Calculation method for wing bending rigidity distribution

A bending stiffness and distribution calculation technology, applied in computing, special data processing applications, instruments, etc., can solve problems such as inability to use wing stiffness distribution and unclear wing structure layout.

Inactive Publication Date: 2016-09-28
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
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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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  • Calculation method for wing bending rigidity distribution
  • Calculation method for wing bending rigidity distribution
  • Calculation method for wing bending rigidity distribution

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Embodiment Construction

[0040] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15
Inventor 陈海黄国宁曾宪昂胡志勇李俊杰
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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