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.