In order to increase structural stiffness of propeller blade，stacking orientation in different regions of the composite propeller blade was optimized respectively. The blade was divided into 4 zones according to its thickness and load condition. Stacking optimization was based on draping simulation results of different zones in the propeller blade，fiber orientation in draping simulation was 0° ，45° ，90° and -45°. Compared with the initial layup scheme of［0/45/0/-45］_sn，the optimized blade layup scheme made the main direction of the laminate close to the line connecting the centre points of each section of the blade. The 1st and 3rd natural frequencies of propeller blade were raised by more than 25% ，the 2nd natural frequency was raised by more than 5%. Displacement of propeller blade under uniformly distributed pressure loads was reduced by 50%，and displacement under thermal loads was reduced by 25%.The expected objective of increasing structural stiffness of blade is achieved by layup optimization. The method of optimization by region not only utilizes the designability of composite materials but also improves the optimization efficiency. It is suitable for layup optimization of complex composite structures.