Accurate stress and strain analysis on bolted joints are of considerable interest in order to design more efficient and safe aerospace structural components. In this paper, the finite element model of aluminium alloy 7075T6 bolted plates which are widely used in aircraft structures, was established. A doublelap joint with a single bolt and double nut is considered in the study. A threedimensional finite element model of the joint was generated, and then subjected to three different pretightening forces followed by different levels of longitudinal tensile load. 3D surfacetosurface contact elements were selected to model the contact between the various components of the bolted joint. The friction effect was considered in the numerical analysis. And the clearance between the bolt and the plates was simulated. Finite element calculation results show that beneficial compressive stress is generated near the hole edge due to the application of the clamping, and that a higher clamping force can significantly reduce the magnitude of the combined tensile stress at the hole edge and also reduce the bearing stress level at the joint when subjected to the longitudinal tensile load.