A predictive method was proposed to estimate the filled hole compressive(FHC) strength of composite laminates based on the load distribution between composite plate and bolt filled in the plate. A MSC.Patran/Nastran based finite element model, which considered surface contact effect, was developed to verify the influence of stacking sequence and bolt stiffness on load distribute factor near the hole. The stress analysis results of surface elements showed that the distribution of contact force between plate and bolt appeared to be cosine over half the hole. With T700/LT-03A carbon fiber composite laminates, experiments concerning three different stacking sequences were taken to derive the open hole and FHC strength. Test results showed that the FHC strength was 30% higher than the open hole compressive strength. The predicted results complied with the experiment results with error less than 5%. Comparison was also applied between the results from the very method and the experiment results of T800/3900-2 shown in other works. The proposed method could well predict the FHC strength with accuracy, and has certain significance in engineering.