Satellite-borne GNSS on-orbit real-time orbit determination method for electric propulsion transfer orbit spacecraft

Abstract

The invention discloses a satellite-borne GNSS on-orbit real-time orbit determination method for an electric propulsion transfer orbit spacecraft, and belongs to the field of spacecraft autonomous orbit determination. GNSS observation data, satellite attitudes and electric thrust broadcast data are obtained in real time through a GNSS receiver, and according to the installation direction of an electric thruster, the system acceleration generated by the electric thrust is converted into an inertial system, the influence of the inertial system acceleration generated by the electric thrust is considered in a pseudo-range real-time orbit determination solving satellite motion equation, the accuracy of priori orbit information is detected by using a pre-test residual error of a pseudo-range observation value, and when the priori orbit information is judged to be inaccurate, the stable output of autonomous orbit determination can be further ensured by adjusting the process noise for compensating the acceleration, and the influence of an electric thrust modeling error in orbit maneuver is avoided. The problem of conventional autonomous orbit determination filtering divergence caused by electric propulsion orbit maneuver of the transfer orbit spacecraft can be solved, orbit determination calculation is stable, and the reliability of autonomous orbit determination is improved.

Description

technical field [0001] The invention relates to the field of autonomous orbit determination of spacecraft, in particular to a method for on-orbit real-time orbit determination of GNSS on-orbit for an electric propulsion transfer orbit spacecraft. Background technique [0002] A transfer orbit spacecraft is a special type of spacecraft with a variable orbit, such as the geosynchronous transfer orbit (GTO), the earth-moon transfer orbit of the lunar probe after launch, etc. At present, the orbit transfer of such spacecraft is completed, and the main propulsion systems used include chemical propulsion, air-cooled propulsion, and electric propulsion. Because ion electric propulsion has the characteristics of wide-range continuous fine adjustment, low noise, long life, and high specific impulse, it is often used Used in missions to transfer orbiting spacecraft. [0003] The high-precision orbit determination of orbit transfer spacecraft is the key to ensure the successful comple...

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a real-time orbit determination method for on-orbit GNSS of an electric propulsion transfer orbit spacecraft, which can overcome the problem of conventional autonomous orbit determination filter divergence caused by the electric propulsion orbit maneuver of the transfer orbit spacecraft, and the orbit determination calculation is stable. Improved reliability of autonomous orbit determination

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