A Meta-Model for composite wingbox sizing in aircraft conceptual design

Toffol, Francesco; Ricci, Sergio

doi:10.1016/j.compstruct.2022.116557

Cited by 6 publications

(6 citation statements)

References 29 publications

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“…These issues are faced and overcome by the new NeOPT module, which performs a refined optimization of the wingbox sized by GUESS. This is now possible thanks to the meta-model approach introduced in [39]: it is a semi-analytical description of the wingbox, where the 3D geometrical and physical properties of the component are arranged so that different analysis model can be managed with a single set of information, and the results obtained in one domain can be easily transferred to other domains. The wingbox is represented with higher fidelity without increasing its complexity in terms of the FEM model.…”

Section: Aero-servo-elastic Optimization and Analysis Frameworkmentioning

confidence: 99%

“…One of the features of the meta-model is its interface with NeoANBA, which is a 2D cross-sectional solver that provides the full 6 × 6 beam stiffness matrix of any hollow section composed of isotropic and/or of orthotropic materials. Beyond the fully coupled stiffness matrix, NeoANBA provides the stress distribution of each element for unit loads, and since the method is linear, it is possible to find the cross-sectional stress state for any combination of internal loads obtained with the stick model [39].…”

Section: Aero-servo-elastic Optimization and Analysis Frameworkmentioning

confidence: 99%

“…Figure 6 shows the workflow adopted by NeOPT: the design variables x, described further on, are processed with a finite-element cross-sectional solver (NeoANBA) [38,39], which provides the stiffness and mass matrices of the beam elements describing the wingbox. This solver is based on the ANBA theory [45], where the cross section is modelled with panels (skins and spars) and concentrated area elements (stringers and spar caps).…”

Section: The Mdo Problem Solved In Neoptmentioning

confidence: 99%

“…For this reason, the sizing approach underwent a major revision in recent years. A new optimization module called NeOPT [36][37][38], based on the novel concept of the wingbox meta-model [39], was created and the existing solvers were improved [40], especially the structural model employed to describe the slender structure of composite wings.…”

Section: Introductionmentioning

confidence: 99%

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Preliminary Aero-Elastic Optimization of a Twin-Aisle Long-Haul Aircraft with Increased Aspect Ratio

Toffol

Ricci

2023

Aerospace

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This paper presents a preliminary study on the improvement of the fuel efficiency of a civil transport aircraft, focusing on the aero-elastic optimization of an increased aspect ratio wingbox. The wing is stretched, increasing its aspect ratio, and a trade-off between the improved aerodynamic efficiency and the structural mass identifies an optimal aspect ratio for such aircraft. The aeroelastic optimization is performed with NeOPT, a structural optimizer for conceptual and preliminary design phases. The analysis considers different materials and structural solutions for the wingbox and tackles aeroelastic constraints, such as flutter and aileron efficiency, from the preliminary design phases. The fuel consumption of the sized aircraft is evaluated with a simplified approach that provides an indication of the fuel efficiency. The results show how a composite wing with increased aspect ratio can save up to 6.9% of fuel burnt with respect to the baseline aluminum wing. The results are extended at fleet level, achieving a 2-million-ton cut in CO2 emissions and a saving of USD 1.28 million on fuel-related costs.

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Section: Aero-servo-elastic Optimization and Analysis Frameworkmentioning

confidence: 99%

Section: Aero-servo-elastic Optimization and Analysis Frameworkmentioning

confidence: 99%

Section: The Mdo Problem Solved In Neoptmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Preliminary Aero-Elastic Optimization of a Twin-Aisle Long-Haul Aircraft with Increased Aspect Ratio

Toffol

Ricci

2023

Aerospace

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“…For this reason, in the WP1 of the HERWINGT project, Polimi is involved in the identification of the best wing configuration to be developed in the following of the project, using its in-house developed code NeoCASS [8] [11] and its optimization module NeOPT [13][14] (Figure 1). When dealing with UHARWs, classical fully-stressed approaches may miss some important aeroelastic aspect of such configurations, for example the wing deformation, the divergence and control surfaces effectiveness.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic design and optimization of strut-braced high aspect ratio wings

Toffol

2023

Materials Research Proceedings

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Abstract. To improve aircraft aerodynamic efficiency, a possible solution is to increase the wing aspect ratio to reduce the induced drag term. As a drawback, the span increase introduces an increment of the wing loads, specially of the wing root bending moment that drives the sizing of the wing. Structural mass must be added to withstand higher loads, reducing the aerodynamic advantage from a fuel consumption point of view, as it can be instinctively seen in the Breguet’s range equation. To limit the load increment due to the increased span, a possible solution is the usage of a strut: this kind of structure modifies the load path spanwise, diminishing the wing internal forces and reducing the wing penalty mass. In this framework, a lot of research is done studying Ultra-High Aspect Ratio Strut-Braced Wing, where the aspect ratio of such configuration is exasperated above 15, and the resulting wing is extremely flexible and may experience large deformation under loading. Moreover, the over determined structure realized by the fuselage-wing-strut connections deserves particular attention to fully characterize the aeroelastic interaction among the structural elements. For this reason, a two-step design approach that exploits NeoCASS (GUESS + NeOPT) is used to provide a sizing of the wing and of the strut considering several structural and aeroelastic constraints (e.g. flutter and ailerons effectiveness).

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