Intersection point moment and position solving algorithm based on orbit analysis perturbation solution

Abstract

The invention discloses an intersection point moment and position solving algorithm based on an orbit analysis perturbation solution. A perturbation model which only considers the long-term item influence of the earth oblateness J2-J4 item is adopted for calculating the intersection point moment, the periodic item influence is ignored to reduce the calculation amount, and the orbital plane orientations of spacecrafts of both parties at the assumed moment are calculated by using a perturbation equation. An intersection point moment is calculated through the geometrical relationship, and the intersection point moment is compared with an assumed moment. If the error is large, the intersection point moment is taken as a new assumed moment to repeatedly calculate the intersection point moment until iteration convergence. Finally, the position of the spacecraft of the opposite party at the intersection point moment is solved by utilizing an osculating orbit element perturbation equation with long-term, long-period and short-period oscillation at the same time. The method not only can accurately calculate the moment and position of the intersection point, but also is simple and easy to implement, saves calculation time, calculation resources and memory, is especially suitable for spaceborne computers with shortage of calculation resources, and has good popularization prospects.

Description

technical field [0001] The invention relates to the technical field of spacecraft orbital dynamics, in particular to an algorithm for solving the intersection time and position based on the orbital analysis perturbation solution. Background technique [0002] To prepare for the spacecraft rendezvous mission, it is necessary to obtain in advance the time when the opponent's spacecraft crosses the orbital plane of the own spacecraft and the position of the opponent's spacecraft at the corresponding time. The orbit of a near-Earth spacecraft (both the opponent’s spacecraft and your own spacecraft are near-Earth spacecraft) is mainly affected by the perturbation of the Earth’s oblateness J2 to J4, except that the average orbital elements will be affected by the long-term perturbation to produce uniform changes In addition, it will also cause long-period and short-period oscillations of the close orbital elements of the spacecraft. The close orbital elements include orbital semi-...

AI Technical Summary

Problems solved by technology

One is to use close orbital elements considering periodic items for calculation, which has high precision, but the calculation amount is too large, which is not conducive to engineering applications; the other is to use simple models without perturbation or only considering the perturbation effect of J2 term , which is less computationally expensive but less accurate

Existing algorithms either have low precision, or require a large amount of computing resources and cannot be applied to on-board computers, and have shortcomings in the application of actual space missions

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