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Method for adjusting fixed point position of satellite stationary orbit

A technology of geostationary orbit and fixed-point position, which is applied in space navigation equipment, spacecraft of space navigation, attitude control, etc., and can solve the problem of low accuracy of satellite fixed-point position adjustment

Inactive Publication Date: 2018-10-02
BEIJING INST OF ELECTRONICS SYST ENG
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Problems solved by technology

[0004] One object of the present invention is to provide a method for adjusting the fixed-point position of a satellite in geostationary orbit to solve the problem of low accuracy in adjusting the fixed-point position of a satellite in geostationary orbit

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  • Method for adjusting fixed point position of satellite stationary orbit
  • Method for adjusting fixed point position of satellite stationary orbit
  • Method for adjusting fixed point position of satellite stationary orbit

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Embodiment Construction

[0056] In order to illustrate the present invention more clearly, the present invention will be further described below in conjunction with preferred embodiments and accompanying drawings. Similar parts in the figures are denoted by the same reference numerals. Those skilled in the art should understand that the content specifically described below is illustrative rather than restrictive, and should not limit the protection scope of the present invention.

[0057] In the prior art, the two-pulse maneuver that only applies lateral thrust is often used to adjust the fixed-point position of the stationary orbit. The first lateral pulse along the lateral direction of the track can change the semi-major axis to reduce the longitude deviation; the second pulse is at the fixed-point position. Applied at the end of the adjustment to eliminate the longitude drift rate. During the long-term fixed-point position adjustment process of the stationary orbit, the field harmonic perturbation...

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Abstract

The invention discloses a method for adjusting a fixed point position of a satellite stationary orbit. The method comprises: S1, calculating orbital transit time of a satellite according to a transferinitial point, an end point and maximum transfer time; S2, calculating a semi-major axis changing amount of a satellite secondary pulse with harmonic term perturbation; S3, calculating a secondary pulse considering tesseral harmonic term perturbation; and S4, calculating a cubic pulse considering the tesseral harmonic term perturbation. Therefore, a problem of low fixed point position adjustmentprecision of the stationary orbit satellite is solved.

Description

technical field [0001] The invention relates to the technical field of satellite orbit control. More specifically, it relates to a method for adjusting a fixed-point position in a satellite geostationary orbit. Background technique [0002] At present, with the increase in the number of geostationary orbit (GEO) satellites, the on-orbit maintenance of geostationary orbit satellites mainly faces the following problems: consumables such as propellants that can be carried by satellite launches are limited and difficult to resupply; orbital debris including scrapped spacecraft It occupies the orbital position for a long time and is difficult to remove. On-orbit service technology will provide a new model for on-orbit maintenance of geostationary orbits. On-orbit service technologies such as on-orbit maintenance, module replacement, fuel filling, and on-orbit rescue can reduce the cost of space missions and extend the life of on-orbit spacecraft. life. In order to reduce the m...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 赵书阁向开恒
Owner BEIJING INST OF ELECTRONICS SYST ENG
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