Abstract
To effectively reduce or eliminate the warping deformation of the slat trailing edge, the prebending design is widely used. However, excessive bending of the slate trailing edge may cause the structure to stick when the slat is retracted, thereby affecting the aerodynamic performance of the aircraft. There is a strong motivation for modeling and analysis of a prebending leading-edge slat. First, the rigid–flexible coupling theory model is established in this paper. Second, a rigid–flexible simulation of a leading-edge slat is carried out based on multibody dynamics and finite element analysis; Besides, the dynamic response properties of the leading-edge slat under multifactor coupling working conditions are obtained. Finally, the influences of the driving speed and prebending angle on the slat retraction are analyzed. The results of this study may help to provide a reference for the evaluation and optimization of the leading-edge slat’s retractability.
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