Load Control for the DC Electrical Power Distribution System of the More Electric Aircraft

Günter, Sandro; Buticchi, Giampaolo; Carne, Giovanni De; Gu, Chunyang; Liserre, Marco; He, Z. Y.; Gerada, Chris

doi:10.1109/tpel.2018.2856534

Cited by 41 publications

(20 citation statements)

References 15 publications

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“…An EPS is comprised of different components, such as power electronics (PE) converters, electric machines, electrochemical energy units, circuit breakers (CBs, also known as solid-state breakers [10] or bus-tie breakers [11]), different loads, etc., that are all connected to appropriate busses and are needed to be taken into consideration when analyzing an EPS. In addition, even though there are similarities between an aircraft EPS and a ground-based microgrid, the aircraft EPS is an isolated onboard microgrid, which is different from microgrids on the ground [12] .…”

Section: Ecsmentioning

confidence: 99%

“…Techniques such as load shedding or approaches similar to ground-based peak load shaving approaches [80] seem possible as well. In [10] for a dc bus, to determine behavior of loads, modification of the bus voltage was taken into consideration. As a result, power consumption was managed with regard to available power, including the power that has been generated and redistributed.…”

Section: G Management Of Aircraft Electric Power Systemsmentioning

confidence: 99%

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Electric Power Systems in More and All Electric Aircraft: A Review

2020

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Narrow body and wide body aircraft are responsible for more than 75% of aviation greenhouse gas (GHG) emission and aviation, itself, was responsible for about 2.5% of all GHG emissions in the United States in 2018. This situation becomes worse when considering a 4-5% annual growth in air travel. Electrified aircraft is clearly a promising solution to combat the GHG challenge; thus, the trend is to eliminate all but electrical forms of energy in aircraft power distribution systems. However, electrification adds tremendously to the complexity of aircraft electric power systems (EPS), which is dramatically changing in our journey from conventional aircraft to more electric aircraft (MEA) and all electric aircraft (AEA). In this paper, we provide an in-depth discussion on MEA/AEA EPS: electric propulsion, distributed propulsion systems (DPS), EPS voltage levels, power supplies, and EPS architectures are discussed. Publications on power flow (PF) analysis and management of EPS are reviewed, and an initial schematic of a potential aircraft EPS with electric propulsion is proposed. In this regard, we also briefly review the components required for MEA/AEA EPS, including power electronics (PE) converters, electric machines, electrochemical energy units, circuit breakers (CBs), and wiring harness. A comprehensive review of each of the components mentioned above or other topics except for those related to steady state power flow in MEA/AEA EPS is out of this paper's scope and should be found somewhere else. At the close of the paper, some challenges in the path towards AEA are presented. Unless the discussed challenges are satisfactorily addressed and solved, arriving at an AEA that can properly operate over commercial missions will not be possible. INDEX TERMS aircraft electrification, all electric aircraft (AEA), electric power system (EPS), more electric aircraft (MEA), power distribution system, steady state power flow analysis.

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Section: Ecsmentioning

confidence: 99%

Section: G Management Of Aircraft Electric Power Systemsmentioning

confidence: 99%

Electric Power Systems in More and All Electric Aircraft: A Review

2020

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“…In [2], the authors explain design methodologies and examples for DC power distribution in an aircraft. In [3], S. Günter discusses challenges in peak power demand, overload conditions, increasing weight and total cost of operation in electric power distribution systems of aircrafts. Moreover, V. Madonna in [4] gives a thorough review about the evolution of electric power generation and power distribution systems in aircrafts.…”

Section: Related Workmentioning

confidence: 99%

Automatic Optimal Synthesis of Aircraft Electric Power Distribution System

Ameri¹,

Mozumdar²,

Chwa³

et al. 2020

IJCDS

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Reliability is one of the most critical design features in Aircraft Electric Power Distribution system (EPDS). In an EPDS, the power is distributed from generators to loads, sensors and actuators through AC and DC distribution buses using control switches. Because of the increasing demands of loads and their power requirements, EPDS design must be optimized in order to have maximum efficiency. In this paper, we propose a synthesis tool based on a need-based design method to obtain the optimal topology of EPDS considering maximum reliability, continuous connectivity, power requirements, and minimum cost. We treat the EPDS as an optimization problem by using Integer Linear Programming (ILP) to achieve minimum cost and maximum reliability while satisfying a set of constraints.

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“…The instability issue was handled in a multi-load DC-power network, and three different types of loads were presented for a DC voltage source. Moreover, the concept of load identification and control was proposed for the DC EPDS of MEA in [103] to satisfy the large amount of power required without increasing the capacity of generators and energy storage, or implementing load shedding. However, it is difficult to model the higher order power dependency to voltage by using the proposed ZIP model, and the calculation accuracy of the load exponent is limited by the noise of the measured signals and the discretization of the analog-to-digital signals when a digital signal processor (DSP) is used.…”

Section: A System Stabilitymentioning

confidence: 99%

Electrical and Electronic Technologies in More-Electric Aircraft: A Review

Liu

Mei

et al. 2019

IEEE Access

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This paper presents a review of the electrical and electronic technologies investigated in moreelectric aircraft (MEA). In order to change the current situation of low power efficiency, serious pollution, and high operating cost in conventional aircraft, the concept of MEA is proposed. By converting some hydraulic, mechanical, and pneumatic power sources into electrical ones, the overall power efficiency is greatly increased, and more flexible power regulation is achieved. The main components in an MEA power system are electrical machines and power electronics devices. The design and control methods for electrical machines and various topologies and control strategies for power electronic converters have been widely researched. Besides, several studies are carried out regarding energy management strategies that intend to optimize the operation of MEA power distribution systems. Furthermore, it is necessary to investigate the system stability and reliability issues in an MEA, since they are directly related to the safety of passengers. In terms of machine technologies, power electronics techniques, energy management strategies, and the system stability and reliability, a review is carried out for the contributions in the literature to MEA. INDEX TERMS More-electric aircraft, machine technologies, power electronics techniques, energy management strategies, system stability and reliability.

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Load Control for the DC Electrical Power Distribution System of the More Electric Aircraft

Cited by 41 publications

References 15 publications

Electric Power Systems in More and All Electric Aircraft: A Review

Electric Power Systems in More and All Electric Aircraft: A Review

Automatic Optimal Synthesis of Aircraft Electric Power Distribution System

Electrical and Electronic Technologies in More-Electric Aircraft: A Review

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