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Space mesh reflector antenna temperature load analysis method based on electromechanical coupling model

An electromechanical coupling and analysis method technology, applied in the direction of electrical digital data processing, special data processing applications, instruments, etc., can solve the problems of not considering the influence of antenna thermal deformation on electrical performance, and the difficulty of predicting the change of antenna electrical performance, etc., to achieve The effect of taking into account the antenna structure performance and electrical performance requirements

Inactive Publication Date: 2017-05-10
XIDIAN UNIV
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Problems solved by technology

This method takes the spaceborne antenna as the object, and predicts the thermal deformation of the spaceborne antenna under extreme working conditions; this method does not take into account the influence of the thermal deformation of the antenna on the electrical performance, and it is difficult to predict the change of the electrical performance of the antenna under the temperature load

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  • Space mesh reflector antenna temperature load analysis method based on electromechanical coupling model
  • Space mesh reflector antenna temperature load analysis method based on electromechanical coupling model
  • Space mesh reflector antenna temperature load analysis method based on electromechanical coupling model

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Embodiment Construction

[0050] Attached below figure 1 , the specific embodiment of the present invention is described in further detail:

[0051] The invention provides a method for analyzing the temperature load of a space mesh reflector antenna based on an electromechanical coupling model, comprising the following steps:

[0052] Step 1, input the parameters provided by the user including the geometric parameters, material parameters and electrical parameters of the space mesh reflector antenna, where the geometric parameters include aperture, focal length, offset distance, minimum distance between the front and rear mesh surfaces, and the material parameters include Material density, cross-sectional area, Young's modulus of elasticity, Poisson's ratio of cable structure, truss structure and wire mesh structure, as well as specific heat capacity, thermal conductivity coefficient, thermal expansion coefficient, surface emissivity, absorptivity, electrical parameters including operating wavelength, ...

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Abstract

The invention discloses a space mesh reflector antenna temperature load analysis method based on an electromechanical coupling model. The method comprises the specific steps of 1, inputting antenna geometric parameters, material parameters and electric parameters; 2, building an antenna structure finite element model; 3, building an antenna heat finite element model; 4, setting a boundary condition; 5, selecting a track; 6, calculating a temperature field; 7, loading temperature field loads; 8, calculating thermal deformation; 9, outputting thermal deformation displacement; 10, calculating facet phase errors; 11, adopting an electromechanical coupling model for calculating an antenna far field electric field; 12, judging whether the electric performance meets the requirement or not; 13, outputting an antenna structural design scheme or 14, updating antenna parameters, and the step 1 continues to be executed. Based on the electromechanical coupling model, temperature load analysis is performed on the space mesh reflector antenna, space mesh reflector antenna electric performance analysis and electromechanical integration optical design can be guided.

Description

technical field [0001] The invention belongs to the technical field of radar antennas, in particular to an electromechanical coupling model-based temperature load analysis method for space mesh reflector antennas in the field of radar antennas. Background technique [0002] Mesh reflector antennas are gradually used in space antenna design due to their light weight and small folded volume. During the operation of the mesh reflector antenna in orbit, it is periodically affected by space radiation heat, and the deformation of the antenna surface caused by thermal deformation has a great impact on the electrical performance of the antenna. The antenna surface error caused by thermal deformation will cause the antenna gain to decrease, the side lobe level to increase, and the beam to tilt, which will seriously affect the performance of the antenna. Therefore, from the perspective of electromechanical coupling, it is necessary to analyze the temperature load of the space mesh re...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/23
Inventor 张树新段宝岩宋立伟李鹏杜敬利张逸群杨东武杨癸庚
Owner XIDIAN UNIV
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