Patent ID: 11941329
Assignee: NANJING UNIVERSITY OF AERONAUTICS AND ASTRONAUTICS
Field: Transport (Mechanical engineering)
Classification: CPC G  B  Y | IPC B  G

Claim 2:
3. The method of claim 1, wherein step (S3) comprises:
(S301) uniformly sampling the medial axis of the fuselage component into the plurality of skeleton points at an interval of 2% of a length of a long diagonal of the bounding box;
(S302) with regard to a skeleton point from the plurality of skeleton points, selecting a point on a front side of the skeleton point and a point on a rear side of the skeleton point, and respectively forming a cross-section slice at the skeleton point, the point on a front side of the skeleton point and the point on a rear side the skeleton point, wherein three cross-section slices are perpendicular to a plane where the medial axis of the fuselage component is located; and
(S303) constructing three local polar coordinate systems centered around the skeleton point, the point on a front side of the skeleton point and the point on a rear side of the skeleton point, respectively, and performing point cloud searching at equal angle by using the three local polar coordinate systems to extract the discrete point set of the cross-section of the fuselage component.