Toward Robust Stability of Aircraft Electrical Power Systems: Using a &amp;mu;-Based Structural Singular Value to Analyze and Ensure Network Stability

Sumsurooah, Sharmila; Odavić, Milijana; Bozhko, Serhiy; Boroyevic, D.

doi:10.1109/mele.2017.2757383

Cited by 9 publications

(6 citation statements)

References 27 publications

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“…Having considered multiple CPLs, authors in [105] analyzed the stability of a hybrid ac-dc MEA EPS. Also, large signal and small signal stability based on Lyapunov methods and robust stability methods were studied in [106] and [107], respectively. To combat and eliminate the problem caused by CPLs, authors in [108] found the solution in real-time power estimation employed and developed by an adaptive back stepping controller.…”

Section: B Stabilitymentioning

confidence: 99%

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: B Stabilitymentioning

confidence: 99%

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

2020

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“…L1 , then the first numerator in (13) cancels the second denominator. Then expression (13) for i S2 becomes identical to expression (11) for i S1 , as desired. Similar logic can be applied to DG 3 , resulting in a selection of K 3 such that K3 L3 = 1 3 K1 L1 .…”

Section: B Stability Of the DC Microgrid In The Presence Of Loads (In...mentioning

confidence: 96%

“…This question was addressed in [10] by an accurate system modeling, detailed design and by allowing a substantial stability margin. Researchers in [13] used the μ-based structural singular value method to improve robust stability. To date, stability of the DC electric power system of MEA remains an open question in world research.…”

Section: Introductionmentioning

confidence: 99%

A Stable and Robust DC Power System for More Electric Aircraft

Mirzaeva

Miller

Goodwin

et al. 2021

2021 IEEE Energy Conversion Congress and Exposition (ECCE)

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More Electric Aircraft' (MEA) is a trend for medium and long haul airliners, in which all functions except propulsion are powered by engine-driven electrical generators. Power systems for MEA are in the process of rapid development. Constant Power Loads (CPL) pose a big challenge for power system stability. This paper proposes a concept of a MEA power system with a common DC bus, where power sharing between generators is achieved without droop or explicit communication.The paper shows how a coordinated response can be achieved by multiple DC-DC converters under PI current control, based on the local current measurements only. It utilises advanced control concepts, including feedforward and multiple degrees-offreedom design. The paper demonstrates stability of the proposed power system with respect to any load type, including CPL. The findings of the paper are validated by detailed simulations and preliminary experimental results.

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“…The aircraft electric system has become more complex and larger with multiple actuators, loads and bus geometries [39] due to the inclusion of power electronics converters in the MEA concept.…”

Section: The Presence Of Cpl In the Aircraft Systemmentioning

confidence: 99%

“…Many of these converters behave as constant power loads (CPL), which means they absorb a higher current when the input voltage decreases and vice-versa. The result is a dynamic characteristic expressed by an incremental negative resistance [39].…”

Section: The Presence Of Cpl In the Aircraft Systemmentioning

confidence: 99%

DC bus power electronic conditioner for electric aircraft system

Pinheiro Dias

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This project deals with the Electric Power Quality (PQ) in aeronautical environments. The More Electric Aircraft (MEA) concept focuses in the replacement of pneumatic and hydraulic actuators by electromechanical actuators and increases the electric power demand in the aircraft. The master project aims to the study and the implementation of a Power Electronic Conditioner (PEC) to mitigate the unwanted effects found in the DC aircraft internal feeders. The PEC must deal with the current unbalance between the positive and negative poles of the DC bus to comply with the standards. The speciĄc objectives are the development of a mathematical dynamic model for the current redistributor used as PEC and the study of control strategies for this aircraft electrical environment. Digital control solutions, with DSPs, FPGAs were studied along the project development. The appendixes provide the paper published in Cobep/Spec 2019 and experimental Setup.

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Toward Robust Stability of Aircraft Electrical Power Systems: Using a μ-Based Structural Singular Value to Analyze and Ensure Network Stability

Cited by 9 publications

References 27 publications

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

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

A Stable and Robust DC Power System for More Electric Aircraft

DC bus power electronic conditioner for electric aircraft system

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