Method for accurately and efficiently calculating dense ephemeris of high-eccentricity orbit

A method for accurately and efficiently calculating a dense ephemeris of a high-eccentricity orbit, wherein the method implements ephemeris calculations of a space object by solving a dynamic equation with initial values and uses a construction algorithm for uneven interpolation nodes, and the method comprises the following steps:

• step 1:
• calculating the initial values, comprising a semi-major axis a0, an orbital period Pt0 and an eccentricity e0 of an osculating orbit of the space object at a time t0;
• step 2:
• introducing a time transformation parameter δ to construct an orbital period transformation factor β;
• step 3:
• determining a number N of the uneven interpolation nodes in one orbital period by an interpolation method;
• step 4:
• constructing a set of uneven interpolation nodes {Tl} from an initial node, and generating ephemeris values on the set of interpolation nodes by numerical integration;
• and
• step 5:
• performing interpolations on dense ephemeris times {ti} according to the set of uneven interpolation nodes {Tl} and the ephemeris values of the set of interpolation nodes, so as to complete all ephemeris calculations.