Abstract:

According to the elliptic orbit equation and angular momentum conservation formula of satellite in polar coordinate system，the kinematic equation in the form of implicit function of the satellite is obtained by integration，and the isochronous point by point trajectory diagram，the change curve diagrams of polar coordinates r and θ with time t of the satellite with eccentricity e = 0.6 are made. It is pointed out that r changes most rapidly with t at the intersection of the elliptical orbit and the right rectum，that is，the radial velocity of the satellite is the largest.The kinematic equation obtained in this paper is actually another expression of Kepler’s equation，but its reasoning process is easier to understand. The detailed integration process and relevant conclusions given in this paper may provide reference for the teaching and learning of relevant contents.

Key words: satellite, elliptical orbit, kinematic equation, isochronous point by point trajectory, polar coordinates