Low-earth-orbit satellite long-term orbit prediction method based on two line element

A technology for orbit forecasting and low-orbit satellites, which is applied in the field of satellite measurement and control, can solve the problems of inflexibility and large STK installation capacity, and achieve the effects of reducing computation, improving forecasting efficiency, and flexible use

Pending Publication Date: 2019-12-20
SHANGHAI AEROSPACE ELECTRONICS CO LTD +1
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Problems solved by technology

Although the current SGP4 in STK can use two lines of root numbers for orbit prediction, the installation capacity of STK is relatively large and it is not flexible

Method used

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  • Low-earth-orbit satellite long-term orbit prediction method based on two line element
  • Low-earth-orbit satellite long-term orbit prediction method based on two line element
  • Low-earth-orbit satellite long-term orbit prediction method based on two line element

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Embodiment Construction

[0031] The following will combine Figure 1 ~ Figure 3 The method for predicting the long-term orbit of low-orbit satellites based on the two-line root number of the present invention is further described in detail.

[0032] First introduce two space coordinate systems - the J2000.0 geocentric celestial coordinate system and the orbital coordinate system at time t.

[0033] In the J2000.0 geocentric celestial coordinate system, the coordinate origin is the earth center, the xy coordinate plane is the J2000 geocentric flat equatorial plane, and the x coordinate axis points to the direction of the J2000 flat vernal equinox;

[0034] The orbital coordinate system at time t, whose coordinate origin is the center of the earth, adopts the true equator plane at time t and the equinox direction at time t as the x′y′ coordinate plane and x′ axis direction of the coordinate system respectively, which is released by NORAD of the United States The coordinate system used by the TLE.

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Abstract

The invention relates to a low-earth-orbit satellite long-term orbit prediction method based on a two line element. The method comprises the following steps: performing related processing on a two line element in an orbital coordiante system at a moment t, thus obtaining a satellite orbital element initial value applicable to an orbit prediction dynamical model in a J2000.0 geocentric celestial coordinate system; and solving the orbit prediction dynamical model by adopting a numerical method, thus obtaining a satellite orbital element prediction result, wherein the related processing comprisesreduction processing performed on angular velocity of peace movement in the two line element, conversion of a mean element into an instant element in the orbital coordinate system at the moment t andconversion of the instant element in the orbital coordinate system at the moment t into an instant element in the J2000.0 geocentric celestial coordinate system. The low-earth-orbit satellite long-term orbit prediction method based on the two line element is high in prediction precision.

Description

technical field [0001] The invention relates to the technical field of satellite measurement and control, in particular to a method for long-term orbit prediction of low-orbit satellites based on two-line radicals. Background technique [0002] The initial orbit elements of satellites are needed in orbit prediction of satellites in orbit. For general users, in many cases, it is difficult to obtain accurate real-time initial orbit elements of satellites in orbit. North American Aerospace Defense Command (NORAD) defined two-line elements (Two-Line Element, TLE), the error of the orbit element is about several hundred meters, to a certain extent, it can meet the long-term orbit forecast ( 3 months), and the number of orbits is published on the Internet regularly, so that users can easily obtain and use them. Therefore, the orbital element (the two-line element) becomes the initial input (ie, the initial orbital element) in the long-term orbit prediction of the satellites in o...

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Application Information

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IPC IPC(8): G01C21/24
CPCG01C21/24Y02T90/00
Inventor 郑典循林合同吴玉清
Owner SHANGHAI AEROSPACE ELECTRONICS CO LTD
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