The invention relates to the field of aircraft structural part
numerical control machining, in particular to a method for controlling drilling hole sites of aircraft structural parts, which comprisesthe steps of selecting a part drilling cutter and
cutting parameters, measuring drilling
axial force, performing
finite element simulation of part weak-rigidity structure drilling cutter relieving deformation to acquire relationships Uy (x, y) and Uz (x, y) between deformation and a
machining area position, judging the
fracture risk degree of the
drill bit, calculating an allowable structure strain value, judging whether the
transverse strain of a
machining area is within an allowable range or not, judging hole site deviation caused by cutter relieving deformation, calculating the caused holesite deviation, and judging whether the hole site deviation caused by deformation meets the hole site requirement or not; if the hole site deviation caused by
transverse strain or deformation does notmeet the allowable requirement, adding an inclined rib support to the part structure, carrying out
simulation calculation again, setting the size and position of the inclined rib, and iterating untilthe
transverse strain and deformation hole site deviation meets the requirement, so as to realize the effective control of the hole site of the hole in the weakly rigid region of the aircraft structural member. A quality problem that the drilling position is out of tolerance is avoided.