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Measurement method of star attitude and solar wing deployment frame accuracy based on laser tracker

A technology of laser tracker and accuracy measurement, which is applied in the direction of measuring devices, instruments, and optical devices, etc., can solve unclear problems, achieve the effect of increasing diversity, increasing measurement methods, and improving system measurement accuracy

Inactive Publication Date: 2018-07-20
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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Problems solved by technology

[0005] The laser tracker is a precise three-coordinate measuring instrument that has appeared in recent years. It has the advantages of high measurement accuracy, large measurement range, real-time speed, and easy movement. It has been widely used in model precision measurement, but so far It has not been verified and used in the star attitude adjustment and the precise measurement of the solar wing deployment frame, and it is not clear how to use this device in the measurement of the solar wing deployment frame

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  • Measurement method of star attitude and solar wing deployment frame accuracy based on laser tracker
  • Measurement method of star attitude and solar wing deployment frame accuracy based on laser tracker

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Embodiment Construction

[0029] The method for measuring the attitude of a star based on a laser tracker and the precision of a solar wing deployment frame of the present invention will be described in detail below in conjunction with the accompanying drawings. These descriptions are only schematic and are not intended to limit the protection scope of the present invention.

[0030] The accuracy measurement method of the solar wing deployment frame includes the measurement method of the levelness and straightness of the guide rail of the solar wing deployment frame. see figure 1 , in a specific embodiment of the precision measurement of the solar wing deployment frame, a laser tracker 1 is set up at a position parallel to the direction of the solar wing deployment frame guide rail 7 and 2 meters to 3 meters away from one end of the solar wing deployment frame 2, and the laser tracker 1 The tracker 1 is leveled so that the vertical axis (Z axis) of the laser tracker coordinate system is perpendicular t...

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Abstract

The invention discloses a satellite attitude and solar wing spreading rack precision measuring method based on a laser tracker. When the solar wing is mounted on the satellite, the laser tracker is used to measure the yaw value, the pitching value, and the rolling value of the satellite, and the levelness and the linearity of the guide rail of the solar wing spreading rack. The satellite attitude and solar wing spreading rack precision measuring method is capable of breaking through the technology bottleneck of the dependence of the precision measurement of the satellite attitude and the solar wing spreading rack during the process of the solar wing mounted on the satellite only on a measuring method using a theodolite provided with a setover head, and then system measurement precision is increased from 0.2mm to 0.1mm, and therefore a requirement of realizing satellite attitude adjusting precision of 0.15mm is satisfied, difficulties generated during a model developing process is solved, and a measuring capability and measuring efficiency are improved.

Description

technical field [0001] The invention belongs to the technical field of industrial measurement, and in particular relates to a method for measuring the attitude of a star and the precision of a solar wing deployment frame based on a laser tracker. Background technique [0002] In the field of aerospace, the solar wing is an important device that converts solar energy into electrical energy and provides it to satellites. Whether it can work normally is related to the success or failure of space missions. Therefore, the normal work of the solar wing has always been highly concerned by the aerospace community. [0003] In the satellite final assembly stage, to ensure the normal operation of the solar wing, on the one hand, in order to ensure the accurate docking of the solar wing and the star, the attitude of the star must meet the design requirements; on the other hand, after the solar wing is installed on the satellite, , the time to start the test must also meet the design r...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01B11/26
Inventor 王伟任春珍李晓欢刘浩淼刘广通陶力阮国伟郭洁瑛刘笑
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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