Orbit determination method for geostationary satellite adapting to orbital maneuver

Abstract

The invention discloses a precision orbit determination method for a geostationary satellite adapting to orbital maneuver and belongs to the field of space metering and controlling. The method comprises the followings: firstly, maneuvering acceleration is calculated; observed quantity Rho i and observed residual error sequences delta Rho i and j are calculated; estimation to public system error Rho b is performed; the public system error Rho b is deducted from the observed residual error sequences delta Rho i and j, so as to obtain systematic deviations of all observation stations; the Rho b is deducted from the observed quantity, then orbit improvement is performed again on observation data of which system errors are deducted, and calculating is performed again on the improved initial state until orbit convergence, and precision orbit determination for the geostationary satellite is accomplished. The precision orbit determination method provided by the invention has the benefits as follows: difficulty in precision orbit determination caused by pushing force produced by air blast of an engine on a GEO satellite during orbital maneuver can be overcome, meanwhile, public systematic error appraisement and an all-station deviation adapting iteration eliminating method are adopted for solving the problem that systematic errors such as satellite clock errors and time delay of all observation station equipment are hard to separate is solved, and the orbit determination forecast accuracy of the GEO satellite during the orbital maneuver can be effectively improved.

Description

Technical field [0001] The patent of the invention belongs to the field of aerospace measurement and control, and relates to a method for precise orbit determination of a geosynchronous satellite (GEO) suitable for orbital maneuvering. Background technique [0002] According to the national aerospace development plan, my country's Beidou-2 satellite navigation system adopts GEO / IGSO / MEO hybrid constellation for passive navigation and positioning. For passive positioning, orbital maneuvering means the temporary failure of the satellite. Because the GEO satellite control system regularly performs momentum wheel unloading and frequent orbital maneuvers, GEO satellites have become a key satellite that affects the navigation performance of the system. The frequent orbital maneuvers of GEO satellites, the poor geometric structure of ground observations, and the difficulty in separating system errors such as satellite clock errors and equipment delays have made GEO satellite precise orb...

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Problems solved by technology

[0003] The purpose of the present invention is: in order to solve the problem that it is difficult to ensure the orbit accuracy of orbit determination and orbit prediction by conventional methods during the orbit maintenance of geosynchronous satellites, the present invention provides a set of practical geosynchronous satellite precise orbit determination methods suitable for orbit maneuvering

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