To increase the computing efficiency of ephemeris prediction for high eccentricity orbit satellites,a variable-step Ad-ams-Cowell integrator with interpolation is proposed in this paper.Used for orbital integration,the method is based on the traditional 8-order Adams-Cowell multi-step method.Based on the characteristics of high eccentricity orbits,variable integral step lengths are adopted at different time in an orbital period.An interpolation formula is introduced to generate ephemerides with a small interval.The proposed method decreases the rounds of satellite motion equation computing,and it is especially ap-plicable for situations where ephemerides are designed to be frequently output.It is validated by using Satellite Tool Kit (STK) High Precision Orbit Propagator (HPOP)model simulation results.Numerical simulation validates the effectiveness and accu-racy of the approach proposed.Examples show that the computing time of the method is far less than that of the traditional multi-step method or HPOP model while keeping a similar accuracy.
NETL
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维普
万方数据
