Calculation method of bend-twist coupling composite wing structure control equation

Abstract

The invention relates to a calculation method of a bend-twist coupling composite wing structure control equation, and belongs to the technical field of aircraft design. The method comprises the stepsof 1, determining a control equation for a bend-twist coupling composite wing structure analysis model and a vibration model; 2, performing discretization on the bend-twist coupling composite wing structure through an N-degree-of-freedom differential quadrature method, and then building a boundary discretization equation according to the stress and boundary supporting condition of the bend-twist coupling composite wing structure; 3, calculating the control equation for the bend-twist coupling composite wing structure with material discontinuity, building an N-degree-of-freedom differential quadrature unit method, forming n regions through division according to different materials so as to form n unit rigidity matrixes, introducing the boundary conditions after the unit rigidity matrixes are assembled, and achieving calculation. According to the calculation method of the bend-twist coupling composite wing structure control equation, the design efficiency is improved, and the method is easily used for parameter evaluation and design for the bend-twist coupling composite wing scheme stage.

Description

technical field [0001] The invention belongs to the technical field of aircraft design, and in particular relates to a method for solving control equations of a bending-torsion coupled composite material wing structure. Background technique [0002] The governing equations of the bending-torsion coupling composite wing analysis model are relatively complicated, and it is difficult to solve them by methods such as Galerkin method and Laplace Transform method. In the continuous case, the derivation process is more complicated and often difficult to solve. Contents of the invention [0003] The purpose of the present invention is to provide a method for solving the governing equations of the bending-torsion coupling composite material wing structure. In combination with the bending-torsion coupling composite material wing analysis model control equations, this paper introduces the differential quadrature method (DQM) to solve, and establishes a method for The four-degree-of-...

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Problems solved by technology

[0003] The purpose of the present invention is to provide a method for solving the governing equations of the bending-torsion coupling composite material wing structure. In combination with the bending-torsion coupling composite material wing analysis model control equations, this paper introduces the differential quadrature method (DQM) to solve, and establishes a method for The four-degree-of-freedom differential quadrature method of the bending-torsion coupled composite material wing analysis model is used to solve the problem of solving the governing equations of the complex bending-torsion coupled composite beam analysis model

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