Abstract: The usual orbit computation methods include the analytical and numerical approaches. For satellites in high eccentricity orbit, numerical method brings more computation, and a perturbation analysis solution is inapplicable. A new method of prediction for high eccentricity orbit is developed, which adopts the position bias between the precise trajectory and twobody dynamic orbit to fit the Chebyshev polynomial coefficients. This method can improve the precision of fitting orbit, and the positions and velocities of the high eccentricity orbit satellites can be calculated more precisely, easily and quickly.

Key words: high eccentricity orbit, Chebyshev polynomial, orbit fitting, precise ephemeris