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A Prediction Method of Thermally Induced Vibration of Large Rotation Composite Material Stretch Arm

A technology of composite materials and prediction methods, used in instrumentation, computing, electrical digital data processing, etc.

Active Publication Date: 2018-10-02
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

It provides a feasible and effective prediction method for solving the problem of coupled thermal-structural dynamic response of large and complex extension arms in space

Method used

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  • A Prediction Method of Thermally Induced Vibration of Large Rotation Composite Material Stretch Arm
  • A Prediction Method of Thermally Induced Vibration of Large Rotation Composite Material Stretch Arm
  • A Prediction Method of Thermally Induced Vibration of Large Rotation Composite Material Stretch Arm

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Embodiment

[0143] 1. Structural parameters and model introduction

[0144] In order to understand more fully the characteristics of this invention and its applicability to engineering practice, the present invention uses Figure 5 The large-rotation extension arm structure shown is an example to illustrate the effectiveness of the method of the present invention. Figure 5 The middle extension arm is a composite thin-walled tube structure with uniform stiffness in the circumferential direction. Its structure and material parameters are listed in Table 1. Solar thermal flow S 0Act suddenly on the extension arm at an angle of incidence β. Assume that the radiation temperature of the space black body is 0K, and the initial temperature of the extension arm is 290K. The extension arm drives the top equipment to move in a large range through the rotation constraint at the root, and the rotation constraint law is expressed as:

[0145]

[0146] In the formula, T s = 15s, ω s = 3rad / s. ...

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Abstract

The invention discloses a thermally-induced vibration prediction method for a large-rotation composite stretching arm. The method includes the steps that a composite stretching arm coupled thermal-structural kinetic control equation is established in a circumferentially-uniform stiffness configuration laying mode; an ANCF beam unit with the thermal effect considered is established based on the Euler-Bernoulli beam theory and the absolute nodal coordinate formulation (ANCF); a composite stretching arm coupled thermal-structural kinetic solution model is established through a Fourier temperature unit and the ANCF beam unit; iterative solution of the coupled thermal-structural kinetic model is carried out by combining the Crank-Nicolson method, the generalized-alpha method and the Newton-Raphson method, and finally the composite stretching arm thermally-induced vibration response is obtained. By means of the method, thermally-induced vibration analysis can be carried out on the stretching arm moving in a large range, coordinate transformation is omitted, and calculation of inertia force becomes quite easy; the method provides effective guidance for future design of complex stretching arm structures and has practical engineering application value.

Description

technical field [0001] The invention is mainly applicable to the coupling / non-coupling thermal-structure dynamic response problem of a composite material extension arm with a large range of motion, and specifically relates to a thermally induced vibration prediction method of a large rotation composite material extension arm. Background technique [0002] Composite extension arms are widely used in spacecraft structural design due to their light weight and small heat capacity. However, the extension arm structures are often large in size and low in stiffness, and such flexible structures are susceptible to structural vibrations induced by extreme thermal loads during rail operation. Such thermally induced vibrations can degrade system performance and even cause structural damage to the spacecraft, thus becoming a typical failure of modern spacecraft. In order to avoid thermally induced vibration during orbit, it is very important to conduct thermally induced vibration study...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG16Z99/00
Inventor 邱志平吕峥王晓军许孟辉仇翯辰陈贤佳
Owner BEIHANG UNIV
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