Multidisciplinary aircraft integration within a collaborative and distributed design framework using the AGILE paradigm

Fioriti, Marco; Boggero, Luca; Prakasha, Prajwal S.; Mirzoyan, Artur; Aigner, Benedikt; Anisimov, Kirill

doi:10.1016/j.paerosci.2020.100648

Cited by 15 publications

(13 citation statements)

References 10 publications

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“…The two versions of the BWB were designed to operate at a cruise Mach of 0.85, for a maximum range of 8500 km, and carrying 450 passengers. Also, in this case, the main results suggested that Similarly, but with more advanced computational tools, a collaborative framework (AGILE [253,254]) among several institutes has designed two versions of the BWB configuration (see Figure 64). The goal of the AGILE innovation project is to prove a 40% speed-up in addressing realistic MDO issues when compared to the current state-of-the-art [255,256].…”

Section: The Blended Wing Body Configurationmentioning

confidence: 95%

“…The results highlighted that the fuel burn rate was reduced by approximately 7%, from the podded BWB to the BLI BWB configuration; furthermore, reductions of about 5% were obtained for the drag coefficient, whereas the distortion index was enhanced by 2%. Similarly, but with more advanced computational tools, a collaborative framework (AGILE [253,254]) among several institutes has designed two versions of the BWB configuration (see Figure 64). The goal of the AGILE innovation project is to prove a 40% speed-up in addressing realistic MDO issues when compared to the current state-of-theart [255,256].…”

Section: The Blended Wing Body Configurationmentioning

confidence: 99%

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A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

Abu Salem,

Palaia,

Bravo-Mosquera

et al. 2024

Designs

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The aim of this review paper is to collect and discuss the most relevant and updated contributions in the literature regarding studies on new or non-conventional technologies for propulsion–airframe integration. Specifically, the focus is given to both evolutionary technologies, such as ultra-high bypass ratio turbofan engines, and breakthrough propulsive concepts, represented in this frame by boundary layer ingestion engines and distributed propulsion architectures. The discussion focuses mainly on the integration effects of these propulsion technologies, with the aim of defining performance interactions with the overall aircraft, in terms of aerodynamic, propulsive, operating and mission performance. Hence, this work aims to analyse these technologies from a general perspective, related to the effects they have on overall aircraft design and performance, primarily considering the fuel consumption as a main metric. Potential advantages but also possible drawbacks or detected showstoppers are proposed and discussed with the aim of providing as broad a framework as possible for the aircraft design development roadmap for these emerging propulsive technologies.

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Section: The Blended Wing Body Configurationmentioning

confidence: 95%

Section: The Blended Wing Body Configurationmentioning

confidence: 99%

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

Abu Salem,

Palaia,

Bravo-Mosquera

et al. 2024

Designs

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“…Four different OBS architectures have been modelled, named: i) C (conventional) ii) MEA1(more electric aircraft 1) iii) MEA2 (more electric aircraft 2) and iv) AEA (all electric aircraft). A description of these architectures can be found in [8] and [9]. The tool provides the masses and the hydraulic, pneumatic, and electric power required by each system during the different phases of the mission profile.…”

Section: Aerodynamics and Aero Rsmmentioning

confidence: 99%

Multidisciplinary Design and Optimization of Regional Jet Retrofitting Activity

Mandorino

Vecchia

Corcione

et al. 2022

AIAA AVIATION 2022 Forum

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A retrofit analysis on a 90 passengers regional jet aircraft is performed through a multidisciplinary collaborative aircraft design and optimization highlighting the impact on costs and performance. Two different activities are accounted for selecting the best aircraft retrofit solution: a re-engining operation that allows to substitute a conventional power-plant platform with advanced geared turbofan and an on-board-systems architecture modernization, considering different levels of electrification. Besides the variables that are directly dependent from these activities, also scenario variables are considered during the optimization such as the fuel price, the fleet size and the years of utilization of the upgraded systems. The optimization is led by impacts of the retrofitting process on emissions, capital

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“…The aircraft design is a collaborative and multidisciplinary process. It involves several experts with different disciplinary competences that often belong to different departments or organizations, such as developing a new generation of multidisciplinary design analysis and optimization (MDAO) frameworks for aircraft design [5]. The design of an aircraft goes through an initial phase of conceptual design in which the requirements requested by customers are considered: technological level, size of the aircraft, appropriate engines, airworthiness; comprehensive solutions in the form of schemes where aspects such as practical knowledge, production methods, and commercial scope have great relevance [6], [7].…”

Section: Introductionmentioning

confidence: 99%

Control surface design for radio-controlled aircraft. Case: SAE Aero Design Micro-class prototype

Márquez¹,

Martínez²,

Martínez³

2021

Rev.Fac.Ing.Univ.Antioquia

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This research article presents a design methodology for primary control surfaces (Ailerons, Rudder and Elevator) for experimental unmanned radio-controlled aircraft. The methodology is based on the proposal and standardization of the required mechanical and aerodynamic analysis for each control surface sizing, considering the SAE Aero Design competition objectives within Micro Class. It is used on empirical results previously described in references about aeronautical design, computerized fluids dynamics (CFD) software, and aircraft controllability regulations in order to obtain the design variables. Based on this information, the iteration sequences required for design were automated by a C++ language code to obtain the optimal characteristics for each surface, thereby reducing the possibility of calculation errors, overall time, and workload invested in the design process. The application of the methodology to the latest aircraft design reduced the total control systems weight to the aircraft’s empty weight ratio to a minimum of 3.4%.

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Multidisciplinary aircraft integration within a collaborative and distributed design framework using the AGILE paradigm

Cited by 15 publications

References 10 publications

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

Multidisciplinary Design and Optimization of Regional Jet Retrofitting Activity

Control surface design for radio-controlled aircraft. Case: SAE Aero Design Micro-class prototype

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