Aircraft Conceptual Design of Commuter Aircraft including Distributed Electric Propulsion

Orefice, Francesco; Nicolosi, Fabrizio; Vecchia, Pierluigi Della; Ciliberti, Danilo

doi:10.2514/6.2020-2627

Cited by 22 publications

(12 citation statements)

References 19 publications

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“…The top-level aircraft requirements provided in the framework of the ELICA project feed the design chain discussed in previous works of the same authors [9][10][11][12]. Additional constraints to the technological level targeting years 2025 and 2035 as possible entrance in service have been fixed by Rolls-Royce driving the weight estimation loop to reliable results.…”

Section: The Challenges Of Electric Aircraftmentioning

confidence: 99%

Design of Hybrid-Electric Small Air Transports

Orefice

Marciello

Nicolosi

et al. 2022

IOP Conf. Ser.: Mater. Sci. Eng.

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The potential benefits of hybrid-electric or full-electric propulsion have led to the proliferation of many concepts over the past decade. The lack of conceptual design methods capable of grasping the effects of the new propulsive technologies is often due to the absence of industrial data supporting the research. In the present work, two objectives are pursued. On the one hand, the introduction of semi-empirical methods for weight estimation based on the data provided by the industrial partners of the ELICA CS2 project. On the other hand, the establishment of generative engineering as a conceptual design tool for propulsive system architecting and fault tolerance analysis. The applications of the proposed conceptual design methods deal with two different years of entrance in service.

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Section: The Challenges Of Electric Aircraftmentioning

confidence: 99%

Design of Hybrid-Electric Small Air Transports

Orefice

Marciello

Nicolosi

et al. 2022

IOP Conf. Ser.: Mater. Sci. Eng.

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“…The project PROSIB, carried out between 2018 and 2021, concerns the study of hybrid-electric propulsion systems applied to commuter aircraft ( [47]) as well as to regional aircraft with both conventional ( [48]) and disruptive architectures.…”

Section: Application To Regional Box-wing Aircraft Designmentioning

confidence: 99%

A DoE-based approach for the implementation of structural surrogate models in the early stage design of box-wing aircraft

Cipolla

Salem

Palaia

et al. 2021

Aerospace Science and Technology

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One of the possible ways to face the challenge of reducing the environmental impact of aviation, without limiting the growth of air transport, is the introduction of more efficient, radically different aircraft architectures. Among these, the box-wing one represents a promising solution, at least in the case of its application to short-to-medium haul aircraft, which, according to the achievement of the H2020 project "PARSIFAL", would bring to a 20% reduction in terms of emitted CO2 per passengerkilometre. The present paper faces the problem of estimating the structural mass of such a disruptive configuration in the early stages of the design, underlining the limitations in this capability of the approaches available by literature and proposing a DoE-based approach to define surrogate models suitable for such purpose. A test case from the project "PARSIFAL" is used for the first conception of the approach, starting from the Finite Element Model parametrization, then followed by the construction of a database of FEM results, hence introducing the regression models and implementing them in an optimization framework. Results achieved are investigated in order to

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“…The adoption of wingtip propellers, counter-rotating with respect to the wingtip vortex, shall increase the aerodynamic efficiency even more. Finally, propulsive efficiency may increase because the thrust is distributed over a larger area [1][2][3][4][5][6].…”

Section: Introductionmentioning

confidence: 99%

“…However, the weight of cables and insulating materials shall not be ignored. Also, the entire powertrain system shall be investigated together with the DEP enabling strategy, since it has been proven that it is convenient to enable the distributed propulsors only in some mission phases like take-off, landing, and/or climb [5][6][7]. It is here remarked that, depending on the electric energy source and powertrain technologies, the aircraft maximum take-off weight may even increase for a given design range.…”

Section: Introductionmentioning

confidence: 99%

“…Even focusing on the aerodynamic aspects only, it is here remarked that the aero-propulsive interaction is not treated by classic preliminary design methods [8][9][10] and not completely captured by recent semi-empirical approaches [2,5,6,11]. For this reason, designers tend to perform numerical analyses also in the conceptual design stage, with the objective to explore many configurations and to develop the most promising.…”

Section: Introductionmentioning

confidence: 99%

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Benchmark of different aerodynamic solvers on wing aero-propulsive interactions

Ciliberti

Bénard

Nicolosi

2022

IOP Conf. Ser.: Mater. Sci. Eng.

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Distributed electric propulsion is a fertile research topic aiming to increase the wing aerodynamic efficiency by distributing the thrust over the wing span. The blowing due to distributed propulsors shall increase the wing lift coefficient for a given planform area and flight speed. This should bring several advantages as wing area, drag, and structural weight reduction, which in turn reduce fuel consumption, allowing airplanes to fly more efficiently. However, there are no consolidated preliminary design methods to size a distributed propulsion system. Numerical analysis is then performed at early stage, where many design variables have not been fixed yet. Therefore, the design space is vast and exploring all the possible combinations is unfeasible. For instance, low-fidelity methods (VLM, panel codes) have a low computational time, but usually they do not account for flow separation and hence they are unable to predict the wing maximum lift. Conversely, high-fidelity codes (CFD) provide more realistic results, but a single drag polar sweep can last days. This work provides a benchmark of different aerodynamic solvers for a typical regional turboprop wing with flaps and distributed propulsion, to better understand the limits of each software in the prediction of aero-propulsive effects.

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Aircraft Conceptual Design of Commuter Aircraft including Distributed Electric Propulsion

Cited by 22 publications

References 19 publications

Design of Hybrid-Electric Small Air Transports

Design of Hybrid-Electric Small Air Transports

A DoE-based approach for the implementation of structural surrogate models in the early stage design of box-wing aircraft

Benchmark of different aerodynamic solvers on wing aero-propulsive interactions

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