Satellite formation initial positioning algorithm based on relative position vector measurement

A relative position vector and satellite formation technology, which is applied in the direction of aerospace vehicle guidance devices, integrated navigators, etc.

Active Publication Date: 2021-01-01
BEIHANG UNIV
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Problems solved by technology

And these filtering methods all need a relatively accurate initial value of the system state quantity

Method used

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  • Satellite formation initial positioning algorithm based on relative position vector measurement
  • Satellite formation initial positioning algorithm based on relative position vector measurement
  • Satellite formation initial positioning algorithm based on relative position vector measurement

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Embodiment Construction

[0097] The following will be combined with figure 1 And technical scheme, take the satellite cluster that three stars A, B, C form as example, the concrete implementation process of the present invention is described in further detail.

[0098] Step 1: Characterize the relative position change by adaptive polynomial fitting

[0099] The invention adopts a method of polynomial fitting to a series of relative position vector measurement data to characterize the relative motion between the stars, and then obtains the relative acceleration information between the stars. By analyzing the change trend of the sum of squares of fitting residuals between different fitting orders, the invention provides an adaptive fitting criterion for selecting an adaptive fitting order. The fitting residual sum of squares is defined as:

[0100]

[0101] According to the rate of change of the sum of squares of residuals between adjacent fitting orders as the selection index of the fitting order,...

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Abstract

The invention provides a satellite formation initial positioning algorithm based on relative position vector measurement. According to the algorithm, the absolute position of the satellite formation is obtained through inverse solution by combining the inter-satellite relative acceleration with the gravitational field model. An adaptive polynomial fitting algorithm for obtaining the inter-satellite relative acceleration by fitting relative measurement data is developed. And a judgment basis for selecting different navigation calculation modes is provided. The navigation result can be used as asatellite state quantity initial value for subsequent precision orbit determination. The algorithm does not depend on external information at all, and has the advantages of high autonomy and strong adaptability.

Description

technical field [0001] The invention provides a completely autonomous satellite formation initial positioning algorithm that does not need external measurement information. It involves an adaptive fitting order polynomial fitting algorithm for extracting relative acceleration from a series of inter-satellite relative position vectors, and a navigation calculation algorithm based on inter-satellite relative motion characteristics, including navigation calculation mode selection criteria and global / local search algorithms. It belongs to the field of navigation technology. Background technique [0002] Satellite formation (also known as distributed satellite system), as an innovative concept in the aerospace field, represents an important direction of aerospace technology research. Compared with a single satellite, satellite formation has improved functions and performance due to its larger number of satellites, and has great application flexibility and safety, so it has beco...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24B64G1/24
CPCG01C21/24B64G1/24
Inventor 孙秀聪耿铖贾振俊陈培
Owner BEIHANG UNIV
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