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A Method for Determining Stiffness Index of Wing Structure with Large Aspect Ratio

A wing structure, large aspect ratio technology, applied in the aerospace field, can solve the problems of blindness, lack of development, passive wing structure design, etc., to avoid passivity, rational stiffness distribution, and improve scientific effects.

Inactive Publication Date: 2017-04-12
BEIHANG UNIV
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  • Application Information

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Problems solved by technology

Regarding how to give specific stiffness design indicators in the early stage of structural design, the research to guide the subsequent structural design has basically not been carried out, making the design of the wing structure relatively passive and blind

Method used

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  • A Method for Determining Stiffness Index of Wing Structure with Large Aspect Ratio
  • A Method for Determining Stiffness Index of Wing Structure with Large Aspect Ratio
  • A Method for Determining Stiffness Index of Wing Structure with Large Aspect Ratio

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Embodiment Construction

[0027] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0028] The present invention is a method for determining the structural stiffness index of a large aspect ratio wing, such as figure 1 shown, including the following steps:

[0029] The first step is to analyze and determine the design requirements of the wing structure stiffness;

[0030] In the overall design stage of the aircraft, the design requirements of various disciplines and subsystems are analyzed according to the overall design requirements, and the static deformation of the wing structure and the design requirements of inherent dynamic characteristics are analyzed. Analyze the design parameters that affect the stiffness distribution of the wing structure, such as load conditions, vertical and horizontal displacements, section rotation angles, mass distribution, bending and torsional vibration frequencies, and modes, to determine the corre...

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Abstract

The invention discloses a determining method for a structural stiffness index of a high-aspect-ratio wing, and belongs to the technical field of aerospace engineering. The determining method mainly includes the following steps: step 1, analyzing and determining structural stiffness design requirements of the wing; step 2, creating a structural stiffness analysis model of the wing; step 3, analyzing structural stiffness distribution, meeting the design requirements, of the wing; step 4, calculating a structural stiffness distribution index curve of the wing by a stiffness simulation analysis platform. According to conventional wing structural design methods, the stiffness design requirements are regarded as starting points, preliminary structural design is firstly performed according to design experiences, stiffness check is then performed, and the structural design is modified repeatedly according to check results to meet the stiffness design requirements. According to the determining method, for passivity and defects of the conventional wing structural design processes, the stiffness distribution index curve is provided before starting of the structural design to guide the wing structural design, so that iteration modification processes are reduced, and scientificity and design efficiency of the wing structural design are improved.

Description

technical field [0001] The invention belongs to the technical field of aerospace, and relates to a method for determining the structural stiffness index of a wing with a large aspect ratio. Background technique [0002] Structural stiffness refers to the ability of a member to resist deformation under load, that is, the external load value required for a member to produce unit deformation, including tension-compression stiffness, bending stiffness, and torsional stiffness. As the flight speed of modern aircraft increases, the problems related to structural stiffness become more and more prominent. If the distribution of structural stiffness is unreasonable, it may cause serious vibration problems, affect the control accuracy of related mechanisms, and cause uneven distribution of structural forces. . For large-aspect-ratio aircraft, the problems of mechanical environment, structural deformation, large structural openings, structural dynamic characteristics, aerodynamic load...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 何景武赵嘉俊袁宁宁何石袁天元严贤怀
Owner BEIHANG UNIV
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