Modeling method for reduced-order model of large flexible structure based on dynamic response recognition

A dynamic response and flexible structure technology, applied in complex mathematical operations, special data processing applications, instruments, etc., can solve the problem that structural dynamics characteristics cannot be accurately captured

Active Publication Date: 2021-10-22
BEIHANG UNIV
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Problems solved by technology

[0005] In view of this, the present invention provides a reduced-order model modeling method for large flexible structures based on dynamic response identification, which is used to overcome the problem that only static response data are used as identification samples in t...

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  • Modeling method for reduced-order model of large flexible structure based on dynamic response recognition
  • Modeling method for reduced-order model of large flexible structure based on dynamic response recognition
  • Modeling method for reduced-order model of large flexible structure based on dynamic response recognition

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Embodiment 1

[0084] The large flexible wing is adopted, and the airfoil adopts NACA0015 symmetrical airfoil, and the wing root is completely fixed. The wing parameters are as follows: wing root chord length 100mm, wing tip chord length 100mm, span length 1000mm, sweep angle 0Deg, no twist angle. The main beam of the wing adopts a rectangular section with a section length of 35mm and a section width of 1.5mm, which is located at 50% of the chord length of the wing. The shape of the wing is maintained by 8 balsa wood box sections, each box section is composed of balsa wood skeleton and heat-shrinkable film skin. In order to reduce the impact on the stiffness of the wing due to the mutual extrusion of the box sections due to bending deformation, the box sections are connected to the main girder at a single point and a certain gap is left between adjacent box sections. In order to adjust the dynamic characteristics and structural deformation of the wing, a counterweight bar is installed at th...

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Abstract

The invention discloses a modeling method for a reduced-order model of a large flexible structure based on dynamic response recognition, which comprises the following steps of: discretizing a nonlinear structure dynamic equation at equal time intervals to form a generalized coordinate discrete sequence, then carrying out discrete Fourier transform on the generalized coordinate discrete sequence to form a frequency domain transform sequence, and finally, carrying out dynamic response recognition on the frequency domain transform sequence; a part of items of a motion equation are exchanged in sequence to form a linear equation set, a mode of multiplying a modal combination by a proportionality coefficient is utilized to construct a test load, the test load is loaded on a structure to calculate dynamic response, dynamic response data are advanced, then a least square solution of the equation set is solved, a nonlinear rigidity coefficient can be given, and a nonlinear structure reduced-order model is established. Compared with a traditional large flexible structure reduced-order model based on statics response data recognition, the large flexible structure reduced-order model based on dynamic response recognition constructed by the method has the advantages that the nonlinear rigidity coefficient is recognized by utilizing a structural dynamic response data sample, and more accurate structural dynamic characteristic information can be provided.

Description

technical field [0001] The invention relates to the technical field, in particular to a method for modeling a reduced-order model of a large flexible structure based on dynamic response identification. Background technique [0002] The requirements of modern aircraft design for flight performance are constantly increasing. Large flexible aircraft represented by high-altitude long-endurance UAVs and flying-wing UAVs have gradually become the research focus of major aviation countries since the 1990s. This type of aircraft can continuously perform tasks such as military reconnaissance, civilian scientific exploration, and communication relay in a more flexible manner. It has a flight altitude and endurance far exceeding that of traditional aircraft, and has broad application prospects. Due to its flight performance requirements, large flexible aircraft usually use a larger wing aspect ratio to increase the lift-to-drag ratio, and at the same time increase the proportion of com...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/23G06F17/11G06F17/14G06F119/14
CPCG06F30/15G06F30/23G06F17/11G06F17/141G06F2119/14Y02T90/00
Inventor 谢长川张铎耀安朝杨超
Owner BEIHANG UNIV
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