Aircraft composite fuselage panel mold firmed on the horizontal automatic fiber placement (AFP) is tudied based on the theoretical mechanics. It proves that the mold weight and section inertia moment are the dominating actors influencing mold stiffness. Firstly

frame unit is constructed by topology optimization. Then

an industrialized base esign proposal is constructed according to the load transmission path among frame unites and steel structure points design rinciple. Three influencing factors which are mold profile

shaped ribs and frame unit numbers are selected based on base esign proposal

and an orthogonal experimental design and simulation analysis for these influencing factors is finished. nalysis results point out that it will realize the performance balance between the mold lightweight and stiffness when ecrease the frame unit numbers and optimize the thickness of mold profile and shaped ribs.