Flex wing minisize aerial craft fluid-solid coupling numerical value emulation method

Abstract

The invention belongs to the flex-wing miniature aircraft auxiliary design technical field. The invention is characterized in that: the following modules which are respectively a structure-flow field entity modeling and basic assumption module, a k-epsilon turbulent flow model flow field analysis module, a linear elastic structure analysis module and a structure-flow field coupling interface module are set in a computer, wherein, the structure-flow field entity modeling and basic assumption module is provided with flexible wings and a three-dimensional model in a circumferential flow field; the k-epsilon turbulent flow model flow field analysis module is used for obtaining distribution pressure on a fluid-solid coupling surface of the flow field under different flight conditions; the linear elastic structure analysis module obtains displacement and speed of flex-wing structure meshes; the structure-flow field coupling interface module obtains deformation of the meshes of the flow field from the obtained displacement of the flex-wing structure meshes, and the deformation is taken as an input condition of the k-epsilon turbulent flow model flow field analysis module and then outputted; distribution pressure on wing surfaces of the flexible wings is obtained according to the distribution pressure of the flow field and taken as an input condition of the linear elastic structure analysis module and then outputted. The flex-wing miniature aircraft has the advantages that: higher accuracy than two dimensional analysis is guaranteed and simultaneously the efficiency of simulation calculation can be improved.

Description

technical field

[0001] The invention relates to a method in the field of computer-aided analysis tools, in particular to a fluid-solid coupling numerical simulation method for a micro-aircraft with flexible wings. Background technique

[0002] Micro air vehicle (MAV, Micro Air Vehicle) has the characteristics of small size, good concealment, light weight, low cost, easy to carry, etc., and has very broad application prospects in military and civilian fields. Generally, micro air vehicles can be divided into rigid wing MAV and flexible wing MAV according to the characteristics of the airfoil. Among them, the design of the flexible wing MAV is based on the principle of bionics. The structure adopts the combination of carbon skeleton and film skin. It has good elasticity and can flexibly change its shape. At the same time, the thin film skin made of special materials can also be integrated with the control system of MAV, which can simplify the geometric model of MAV. With the...

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