The invention belongs to the technical field of aircraft component
assembly, and particularly relates to a method for judging the
machinability of an aircraft component compensation layer, which comprises the following steps of: obtaining a rule between a
cutting load and a
cutting parameter through a
cutting test, and determining a limit cutting parameter; combining the structural characteristics of the section, partitioning the
processing surface of the compensation layer, and calculating to obtain the deformation of all relative stiffness minimum points on the section and the minimum structural stiffness; designing a box section test piece according to requirements, performing partitioning according to box section structural characteristics, and obtaining deformation of all relative rigidity minimum points on a box section and the minimum
structural rigidity through calculation; and determining critical
machining deformation, and judging the
machinability of the section compensation layer on the basis of the critical
machining deformation in combination with rules among the parameters, so that optimization of the cutting parameters of all the partitions is achieved. According to the method, a process calculation and
analysis method is provided for
machinability judgment of the section compensation layer liner, the problems of
machining vibration and debonding in the
machining process can be predicted, and parts which cannot be machined can be accurately positioned.