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Low-orbit satellite orbit determination method in initial orbit injection stage

A technology for low-orbit satellites and satellites, which is applied in the field of satellite orbit determination, and can solve problems such as lost satellites, satellites deviating from initial orbit parameters, and inability to capture satellites

Pending Publication Date: 2020-04-24
BEIJING GUODIAN GAOKE TECH CO LTD
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  • Claims
  • Application Information

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Problems solved by technology

[0003] The purpose of the present invention is to provide an autonomous orbit determination method suitable for the initial stage of low-orbit satellite launch, so as to solve the technical problem that the actual orbit of the satellite continuously deviates from the initial orbit parameters in the prior art, thus causing the ground to fail to capture the satellite or even lose the satellite.

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  • Low-orbit satellite orbit determination method in initial orbit injection stage
  • Low-orbit satellite orbit determination method in initial orbit injection stage
  • Low-orbit satellite orbit determination method in initial orbit injection stage

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Embodiment Construction

[0027] The technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Apparently, the described embodiments are some of the embodiments of the present invention, but not all of them.

[0028] The components of the embodiments of the invention generally described and shown in the figures herein may be arranged and designed in a variety of different configurations. Accordingly, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely represents selected embodiments of the invention.

[0029] Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0030] This method uses the earth's magnetic field information measured by the ...

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Abstract

The invention discloses an autonomous orbit determination method suitable for an initial launching stage of a low-orbit satellite. Earth magnetic field information measured by a satellite magnetometeris used as an observed quantity, a state equation and an observation equation are used, a recursion formula of state quantities which are a position, a speed and an attitude of a satellite is established under initial conditions, and orbit information is continuously corrected and output through iteration and filtering of multi-point information so that satellite full-magnetic autonomous navigation calculation is realized. The satellite can still calculate more accurate orbit parameters without depending on a GNSS system, and a ground system can ensure that a ground antenna continuously and stably tracks the satellite by using the orbit parameters downloaded by the satellite.

Description

technical field [0001] The invention relates to the field of satellite orbit determination, in particular to an autonomous orbit determination method suitable for the initial stage of low-orbit satellite launch. Background technique [0002] At present, my country's low-orbit micro-satellites mainly use the on-board GNSS navigation system to obtain real-time position and velocity information of satellites to determine satellite orbits. The GPS data received by the satellite is usually the position and velocity of the satellite in the inertial system. We calculate the satellite's orbital parameters r, V, a, e, i, Ω, ω, λ according to the orbital recursion formula, and finally calculate the orbit Extrapolate the root number, and use this as the initial value for orbital extrapolation. This method must rely on a separate GNSS navigation device, and must ensure that the external navigation systems (Beidou, GPS) it depends on are available. Among low-orbit satellites, microsate...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24G01C21/20G01S19/48G01C21/08
CPCG01C21/24G01C21/20G01S19/48G01C21/08
Inventor 唐尧朱莲枝单黎明李云鹏吕强
Owner BEIJING GUODIAN GAOKE TECH CO LTD
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