Satellite autonomous orbit determination method based on satellite-borne GNSS multiple antennas

An autonomous orbit determination and multi-antenna technology, applied in satellite radio beacon positioning systems, radio wave measurement systems, integrated navigators, etc., to achieve high orbit determination accuracy and wide application range

Active Publication Date: 2014-03-26
SPACE STAR TECH CO LTD
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Problems solved by technology

[0005] The technical solution of the present invention is to overcome the deficiencies of the prior art and provide a satellite autonomous orbit determination method based on satellite-borne GNSS multi-antenna. Antenna orbit determination, this method has a wider range of applications and has great engineering practical value and military strategic significance

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  • Satellite autonomous orbit determination method based on satellite-borne GNSS multiple antennas
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  • Satellite autonomous orbit determination method based on satellite-borne GNSS multiple antennas

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Embodiment Construction

[0041] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0042] The present invention provides a real-time orbit determination method based on space-borne GNSS multi-antenna. This technology fully uses the GNSS observations of each antenna for real-time filtering processing to ensure that the GNSS receiver outputs high-precision navigation and positioning results. Compared with single-antenna orbit determination, This method has a wider scope of application and has great engineering practical value and military strategic significance.

[0043] Such as figure 1 Shown, concrete steps of the present invention are as follows:

[0044] A satellite autonomous orbit determination method based on satellite-borne GNSS multi-antenna comprises steps as follows:

[0045] (1) The autonomous orbit determination starts, and the system is initialized (setting the initial value of the global variable).

[0...

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Abstract

A satellite autonomous orbit determination method based on satellite-borne GNSS multiple antennas. According to the method, a Kalman filter is extended; multiple GNSS antennas measured pseudorange observation values are made full use of to carry out real-time filtering correction of an orbit prediction value using a high precision mechanical model; and high precision satellite orbit information is obtained. According to the invention, the problems of the high precision orbit determination in a complex posture maneuver can be solved. In the invention, the orbit determination result is high in precision, good in stability, and highly real-time, can meet the orbit determination demand of the low orbit satellite and high precision satellite, can be widely applied to the high precision orbit determination of the space station, high resolution earth observation satellite and other space missions, and has a wide promotion and application prospect.

Description

technical field [0001] The invention relates to a method for satellite autonomous orbit determination based on satellite-borne GNSS multi-antennas, which can solve the problem of high-precision orbit determination in the case of complex attitude maneuvers, and belongs to the technical field of satellite autonomous orbit determination. Background technique [0002] With the rapid development of satellite application technology, in order to complete corresponding scientific tasks, satellites need to have three-axis attitude and large-angle agile maneuverability. In Agile mode, the GNSS receiver should be able to maintain a fixed position. However, under large-angle three-axis attitude maneuvering, if a low-orbit satellite uses only one GNSS antenna, its main lobe cannot always point to the zenith, and may even point to the center of the earth, seriously affecting the normal operation of the GNSS receiver. [0003] On the other hand, there are many loads and antennas on the en...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01S19/36G01S19/23G01C21/24
CPCG01C21/24G01S19/33
Inventor 张万威陈姗姗王杰徐其超王甫红
Owner SPACE STAR TECH CO LTD
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