Aeroelastic method to investigate nonlinear elastic wing structures

Bramsiepe, Kjell; Klimmek, Thomas; Krüger, Wolf R.; Tichy, Lorenz

doi:10.1007/s13272-022-00596-0

Cited by 4 publications

(9 citation statements)

References 10 publications

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“…The structural model is accurate up to a beam deflection of approximately 15%, but the modeling error increases for larger deflections due to the neglect of geometric nonlinearities [28]. For the reference wing, the relative wingtip deflection in the 2.5 g maneuver is 2.0% with respect to the semi-span.…”

Section: Results Of the Aeroelastic Analysismentioning

confidence: 99%

“…Degressive stiffness is beneficial to maintain the straight wing shape in cruise while achieving high load alleviation potential at elevated loads. Therefore, degressive stiffness is also the focus of other load alleviation concepts in the literature, which investigate degressive-stiffness wings [31,32] or aeroelastic hinges with nonlinear spring stiffnesses [33,34].…”

Section: Discussionmentioning

confidence: 99%

“…For the latter, the VLM implemented in the Loads Kernel tool is used [26,27]. The structural analysis is performed with beam elements implemented in a Python routine, which was verified with MSC.Nastran [28].…”

Section: Aeroelastic Modelmentioning

confidence: 99%

“…The actuator can be operated in a passive or active mode, where in active mode the stiffness is reduced with increasing loads. The structural model of the wing consists of a beam structure instead of a high-fidelity model with shell elements to reduce the modeling effort of new technologies [28]. Figure 5 illustrates a concept sketch of the structural elements used in the aeroelastic model.…”

Section: Aeroelastic Modelmentioning

confidence: 99%

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Aeroelastic Analysis of Actuated Adaptive Wingtips Based on Pressure-Actuated Cellular Structures

Meyer

Hühne

Bramsiepe

et al. 2023

AIAA SCITECH 2023 Forum

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Folding wingtips are in the focus of research for their potential to counteract the challenges posed by high aspect ratio wings, such as airport conformity and increased wing root bending moment. Existing concepts for in-flight folding and morphing wingtips either enable passive load alleviation by adding free-flapping aeroelastic hinges to the wingtips or allow for advanced flight control and mission adaptability by actively deflecting the wingtips. In contrast, actuated adaptive wingtips combine the functionalities of passive and active in-flight folding wingtips by using a stiffness-adaptive aeroelastic hinge that is actively adjustable in flight. The objective of this paper is the aeroelastic analysis of a wing equipped with an adaptive-stiffness hinge. While the structural design of the wingtip actuator based on pressure-actuated cellular structures (PACS) was developed in a previous study, in this study the authors verify the concept of actuated adaptive wingtips through aeroelastic analysis. The aeroelastic model consists of a reduced beam structure coupled with the vortex lattice method. In the structural model, the PACS-based adaptive-stiffness hinge is implemented as an equivalent beam element and a pair of counteracting moments. This study shows that the investigated PACS actuator, which is structurally designed from glass-fiber reinforced plastic, is capable of bearing the loads acting on the wingtips of a Cessna Citation X. The adaptive-stiffness hinge, positioned between 86.7% and 91.2% of the semi-span, reduces the wing root bending moment by up to 7.8% in a 2.5 g maneuver load case, while keeping the wing straight in cruise. A further increase in load alleviation potential can be achieved in the future by extending the actuator's operating envelope and thus increasing its load-bearing capacity so that the actuator can be positioned more inboard. The functional verification of the actuated adaptive wingtip concept by means of aeroelastic analysis forms the basis for the manufacturing and testing of a functional prototype.

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Section: Results Of the Aeroelastic Analysismentioning

confidence: 99%

Section: Discussionmentioning

confidence: 99%

Section: Aeroelastic Modelmentioning

confidence: 99%

Section: Aeroelastic Modelmentioning

confidence: 99%

See 2 more Smart Citations

Aeroelastic Analysis of Actuated Adaptive Wingtips Based on Pressure-Actuated Cellular Structures

Meyer

Hühne

Bramsiepe

et al. 2023

AIAA SCITECH 2023 Forum

Self Cite

View full text Add to dashboard Cite

show abstract

“…For the latter, the VLM implemented in the Loads Kernel tool is used [24,25]. The structural analysis is performed with beam elements implemented in a Python routine, which was verified with MSC.Nastran [26].…”

Section: Aeroelastic Modelmentioning

confidence: 99%

Aeroelastic Analysis of Actuated Adaptive Wingtips Based on Pressure Actuation

Meyer,

Hühne,

Bramsiepe

et al. 2024

Journal of Aircraft

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Folding wingtips address the challenges posed by high-aspect-ratio wings, such as airport conformity and increased wing root bending moment. Actuated adaptive wingtips extend the functionalities of folding wingtips by using a stiffness-adaptive aeroelastic hinge that is actively adjustable in flight. The objective of this paper is the aeroelastic analysis of a wing equipped with an adaptive-stiffness hinge. While the structural design of the wingtip actuator based on pressure-actuated cellular structures (PACS) was developed in a previous study, in this study the authors verify the concept of actuated adaptive wingtips through aeroelastic analysis. This study shows that the investigated PACS actuator, structurally designed from glass-fiber-reinforced plastic, is capable of bearing the loads acting on the wingtips of a Cessna Citation X. The adaptive-stiffness hinge, positioned between 86.7 and 91.2% of the semispan, reduces the wing root bending moment by up to 7.8% in a 2.5[Formula: see text] maneuver load case, while keeping the wing straight in cruise. A further increase in load alleviation potential can be achieved in the future by extending the actuator’s operating envelope and thus increasing its load-bearing capacity. The functional verification of the actuated adaptive wingtip concept by means of aeroelastic analysis forms the basis for the manufacturing and testing of a functional prototype.

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Investigation of Hybrid Laminar Flow Control Capabilities from the Flight Envelope Perspective

Karpuk,

Mosca

2024

Journal of Aircraft

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The present work conducts a multifidelity aerodynamic design of a medium-range commercial aircraft wing featuring hybrid laminar flow control (HLFC) technology. The design was performed to investigate the capabilities of the HLFC, considering the entire design flight envelope, low-speed performance requirements, and various potential mission scenarios. A combination of medium-fidelity aerodynamic design tools for laminar flow control using MSES-COCO-LILO, CFD RANS for high-lift cases, the quasi-three-dimensional for database generations, and SUAVE for mission analysis were used to design and assess aircraft’s performance with the HLFC wing. Studies of the design objective demonstrated a conflict between friction and compressibility drag that strongly affects the design objective function and the wing performance at various off-design conditions. A strong dependence of HLFC on flight conditions was observed to indicate technology performance limitations and a tradeoff between airplane emissions, range, and costs. Finally, a comparison of medium- and low-fidelity performance results showed deviations in the design fuel burn of 4%, a minimum possible harmonic range difference of 3%, and direct operating costs of 2%. The outcome suggests the need for better compressibility and parasite drag models for early design stages to accurately model the HLFC technology without introducing complicated methods at the first sizing steps.

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Aeroelastic method to investigate nonlinear elastic wing structures

Cited by 4 publications

References 10 publications

Aeroelastic Analysis of Actuated Adaptive Wingtips Based on Pressure-Actuated Cellular Structures

Aeroelastic Analysis of Actuated Adaptive Wingtips Based on Pressure-Actuated Cellular Structures

Aeroelastic Analysis of Actuated Adaptive Wingtips Based on Pressure Actuation

Investigation of Hybrid Laminar Flow Control Capabilities from the Flight Envelope Perspective

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