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

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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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 technology has large errors and cannot form a scientific quantitative It cannot objectively reflect the structural characteristics of long beams, and cannot accurately calculate the stiffness of long beam structural parts, so it cannot provide an effective basis for the formulation of aviation long beam structural parts processing plans.

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