Nonlinear vibrational response of a deformable sandwich structure for morphing wing applications: Modeling, construction, and experimental tests

Abstract

In this paper, we present time-dependent or dynamic behavior of a new flexible sandwich structure that could be employed in morphing aircrafts with the capability to adapt their shape in various flight conditions. In aircrafts with adjustable wings, the deformable section can be regarded as a cantilever beam. Consequently, samples of the proposed sandwich structure are constructed in the form of beam. In this context, the overall design of the structure and its composition are initially outlined. Subsequently, the methodology of performing experimental tests to investigate the dynamic properties of the structure is described, which were assessed through a laser-point speedometer device. In order to attain a flexible and strong sandwich structure, a silicone elastomeric material has been utilized in the structure. Therefore, the performance of the ultimate structure will be nonlinear. In this regard, an extensive study of the mechanical properties of each component of the structure is conducted. Additionally, the finite element method is implemented using the Abaqus software to simulate the samples in accordance with experimental tests. The results obtained from both experimental and numerical methods corroborate the findings of the study.