Wing weight model for conceptual design of nonplanar configurations

Andrews, Stephen A.; Perez, Ruben E.; Wowk, Diane

doi:10.1016/j.ast.2015.02.011

Cited by 22 publications

(6 citation statements)

References 23 publications

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“…Distributing the load between the aft and the fore wing in the BW results in a different moment distribution. The box wing has been shown to offer a lower bending moment and shear force which can relieve constraints in the design of multifunctional composites for the skins, spars, stringers and ribs of the wing [62]. In terms of aerodynamics effects, the induced drag can be reduced by up to 20% compared to conventional wings because of the higher aspect ratio and Oswald efficiency [60].…”

Section: Slender Wingsmentioning

confidence: 99%

“…The box wing can be designed to be slightly heavier or lighter than the conventional wing depending on the optimisation parameters. The BW was sized assuming that the aerodynamic load was equally distributed between the fore and the aft wing as per the biplane theory [62]. The two wing surfaces were sized to be of equal surface area, and their total surface area to be equal to that of the conventional wing.…”

Section: Slender Wingsmentioning

confidence: 99%

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Structural Power Performance Targets for Future Electric Aircraft

et al. 2021

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The development of commercial aviation is being driven by the need to improve efficiency and thereby lower emissions. All-electric aircraft present a route to eliminating direct fuel burning emissions, but their development is stifled by the limitations of current battery energy and power densities. Multifunctional structural power composites, which combine load-bearing and energy-storing functions, offer an alternative to higher-energy-density batteries and will potentially enable lighter and safer electric aircraft. This study investigated the feasibility of integrating structural power composites into future electric aircraft and assessed the impact on emissions. Using the Airbus A320 as a platform, three different electric aircraft configurations were designed conceptually, incorporating structural power composites, slender wings and distributed propulsion. The specific energy and power required for the structural power composites were estimated by determining the aircraft mission performance requirements and weight. Compared to a conventional A320, a parallel hybrid-electric A320 with structural power composites >200 Wh/kg could potentially increase fuel efficiency by 15% for a 1500 km mission. For an all-electric A320, structural power composites >400 Wh/kg could halve the specific energy or mass of batteries needed to power a 1000 km flight.

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Section: Slender Wingsmentioning

confidence: 99%

Section: Slender Wingsmentioning

confidence: 99%

Structural Power Performance Targets for Future Electric Aircraft

et al. 2021

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“…• in [23], which is based on a multidisciplinary optimization framework implementing the equivalent beam finite element model described in [24] to evaluate wing mass.…”

Section: State Of the Art Of Box-wing Structural Mass Estimationmentioning

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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“…Various studies have been performed in mass models for conceptual design of conventional wings. Some developed wing mass estimation models for commercial and transport aircraft [2,5] and others for more unconventional configurations, such as nonplannar configurations [6,3,7] or high speed transport [8]. However, very few studies have focused on morphing wings.…”

Section: Introductionmentioning

confidence: 99%