Research And Application Of Satellite Orbit Prediction Method Based On Osculating Kepler Element

Satellite orbit prediction has great guiding significance in station tracking satellite and receiving data,area target or point target imaging access,satellite imaging and planning.TLE and Osculating Kepler Element are most commonly used to predict satellite orbit now.SGP4 model which is based on TLE can quickly predict satellite position and velocity,but its accuracy is not high for long time prediction.The user needs to update TLE frequently to ensure prediction accuracy.If we know satellite physical parameters and space dynamic parameters,we can use Osculating Kepler Element to predict satellite orbit more accurately.Models and software for orbit prediction based on Osculating Kepler Element have been developed at home and abroad,of which 26 orbit calculation program and HPOP model of STK software are widely used.But their low efficiency for predicting high density ephemeris and nonextensible restrict their application in a deeper level.Therefore,the research of orbit prediction method based on Osculating Kepler Element has great significance in quickly and effectively predicting satellite position and velocity.For the sun synchronous orbit,the geosynchronous orbit,and high eccentricity orbit,this article establishes a perturbation force model which considers all kinds of main force,and proposes a high efficiency orbit prediction method based on Osculating Kepler Element.The main research contents and work are as follows:1)A perturbation force model which is suitable for different altitudes is established.The non-spherical earth and uneven quality perturbation,the gravities perturbation of the sun and the moon,the solar radiation pressure perturbation,and the upper atmospheric drag perturbation are considered in this model.2)Provide a method named WIAC based on osculating element for orbit prediction.On the base of using Adams-Cowell method to solve the orbit differential equation,introduce position and velocity interpolation formula to improve efficiency for predicting high density ephemeris.Then design a specific variable-step integration to adapt to the characteristic of high eccentricity orbit.Compared with the 26 orbit calculation program and HPOP model,the method improves the computational efficiency of high precision orbit prediction.3)The WIAC method is applied to orbit computing services.The method is used to realize many relevant functions,including the longitude and latitude calculation for sub-satellite point,the solar altitude angle calculation,the receiving station tracking prediction,the earth shading time calculation,the ground imaging calculation,area target or point target imaging access calculation,the Kepler elements prediction,and the relay satellite communications circle access calculation.