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Electromechanical integration optimization design method for space mesh antenna under action of temperature load

An optimization design, electromechanical integration technology, applied in design optimization/simulation, calculation, electrical digital data processing and other directions, can solve the problem of not considering the influence of the thermal deformation and electrical performance of the antenna, and it is difficult to predict the change of the electrical performance of the antenna.

Inactive Publication Date: 2017-03-22
XIDIAN UNIV
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  • Application Information

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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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  • Electromechanical integration optimization design method for space mesh antenna under action of temperature load
  • Electromechanical integration optimization design method for space mesh antenna under action of temperature load
  • Electromechanical integration optimization design method for space mesh antenna under action of temperature load

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Embodiment Construction

[0070] Attached below figure 1 , the specific embodiment of the present invention is described in further detail:

[0071] The invention provides an electromechanical integration optimization design method under the temperature load of a space mesh antenna, which includes the following steps:

[0072] Step 1. Input the parameters provided by the user including the geometric parameters, material parameters and electrical parameters of the space mesh antenna. The geometric parameters include the aperture, focal length, offset distance, and the minimum distance between the front and rear mesh surfaces. The material parameters include the cable structure , Material density, cross-sectional area, Young's modulus of elasticity, Poisson's ratio of truss structure and wire mesh structure, and specific heat capacity, thermal conductivity coefficient, thermal expansion coefficient, surface emissivity, absorptivity, electrical parameters including operating wavelength, feed source Param...

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Abstract

The invention discloses an electromechanical integration optimization design method for a space mesh antenna under the action of a temperature load. The design method comprises the specific steps of (1) inputting geometric parameters, material parameters and electric parameters of the antenna; (2) building a structural finite element model of the antenna; (3) building a thermal finite element model of the antenna; (4) setting a boundary condition; (5) selecting an orbit; (6) calculating a temperature field; (7) loading a temperature field load; (8) calculating thermal deformation; (9) outputting a thermal deformation displacement; (10) calculating an ideal far electric field of the antenna; (11) approximately calculating a change quantity of the far electric field of the antenna; (12) calculating the far electric field of the antenna; (13) judging whether electric performance meets a requirement or not; (14) outputting an antenna structure design scheme; and (15) updating the antenna parameters. According to the design method, the electric performance of the space mesh antenna under the action of the temperature load is analyzed by adopting the approximate calculation method, and the electromechanical integration optimization design of the antenna structure is realized.

Description

technical field [0001] The invention belongs to the technical field of radar antennas, and in particular relates to an electromechanical integration optimization design method of a space mesh antenna under temperature load in the field of radar antennas. Background technique [0002] Mesh antennas are gradually used in space antenna design due to their advantages of light weight and small folded volume. During the operation of the mesh 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, it is necessary to analyze the temperature load of the space mesh antenna in orbit, and propose an approximate calcu...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/23
Inventor 张树新杜敬利张岳震张顺吉张逸群宋立伟杨东武
Owner XIDIAN UNIV
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