A Nonlinear Feature Detection Method of Spacecraft Structure Driven by Free Vibration Displacement Response

A technology of spacecraft structure and nonlinear characteristics, which can be used in instruments, complex mathematical operations, calculations, etc.

Active Publication Date: 2021-03-02
SOUTHEAST UNIV
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  • Abstract
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  • Application Information

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Problems solved by technology

The main reason is that the existence of nonlinearity makes the analysis method of the spacecraft structure more complex, making the dynamic behavior of the spacecraft difficult to predict.

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  • A Nonlinear Feature Detection Method of Spacecraft Structure Driven by Free Vibration Displacement Response
  • A Nonlinear Feature Detection Method of Spacecraft Structure Driven by Free Vibration Displacement Response
  • A Nonlinear Feature Detection Method of Spacecraft Structure Driven by Free Vibration Displacement Response

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Embodiment Construction

[0041]The technical solution of the present invention will be further described below in conjunction with the drawings and embodiments.

[0042]This embodiment uses a five-degree-of-freedom non-linear spring-damping-mass system to illustrate the process of the method of the present invention, such asfigure 1 The flow chart of the implementation of this method is shown. The masses of the mass blocks are: m1=20kg, m2=10kg, m3=15kg, m4=10kg, m5=5kg; linear spring stiffness coefficient k1=20N / m, k2=10N / m, k3=40N / m, k4=50N / m, k5=100N / m; the stiffness coefficient of the nonlinear spring is shown in Table 1:

[0043]Table 1 Non-linear spring stiffness coefficient parameter values

[0044]

[0045]Using proportional damping, that is, the proportional damping coefficients are 0.01 and 0.01 respectively, the present invention includes the following steps:

[0046](1) Impose initial displacements of different magnitudes on the structure to be inspected, and extract the measured position movement response of ...

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Abstract

The invention provides a method for detecting nonlinear features of a spacecraft structure driven by free vibration displacement response. The measured position movement response under the state; (2) The dynamic mode decomposition of the structure free vibration displacement response under the first initial displacement is carried out to obtain the dynamic mode matrix of the structure and its corresponding eigenvalues; (3) The decomposition obtained The dynamic mode matrix and its corresponding eigenvalues ​​reconstruct the position movement response under the second enlarged initial displacement condition, and analyze the difference between the measured position movement response under the second enlarged initial condition, and detect The existence of structural nonlinearity. For the detection problem of nonlinear features in the spacecraft structure containing hinges, directly using the displacement response of the structure in the free vibration state can effectively judge whether there are nonlinear features in the spacecraft structure.

Description

Technical field[0001]The invention belongs to the field of non-linear structure recognition, and in particular relates to a non-linear detection method driven by free vibration displacement response data.Background technique[0002]With the development of spacecraft structures toward large sizes, the forms of spacecraft structures have become more and more diverse, and the dynamic characteristics of the spacecraft have become more complex. How to judge whether the structure has non-linear characteristics from the dynamic response of the spacecraft structure is one of the key issues that affect the establishment of an accurate analysis model of the spacecraft structure. The main reason is that the existence of nonlinearity makes the analysis method of the spacecraft structure more complicated, making the dynamic behavior of the spacecraft difficult to predict. Detecting the existence of nonlinearity in the spacecraft structure is helpful for qualitative judgment and qualitative analysi...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/16G06K9/62
CPCG06F17/16G06F18/2136
Inventor 费庆国曹芝腑姜东靳慧杭晓晨朱锐
Owner SOUTHEAST UNIV
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