Analysis of large tooling rigidity for SimSolid under binding constraints

This paper addresses the problems of long rigidity verification cycle and complex structural rigidity verification calculation in the large wing tooling design stage, and proposes a method of using binding constraint replacement bolts and welding. By establishing a simplified analysis model, the rigidity deformation of the airfoil frame under no-load, single-sided load and double-sided load conditions was analyzed using Simsolid software. The research finds that after the product is launched, the maximum deformation of the tooling under unilateral loading or bilateral loading is approximately 0.1mm, meeting the design requirement that the tooling deformation is less than 0.1mm when the product is put on the tooling. The results show that under the condition of binding constraints, the analysis results obtained by using Simsolid software are reliable, with a short working cycle and small computational complexity, and have great advantages in the initial design stage.