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Real-time high precision satellite structure thermal deformation measurement method

A real-time measurement, satellite structure technology, applied in the testing of machine/structural components, measurement devices, material thermal analysis, etc., can solve the problem of inability to meet real-time measurement of thermal deformation, and achieve light weight, small structural impact, and small volume. Effect

Inactive Publication Date: 2018-04-06
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

However, none of them can meet the purpose of real-time measurement of thermal deformation

Method used

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  • Real-time high precision satellite structure thermal deformation measurement method
  • Real-time high precision satellite structure thermal deformation measurement method
  • Real-time high precision satellite structure thermal deformation measurement method

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Embodiment Construction

[0026] The present invention will be described in further detail below in conjunction with the accompanying drawings, but this is only exemplary and not intended to limit the protection scope of the present invention.

[0027] figure 1 In the method of the present invention, the radio frequency displacement label is pasted on the surface of the satellite structure plate under test. In the diagram of the radio frequency displacement label point, the black circle represents the radio frequency displacement label point, and the white circle represents the temperature sensor. Take the tested structural board with a size of 500mm*300mm as an example, on the front of the board, 15 RF antennas with RF displacement tags are uniformly pasted, and a temperature sensor is pasted next to it to monitor the temperature at this point. A radio frequency displacement label point is pasted on the fixed bracket of the structural plate, and this point is used as a reference point to eliminate the...

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Abstract

The invention discloses a real-time high precision satellite structure thermal deformation measurement method. The method comprises steps that radio frequency antennas of multiple radio frequency displacement labels are uniformly pasted on the surface of a measured satellite structure board, and a reception radar sensor is further mounted and fixed so that all the radio frequency displacement labels are in the visual field of a radar device; a heating plate is utilized to heat the measured satellite structure board, the position information and the displacement information of each label calculated by the radar sensor are acquired through a computer, the temperature information of a temperature sensor is further acquired, and least square fitting is utilized to calculate the deformation distribution diagram of the measured structure board surface changing along with the temperature. The method is advantaged in that thermal deformation measurement requirements of multiple types of satellite structure materials including carbon fiber materials, aluminum alloy and titanium alloy and so on can be satisfied, measurement precision is better than 0.05mm, and the measurement sampling frequency can reach 10kHZ.

Description

technical field [0001] The invention belongs to the technical field of industrial measurement, and in particular relates to a real-time high-precision measurement method for thermal deformation of a satellite structure combined with a displacement tag and a displacement measurement radar. The method is mainly used in the field of aerospace precision measurement. Background technique [0002] The on-orbit dimensional stability of the satellite structure is an important factor for the improvement of the satellite's function. The temperature change of the on-orbit environment will cause the deformation of the satellite structure, which will not only affect the health of the satellite itself, but even affect the normal operation of the satellite payload in severe cases. Structural deformation monitoring of satellites can be used to improve the structural design of spacecraft and provide a basis for active control, which is of great significance to ensure the long-term effective o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01B15/06G01N25/00G01M99/00
CPCG01B15/06G01M99/002G01N25/00
Inventor 陶力阮国伟刘笑隆昌宇张禹杭段城旭郭洁瑛金帮华任春珍
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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