Spacecraft attitude determination method and system based on inter-satellite measurement information
A technology for measuring information and determining methods, applied in the field of spacecraft attitude determination, can solve the problems of not making full use of effective resources on the planet, and achieve the effect of light weight, simple and clear principle, and easy realization
Active Publication Date: 2020-10-30
INNOVATION ACAD FOR MICROSATELLITES OF CAS +1
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Problems solved by technology
[0003] The object of the present invention is to provide a spacecraft attitude determination method and system based on inter-satellite measurement information, to solve the problem that the existing attitude determination accuracy method does not make full use of effective resources on the star
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Embodiment 1
[0081] Embodiments of the present invention provide a spacecraft attitude determination method based on inter-satellite measurement information, such as figure 1 As shown, the spacecraft attitude determination method based on inter-satellite measurement information includes: measuring the orbital information of the local star and the target star, and obtaining the relative position information between the local star and the target star; Alignment-related parameters are converted into inter-satellite vectors representing the attitude characteristics of the spacecraft; directly obtain the measurement information of the attitude sensor on the star; through two-vector attitude determination, the relative position information, the inter-satellite vector and the The measurement information is fused to form spacecraft attitude information, and the three-axis attitude of the spacecraft is determined according to the spacecraft attitude information.
[0082] Specifically, in the spacec...
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The invention provides a spacecraft attitude determination method and system based on inter-satellite measurement information. The method comprises the steps of measuring the orbit information of a local satellite and a target satellite, and obtaining the relative position information between the local satellite and the target satellite, converting parameters related to sight line axis alignment of the inter-satellite measurement photoelectric equipment into inter-satellite vectors representing attitude characteristics of the spacecraft, directly acquiring measurement information of an attitude sensor on the local satellite, and through double-vector attitude determination, fusing the relative position information, the inter-satellite vector and the measurement information to form spacecraft attitude information, and determining the three-axis attitude of the spacecraft according to the spacecraft attitude information.
Description
technical field [0001] The invention relates to the technical field of spacecraft attitude determination, in particular to a method and system for determining the attitude of a spacecraft based on inter-satellite measurement information. Background technique [0002] In the existing literature, some literatures research the GPS-like multi-spacecraft cooperative navigation for cooperative targets through inter-satellite communication, and some literatures use gyroscope and inter-satellite measurement information, combined with filtering methods, for non-cooperative targets. Relative navigation and relative attitude determination of non-cooperative targets are studied. It can be seen that the existing literature focuses on how to use the inter-satellite measurement information and other sensor information on the star to determine the relative attitude between the local star and the target star, while ignoring that the inter-satellite measurement information is actually related...
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Login to View More IPC IPC(8): G01C21/24
CPCG01C21/24
Inventor 陈婷容建刚张科科刘善伍王俊孙国文
Owner INNOVATION ACAD FOR MICROSATELLITES OF CAS