A threedimensional finite element model of the joint assembly is built, and the failure evolution process of the composite laminate is analyzed. The numerical analysis model is modified by regulating initial stiffness coefficients of the laminate based on the strength test data. The joint strength of the modified numerical model is fitted well with that of static loading test. It follows that the approximate dual linear characteristics is found in the tensile test curves before the ultimate strength is met, and tensile load attenuation surge happens at the point where the gradient discontinuity occurs. The contact faces of the tensile test specimen encounter a process from initial static friction state, transient slide friction state to final static friction equilibrium state. When there is a M6 bolt with 8 N·m tightening torque, its tensile strength is the maximum, and the relative errors of joint strength between the numerical analysis results and that of the tensile test are all less than 6.7%. The best joint strength can be obtained to proper tightening torque, whereas excessive tightening torque may lead to strength reduction.