Abstract:The use of pressure-actuated cellular structures (PACS) is an effective approach for the application of compliant mechanisms. Analogous to the model in nature, the Venus flytrap, they are made of discrete pressure-activated rows and can be deformed with high stiffness at a high deformation rate. In previous work, a new innovative approach in their integral textile-based manufacturing has been demonstrated based on the weaving technique. In this work, the theoretical and experimental work on the further develop… Show more
“…The next step in realizing PACS-based actuated adaptive wingtips is the experimental proof with a functional prototype. Ongoing research investigates the integral textile manufacturing of PACS from woven glass-fiber reinforced plastic [35,36]. The integral manufacturing of single-row cellular structures was successfully demonstrated by the authors [35].…”
Section: Discussionmentioning
confidence: 99%
“…However, PACS actuators allowing for adaptive stiffness and active deflection require two antagonistic rows of cells. The extension of the weaving process to more complex double-row cellular structures is part of current work [36]. Considering manufacturing-specific constraints in the design process is essential for the successful realization of PACS actuators with high load-bearing capacity.…”
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.
“…The next step in realizing PACS-based actuated adaptive wingtips is the experimental proof with a functional prototype. Ongoing research investigates the integral textile manufacturing of PACS from woven glass-fiber reinforced plastic [35,36]. The integral manufacturing of single-row cellular structures was successfully demonstrated by the authors [35].…”
Section: Discussionmentioning
confidence: 99%
“…However, PACS actuators allowing for adaptive stiffness and active deflection require two antagonistic rows of cells. The extension of the weaving process to more complex double-row cellular structures is part of current work [36]. Considering manufacturing-specific constraints in the design process is essential for the successful realization of PACS actuators with high load-bearing capacity.…”
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.
“…Thus, they constitute primary load-bearing structural composites at their web-flange junction, which is mainly considered a critical area and ought to be highly reliable. [5][6][7][8][9] The boltless composite joining is one of the important challenges in the aerospace and automotive industry. [10] Although conventional mechanical joining has been optimized, it introduces extra weight due to increased thickness at the assembled component's junction point near the bolts and the additional weight of bolts.…”
Section: Introductionmentioning
confidence: 99%
“…Thus, they constitute primary load‐bearing structural composites at their web‐flange junction, which is mainly considered a critical area and ought to be highly reliable. [ 5–9 ]…”
The woven profiled structures and their composites are beneficial for automobiles specifically E‐vehicles due to near‐net‐shape manufacturing, snug‐fitting, and lightweight. This study reported the junction strength of 3D integrally woven, and stitched profile structures such as L, U, +, ±, T, Pi, and H produced using high‐strength polyester yarn and their composites. The junction strength of integrally woven profiles and their composites was higher than that of stitched profiles. The stitched profile composites failed at the stitch line mainly due to delamination, leading to incomplete reinforcement strength realization. However, the integrally woven profile composites fail due to fracture of yarns within the reinforcement, leading to higher junction strength.
“…The warp is along the length and the weft is along the width of the fabric. Individual warp and weft yarns are called the ends and picks [ 4 ]. The interlacement of the ends and picks with each other produces a coherent and stable structure.…”
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