Fitting method for optimal position and attitude of large aircraft component

The invention discloses a fitting method for the optimal position and posture of a large part of an airplane, and relates to the technical field of airplane digital assembly. In the actual situation, the situation that the feature points do not meet the permitted out-of-tolerance range all the time exists, and then the actual attitude adjustment result does not meet the requirement, so that the out-of-tolerance range is widened, and it is guaranteed that the feature points of the large aircraft component are all within the permitted out-of-tolerance range. The situation not only sacrifices the precision of some core key feature points, but also is influenced by other feature points with poor precision, so that the quality of adjusting the position and posture of the large part of the aircraft is not high, and the overall assembly level of the aircraft is possibly reduced. According to the method, when the conditions are encountered, grade distribution and reasonable selection and rejection are carried out on