Geometric nonlinear static aeroelasticity analysis method based on structure reduced-order model

A static, aeroelastic and geometrically nonlinear technology, applied in special data processing applications, instruments, electrical digital data processing, etc., to achieve the effect of reducing computing resource consumption and improving computing efficiency

Inactive Publication Date: 2018-05-18
BEIHANG UNIV
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Problems solved by technology

This method solves the problem of nonlinear fast structure calculation and explicit calculation, and can be applied to the geometric nonlinear aeroelastic analysis and calculation of aerospace vehicles

Method used

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  • Geometric nonlinear static aeroelasticity analysis method based on structure reduced-order model
  • Geometric nonlinear static aeroelasticity analysis method based on structure reduced-order model
  • Geometric nonlinear static aeroelasticity analysis method based on structure reduced-order model

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Embodiment Construction

[0081] The specific implementation method of the geometrically nonlinear static aeroelastic analysis solution based on the structural reduced-order model according to the present invention will be described in detail below in conjunction with the accompanying drawings and embodiments.

[0082] As the large flexible airfoil adopted for the purpose of illustration, the airfoil adopts NACA0015 symmetrical airfoil, and the root of the wing is fully fixed. The wing parameters are as follows: wing root chord length 60mm, wing tip chord length 60mm, span length 483mm, sweep angle 0Deg, no twist angle. The main beam of the wing adopts a rectangular section with a section length of 7.03mm and a section width of 1.14mm, which is located at 50% of the chord length of the wing. The shape of the wing is maintained by 12 balsa wood box sections, and each box section is composed of a balsa wood skeleton and a heat-shrinkable film skin. The box section is connected to the main beam at a sing...

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Abstract

The invention provides a geometric nonlinear static aeroelasticity analysis method based on a structure reduced-order model. The method includes: building an aircraft wing or full-aircraft finite element model, presetting follow-up test load, and using finite element software to solve corresponding test deformation; under a given nonlinear rigidity coefficient form, performing regression analysison the follow-up test load and the test deformation to solve a nonlinear rigidity coefficient and built the structure reduced-order model; applying the structure reduced-order model to aircraft geometric nonlinear static aeroelasticity analysis, and building aircraft wing geometric nonlinear static aeroelasticity deformation calculation flow and full-aircraft geometric nonlinear static aeroelasticity trim analysis flow. The method has the advantages that the cubic polynomial nonlinear rigidity coefficient is given, an aerodynamic force follow-up effect and extension-direction deformation underaircraft wing geometric nonlinear large deformation are considered, the reasonability and accuracy of geometric nonlinear static aeroelasticity analysis are increased, and efficient analysis and calculation of geometric nonlinear static aeroelasticity deformation and trim are benefited.

Description

technical field [0001] This design provides a geometrically nonlinear static aeroelastic analysis method based on a structural reduced-order model. It belongs to the field of computational structural dynamics and aircraft aeroelastic analysis. Background technique [0002] Aeroelasticity mainly studies the mechanical behavior of elastic objects in air flow. The elastic body will deform and vibrate under the action of aerodynamic load, and the deformation and vibration will in turn affect the distribution and size of the aerodynamic load. Such coupling effects will produce different aeroelastic problems under different conditions, including static aeroelastic divergence, Flutter, gust response and more. The phenomenon of aeroelasticity has played an important role in the historical development of powered flight. [0003] The large deformation geometric nonlinear aeroelastic problem is a nonlinear aeroelastic problem proposed in the late 1990s. On the one hand, structural ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/23Y02T90/00
Inventor 谢长川安朝杨澜杨超
Owner BEIHANG UNIV
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