Sizing of the energy storage system of hybrid-electric aircraft in general aviation

Geiß, Ingmar; Voit-Nitschmann, R.

doi:10.1007/s13272-016-0220-5

Cited by 25 publications

(13 citation statements)

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“…Considering that the trust vector is parallel to the climb trajectory, the variation of the climb angle during the flight is negligible, and taking into account the dynamic Equation (A4), the duration of the climb [22] can be calculated by integrating the following equations:…”

Section: Climb Phase Dynamics Equationmentioning

confidence: 99%

“…The problem is solved by the optimization of three different objective functions related to the energy cost, which is the primary energy required in order to guarantee flight completion and the reduction of CO 2 emissions. In [22], the size of the hybrid storage system which is constituted by supercapacitors and batteries is optimized and the objective function is inherent to the reduction of the total mass of the primary energy. In [13], a simple conceptual design approach is proposed to determine the optimal size of the battery system in order to maximize the range or duration of the flight for the available fuel in the aircraft's tank.…”

Section: Introductionmentioning

confidence: 99%

“…In [13], a simple conceptual design approach is proposed to determine the optimal size of the battery system in order to maximize the range or duration of the flight for the available fuel in the aircraft's tank. In [22,23], a sizing tool for reducing the global storage system's weight by taking several constraints (environmental and electrical ones) into account and by adjusting some parameters-such as the discharge ratio of the storage components and the ambient temperature-within a proper energy management strategy was proposed. The sizing method was improved upon with an optimization algorithm solved by a simulated annealing method.…”

Section: Introductionmentioning

confidence: 99%

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Optimization of the Energy Storage of Series-Hybrid Propelled Aircraft by Means of Integer Differential Evolution

2019

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The possibility of realizing full electric or hybrid electric propulsion for aircraft has been considered due to the constant growth in the use of electric technologies in aircraft and the availability of high-power-density electrical machines and converters. In this paper, an optimized design approach is proposed with reference to the optimal trade-off between energy storage system sizing and the fuel mass of a series of hybrid aircraft. The problem is approached using an integer optimization algorithm based on differential evolution and by mixing both the flight mechanics and the electrical issues inherent to hybrid flights. This method has been validated by means of implementing numerical simulations and the results are reported and discussed in the paper.

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Section: Climb Phase Dynamics Equationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Optimization of the Energy Storage of Series-Hybrid Propelled Aircraft by Means of Integer Differential Evolution

2019

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“…Therefore, if the use case for an electric-hybrid aircraft includes mainly short flights then carrying battery capacity can be beneficial for the overall (primary) energy consumption. 2 If, however, the use case involves higher flight ranges and/or high cruise speeds, only a small fraction of the energy needed for flight can be covered by the battery. In this case, the advantage of using electric energy from batteries for cruise flight is overcompensated by the disadvantage of the increased weight of the aircraft due to the large battery system.…”

Section: Why Go Hybrid?mentioning

confidence: 99%

Sizing of fuel-based energy systems for electric aircraft

Geiß

Voit-Nitschmann²

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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Optimized electric motors are lighter and smaller than conventional piston engines. As a result, new airplane configurations are feasible as motors can be placed in unconventional positions. Through careful aircraft design higher aerodynamic efficiencies of airframe, propeller, and propeller integration can be achieved. The energy density of current batteries, however, still limits strongly the range of purely battery powered aircraft. But if the energy is stored in liquid fuel and converted by a generator into electric energy, then the advantages of electric propelled airplanes and conventional combustion engines can be combined. But which combustion engine is optimal for such a serial-hybrid electric aircraft? In this new propulsion chain, other boundary conditions apply to the combustion engine than in conventional aircraft designs. These boundary conditions interact with the characteristics of combustion engines. An example for an engine characteristic is that different kinds of piston engines exist. It can be observed that technologies, which result in lighter piston engines, are associated with lower efficiencies and vice versa. In this paper it will be shown through considerations on aircraft level, that the optimal combustion engine for an electric-hybrid airplane should be heavier and more efficient than the optimal combustion engine for a conventional aircraft.

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“…There has been a surge in research related to (hybrid-) electric propulsion (HEP) over the past decade, since this technology has the potential to reduce the energy consumption and in-flight emissions of commercial aircraft and, therefore, to bring the aviation sector closer to the sustainability targets established by the European Commission [1] and NASA [2]. Previous studies have shown that hybrid-electric [3,4] and fully-electric [5] general-aviation aircraft can lead to a reduction in both emissions and operating costs for short ranges, when compared to fuel-based alternatives.…”

Section: Introductionmentioning

confidence: 99%