Hybrid electric distributed propulsion overall aircraft design process and models for general aviation (FAST GA)

Ruscio, Juan Pablo; Jézégou, Joël; Bénard, Emmanuel; Pacheco, Adriana; Laonet, P; Castilla, R Alonso

doi:10.1088/1757-899x/1024/1/012072

Cited by 8 publications

(4 citation statements)

References 3 publications

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“…A design trend on hybrid-electric architectures is to employ the EMs to deliver the additional thrust during takeoff, while the ICE could be reduced in size (Sliwinski et al 2017). Software tools as "FAST-CS25" are employed to evaluate the feasibility of DP architectures (Ruscio et al 2021). The effect of HEP with DP on aircraft performance is studied with the help of a weight estimation method called Class-II, to size the aircraft including aero-propulsive interaction, and to estimate the energy consumption (Hoogreef et al 2019).…”

Section: Developments In Aircraft Design and Systems Integrationmentioning

confidence: 99%

Aircraft Hybrid-Electric Propulsion: Development Trends, Challenges and Opportunities

Rendón

et al. 2021

J Control Autom Electr Syst

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The present work is a survey on aircraft hybrid electric propulsion (HEP) that aims to present state-of-the-art technologies and future tendencies in the following areas: air transport market, hybrid demonstrators, HEP topologies applications, aircraft design, electrical systems for aircraft, energy storage, aircraft internal combustion engines, and management and control strategies. Several changes on aircraft propulsion will occur in the next 30 years, following the aircraft market demand and environmental regulations. Two commercial areas are in evolution, electrical urban air mobility (UAM) and hybrid-electric regional aircraft. The first one is expected to come into service in the next 10 years with small devices. The last one will gradually come into service, starting with small aircraft according to developments in energy storage, fuel cells, aircraft design and hybrid architectures integration. All-electric architecture seems to be more adapted to UAM. Turbo-electric hybrid architecture combined with distributed propulsion and boundary layer ingestion seems to have more success for regional aircraft, attaining environmental goals for 2030 and 2050. Computational models supported by powerful simulation tools will be a key to support research and aircraft HEP design in the coming years. Brazilian research in these challenging areas is in the beginning, and a multidisciplinary collaboration will be critical for success in the next few years.

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Section: Developments In Aircraft Design and Systems Integrationmentioning

confidence: 99%

Aircraft Hybrid-Electric Propulsion: Development Trends, Challenges and Opportunities

Rendón

et al. 2021

J Control Autom Electr Syst

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“…The program is an open-source tool for aircraft sizing and optimization, developed since 2015 by ISAE-SUPAERO and ONERA. [12][13][14] [15] To effectively apply optimization methods and explore the wide space of variables in which we can search for new aircraft configurations, tools for the automatic modelling of aircraft external geometry are essential. A typical solution providing such capabilities is OpenVSP.…”

Section: Introductionmentioning

confidence: 99%

Parametric model of aircraft external geometry as a component of FAST-OAD aircraft preliminary design system.

Grendysa

Jézégou

Bénard

2023

J. Phys.: Conf. Ser.

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Rapid evolutions in fields such as aerospace propulsion, materials engineering, geometry modelling tools or optimization tools provide the opportunity to search for novel configurations of future aircraft in an expanding domain. In order to effectively explore the space of variables of constantly expanding size, one needs tools that give the ability to automate this process. Such a tool is the Future Aircraft Sizing Tool for Overall Aircraft Design or FAST-OAD. FAST-OAD allows for rapid estimation of aircraft size, based on set, so-called Top Level Aircraft Requirements (TLARs) by using multi-disciplinary and multi-fidelity analysis and optimization. An essential component of such a system is a module capable of modelling the external geometry of the calculated case. This article describes an attempt to use a powerful commercial Computer Aided Design software, Siemens NX, to model the aircraft external geometry based on the results of the analysis performed by FAST-OAD. This approach, compared to previous works, brings some limitations but, on the other hand, gives the possibility to base the geometry on a mathematically consistent model and helps to better understand the set of parameters necessary to describe the geometry correctly. The main objective of this research is to provide a tool that allows the automatic generation of aircraft exterior geometry based on the output parameters received from the FAST-OAD package. An additional goal of this activity is to determine the parameter set necessary to properly define the external geometry, but at the same time not containing redundant, dependent geometric parameters. The minimum number of independent parameters necessary to completely describe the external geometry is sought.

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“…For weight estimation of high aspect ratio wings, analytical formulations based on beam and material strength theories have proven to better perform than statistical models with a similar computational cost [5]. These methods have been implemented into the preliminary design tool FAST-OAD [6](jointly developed by ONERA and ISAE-SUPAERO) and tested on a general aviation distributed propulsion concept [7]. Here, the developments are extended to commercial transport aircraft with strut-braced wings.…”

Section: Introductionmentioning

confidence: 99%

Multi-fidelity weight analyses for high aspect ratio strut-braced wings preliminary design

Delavenne

Bénard

Defoort

et al. 2022

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

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In the wake of ”flygskam” movement that emerged in Sweden a couple of years ago many voices recently raised denounce the environmental footprint of aviation. Even if the real impact of the sector could appear rather limited the critics reveal the necessity to propose cleaner aircraft to both meet public expectations and environmental goals. Because the classical wing-tube configuration seems to have reached its limits, disruptive designs must be considered. Among the perspectives to reduce emissions, high-aspect ratio wings represent a promising path to be explored within the European CleanSky2 project U-HARWARD. Indeed, substantial diminution of induced drag are expected from those new configurations resulting in fewer fuel consumption. To achieve high-aspect ratio without compromising the structural weight strut can be introduced. They allow for an alleviation of the bending moment at the wing root and therefore lighter structures. However, the consideration of those new wing configuration at early design stages is not straightforward and new methods have to be introduced. In this paper, we present three different fidelity approaches to tackle with (ultra) high-aspect ratio strut-braced wings sizing and weight estimation in preliminary design context. Already existing analytical formulations for the wings are extended, intermediate fidelity aero-structural coupling has been developed and high-fidelity structural representation are considered. Depending on the maturity of the concept these methods could be used to explore the design space, to refine the optimum or to analyse the final concept. Validation with respect to reference configurations is provided. Then the methods are applied to the analysis of strut-braced wings.

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Hybrid electric distributed propulsion overall aircraft design process and models for general aviation (FAST GA)

Cited by 8 publications

References 3 publications

Aircraft Hybrid-Electric Propulsion: Development Trends, Challenges and Opportunities

Aircraft Hybrid-Electric Propulsion: Development Trends, Challenges and Opportunities

Parametric model of aircraft external geometry as a component of FAST-OAD aircraft preliminary design system.

Multi-fidelity weight analyses for high aspect ratio strut-braced wings preliminary design

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