Variable-section aeronautical long beam structural member flexural rigidity calculating method

A calculation method and flexural rigidity technology, which are applied in the field of flexural rigidity calculation of variable-section aviation integral long beam structural parts, can solve the problems of inability to objectively reflect the structural characteristics of long beams, large technical errors, and inability to form quantitative expressions.

Inactive Publication Date: 2018-04-27
BINZHOU UNIV
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Problems solved by technology

[0004] At present, the analysis of the change of the stiffness of the long beam structure is mainly through the observation of the main dimensions and structural characteristics of the variable cross-section long beam by the engineer, and the qualitative evaluation of the stiffness of the variable cross-section long beam is given. This t

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  • Variable-section aeronautical long beam structural member flexural rigidity calculating method
  • Variable-section aeronautical long beam structural member flexural rigidity calculating method
  • Variable-section aeronautical long beam structural member flexural rigidity calculating method

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[0018] The present invention will be further described below in conjunction with specific embodiments. The specific embodiments are described by the inverse calculation process of the stiffness of a variable cross-section aviation beam. The determination includes the following steps:

[0019] Step 1: Use general commercial finite element software to construct a uniform cross-section long beam and a variable cross-section aviation long beam, both of which have the same main body length, width and height. Finite element analysis model see figure 1 As shown, the length, width, and height of the uniform cross-section beam are 762mm, 50mm, and 30mm respectively; refer to the finite element analysis model figure 2 As shown, the variable cross-section beam is a three-frame aviation beam, and the wall thickness of the bulkhead is 3mm.

[0020] Step 2: Establish the finite element model analysis steps, material properties, and connection relations, through the three-point bending method, se...

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Abstract

The invention relates to a variable-section aeronautical long beam structural member flexural rigidity calculating method, is based on a three-point press-bending mechanics model and belongs to the aeronautical structural mechanics field. The method comprises steps that 1), equal-section and variable-section long beam members are constructed for comparison; 2), bending deformation curves of the equal-section long beam member and the variable-section long beam member subjected to external loads are calculated through a three-point press-bending finite element model; 3), the total bending strainenergy of the two long beams is calculated through the finite element bending deformation curves; 4), a bending deformation curve and the bending strain energy of the equal-section beam are calculated through utilizing an equal-section beam three-point press-bending analysis model; and 5), the results of 2), 3) and 4) are compared, and the backstepping method is utilized to find equivalent section inertia moment and equivalent stiffness of the variable-section beam. The method is advantaged in that variable-section beam flexural rigidity is given, estimating rigidity based on experience is avoided, data precision is improved, the theoretical basis is provided for beam part clamping schemes and processing deformation control in the processing process, the tool manufacturing period is shortened, and efficiency is improved.

Description

Technical field: [0001] The invention relates to a stiffness calculation method of an aviation integral long beam structure, in particular to a calculation method of the flexural rigidity of a variable cross-section aviation integral long beam structure. Background technique: [0002] Stiffness refers to the ability of the workpiece to resist elastic deformation. In the macroscopic elastic range, stiffness is the proportional coefficient proportional to the load of the part and the deformation displacement. Changing the structural form of the workpiece has a significant impact on the stiffness. For beams with equal cross-sections, the stiffness calculation formula in material mechanics can be used, that is, the product of the elastic modulus per unit length and the moment of inertia of the section is expressed as the stiffness. [0003] As the material is continuously removed during the machining process of aerospace integral structural parts, the stiffness of the workpiece ...

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Application Information

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IPC IPC(8): G01M5/00G06F17/50
CPCG01M5/0041G06F30/23
Inventor 黄晓明
Owner BINZHOU UNIV
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