Three-axis gyro polarity testing method based on whole satellite motion

A polarity test and gyro technology, applied in the field of testing, can solve problems such as data that have not yet been collected, and achieve the effect of increasing test coverage, ensuring accuracy, and simplifying the test process

Inactive Publication Date: 2017-05-31
SHANGHAI SATELLITE ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Foreign GOES-N, GOES-R, and Eurostar E3000 satellite platforms also use a large number of gyroscopes as attitude measurement components, but similar data have not been collected

Method used

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  • Three-axis gyro polarity testing method based on whole satellite motion
  • Three-axis gyro polarity testing method based on whole satellite motion

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Embodiment Construction

[0032] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0033] Such as figure 1 As shown, the present invention is based on the three-axis gyro polarity testing method of whole star motion and comprises the following steps:

[0034] Step 1: Set the satellite 2 in the mode of using gyroscopes for attitude measurement, set the attitude control system to be fully healthy, disable FDIR, and set a group of three mutually perpendicular gyroscopes to be on duty;

[0035] Step 2: Control the two-axis turntable 1 to make the satellite rotate around the rolling...

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Abstract

The invention provides a three-axis gyro polarity testing method based on a whole satellite motion. The method comprises the following steps: 1, setting a satellite in a mode of performing attitude measurement by using a gyro; 2, controlling a two-axis turntable to enable the satellite to forwards rotate at angular velocity of 0.05 degree per second around a rolling shaft, and observing the three-axis angular velocity of the satellite downloaded by remote measuring in the rotating process; 3, controlling the two-axis turntable to enable the satellite to reversely rotate at angular velocity of -0.05 degree per second around the rolling shaft; 4, controlling the two-axis turntable to enable the satellite to forwards rotate at angular velocity of 0.05 degree per second around a yaw axis; 5, controlling the two-axis turntable to enable the satellite to reversely rotate at angular velocity of -0.05 degree per second around the yaw axis; 6, controlling the two-axis turntable to rotate by 90 degrees around the yaw axis; 7, controlling the two-axis turntable to enable the satellite to reversely rotate at angular velocity of -0.05 degree per second around a pitch axis; 8, finally completing check and confirmation of polarities of all the gyros. According to the method disclosed by the invention, the accuracy of the satellite on-orbit gyro polarity is guaranteed.

Description

technical field [0001] The invention relates to a test method, in particular to a three-axis gyro polarity test method based on whole star motion. Background technique [0002] With the continuous development of applications, the accuracy requirements of satellite ground imaging are increasing day by day, and higher and higher requirements are put forward for the accuracy of attitude control and attitude determination of satellites. In order to achieve high-precision attitude control and attitude determination, it is necessary to use a high-precision star sensor and a high-precision gyroscope for combined attitude determination, and use the characteristics of high short-term accuracy of the gyroscope to measure the short-term attitude change of the satellite. [0003] When using a gyroscope to measure the angular velocity of a satellite, the following relationship is satisfied (1): [0004] WG=C·W………………………………(1) [0005] Among them, WG is the N row and column vector of the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 曾擎边志强陈晓杰王皓沈毅力
Owner SHANGHAI SATELLITE ENG INST
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