Atmospheric resistance perturbation modeling and calculating method for low earth orbit satellite

A technology for atmospheric drag and low-orbit satellites, which is applied to integrated navigators, instruments, adaptive control, etc., can solve problems such as atmospheric drag perturbation calculation errors, and achieve the goal of improving orbit determination accuracy and overcoming atmospheric drag perturbation calculation errors. Effect

Active Publication Date: 2020-06-05
CHINA XIAN SATELLITE CONTROL CENT
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Problems solved by technology

[0009] The purpose of the present invention is to provide a low-orbit satellite atmospheric resistance perturbation modeling and calculation method, which solves the problem that a single atmospheric resistance factor in the prior art is difficult to accurately describe the calculation error of atmospheric resistance perturbation caused by atmospheric changes

Method used

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  • Atmospheric resistance perturbation modeling and calculating method for low earth orbit satellite
  • Atmospheric resistance perturbation modeling and calculating method for low earth orbit satellite
  • Atmospheric resistance perturbation modeling and calculating method for low earth orbit satellite

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Embodiment

[0051] A low-orbit satellite atmospheric resistance perturbation modeling and calculation method of the present invention is specifically combined with the precise orbit determination process of the satellite for description, as shown in figure 1 shown.

[0052] 1. Measurement data preprocessing

[0053] Collect the measurement data Z of the low-orbit satellites from the ground tracking equipment, preprocess the measurement data on the selected orbit determination arc, and eliminate the gross errors and outliers in the measurement data to obtain the orbit determination observation value

[0054] 2. Set the initial rough track Y * , Atmospheric resistance factor C of each node d,i :

[0055] The initial rough orbit of the satellite is obtained by the initial orbit determination process of the satellite, and the general accuracy is about 1km or worse. The initial rough orbit of the satellite is used as the initial value of the satellite orbit state parameters in the iterati...

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Abstract

The invention discloses an atmospheric resistance perturbation modeling and calculating method for a low earth orbit satellite. The method is specifically implemented according to the following steps:1, establishing a Box-Wing model of a satellite; 2, establishing a piecewise linear atmospheric resistance perturbation model; 3, according to the Box-Wing model established in the step 1 and the piecewise linear atmospheric resistance perturbation model established in the step 2, calculating the folded atmospheric resistance perturbation acceleration at the moment t. By utilizing the method to calculate the atmospheric resistance perturbation of the satellite, atmospheric resistance perturbation calculation errors caused by the fact that a traditional single atmospheric resistance factor isdifficult to accurately describe atmospheric changes can be overcome, the orbit determination precision is effectively improved, and technical support is provided for precise orbit determination of alow-orbit satellite, especially precise orbit determination under special conditions such as magnetic storm.

Description

technical field [0001] The invention belongs to the technical field of low-orbit satellite precision orbit determination, and relates to a low-orbit satellite atmospheric resistance perturbation modeling and calculation method. Background technique [0002] The wide application of satellite technology has put forward higher and higher requirements for the accuracy of satellite orbit determination. The accuracy of satellite orbit determination mainly depends on two factors, one is the quality of measurement data, and the other is the adopted orbit determination strategy and method. In a high-precision measurement system, the accuracy of the satellite dynamic model is often difficult to meet the accuracy requirements. It is necessary to increase the estimated atmospheric drag factor, solar light pressure coefficient, or introduce periodic empirical force, or even use a simplified dynamic method in the process of precise orbit determination. On the other hand, when the error o...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24G05B13/04G05D1/10
CPCG01C21/24G05B13/045G05D1/10
Inventor 王家松陈建荣朱俊何雨帆王彦荣王冲呼延宗泊李杰刘斌
Owner CHINA XIAN SATELLITE CONTROL CENT
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