Calculation method for wing bending rigidity distribution

Abstract

The invention relates to a calculation method for wing bending rigidity distribution and belongs to the field of aeroelasticity. The method comprises the steps that firstly, the lift force distribution of a wing is equivalent to the oval lifting force distribution, and a distribution function of the wing lifting force along wingspan under the equivalent condition is acquired; secondly, a bending moment expression of any position on the wingspan of the wing is acquired according to the distribution function of the wing lift force along the wingspan; then, with the bending rigidity of a position on the root part of the wing being a reference, the normalization bending rigidity distribution of the wing along the wingspan is acquired, and the bending rigidity of the root part of the wing is calculated; finally, the actual bending rigidity distribution of the wing along the wingspan is acquired according to the normalization bending rigidity distribution of the wing along the wingspan and the bending rigidity of the root part of the wing. The calculation method for the wing bending rigidity distribution is applicable to the later period and the primary design stage of a wing concept design, and under the situation that design conditions are not sufficient, the rigidity distribution of the wing can be quickly acquired through the method.

Description

technical field [0001] The invention relates to the field of aeroelasticity, in particular to a method for calculating the distribution of wing bending stiffness. Background technique [0002] As one of the key components of the aircraft, the stiffness distribution of the wing is the most critical parameter affecting the aeroelasticity of the wing and even the whole aircraft. When designing the wing surface, it is necessary to ensure that the wing surface has "sufficient" stiffness. However, in the late stage and preliminary design stage of wing concept design, the structural arrangement of the wing is not yet clear, and the stiffness distribution of the wing cannot be obtained by traditional calculation methods. Contents of the invention [0003] In order to solve the above problems, the present invention provides a method for quickly calculating the distribution of wing bending stiffness, which is suitable for the later stage of wing concept design and the preliminary d...

AI Technical Summary

Problems solved by technology

However, in the later and preliminary design stages of the conceptual design of the wing, the structural arrangement of the wing is still unclear, and the stiffness distribution of the wing cannot be obtained using traditional calculation methods

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