Analysis of Wing Morphing via Frame Buckling

Phani, A. Srikantha; Butler, Richard; Habgood, Stephen; Bowen, Christopher R.

doi:10.2514/6.2008-1792

Cited by 4 publications

(2 citation statements)

References 4 publications

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“…Taking this concept to its extreme consequences, the designer could also conceive the structure operating in the flight envelope at the limit of the conditions of structural instability, keeping in mind that no permanent deformations are allowed inside it. On the other hand, some recent development looking at future aircrafts is exploring solutions exploiting local structural instabilities for aircraft specific operational purposes (such as the morphing solutions reported in Gano et al, 2003;Ursache et al, 2004;Barrett et al, 2005;Vos et al, 2007;Phani et al, 2008;Kuder et al, 2013).…”

Section: Relevance Of Results In the Design Of Aeronautic Structuresmentioning

confidence: 99%

Buckling Behavior of Poly-Phenylene-Sulfide/Carbon L-Shaped Stringers and a Stiffened Panel Obtained by Induction Welding

Scarselli

Pappadà²,

Buccoliero

et al. 2020

Front. Mater.

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Although the high performance thermoplastics matrix composites have been studied for more than 30 years, only recently their advantages have been properly perceived and exploited, for a wide range of applications either in secondary either in primary aeronautical structures. In this work, compression testing of a flat panel stiffened with L-shaped stringers made of poly-phenylene-sulfide (PPS) matrix reinforced with carbon fibers is presented. The stiffeners were joined to the base plate by induction welding, as reported in a former study. The numerical activities, aimed at static, buckling and postbuckling analysis, first of a single stringer, then of the stiffened panel under compressive load, provided results in good agreement with the experimental ones. The analyses were performed taking into account either for the geometric non-linearity associated with the large deformations of the structures under the action of compressive loads either for the local buckling of the flanges composing the stringers. Experimental activities were aimed at the characterization of the adopted materials with a special focus on the determination of buckling loads either of an L-shaped stringer either of a panel stiffened with four stingers. In both cases, an excellent structural behavior was shown, the panel and a single stringer being able to take huge loads after the first buckling appeared. The panel, in particular, showed an excellent post-buckling strength and broke by buckling failure of stringers. The welded interfaces did not fail indicating that thermoplastic welding is a suitable technique for assembly composite structural elements.

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Section: Relevance Of Results In the Design Of Aeronautic Structuresmentioning

confidence: 99%

Buckling Behavior of Poly-Phenylene-Sulfide/Carbon L-Shaped Stringers and a Stiffened Panel Obtained by Induction Welding

Scarselli

Pappadà²,

Buccoliero

et al. 2020

Front. Mater.

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“…With the use of flexible wings, the structure deformation cannot be ignored, the rigid body models cannot meet the requirement of accuracy, and scholars tend to build flexible multibody model for morphing aircraft. Phani et al 10 modeled the morphing aircraft via buckling of structures in multi-element structural components. Snyder et al 11 investigated the vibration and flutter instabilities during the wing’s folding by finite element method.…”

Section: Introductionmentioning

confidence: 99%

Equivalent dynamic modeling of flexible morphing aircraft

Wei

Wang

Zheng³

et al. 2021

Science Progress

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A morphing aircraft can maintain optimal flight performance by adaptively changing shape. However, large deformation and fast motion of aircraft modules lead to complicated dynamics during morphing process. This paper proposes a mechanistic equivalent model with parameters identified by optimization method. Based on the dynamics of the aircraft modules with large deformation and fast motion and considering the coupling characteristics of rigid bodies and gimbal joints, an equivalent dynamic model of morphing aircraft is built in this study. Considering the huge amount of highly coupled parameters in the equivalent model, particle swarm optimization algorithm is used to identify the equivalent parameters based on the sample data of flexible model. By comparing the simulation results of proposed model to those of rigid model and flexible model, it can be seen that the accuracy of the proposed equivalent model is comparable to that of the flexible model, but the computational load is only 10% of that of flexible model. Further, based on this high-fidelity model with low computational load, an optimized morphing process is obtained, and the attitude variation during morphing is reduced by 4.23%.

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