Structural finite-element parametric modeling method applicable to grating-configuration rudder surface

Abstract

The invention discloses a structural finite-element parametric modeling method applicable to a grating-configuration rudder surface. According to the method, a mapping transformation method based on a finite element model and a parametric approach to achieving conversion from two-dimensional mesh parameterization division to three-dimensional appearance expansion are adopted. The method includes the steps of specifically conducting two-dimensional plane projection on the grating-configuration rudder surface, extracting characteristic parameters, and conducting two-dimensional parameterization division; building a mapping relation between a two-dimensional finite element mesh and a three-dimensional finite element mesh, designing a numbering rule for finite element mesh points, and achieving conversion from the two-dimensional mesh to the three-dimensional appearance expansion; by means of a high-level computer language program, implementing the structural finite-element parametric modeling procedures for the grating-configuration rudder surface. By using the method, in a conceptual design phase or a preliminary design phase, the structural modeling efficiency can be greatly increased, the costs of time and manpower are low, parameters of self-compiled programs can be adjusted quickly, analysis applicability is high, the obtained model is applicable to analytical calculation of structural vibration, structural dynamics and the like, and the method is applicable to grating-configuration rudder surfaces and grating-configuration airfoils.

Description

technical field [0001] The invention relates to a structural finite element parameterized modeling method of a rudder surface, which belongs to the field of aircraft structure finite element modeling and is suitable for the finite element parameterized modeling of a rudder surface with a grid configuration. Background technique [0002] Aircraft design is a huge and complex project, which has the characteristics of long development cycle, high development cost, and large investment of manpower. The development of a new aircraft usually goes through the demonstration stage, the scheme stage (conceptual design and preliminary design stage), the engineering development stage (detailed design stage), the design finalization stage and the production finalization stage. Among them, the demonstration stage and the scheme stage are the main design stages. After these two design stages are completed, the entire configuration of the aircraft is basically determined, that is, the degre...

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Problems solved by technology

However, the parametric realization of the model is also restricted by the data interface and the model description method, and it is difficult to realize the parametric realization of the complex real model; the high-level computer language can start from the bottom layer of the geometric modeling, the design of the algorithm is flexible, and the parametric description is not difficult. Limited by the complexity of software module functions and models, but the generality of the method is the main challenge

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