In morphing aircraft

achieving smoothness

continuity

and seamless connection of wing surfaces during deformation remains a major challenge in structural design. To address the issue of wrinkling that frequently occurs in conventional flexible skins under compression

this paper proposes a corrugated flexible morphing framework with displacement constraints. Firstly

considering the bending-compression coupling inherent in traditional corrugated structures

a novel corrugated configuration is designed by introducing displacement constraints at critical locations

which effectively suppresses compression-induced deformation during bending. Taking into account the anisotropic characteristics of the structure

it is simplified into a beam-element model

and a chain-based algorithm is developed to establish a largedeformation computational method under displacement constraints. The mechanical responses of the structure under flexible skin constraints and uniformly distributed loads are further analyzed. Finally

a prototype of a morphing trailing edge based on the proposed corrugated structure is fabricated and experimentally validated. The results demonstrate that the trailing-edge structure achieves large deformation of up to ±20°

while maintaining good surface smoothness and continuity throughout the morphing process

with no local buckling observed in the flexible skin. This design provides a new theoretical basis and engineering pathway for the design and optimization of flexible trailing-edge structures.