Check patentability & draft patents in minutes with Patsnap Eureka AI!

A Calculation Method of Torsional Stiffness of Airplane Wing with Large Aspect Ratio

A technology with torsional rigidity and large aspect ratio, applied in calculation, special data processing applications, instruments, etc., can solve problems such as inability to produce or assemble, large dimensional data errors, and low efficiency, and achieve the goal of shortening the design cycle and improving precision Effect

Active Publication Date: 2018-08-24
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
View PDF1 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method has the following disadvantages: first, the determination of the first-round structural parameters requires the experience of the designer, and the dimensional data given by experience often has large errors, and may even fail to produce or assemble; second, multiple rounds are required times of iterations, long time and low efficiency, seriously affecting the aircraft design cycle

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
  • A Calculation Method of Torsional Stiffness of Airplane Wing with Large Aspect Ratio
  • A Calculation Method of Torsional Stiffness of Airplane Wing with Large Aspect Ratio
  • A Calculation Method of Torsional Stiffness of Airplane Wing with Large Aspect Ratio

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0019] In order to better understand the calculation method of the torsional stiffness of the large aspect ratio aircraft wing according to the program of the present invention, a preferred embodiment of the calculation method of the large aspect ratio aircraft wing torsional stiffness of the present invention will be further elaborated below in conjunction with the accompanying drawings illustrate.

[0020] combine Figure 1-3 , the calculation method of the large aspect ratio aircraft wing torsional stiffness provided by the present invention comprises the following steps:

[0021] S1: Organize and collect the structural parameters of similar aircraft wings in service;

[0022] S2: Calculate the torsional stiffness of the similar aircraft wing in active service according to the collected structural parameters of the similar aircraft wing in active service;

[0023] S3: By regularizing the torsional stiffness data of similar aircraft in service obtained in S2, the relations...

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 belongs to the field of aircraft structural mechanics and particularly relates to a calculation method for the torsional rigidity of a high aspect chord ratio aircraft wing. Compared with an existing method, according to the calculation method for the torsional rigidity of the high aspect chord ratio aircraft wing, through the collection of torsional rigidity data of active service similar high aspect chord ratio aircraft wings, a rule therein is found, the torsional rigidity of the wing of a newly developed aircraft is given, the method that the torsional rigidity of the wing is given according to experience before is avoided, the precision of the data is improved, and the design period is shortened.

Description

technical field [0001] The invention relates to the technical field of aircraft structure design, in particular to a calculation method for the torsional stiffness of an aircraft wing with a large aspect ratio. Background technique [0002] When the newly developed aircraft is in the scheme design stage, the structural design will be carried out in the next step after the external dimensions are determined. However, the design of the wing structure requires torsional stiffness data to guide the design. The previous practice was to refer to the wing design of the same type of aircraft in service, and determine the first-round relevant structural parameters based on experience. This method has the following disadvantages: first, the determination of the first-round structural parameters requires the experience of the designer, and the dimensional data given by experience often has large errors, and may even fail to produce or assemble; second, multiple rounds are required Ite...

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 张磊张丽
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
Features
  • R&D
  • Intellectual Property
  • Life Sciences
  • Materials
  • Tech Scout
Why Patsnap Eureka
  • Unparalleled Data Quality
  • Higher Quality Content
  • 60% Fewer Hallucinations
Social media
Patsnap Eureka Blog
Learn More

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

© 2025 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com