Structure reduced-order model-based geometric nonlinear static aeroelastic full-aircraft trim method

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

Inactive Publication Date: 2018-08-03
BEIHANG UNIV
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Problems solved by technology

This method solves the problem of nonlinear fast structure calculation and explicit calculation, and

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  • Structure reduced-order model-based geometric nonlinear static aeroelastic full-aircraft trim method
  • Structure reduced-order model-based geometric nonlinear static aeroelastic full-aircraft trim method
  • Structure reduced-order model-based geometric nonlinear static aeroelastic full-aircraft trim method

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Embodiment Construction

[0084] The specific implementation method of the geometrically nonlinear static aeroelastic full-machine trim analysis and 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.

[0085] 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 t...

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Abstract

The invention provides a structure reduced-order model-based geometric nonlinear static aeroelastic full-aircraft trim method. The method comprises the steps of firstly building a full-aircraft finiteelement model of an aircraft, giving a follow-up test load and solving corresponding test deformation through finite element software; secondly solving a nonlinear stiffness coefficient by performingregression analysis on the follow-up test load and the test deformation in a given nonlinear stiffness coefficient form to build a structure reduced-order model; and finally applying the model to thegeometric nonlinear static aeroelastic full-aircraft trim analysis of the aircraft, and establishing wing geometric nonlinear static aeroelastic deformation calculation and full-aircraft geometric nonlinear static aeroelastic trim analysis processes. The nonlinear stiffness coefficient in a cubic polynomial form is given, and the aerodynamic follow-up effect and the spanwise deformation under thewing geometric nonlinear large deformation are considered, so that the reasonability and accuracy of geometric nonlinear static aeroelastic analysis are improved and the efficient analysis calculation of geometric nonlinear aeroelastic deformation and trim is facilitated.

Description

technical field [0001] This design provides a geometrically nonlinear static aeroelastic full machine trim 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, st...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23Y02T90/00
Inventor 谢长川安朝杨澜杨超
Owner BEIHANG UNIV
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