Method for measuring installation attitude of spacecraft high-precision instrument based on laser tracker

Abstract

The invention provides a method for measuring the installation attitude of a spacecraft high-precision instrument based on a laser tracker, and the method comprises the following steps: enabling an absolute laser tracker with an automatic target locking function to be installed on an automatic guide trolley, and enabling the laser tracker and the automatic guide trolley to move together; moving the laser tracker to a preset measurement position through the automatic guide trolley; and reserving three measurable target spots which are not located on the same straight line on a mounting base of the instrument to be measured and used for placing an optical pyramid mirror, and measuring parameter measurement values by utilizing a laser tracker respectively, so that the position of the bottom surface of the instrument to be measured in a geodetic coordinate system can be obtained. Compared with the traditional method for measuring the pose of the reference cubic mirror by using three to four theodolites, the measurement method disclosed by the invention only needs one laser tracker and one automatic guide trolley, so that the cost is greatly reduced, the mutual aiming of a plurality of theodolites is avoided, the light path shielding in the mutual aiming process of the theodolites does not need to be considered, and the measurement precision and the measurement efficiency are improved.

Description

technical field [0001] The invention relates to the technical field of industrial measurement, in particular to a method for measuring the installation attitude of a high-precision instrument of a spacecraft based on a laser tracker. Background technique [0002] With the development of economy and technology, spacecraft represented by communication satellites have begun to be commercialized and mass-produced, and satellite Internet has officially been included in the scope of new infrastructure. There is an urgent need to improve the efficiency of spacecraft manufacturing and reduce manufacturing costs. The measurement method of traditional spacecraft high-precision instruments is relatively simple. Three to four theodolites are used to build a station to measure the pose of the reference cubic mirror to recheck the installation accuracy of the instrument. The measurement and debugging cycle is long and the cost is high. [0003] After searching, the patent document CN10474...

AI Technical Summary

Problems solved by technology

Although this prior art overcomes the improvement in the control of thermal deformation of the structure, the disadvantage is that it still cannot efficiently improve the installation accuracy of the re-inspection instrument

Although the measurement method of this prior art saves a gyro theodolite, a lot of data still needs to be measured, and can combine several data to calculate the attitude angle of the measured reference cubic mirror relative to the geodetic coordinate system

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