management Strategy Based on Optimal Droop Gain Design for More Electric Aircraft

Mohamed, Mohamed A. A.; Yeoh, Seang Shen; Atkin, Jason; Hussaini, Habibu; Bozhko, Serhiy

doi:10.1109/tte.2022.3159731

Cited by 7 publications

(5 citation statements)

References 11 publications

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“…The 270 HVDC EPS concept is now considered as optimal option for future aircraft due to its relative simplicity, flexibility, and unique ability of DC systems to supply an uninterrupted power to electrical loads [28]. Because the control and design of variable frequency AC distribution and power electronics interface remain challenges, this EPS is complex and heavy.…”

Section: More Electric Aircraft and Its Insulation Risksmentioning

confidence: 99%

“…In addition, the quality of PCB also needs special consideration, which might be critical to reduce the distorted electric field at the triple point. And the thermal and electrical stresses in the PCB play important role in the ageing and damage process of the whole module, which is influential on the reliability of power system in aircraft. With the development of aircraft electrification technology, the EPS is becoming more and more complex [163]. HVDC topology is considered a very promising architecture for future MEA.…”

Section: Problems and Prospectsmentioning

confidence: 99%

“…(4) With the development of aircraft electrification technology, the EPS is becoming more and more complex [163]. HVDC topology is considered a very promising architecture for future MEA.…”

Section: Problems and Prospectsmentioning

confidence: 99%

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A review on insulation challenges towards electrification of aircraft

Jiang

et al. 2023

High Voltage

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Compared to the traditional aircraft, electrification of power system in aircraft has potential to revolutionise the aviation industry. Typically, more-electric aircraft (MEA), even all-electric aircraft has been developed and delivered to decrease the greenhouse gas emission and increase the energy efficiency. The next generation of MEA will operate at high voltage to facilitate the transfer of significant levels of electrical power in an electrified aircraft. However, the higher voltage inevitably leads to an increased risk to the insulation of the electrical components and power system. This study aims to provide a critical overview of the insulation challenges from the perspective of electrified aircraft, typically MEA application. The development of MEA and the special working conditions are explained at the beginning. Then the insulation challenges of power modules, electric machines, aeronautical cables etc. are discussed in detail. Finally, the existing technical barriers and future prospects of insulation for electrified aircraft are summarised. It provides a reference for the future design and test in power system of next generation MEA and related electrified air transportations.

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Section: More Electric Aircraft and Its Insulation Risksmentioning

confidence: 99%

Section: Problems and Prospectsmentioning

confidence: 99%

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A review on insulation challenges towards electrification of aircraft

Jiang

et al. 2023

High Voltage

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“…The CHIL tests of the present subsection are used as a proof of concept of the developed control method under real-time implementation, considering the influence of second order effects such as computational and PWM delays, quantization errors of the embedded ADCs in the microcontroller, deadtime of the inverter, etc. [22], [29], [30]. 20) is similar, for various combinations of k and ωr values (with respect to the maximum and minimum boundaries that are defined with the use of the 6-step design algorithm of Subsection B, Section III); this figure verifies that a high k-value satisfies the wide gain margin requirement of the topology, while ensuring that this constant gain is oriented at the low frequency range (which is desirable for the stable operation of the circuitry).…”

Section: Performance Validation Via Simulations and Real-time Chil Im...mentioning

confidence: 99%

Flexible Interlinking Converter With Enhanced FRT Capability for On-Board DC Microgrids

Apostolidou

Rigogiannis

Papanikolaou

et al. 2023

IEEE Open J. Veh. Technol.

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In this paper, a flexible interlinking dc/dc converter with enhanced FRTC is proposed to satisfy the advanced requirements of modern on-board DC MGs; the topology uses a non-isolated switched capacitor-type multilevel converter in combination with a cascaded step up/down converter to facilitate the incorporation of various types of energy storage and/or production units in a DC MG. Overall, a high voltage conversion ratio between the dc bus of the MG and the power unit is achieved. The proposed configuration facilitates the CCM operation of both the power unit and the DC MG and it is characterized by bidirectional power flow capability, enhanced FRTC, zero switching losses for the multilevel converter, limited complexity of the control scheme (compared to the counterpart multilevel solutions) and low real-time communication demands, corresponding so to the increasing flexibility needs of the EMS of modern MGs. The mathematical analysis and the dynamic performance of the control scheme of the proposed topology concept are evaluated via MATLAB/Simulink simulations and real-time CHIL tests, with the use of a 1202 dSPACE platform and an external dsPIC30F4011 microcontroller.

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“…The trends set by more electric aircraft (MEA) aim to reduce the number of pneumatic, mechanical and hydraulic systems and replace them with electrically powered actuators [1]. This goal of electrifying the aerospace sector is also supported by the Clean Sky 2 programme, which aims to be the main contributor to the Commission's Flightpath 2050 goals, set by ACARE.…”

Section: Introductionmentioning

confidence: 99%

Electric Aerospace Actuator Manufactured by Laser Powder Bed Fusion

Lizarribar,

Prieto,

Aristizabal

et al. 2023

Aerospace

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Recent advances in manufacturing methods have accelerated the exploration of new materials and advantageous shapes that could not be produced by traditional methods. In this context, additive manufacturing is gaining strength among manufacturing methods for its versatility and freedom in the geometries that can be produced. Taking advantage of these possibilities, this research presents a case study involving an electric aerospace actuator manufactured using additive manufacturing. The main objectives of this research work are to assess the feasibility of additively manufacturing electric actuators and to evaluate potential gains in terms of weight, volume, power consumption and cost over conventional manufacturing technologies. To do so and in order to optimise the actuator design, a thorough material study is conducted in which three different magnetic materials are gas-atomised (silicon iron, permendur and supermalloy) and test samples of the most promising materials (silicon iron and permendur) are processed by laser powder bed fusion. The final actuator design is additively manufactured in permendur for the stator and rotor iron parts and in 316L stainless steel for the housing. The electric actuator prototype is tested, showing compliance with design requirements in terms of torque production, power consumption and heating. Finally, a design intended to be manufactured via traditional methods (i.e., punching and stacking for the stator laminations and machining for the housing) is presented and compared to the additively manufactured design. The comparison shows that additive manufacturing is a viable alternative to traditional manufacturing for the application presented, as it highly reduces the weight of the actuator and facilitates the assembly, while the cost difference between the two designs is minimal.

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Efficiency Focused Energy Management Strategy Based on Optimal Droop Gain Design for More Electric Aircraft

Cited by 7 publications

References 11 publications

A review on insulation challenges towards electrification of aircraft

A review on insulation challenges towards electrification of aircraft

Flexible Interlinking Converter With Enhanced FRT Capability for On-Board DC Microgrids

Electric Aerospace Actuator Manufactured by Laser Powder Bed Fusion

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