Structural Sizing for Buckling Critical Body Structure of Advanced Aircraft

摘要

A method of sizing body structure of advanced aircraft to preclude buckling has been presented. In addition to providing a structural weight estimate, the method gives information of direct interest to the designer. For example, it is shown that for skin-stringer-frame body structure the skin and stringers combined always weigh three times the frames for minimum weight, regardless of loads, structural geometry, or material. Also, it is shown that structural weight for buckling critical structure depends on material properties according to the ratio ρ/√/E, where ρ and E are the density and Young's modulus of the structural material.