Method for measuring posture angle of base cubic mirror based on gyro theodolite

A technology for measuring benchmarks and theodolite, which is applied in directions such as navigation through speed/acceleration measurement, and can solve problems such as reduced accuracy and difficult implementation

Inactive Publication Date: 2015-01-07
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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Problems solved by technology

The second method reduces the cost and improves the measurement efficiency due to the use of an electronic theodolite to collimate and measure one of the mirrors, but this method requires mutual aiming between the electronic theodolite and the gyro theodolite, thus reducing the accuracy, and in some Under complex on-site working conditions, it is difficult to implement because the mutual aiming optical path is blocked

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  • Method for measuring posture angle of base cubic mirror based on gyro theodolite
  • Method for measuring posture angle of base cubic mirror based on gyro theodolite

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[0044] The following introduces the specific implementation mode as the content of the present invention, and the content of the present invention will be further clarified through the specific implementation mode below. Of course, the following specific embodiments are described only to illustrate different aspects of the present invention, and should not be construed as limiting the scope of the present invention.

[0045] Commercially available gyro theodolites include three measurable parameters, namely azimuth, zenith distance and horizontal angle, and electronic theodolites include two measurable parameters, namely horizontal angle and zenith distance. Orthogonal reference cubes consist of six faces, four adjacent side faces and upper and lower opposite top and bottom faces, see for example figure 1 . The collimating surfaces of the present invention are the side surfaces of the reference cubic mirror instead of the top surface and the bottom surface.

[0046] Such as...

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Abstract

The invention discloses a method for measuring the posture angle matrix of a base cubic mirror, relative to a geodetic coordinate system based on a gyro theodolite. The method comprises the following steps: firstly, measuring any two adjacent side surfaces of the base cubic mirror in an alignment manner by the gyro theodolite and an electronic theodolite respectively to obtain the azimuth angle and zenith distance of the gyro theodolite in the alignment direction and the zenith distance of the electronic theodolite in the alignment direction; secondly, calculating through a vertical relationship between the two surfaces to obtain the azimuth angle of the electronic theodolite in the alignment direction; finally, obtaining the posture angle matrix of the base cubic mirror, relative to the geodetic coordinate system. According to the method, one gyro theodolite is omitted, so that the cost is reduced; meanwhile, the mutual alignment between a general theodolite and the gyro theodolite is avoided, so that the measurement precision and efficiency are improved, and the light path shielding during mutual alignment under the complicated working condition is prevented.

Description

technical field [0001] The invention belongs to the technical field of industrial measurement, and specifically relates to a method for comprehensively utilizing a gyro theodolite and an electronic theodolite to measure the attitude angle of a reference cubic mirror relative to a geodetic coordinate system. North measurements as well as relative attitude angle measurements between devices. Background technique [0002] In the integrated manufacturing and testing process of modern large-scale precision systems represented by the spacecraft assembly test, it is necessary to precisely measure the attitude angle of the inertial equipment relative to the earth coordinate system. The inertial equipment under test usually uses a reference cubic mirror to characterize the body coordinate system of the device, and uses three mutually orthogonal plane mirror normals on the cube mirror to represent the coordinate axis orientation of the device body coordinate system. Therefore, measur...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/18
CPCG01C21/18
Inventor 杨再华马强易旺民万毕乐闫荣鑫郭洁瑛阮国伟刘浩淼任春珍陶力刘涛段晨旭
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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