This invention discloses a method for determining the force boundary of a tooling flag used in large wing
assembly, comprising: Step 1, establishing a three-dimensional geometric model of the tooling flag in the large wing
assembly tooling, and obtaining a simplified model of the tooling flag through simplification
processing, and determining the
center of mass of the wing model in the simplified model; Step 2, setting mechanical boundary conditions for the simplified model of the tooling flag; Step 3, establishing constraint equations based on the simplified model of the tooling flag and the
center of mass of the wing model; Step 4, applying a concentrated load to the
center of mass of the wing model in the simplified model of the tooling flag, and solving for the
displacement field and
stress field results of the simplified model of the tooling flag under the concentrated load, in order to determine whether the design stiffness of the simplified model of the tooling flag meets the requirements; Step 5, solving for the
stress field results of the simplified model of the tooling flag under the concentrated load on the simplified model of the tooling flag obtained in Step 4 that meets the
stiffness design requirements, and calculating the force boundary of each tooling flag in the simplified model of the tooling flag. The technical solution provided by the embodiments of the present invention solves the problem that the traditional design method for the stress boundary of the tooling flag does not take into account the actual
spatial distribution of the tooling flag, resulting in a large difference from the actual situation. This leads to inaccurate stress on the designed tooling flag, unreasonable distribution position and quantity of the tooling flag, and consequently, excessive stress on local tooling flags, causing deformation of the entire wing tooling.