A Finite Element Analysis Method for Carrier Vehicle Skin Stringer Structure

A finite element and skinning technology, applied in the field of finite element analysis, can solve the problems of highly repetitive, error-prone, and dependent work, and achieve the effect of reducing repetitive work and improving work efficiency

Active Publication Date: 2016-06-29
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
View PDF1 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

These two methods are primary applications of CAE tools, without data and experience accumulation, highly repetitive work, extremely dependent on the experience of analysts, and prone to errors

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

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0026] A finite element analysis method for a carrier rocket skin stringer structure, the steps are:

[0027] 1) Establish a finite element model for the skin. The skin is made of 1mm thick aluminum sheet in 2A12T4 state, with an elastic modulus of 70GPa, Poisson's ratio of 0.3, yield stress of 270MPa, ultimate strength of 400MPa, and elongation after fracture of 13%. Stored in the database, marked as A1;

[0028] The middle surface diameter of the skin is 1700mm, the height is 2500mm, and the thickness is 1mm, which is stored in the database and marked as B1;

[0029] 2) Establish a finite element model for the stringer. The stringer is made of 2A12T4 aluminum profile, with an elastic modulus of 70GPa, Poisson’s ratio of 0.3, yield stress of 295MPa, ultimate strength of 390MPa, and elongation after fracture of 10%. In the database, marked as A2;

[0030] The cross-section of the stringer is "T-shaped", and the size has two specifications: specification 1, the width of the e...

Embodiment 2

[0039] A finite element analysis method for a carrier rocket skin stringer structure, the steps are:

[0040] 1) Establish a finite element model for the skin, the skin material is A1 in Example 1, and the properties are retrieved from the database;

[0041] The skin size adopts B1 in Embodiment 1, and the size is retrieved from the database;

[0042] 2) Establish a finite element model for the stringer. The stringer is made of 7A09T4 aluminum profile, with an elastic modulus of 70GPa, Poisson’s ratio of 0.3, yield stress of 440MPa, ultimate strength of 500MPa, and elongation after fracture of 8%. In the database, marked as A4;

[0043] The cross-section of the stringer is "T-shaped", adopts C2 in Embodiment 1, and the size is retrieved from the database;

[0044] 3) Establish a finite element model for the ring frame, the stringer material is A3 in Example 1, and the properties are retrieved from the database;

[0045] The cross-section of the ring frame is a square frame,...

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 relates to a method for analyzing finite elements of skin-stringer structures of carrier rockets, and belongs to the field of technologies for analyzing the strength of structures. The method can be used for quickly analyzing the strength of the structures, and also can be used for quick modeling. The method has the advantages that procedures for analyzing the strength of the skin-stringer structures are standardized, material data and parameter data of the structures are accumulated, and efficiency merits of analytical standards and databases are utilized, so that the work efficiency and the analytical quality can be improved.

Description

technical field [0001] The invention relates to a finite element analysis method for a carrier rocket skin stringer structure, which can be used for rapid structural strength analysis and rapid modeling, and belongs to the technical field of structural strength analysis. Background technique [0002] The skin stringer structure has the characteristics of low cost, simple process, and high load-carrying capacity, which is conducive to structural lightweight, and is a structural form commonly used by launch vehicles at home and abroad. At present, there are two methods for the strength analysis of the skin stringer structure: (1) Use Pro / E and other CAD tools to establish a geometric model, and then import it into the CAE software through an intermediate format file, and then perform attribute assignment, meshing, and loading And boundary conditions, selection of solution algorithms, submission of calculations and other routine finite element analysis work. (2) Directly use C...

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 Patents(China)
IPC IPC(8): G06F17/50
Inventor 章凌张希王斌徐珊珊杨帆林川
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Try Eureka
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap