基于干涉接触的前缘缝翼尾缘结构设计与分析

The leading edge slat is an important lift increasing device in the take-off and landing stages of large aircraft. But affected by its own body stiffness and support stiffness, the slat is prone to warpage and deformation under aerodynamic load, resulting in gaps with the wing box, which affects the aerodynamic efficiency of the wing. To eliminate the deformation of slat in cruise and improve the aerodynamic efficiency of the wing, the leading edge slat interference trailing edge structural design technology is proposed in this paper. Firstly, the main factors affecting the normal and chord deformation of slat structure are theoretically analyzed. Then, taking the leading edge slat of a large domestic aircraft as the research object, the influence of skin and other structural dimensions on the stiffness of slat body is discussed in detail from two aspects of weight and deformation. Finally, on the premise of maintaining the size and weight of the original slat structure, the leading edge slat interference trailing edge structure is designed. The results show that the proposed interference trailing edge structure can maintain the state of non separation from the wing under the aerodynamic load of cruise condition, improve the aerodynamic performance, and effectively avoid the increase of weight.