Method for calculating lateral bending rigidity of section of airframe door frame area of airframe

A method for calculating the lateral bending rigidity of the section of an aircraft fuselage door frame area comprises the steps that design parameters of an aircraft fuselage and a door frame are known, the parameters comprise the fuselage skin thickness, the fuselage radius, the cross section area of fuselage stringers, the fuselage stringer distance and the area of threshold beams, the fuselage section where the middle position of the aircraft fuselage door frame is located is selected as a calculation object, and the moment of inertia of the fuselage section relative to the section centroid axis is calculated, wherein the moment of inertia is the lateral bending rigidity of the fuselage section. 一种飞机机身门框区截面侧向弯曲刚度的计算方法，已知飞机机身和门框的设计参数，该参数包括机身蒙皮厚度、机身半径、机身长桁的横截面面积、机身长桁间距和门槛梁的面积，选取飞机机身门框中间位置所在的机身截面为计算对象，计算上述机身截面相对于截面形心轴的惯性矩，该惯性矩即为该机身截面的侧向弯曲刚度。