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Value calculating method of thermal residual stress of fiber reinforced composite material under low temperature

A composite material and residual stress technology, which is applied in calculation, image data processing, 3D modeling, etc., can solve the problems of complex cost, difficulty in accurately measuring the microscopic residual stress of composite materials, etc., so as to achieve real and reliable calculation results and better calculation results. Effect

Inactive Publication Date: 2018-05-29
DALIAN UNIV OF TECH
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  • Summary
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  • Claims
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Problems solved by technology

However, these experimental methods are usually complicated and expensive, and it is difficult to accurately measure the microscopic residual stress of composite materials.

Method used

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  • Value calculating method of thermal residual stress of fiber reinforced composite material under low temperature
  • Value calculating method of thermal residual stress of fiber reinforced composite material under low temperature
  • Value calculating method of thermal residual stress of fiber reinforced composite material under low temperature

Examples

Experimental program
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Embodiment

[0042] The improved fiber random distribution algorithm proposed by the present invention is shown in the schematic diagram figure 2 , See the flowchart image 3 . Specific steps are as follows:

[0043] ①Set the initial parameters, including the length a and width b of the target window, fiber diameter d f , Target fiber volume content Minimum fiber spacing l min And maximum fiber spacing l max .

[0044] ② In the target window with length a and width b, take the center of the window as the origin of coordinates, the horizontal direction as the x-axis, and the vertical direction as the y-axis. In the center area of ​​the window (for example, take |x 1 | 1 | figure 2 The dashed box in a) randomly fill in a point (x 1 ,y 1 ) As the center of the first fiber.

[0045] ③Fill in the second point (x 2 ,y 2 ) As the center of the second fiber, the position of the point is determined by two parameters: point (x 1 ,y 1 ) And point (x 2 ,y 2 ) Distance l 1 , And the direction angle θ b...

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Abstract

The invention discloses a value calculating method of a thermal residual stress of a fiber reinforced composite material under a low temperature. The method comprises the following steps of a, based on fiber random distribution, constructing a representative volume element (RVE) of a composite material; b, dividing a network for the composite material and acquiring a finite element model requiredby calculation; c, endowing the finite element model to thermal / mechanical performance parameters of a fiber and a matrix material which are related to a temperature; d, adding a periodic boundary condition for the finite element model; and e, applying a temperature load to the finite element model and calculating and acquiring the thermal residual stress. By using the method, operation is simpleand prediction precision is high; the method can play an important role in predicting the low temperature residual stress of the composite material so as to lay the foundation for the application of the composite material in a low temperature field.

Description

Technical field [0001] The invention belongs to the field of composite materials, and in particular relates to a numerical calculation method for the thermal residual stress of a fiber reinforced composite material at low temperature. Background technique [0002] The research and development of large-scale launch vehicles have increasingly higher requirements for lightweight rocket structures. The low-temperature propellant storage tank is the component with the largest weight and volume in the structure of the rocket body, and its lightweight level is the core factor to measure the structural efficiency. Fiber-reinforced resin-based composite materials have the advantages of high specific modulus and specific strength, good fatigue performance, and low thermal conductivity, and have been widely used in the aerospace field. The research report of the National Aeronautics and Space Administration (NASA) shows that the low-temperature propellant tank made of composite materials c...

Claims

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Application Information

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IPC IPC(8): G06T17/20
CPCG06T17/20
Inventor 杨雷武湛君徐浩刘科海高东岳李志伟
Owner DALIAN UNIV OF TECH
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