Large aviation structural parts have the characteristics of complex structure

small wall thickness and large material removal rate

which are easy to produce machining deformation and have a great influence on product quality. Due to technical blockade

imported raw materials with better performance are difficult to obtain and costly. Because of the uneven distribution of residual stress

the machining deformation of domestic blank is uncontrollable

which makes the problem more prominent. On the basis of analyzing the machining deformation mechanism and the current process scheme

the technical conflicts are found by using the analysis tool of TRIZ innovation theory. Based on contradiction matrix and innovation principle

a solution of "adaptive clamping of aircraft large structural parts" is proposed. In practical application

this scheme can effectively avoid the deformation of parts and improve the clamping efficiency

reduce the production cost

achieve remarkable results.