Nonlinear substructure method suitable for complex large flexible aircraft modeling

Abstract

The invention discloses a nonlinear substructure method suitable for complex large flexible aircraft modeling. A large flexible aircraft model is divided into wing components and fuselage components (including empennages and the like); a wing part is modeled by adopting a nonlinear structure reduced-order model; a large-deformation structure kinetic equation is constructed by utilizing a nonlinearrigidity coefficient, and a test load is constructed by utilizing a mode of multiplying a modal combination by a proportionality coefficient; on the basis, a nonlinear stiffness coefficient is solvedby adopting a method for carrying out regression analysis on an input test load and corresponding structural deformation, and a nonlinear structure order reduction model is formed; and linear modal modeling is carried out on the fuselage component. A constraint mode is solved by applying a fixed interface mode comprehensive method to a wing component, a residual mode is solved by applying a freeinterface mode comprehensive method to a fuselage component, and then a structural kinetic equation is formed through an interface displacement and force coordination condition comprehensive set. According to the method, the modeling cost is greatly reduced, and the modeling and structure analysis efficiency is improved.

Description

technical field [0001] The invention belongs to the technical field of structural dynamics and aircraft aeroelasticity analysis, and in particular relates to a nonlinear substructure method suitable for structural modeling of complex and large flexible aircraft. Background technique [0002] With the rapid development of technologies such as computers, electronics, materials, and controls, the application range of aviation vehicles continues to expand, and the requirements for flight performance continue to increase. Along with this, there is an urgent need for new design ideas and analysis methods. Since the 1990s, large flexible aircraft represented by high-altitude long-endurance UAVs and flying-wing UAVs have gradually become the research focus of major aviation countries. This type of aircraft can continuously perform tasks such as military reconnaissance, civilian scientific exploration, and communication relay in a flexible manner. It has a flight altitude and enduran...

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Problems solved by technology

[0007] In order to overcome the problems of high modeling cost and low calculation efficiency of the traditional structural modeling method in large flexible and complex aircraft models, the present invention performs structural modeling and calculation analysis of complex models based on nonlinear structural reduction model and modal synthesis method, Using the idea of ​​the substructure method, the wing components are modeled as geometrically nonlinear components using the nonlinear structural reduction model, and the fuselage components are modeled as linear components using linear modal modeling. Finally, the modal synthesis method is used to coordinate the interface The conditions are regrouped to form the whole machine structure model, and an efficient and accurate geometric nonlinear structural modeling analysis method for large flexible aircraft is proposed, which can further reduce the structural modeling cost of complex large flexible aircraft models, and improve the modeling and structure Analysis efficiency

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