Development of a Multi-fidelity Design, Analysis, and Optimization Environment for Future Transport Aircraft

Karpuk, Stanislav; Mosca, Valerio; Liu, Chuanzhen; Elham, Ali

doi:10.2514/6.2022-0686

Cited by 8 publications

(4 citation statements)

References 25 publications

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“…The study of the aeromechanical features of a commercial aircraft can be approached on different levels with the use of tools and methods of different fidelity [53][54][55][56]. Depending on the study to be carried out, and on the maturity of the design process, there are appropriate choices that allow for optimising the trade-off between the reliability of the numerical results and the computational cost/time [57][58][59][60][61]. In this context, Table 1 briefly summarises the characteristics of a set of different fidelity methods that can be used to characterise the aerodynamic derivatives of typical commercial aircraft.…”

Section: Methodology Descriptionmentioning

confidence: 99%

Preliminary Analysis of the Stability and Controllability of a Box-Wing Aircraft Configuration

Abu Salem,

Palaia,

Quarta

et al. 2023

Aerospace

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This paper presents a study on the aeromechanical characteristics of a box-wing aircraft configuration with a focus on stability, controllability, and the impact of aeromechanical constraints on the lifting system conceptual design. In the last decade, the box-wing concept has been the subject of several investigations in the aeronautical scientific community, as it has the potential to improve classic aerodynamic performance, aiming at reducing fuel consumption per unit of payload transported, and thus contributing to a reduction in aviation greenhouse emissions. This study characterises the aeromechanical features of a box-wing aircraft, with a specific focus on the correlations between the aeromechanical constraints and the (main) aircraft design parameters. The proposed approach provides specific insights into the aeromechanical characteristics of the box-wing concept, both in the longitudinal and lateral plane, which are useful to define some overall design criteria generally applicable when dealing with the conceptual design of such an unconventional aircraft configuration.

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Section: Methodology Descriptionmentioning

confidence: 99%

Preliminary Analysis of the Stability and Controllability of a Box-Wing Aircraft Configuration

Abu Salem,

Palaia,

Quarta

et al. 2023

Aerospace

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“…As an open-source tool, it enables the usage and improvement of existing methods and the implementation of new ones. Karpuk et al [4] have developed an initial sizing framework for a conventional aircraft with combustion engines, using SUAVE as a standalone sizing tool. However, SUAVE is mainly used as a mission solver.…”

Section: Introductionmentioning

confidence: 99%

Preliminary hybrid-electric aircraft design with advancements on the open-source tool SUAVE

Mangold¹,

Eisenhut²,

Brenner³

et al. 2023

J. Phys.: Conf. Ser.

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The large variety of possible propulsion architectures for environmentally friendly and sustainable aircraft concepts create opportunities for the overall aircraft design. In particular, hybrid-electric aircraft have an increased number of additional components that must be implemented in the aircraft design tool. Primary and secondary energy sources can be used to achieve the necessary reduction in emissions. The preliminary aircraft design tool SUAVE offers the basic setup necessary to integrate the electrification of the propulsion system into the aircraft design. For this purpose, SUAVE has been extended to enable an iterative sizing loop for hybrid-electric aircraft. Hence, many propulsion architectures are easily adaptable. Additional components can be included and their interactions are considered. Furthermore, the fidelity levels of the models are modifiable. Moreover, the top-level aircraft requirements are transformed into a sizing chart to calculate the necessary power and wing loading. Thereby, a reasonable hybridization factor of installed power can be identified. This definition of hybridization implies a specific energy management strategy. As a result, hybridization and the energy management strategy are directly coupled and have to be considered together. Finally, in the postprocessing, the raw data is processed and can be evaluated with figures of merit. This procedure converts the results into a descriptive value and facilitates the comparison to other configurations. The figures of merit include evaluations for emissions, operational aspects and development costs and effort.

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“…High-fidelity analysis becomes a relevant approach when the basic parameters are available and aircraft components need to be improved for specific effects. However, this solution implies high computational power and cost (for a complete overview of the fidelity layers, see [18]).…”

Section: Introductionmentioning

confidence: 99%

Investigations on the Potentials of Novel Technologies for Aircraft Fuel Burn Reduction through Aerostructural Optimisation

Mosca

Elham

2022

Aerospace

Self Cite

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A physics-based optimisation framework is developed to investigate the potential advantages of novel technologies on the energy efficiency of a midrange passenger aircraft. In particular, the coupled-adjoint aerostructural analysis and optimisation tool FEMWET is modified to study the effects of active flow control at different load cases for conventional and unconventional wing configurations. This multidisciplinary design optimisation (MDO) framework presents the opportunity to optimise the wing considering static aeroelastic effect and, by its gradient-based method, save substantial computational time compared to high-fidelity tools, keeping a satisfying level of accuracy. Two different configurations are analysed: a forward- and backward-swept wing aircraft, developed inside the Cluster of Excellence SE2A (Sustainable and Energy-Efficient Aviation). The forward-swept configuration is sensitive to the aeroelastic stability effect, and the backward configuration is influenced by the aileron constraint. They may lead to a weight increment. Sensitivity studies show the possible role of key parameters on the optimisation results. The highest fuel weight reduction achievable for the two configurations is 5.6% for the forward-swept wing and 9.8% for the backward configuration. Finally, both optimised wings show higher flexibility.

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Development of a Multi-fidelity Design, Analysis, and Optimization Environment for Future Transport Aircraft

Cited by 8 publications

References 25 publications

Preliminary Analysis of the Stability and Controllability of a Box-Wing Aircraft Configuration

Preliminary Analysis of the Stability and Controllability of a Box-Wing Aircraft Configuration

Preliminary hybrid-electric aircraft design with advancements on the open-source tool SUAVE

Investigations on the Potentials of Novel Technologies for Aircraft Fuel Burn Reduction through Aerostructural Optimisation

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