Abstract: In order to solve the problem of asymmetric distributed aerodynamic loads on the helicopter door, a least squares method is used to fit the data of the existing pressure on the aerodynamic nodes of the helicopter door, and to calculate the pressure on the FEM nodes, by the use of the function of the patran field, to realize the quick loading on FEM nodes. This method is proved to be steady and reliable through the experiment of putting the asymmetric distributed aerodynamic load on the helicopter door. The asymmetric distributed aerodynamic loading on the surface can be implemented faster by using this method, and the FEM analysis with the asymmetric distributed load can be made effectively.