Method for calculating rigidity of aircraft airfoil surface structure

Abstract

The invention discloses a method for calculating the rigidity of an aircraft airfoil surface structure. The method includes the steps that an airfoil-surface-structure finite element analysis model is built, wherein the airfoil-surface-structure finite element analysis model should be corrected through a static test and can really simulate the rigidity of the structure; sections of the root are restrained in the finite element analysis model, and then finite element analysis is carried out; the torsional rigidity of the structure is reversely derived through torsional deformation of the sections, and then the rigidity center positions of the sections are determined through a torsional rigidity calculation formula; and when the bending rigidity of the structure is calculated, small-deformation assumption is adopted, the finite element analysis is fitted to obtain displacement at the rigidity centers of the sections, a structure bending rigidity calculation formula is obtained accordingly, and the rigidity, the rigidity center positions and the bending rigidity of the aircraft airfoil surface structure are rapidly and accurately calculated through the structure bending rigidity calculation formula. In this way, the rigidity, the rigidity center positions and the bending rigidity of the aircraft airfoil surface structure are rapidly and accurately calculated; and in addition, experiments in aircrafts in multiple types verify that the algorithm is correct in principle, easy and convenient to implement and capable of meeting the aircraft designing requirement.

Description

technical field [0001] The invention relates to the technical field of aircraft stiffness structures, in particular to a method for calculating the stiffness of an aircraft wing surface structure. Background technique [0002] Aircraft structure design must not only meet strength requirements, but also consider stiffness requirements; in order to ensure that the aircraft has the expected aerodynamic performance at the time of design, the airfoil structure must have sufficient overall stiffness, such as the torsional deformation of the section at a certain distance from the wing root , it is not allowed to exceed a certain limit angle, and the deflection of the airfoil should not exceed the allowable value. At the same time, the same requirements are also required for local stiffness, especially for high-speed aircraft, the uneven deformation of the wing surface will seriously affect the aerodynamic characteristics of the aircraft. Stiffness requirements do not mean that the...

AI Technical Summary

Problems solved by technology

However, at present, there is no relatively mature and practical method for calculating the structural stiffness of aircraft wing surfaces. Engineering algorithms are basically used to calculate the torsional stiffness, rigid center position, and bending stiffness of the structure according to the structural form and size. It is relatively complex, with many closed rooms and irregularities. Using engineering algorithms to calculate, not only the workload is large, but also the process of structure simplification is prone to large errors

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