This article aims to solve the problem of assembling between composite material fuselage bucket sections. An orbital junction structure is designed for the composite material aircraft fuselage panel using omega shaped stringers, which includes simple structural components such as stringer joints, strap plates, shim, and fasteners. Using a defined finite element method, the load transfer characteristics of the structure, as well as the influence of parameters such as the size and layer of each structural component on the mechanical properties including load distribution of structural components, fastener loads, hole bearing, etc., were analyzed and calculated. Finally, an optimized structural design and parameters were proposed based on the calculation results, and calculation analysis was conducted provide some guides for the design of similar structures.