Benefits of higher voltage levels in aircraft electrical power systems

In recent years, the electrical power capacity is increasing rapidly in more electric aircraft (MEA), since the conventional mechanical, hydraulic and pneumatic energy systems are partly replaced by electrical power system. As a consequence, capacity and complexity of aircraft electric power systems (EPS) will increase dramatically and more advanced aircraft EPSs need to be developed. This paper gives a brief description of the constant frequency (CF) EPS, variable frequency (VF) EPS and advanced high voltage (HV) EPS. Power electronics in the three EPS is overviewed.

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“…Compared with the conventional 115V EPS, power transmission loss and converter weight can be reduced by 50.7% and 42.5% respectively [21]. Fig.…”

Section: High Voltage Ac (Hvac) Aircraft Epsmentioning

confidence: 99%

“…By doing this, the feeder cable current could be reduced dramatically. Also, lower cable weight, higher efficiency and lower consumption could be achieved [20] [21].…”

Section: Future Aircraft Epsmentioning

confidence: 99%

Review of aircraft electric power systems and architectures

Zhao

Guerrero

2014

2014 IEEE International Energy Conference (ENERGYCON)

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“…According to the aeronautical standard [28], the maximum allowable DC voltage is 270 V, which cannot be sufficient when a high power is required. In the paper, the investigations shown in the following sections are carried out assuming the possibility to use both the 270 V and the 540 V voltage levels on the DC-link [29,30]. As previous mentioned, the storage system is connected to the DC-link using a DC-DC converter: the use of this converter allows the stabilization on the DC-link also during the performance of electric power-train, when the discharge of currents determines the reduction of output voltage of the battery pack.…”

Section: Optimal Design Of Battery Storage Systemsmentioning

confidence: 99%

Modeling and Investigation of a Turboprop Hybrid Electric Propulsion System

et al. 2018

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Hybrid electric propulsion in the aviation field is becoming an effective alternative propulsion technology with potential advantages, including fuel savings, lower pollution, and reduced noise emission. On the one hand, the aeroengine manufacturers are working to improve fuel consumption and reduce pollutant emissions with new combustion systems; on the other hand, much attention is given to reducing the weight of the batteries increasing the energy density. Hybrid electric propulsion systems (HEPS) can take advantage of the synergy between two technologies by utilizing both internal combustion engines (ICEs) and electric motors (EMs) together, each operating at their respective optimum conditions. In the present work, some numerical investigations were carried out by using a zero-dimensional code able to simulate the flight mission of a turboprop aircraft, comparing fuel consumption and pollutant emissions of the original engine with other two smaller gas turbines working in hybrid configuration. An algorithm has been implemented to calculate the weight of the batteries for the different configurations examined, evaluating the feasibility of the hybrid propulsion system in terms of number of non-revenue passengers.

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“…The MEA will benefit from the reduced maintenance cost and increased reliability by putting more emphasis on the utilization of electrical power instead of hydraulic and pneumatic power. However this trend has a severe impact on aircraft electric power system (EPS) design [1]- [2] and many new paradigms are currently in a focus of engineering studies [3]. One of them assumes the EPS architecture similar to microgrid with multiple-sources and multiple loads connected to the common bus.…”

Section: Introductionmentioning

confidence: 99%

Analysis of droop control methods in DC microgrid

Gao

Gü

Bozhko

et al. 2014

2014 16th European Conference on Power Electronics and Applications

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This paper deals with the droop control of load sharing among multiple sources in DC microgrid. The DC Electrical Power Distribution System (EPDS) with parallel sources are under study in this paper. The voltage-fed and the current-fed paradigms are investigated including the cases when the cable impedances cannot be neglected. Global voltage feedback and local voltage feedback are discussed in terms of currentfed approach. The effect of different methods on the power sharing accuracy is presented. In addition, an enhanced voltage compensation method is proposed for both approaches. The analysis is validated by simulation studies.

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Benefits of higher voltage levels in aircraft electrical power systems

Cited by 60 publications

References 2 publications

Review of aircraft electric power systems and architectures

Review of aircraft electric power systems and architectures

Modeling and Investigation of a Turboprop Hybrid Electric Propulsion System

Analysis of droop control methods in DC microgrid

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