Non-cooperative low-thrust maneuvering target orbit determination method, device, equipment and medium

Abstract

The present application relates to a non-cooperative low-thrust maneuvering target orbit determination method, device, computer equipment and storage medium. The method includes: proposing an orbit determination method for thrust acceleration modeling in the local orbit coordinate system of the tracked non-cooperative target, deriving the calculation equation of the extended state quantity transfer matrix including acceleration components under the high-precision perturbation orbit model, through Radar observation data and the least squares method are used to improve the orbit of non-cooperative small-thrust maneuvering targets, and finally the orbit prediction is carried out through the determined extended state quantity, which can effectively determine the orbit of non-cooperative targets with continuous low-thrust maneuvering, and can be used to solve non-cooperative Orbit determination for satellites performing continuous low-thrust maneuvers during climb or descend.

Description

technical field [0001] The present application relates to the field of space situational awareness, and in particular to a method, device, computer equipment and storage medium for determining the orbit of a non-cooperative low-thrust maneuvering target based on acceleration modeling in a local orbit system. Background technique [0002] Precise orbit determination and high-precision orbit extrapolation of non-cooperative maneuvering targets are of great significance to space situational awareness tasks such as target cataloging and collision warning. [0003] The Starlink satellite implements continuous low-thrust maneuvers, but due to the non-cooperative target, its maneuvering strategy is unknown, and it is difficult to accurately model its thrust acceleration. The dynamic equations of the absolute orbital motion of space targets are generally described in the J2000 geocentric inertial frame; however, in practical tasks, in order to save energy, the orbital maneuvering of...

AI Technical Summary

Problems solved by technology

[0003] Starlink satellites implement continuous small-thrust maneuvers, but because the target is not cooperative, its maneuver strategy is unknown, and it is difficult to accurately model its thrust acceleration

The dynamic equation of the absolute orbital motion of a space target is generally described in the J2000 geocentric inertial system; however, in actual missions, in order to save energy, the orbital maneuver of the spacecraft is generally along the track or the normal direction; because the spacecraft rotates around the earth, The direction vector of the trajectory or normal maneuver in the inertial system is also rotating and changing, and it is difficult to directly describe the thrust acceleration vector in the inertial system to obtain a converged trajectory improvement solution through state expansion and least squares estimation; therefore, it is difficult to achieve Orbit Determination and Extrapolation Forecast of Maneuvering Section of Non-cooperative Small Thrust Maneuvering Satellite

Images