Method for tracking ground station through low earth orbit space-borne antenna

A spaceborne antenna and ground station technology, applied in the direction of antennas, electrical components, etc., can solve the problem of calculating the pointing angle of the spaceborne antenna, which is not given, etc.

Active Publication Date: 2015-02-04
XIAN INSTITUE OF SPACE RADIO TECH
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  • Abstract
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Problems solved by technology

This document only does not give how to calculate the pointing angle of the spaceborne antenna to the ground station

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  • Method for tracking ground station through low earth orbit space-borne antenna
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  • Method for tracking ground station through low earth orbit space-borne antenna

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Embodiment Construction

[0062] First introduce the principle of the present invention:

[0063] (1) First solve the conversion between satellite time and UTC time used in orbit calculation. According to the sailing time provided by the satellite data management system, the UTC of the antenna pointing time is calculated by using Julian time.

[0064] (2) Due to the influence of orbit perturbation factors, there will be a large error in the accuracy of orbit prediction. For orbits below 800km, considering the complexity of the atmospheric model and the computing power of the on-board computer, the present invention considers the J 2 , J 3 , J 4 The perturbation item and atmospheric resistance perturbation compensation, use the satellite initial average orbital elements to calculate the satellite instantaneous orbital elements at the pointing time of the antenna.

[0065] (3) Complete the following calculations in sequence: calculate the position of the satellite in the J2000 inertial coordinate sys...

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Abstract

The invention provides a method for tracking a ground station through a low earth orbit space-borne antenna. The method comprises the following steps: 1) calculating UTC at the next pointing moment of the antenna; 2) calculating the number of transient satellite orbit at the next pointing moment of the antenna; 3) calculating the position of the satellite under a J2000 inertial coordinate system; 4) calculating the position of the ground station under the J2000 inertial coordinate system at the next pointing moment of the antenna; 5) calculating the opposite position vectors of the satellite and the ground station under the J2000 inertial coordinate system; 6) calculating the vector of the opposite position vectors of the satellite and the ground station under geo-center camber line; 7) calculating the vector of the opposite position vectors of the satellite and the ground station under the satellite orbit coordinate system; 8) calculating the vector of the opposite position vectors of the satellite and the ground station under a satellite body system; 9) calculating the vector of the opposite position vectors of the satellite and the ground station under an antenna coordinate system; 10) obtaining an antenna pointing angle, and driving the antenna to perform pointing tracking for the ground station.

Description

technical field [0001] The method relates to a method for a low-orbit satellite-borne antenna to track a ground station, especially requires high pointing accuracy, and belongs to the technical field of antenna control. Background technique [0002] With the increasing number of tasks such as spacecraft data relay, inter-satellite links, and high-resolution observation of the earth, the demand for terminal spot beam tracking antennas also increases. The spot beam tracking antenna is used to complete the pointing and tracking of the ground station, relay satellite or target star to achieve high-speed data transmission. Therefore, when the antenna aperture is constant, the antenna has higher gain and narrower beam width, and the tracking accuracy of antenna tracking is particularly important for the completion of the task. Tracking accuracy is composed of implementation error, installation error, attitude error, and thermal deformation, among which the implementation error of...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01Q3/00
Inventor 周勇胡晓曦许智胡炜吕芝艳庞洁
Owner XIAN INSTITUE OF SPACE RADIO TECH
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