Satellite attitude determination method and system based on Samsung sensor

A star sensor and satellite attitude technology, applied in attitude control, instruments, aircraft, etc., can solve the problem of not fully utilizing effective resources, achieve high reliability, easy implementation, and reduce the effect of attitude determination error

Inactive Publication Date: 2017-06-27
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

[0003] At present, the domestic satellite attitude measurement system is generally equipped with 3 to 4 star sensors, but the measurement data of 1 or 2 star sensors are generally introduced in the process of satellite attitu

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  • Satellite attitude determination method and system based on Samsung sensor
  • Satellite attitude determination method and system based on Samsung sensor
  • Satellite attitude determination method and system based on Samsung sensor

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Embodiment Construction

[0046] Specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0047] like figure 1 As shown, a method for determining satellite attitude based on a Samsung sensor is disclosed, and the method specifically includes the following steps:

[0048] S1. Calculate the components of the optical axis vectors of the three star sensors in the satellite body coordinate system.

[0049] When the installation error is not considered, the installation matrices of any three star sensors 1, 2, and 3 in the satellite body coordinate system are C b1 、C b2 and C b3 .

[0050] Accordingly, the components of the optical axis vectors of the three star sensors in the satellite body coordinate system are obtained, as shown in formula (1):

[0051]

[0052] In formula (1), Indicates the component of the #sensor optical axis vector in the & coordinate system, where i represents the inertial coordinate system, b represents ...

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Abstract

The invention discloses a satellite attitude determination method based on a Samsung sensor. The method comprises the steps of obtaining a matrix of optical axis vectors of three star sensors under a satellite ontology coordinate system; obtaining the matrix of the optical axis vectors of the three star sensors under inertial system coordinates; and based on a transformation matrix of the inertial system coordinates and the satellite ontology coordinate system and a transformation matrix of an orbit coordinate system to the inertial coordinate system, obtaining an attitude matrix of the orbit coordinate system to the satellite ontology coordinate system. The method of the invention is applicable to the installation of the satellites with three or more star sensors, can make full use of on-board resources, can compensate the shortcoming of poor precision of the single-star sensor optical axis, avoids the introduction of a cross-product vector in a double star sensor attitude determination algorithm, reduces attitude determination errors, and is high in reliability, simple in algorithm, and easy in on-board software implementation.

Description

technical field [0001] The invention relates to satellite high-precision attitude determination technology, in particular to a satellite attitude determination method and system based on three-star sensors, which are suitable for satellites installed with three or more star sensors. Background technique [0002] With the expansion of spaceborne earth observation missions, higher and higher requirements are put forward for the control accuracy and stability of satellites, especially for the pointing accuracy of satellites. In order to ensure the pointing accuracy of the satellite, it is necessary to use a high-precision attitude determination algorithm to ensure the accuracy of the satellite attitude calculation. High-precision attitude determination technology usually uses star sensors to complete attitude calculation. However, the attitude measurement error of the star sensor is larger in the direction of the optical axis and smaller in the direction of the vertical optica...

Claims

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Application Information

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IPC IPC(8): G05D1/08G01C21/00
CPCB64G1/244G01C21/00
Inventor 郭思岩张涛王文妍张艳召陈为伟
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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