On-orbit real-time orbit determination method for electric propulsion transfer orbit spacecraft on-board gnss

Abstract

The invention discloses a real-time orbit determination method for on-orbit satellite-borne GNSS of an electric propulsion transfer orbit spacecraft, which belongs to the field of spacecraft autonomous orbit determination. The invention obtains GNSS observation data, satellite attitude and electric thrust broadcast data in real time through a GNSS receiver. According to the installation direction of the electric thruster, the acceleration of the local system generated by the electric thrust is converted to the inertial system, and the influence of the acceleration of the inertial system generated by the electric thrust is considered in the pseudo-range real-time orbit determination to solve the satellite motion equation. The pre-residuals test the accuracy of the prior orbit information. When the prior orbit information is judged to be inaccurate, the process noise of the compensation acceleration can be adjusted to further ensure the stable output of the autonomous orbit determination, free from the modeling error of the electric thrust in the orbit maneuver. Impact. The invention can overcome the problem of the conventional autonomous orbit determination filter divergence caused by the electric propulsion orbit maneuver of the transfer orbit spacecraft, the orbit determination calculation is stable, and the reliability of the 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 real-time orbit determination method for on-orbit on-orbit GNSS of an electric propulsion transfer orbit spacecraft. Background technique [0002] The transfer orbit spacecraft is a special type of spacecraft with variable orbits, such as the geosynchronous transfer orbit (GTO), the earth-moon transfer orbit after the launch of the lunar probe, etc. At present, the main propulsion systems used to complete the orbital transfer of such spacecraft are chemical propulsion, cold air propulsion, electric propulsion, etc. Because ion electric propulsion has the characteristics of wide range continuous fine adjustment, low noise, long life and high specific impulse, etc. Used in missions to transfer orbital spacecraft. [0003] The high-precision orbit determination of orbit transfer spacecraft is the key to ensuring the smooth completion of scientific tasks...

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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