Performance Calculation for Hybrid-Electric Aircraft integrating Aero-Propulsive Interactions

Orefice, Francesco; Corcione, Salvatore; Nicolosi, Fabrizio; Ciliberti, Danilo; Rosa, Giuseppe De

doi:10.2514/6.2021-1640

Cited by 9 publications

(9 citation statements)

References 20 publications

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“…Namely a gus turbine can be either tip-or inner-mounted and connected to the electrical motor (EM) cluster through an electric generator (EG) mounted just behind. The number of electrical engines is then depending upon many aspects which are not addressed in this paper but are dealt with in [11]. Also, a hybrid configuration can be conceived where a battery pack is used to feed power to the electric engines to optimize power consumption.…”

Section: Statement Of the Problemmentioning

confidence: 99%

Aeroelastic assessment of distributed electric propulsion wings

Memmolo

Marano

Maio

et al. 2022

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

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During recent years, aircraft manufacturers focused on environmentally friendly and aerodynamically efficient aircraft concepts that could allow a radical reduction of emissions. The use of a hybrid-electric powertrain is one of the most effective ways to design near-zero-emission aircraft. These aircraft are highly performing and sophisticated so the design process must be extremely accurate. Among the various innovative aspects, the use of distributed engines to improve aerodynamic performance poses new challenges from a structural perspective due to the tip-mounted propeller demanding a complicated design due to reduced flutter performance. This results in higher stiffness requirements and consequently increased mass. Both the weight penalty needed to prevent dynamic instability, and the wing aeroelastic tailoring, crucial to minimize such an additional weight, is of utmost importance. Because of setting up a preliminary approach to estimate the static and dynamic effects of such a non-conventional wing architecture, the present paper shows a comprehensive structural analysis of a wing opportunely designed according to certification specification and equipped with a variable position powertrain. Several different engines are then moved along the wingspan to estimate how it affects the dynamic response using a simplified beam-stick finite element model. The results show that the engine position strongly affects the flutter velocity with a particular band bell curve over the wingspan with the maximum in between 60-70% wingspan. In addition, it is worth noting how the tip propeller may cause a reduction of flutter velocity with respect to the conventional configuration with the turbine mounted in between 30-40% wing-span.

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Section: Statement Of the Problemmentioning

confidence: 99%

Aeroelastic assessment of distributed electric propulsion wings

Memmolo

Marano

Maio

et al. 2022

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

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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%

“…In the case of the ELICA project, the serial/parallel partial hybrid electric powertrain seems to be the most promising in terms of flexibility and global efficiency for the configuration considered. This architecture, reported in figure 2, is modelled through the powertrain equations proposed in literature [11,13]. Two propulsive lines are considered.…”

Section: Powertrain Modellingmentioning

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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“…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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Performance Calculation for Hybrid-Electric Aircraft integrating Aero-Propulsive Interactions

Cited by 9 publications

References 20 publications

Aeroelastic assessment of distributed electric propulsion wings

Aeroelastic assessment of distributed electric propulsion wings

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

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