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Top combination polarity testing device and use method thereof

A polarity test and gyro technology, used in the field of spacecraft testing, can solve the problems of large curve jitter, unable to control the rotation angular rate, limited angle range, etc., to ensure safety, improve test efficiency and accuracy.

Pending Publication Date: 2022-04-12
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

However, the above-mentioned polarity test method has the following disadvantages: 1. It is dangerous, and generally two people are required to cooperate in the operation for safety and security; Identify the input angular velocity; 3. Due to the limited physical strength and control ability of human beings, it is impossible to control the angular rate of rotation well, and it often occurs that the gyro combination identification is intermittent and the degree of curve jitter is too large.

Method used

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  • Top combination polarity testing device and use method thereof
  • Top combination polarity testing device and use method thereof

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Embodiment Construction

[0038] A gyroscope combined polarity testing device and its usage method proposed by the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. The advantages and features of the present invention will become clearer from the following description. It should be noted that the drawings are in a very simplified form and all use imprecise scales, which are only used to facilitate and clearly assist the purpose of illustrating the embodiments of the present invention. In order to make the objects, features and advantages of the present invention more comprehensible, please refer to the accompanying drawings. It should be noted that the structures, proportions, sizes, etc. shown in the drawings attached to this specification are only used to match the content disclosed in the specification, for those who are familiar with this technology to understand and read, and are not used to limit the implementation ...

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Abstract

The invention discloses a gyroscope combination polarity testing device and a use method thereof, and the gyroscope combination polarity testing device comprises a shell; the platform assembly is arranged on the shell and is used for bearing a gyroscope combination; the transmission mechanism comprises a worm, is positioned in the shell and is rotationally connected with the side wall of the shell; the worm gear is positioned above the worm and is respectively connected with the worm and the platform assembly; and the worm rotates to drive the worm gear and the platform assembly to rotate so as to carry out polarity test on the gyroscope combination. According to the invention, the polarity test of the gyroscope combination can be rapidly, easily and stably completed through the worm and worm gear type transmission mechanism, so that the test efficiency and precision are improved, and the labor cost is effectively reduced.

Description

technical field [0001] The invention relates to the technical field of spacecraft testing, in particular to a gyroscope combined polarity testing device and a using method thereof. Background technique [0002] As the angular rate sensor of the spacecraft, the gyro combination can directly measure the three-axis inertial angular rate of the satellite; at the same time, it can be used in conjunction with the star sensor and other angle sensors to provide important real-time control feedback information for the attitude maneuver and stability control of the spacecraft. . For the attitude control system of the spacecraft, the polarity test of the sensor and the actuator is an important link to ensure the correct operation of the attitude control system. [0003] For the polarity test method of the gyro combination, at this stage, it is mainly to manually lift the gyro combination stand-alone and rotate it around a certain axis, so as to simulate the rotation direction of the s...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00
Inventor 王同辉史康李德婷黄用高四宏
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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