Carbon Fiber Reinforced Polymer (CFRP) has become a core material for the lightweight design of primary load-bearing components in next-generation aircraft

owing to its high specific strength and stiffness

corrosion resistance

and structural tailorability. However

due to the intrinsic anisotropic mechanical behavior and weak interlaminar strrength

CFRP components are prone to non-uniform deformation and stress distribution during assembly

resulting from accumulated manufacturing tolerances and assembly coordination requirements. In severe cases

this can lead to irreversible damage modes such as fiber/matrix interface debonding

interlaminar shear failure

and matrix microcrack propagation. Focusing on the need for stress control during the assembly of aircraft composite panels

this study comprehensively considers key process steps including clamping and positioning

gap compensation

and mechanical joining. It reviews the current state of research and application of related technologies domestically and internationally—from the optimization and online adjustment of positioning layouts

gap measurement and compensation

to process control in mechanical joining. Future development directions for stress control technology in composite panel assembly are proposed

providing a reference for low- or no-stress assembly of flexible composite components.