The invention provides a method and a
system for acquiring two rows of elements by a numerical
orbit recursion device. The method comprises the following steps of: inputting a two-row element template; determining
orbit time reference points corresponding to the two rows of elements; according to a set numerical value
recursion device model, a numerical value
recursion device obtains a position value sequence of the track in the set space coordinate
system within a period of time; converting the position value sequence obtained by the numerical recursion device into a true equatorial mean equinox coordinate
system; obtaining two rows of elements by using a single-
point method through the two rows of element templates; taking the two rows of elements obtained by the single-
point method as an initial
orbit, and solving an orbit parameter
estimation value in the two rows of elements under an
optimal criterion by utilizing a least square method; calculating an orbit residual error sequence corresponding to an orbit parameter
estimation value in the two rows of elements; and fitting the residual error by using a polynomial model to obtain a compensation item. The method is easy to implement, the numerical orbit recursion device can be effectively applied to be converted into two rows of elements, and the method can be compatible with time periods with orbit maneuvering.