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Satellite attitude determination precision evaluation method and system

A technology for satellite attitude and accuracy assessment, applied in measurement devices, instruments, etc., to achieve the effect of improving satellite design, wide application range and small resource occupation

Pending Publication Date: 2022-02-25
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology

[0009] The installation angles of the two star sensors are limited, and they can only be installed symmetrically with respect to the YOZ plane of the satellite system;

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  • Satellite attitude determination precision evaluation method and system
  • Satellite attitude determination precision evaluation method and system
  • Satellite attitude determination precision evaluation method and system

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Embodiment Construction

[0084] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0085] In this embodiment, the number of star sensors configured is 3, which are respectively star sensors A, star sensors B, and star sensors C. In practical applications, as long as the number of star sensors is greater than or equal to 2, the method of the present invention can be used, as figure 1 and figure 2 shown.

[0086] In S1, the on-board computer obtains the original quaternion observations of the three star sensors through the on-board data transmission bus, and at the same time solves the satellite attitude quaternion in real time, and periodically sends the original measurement quaternion of each star sensor with time scale Q A , Q B , Q C The satellite attitude quaternion Q is transmitted to the on-board data transmission unit through the on-board data bus, and then transmitted to the ground data transmission recei...

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Abstract

The invention relates to a satellite attitude determination precision evaluation method and system. The method comprises the steps: collecting the quaternion original measurement data of all two or more star sensors installed on a satellite through a satellite-borne computer, downloading the original measurement data of all the star sensors and the satellite attitude quaternion determined by the on-satellite computer in real time to the ground through a data transmission channel; acquiring the inertial attitude angular velocity of the three axes of the satellite and the inertial attitude angular velocity of the three axes of each star sensor during the evaluation period; processing the obtained original measurement data of the star sensor and the attitude quaternion determined on the satellite in real time to further obtain a high-frequency part and a low-frequency trend term in measurement errors of the two kinds of data; processing the high-frequency part of the measurement error to obtain a satellite attitude determination high-frequency error evaluation standard and an evaluation result; and processing the measurement error low-frequency trend term to obtain a star sensor installation reference stability evaluation result, a satellite attitude determination low-frequency error evaluation standard and an evaluation result.

Description

technical field [0001] The invention relates to a method and system for assessing satellite attitude determination accuracy, which belongs to the technical field of satellite on-orbit performance evaluation, and can be applied to rapid assessment of attitude determination accuracy after a satellite enters orbit. Background technique [0002] With the continuous improvement of the satellite payload attitude determination accuracy requirements of space missions, the attitude measurement accuracy of the satellite configuration sensors is also getting higher and higher. At present, the star sensor is the sensor with the highest attitude measurement accuracy on almost all satellites, but the satellite attitude determination accuracy based on the star sensor measurement still lacks a general, effective and quick evaluation method. [0003] Most low-orbit remote sensing satellites indirectly evaluate the accuracy of satellite attitude determination through satellite-ground joint ca...

Claims

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Application Information

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IPC IPC(8): G01C25/00
CPCG01C25/00
Inventor 王家炜莫凡景泉陈曦李少辉刘希刚高洪涛赵利民张晓峰黄宇飞
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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