In order to solve the problem of the positioning and nondestructive holding of the fuselage panel of the large composite material

the paper puts forward the flexible tooling structure scheme based on mixed joint positioning and vacuum adsorption. On the basis of the analysis of the position process and the vacuum adsorption process of composite materials panel

design a kind of integrated X axis and Y axis tandem cross sliding table

parallel connection of Z axis and B angle adjustment module

vacuum adsorption and A angle adaptive flexible tooling structure. And the function test results of flexible tooling test pieces show that the positioning and adsorption of the flexible tooling are stable and accurate

and the adsorption is safe and reliable

which satisfy the requirements of positioning and nondestructive clamping function.