Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Method for optimizing structural parameters based on symbolic operation results of sparse matrix

A sparse matrix and symbolic operation technology, applied in design optimization/simulation, calculation, electrical and digital data processing, etc., can solve problems such as low design efficiency and low optimization efficiency, and achieve the effect of improving design efficiency.

Active Publication Date: 2018-04-20
CHINA AIRPLANT STRENGTH RES INST
View PDF6 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, with the improvement of computer hardware technology, finely divided finite element grids are often used for increasingly complex structural design forms. The finite element model of millions of nodes in the design is quite common, and the finite element model of this scale is repeatedly called for optimization. The design efficiency is relatively low
refer to figure 2 , the analysis process in the traditional optimization design is used as a black box call, and the response is obtained by repeatedly calling the solver, and the optimization efficiency is low

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Method for optimizing structural parameters based on symbolic operation results of sparse matrix
  • Method for optimizing structural parameters based on symbolic operation results of sparse matrix
  • Method for optimizing structural parameters based on symbolic operation results of sparse matrix

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0022] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention discloses a method for optimizing structural parameters based on symbolic operation results of a sparse matrix and belongs to the technical field of strength analysis of aircraft structures. The method mainly includes firstly generating a stiffness matrix through a finite element analysis method; secondly performing a matrix transformation on the stiffness matrix with a minimum filling element as a target, and establishing a mapping relationship; using the transformation to perform equivalent transformation on the right-end item of a load and then performing numerical decomposition, and forming a triangular decomposition matrix of a sparse matrix of linear equations; using results of matrix decomposition to perform finite element analysis to perform optimization calculation;using updated design variables to perform numerical item replacement operations by using the mapping relationship; and finally repeating the optimization process until the optimization converges. According to the method, the result of the first symbol operation is made full use of to perform the numerical decomposition operation. In the entire design process, only one symbolic operation needs to be performed. Compared with a traditional design process, theoretically the method shortens the design time by about 50%.

Description

technical field [0001] The invention belongs to the technical field of aircraft structural strength analysis, and in particular relates to a method for optimizing structural parameters based on sparse matrix symbolic operation results. Background technique [0002] In order to complete the research and development design of the structure with high quality under the limited time and funds, it is an inevitable choice to design by means of optimization. Optimal design is increasingly becoming an effective means for people to solve the contradictions of safety, performance, time and cost. After decades of hard work, the development of optimization techniques has made great progress in theory and application. [0003] Due to historical reasons, in the traditional optimization design process, the finite element analyzer is artificially isolated from the optimization process, and the results of the optimizer after numerical optimization must be returned to the analyzer for a comple...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23G06F2111/10
Inventor 王立凯聂小华郭瑜超罗利龙张生贵
Owner CHINA AIRPLANT STRENGTH RES INST
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products