A Method of Attitude Determination Based on Fusion of Measurement Information from Multiple Star Sensors

A technology of star sensor and determination method, which is applied in the direction of integrated navigator and so on

Active Publication Date: 2018-01-05
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0005] The technical problem of the present invention is: to overcome the deficiencies of the prior art, to propose a high-precision attitude determination method based on the fusion of multiple star sensor measurement information, and to solve the problem of using multiple star sensor measurement information fusion to achieve high-precision attitude determination The problem

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  • A Method of Attitude Determination Based on Fusion of Measurement Information from Multiple Star Sensors
  • A Method of Attitude Determination Based on Fusion of Measurement Information from Multiple Star Sensors

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[0054] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0055] Such as figure 1 Shown, the concrete realization process of the present invention is as follows:

[0056] (1) The spacecraft uses star sensors to determine its attitude during orbital flight. In order to achieve high-precision attitude determination, the spacecraft is equipped with N (N≥2) star sensors, and two of them are selected when determining the attitude. A star sensor, denoted by star sensor A and star sensor B respectively, wherein the attitude measurement result obtained by star sensor A in an attitude determination period ΔT is denoted by q mAi Indicates that the time for each attitude acquisition is t mAi Indicates that q mAi =[q mA1i q mA2i q mA3i q mA4i ] T , i=1~N A ; The attitude measurement result corresponding to star sensor B is represented by q mBi =[q mB1i q mB2i q mB3i q mB4i ] T Indicates tha...

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Abstract

An attitude determination method based on multiple star-sensor measure information fusion is disclosed and is applicable to attitude determination of spacecrafts with high-precision attitude determination requirement, and the attitude output frequency of a star sensor is larger than the attitude determination period of a spacecraft. The disclosed method is different from a conventional method of directly using the star sensor for attitude measurement outputting, concretely, after multiple star sensor measurement results are obtained within one attitude determination period, data fusion of the star sensor measurement results is performed according to weight, and the weight coefficient value is related to the star time difference of the star sensor measurement time and the current attitude determination time. Therefore, the method is capable of optimizing the fusion result when data fusion is performed, and satisfies high-precision demand on attitude determination in the field of spacecraft application.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude control, and relates to an attitude determination method based on the fusion of measurement information of multiple star sensors. Background technique [0002] With the continuous development of spacecraft technology, higher requirements are put forward for the accuracy of spacecraft attitude determination and attitude control, among which high-precision attitude control is also based on high-precision attitude determination. High-precision attitude determination depends on high-precision attitude sensors. For example, the existing high-precision attitude determination systems use high-precision star sensors to obtain the attitude of the spacecraft. The star sensor measures the angle between the known star line of sight and the reference axis by being sensitive to stellar radiation. It is a high-precision inertial absolute attitude sensor. Generally, the optical axis measurement accuracy of the ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/24
CPCG01C21/24
Inventor 田科丰王新民刘一武董筠褚永辉刘其睿张斌曾春平李鹤
Owner BEIJING INST OF CONTROL ENG
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