Safety margin calculation method of wing reinforced wallboard

Abstract

The invention discloses a safety margin calculation method of a wing reinforced wallboard. The safety margin calculation method of the wing reinforced wallboard comprises the following steps: step 1: acquiring parameters of a long truss unit and a skin covering the long truss unit, and relative position relation parameters between the long truss unit and the skin; step 2: acquiring relative position relation parameters between the wing reinforced wallboard and a wing box; step 3: calculating allowable compression stress of the long truss unit through a formula; step 4: calculating an allowable carrying capacity of the long truss unit, an actual working load of the long truss unit, a shearing allowable value of the wing reinforced wallboard and actual shearing stress on the wing reinforced wallboard in actual work through formulas; and step 5: calculating a safety margin of the wing reinforced wallboard through a formula. According to the safety margin calculation method of the wing reinforced wallboard, disclosed by the invention, the strength of the wing reinforced wallboard is metered in a manner of solving the safety margin of the wing reinforced wallboard; and the method is verified by a test, the structure efficiency can be improved and the design period is shortened.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to a method for calculating a safety margin of a wing stiffened wall plate. Background technique [0002] In the prior art, the "EULER-JOHNSON" equation is usually used to calculate the safety margin of the wing stiffened panel. However, the following three problems cannot be solved by the stress intensity calculation based on the "EULER-JOHNSON" equation: [0003] 1. The calculation point does not correspond to the analysis point. When calculating the uniaxial compression bearing capacity of the panel, the skin is converted to the stringers. During the calculation, it is considered that the load acts on the centroid of the assembly (effective skin area and stringer area); while the centroid of the stringer of the actual wing structure and the centerline of the skin do not coincide, but it is simplified to one point in the stress analysis (that is, on the centerline of the skin)...

AI Technical Summary

Problems solved by technology

[0004] 2. The stringer stress and skin stress in the stringer unit are also different;

[0005] 3. Effect of skin effective width

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