A Method for Predicting the Orbit of an Autonomous Satellite

Abstract

The invention discloses an on-satellite autonomous satellite orbit prediction method. Firstly, a user comprehensively considers prediction precision of an orbit and the acceptable running time of an actual project and presets an orbit prediction period and segment time intervals, and a ground control system performs precise prediction on orbit prediction requirements proposed by the user to generate all segment initial orbital parameters in the orbit prediction period; secondly, the ground control system inputs the generated segment initial orbital parameters into an on-satellite control system sequentially in accordance with the preset segment time intervals as the input of the on-satellite control system autonomous satellite orbit prediction; and finally, the on-satellite control systemperforms on-satellite autonomous orbit prediction of based on the segment initial orbital parameters. Based on satellite-ground cooperation, the high computing power of the ground is effectively exerted. The operation time of an on-satellite autonomous satellite orbit prediction algorithm is reduced. Engineering practice precision of orbit prediction is balanced.

Description

technical field [0001] The invention belongs to the technical field of aerospace orbit dynamics, and relates to an on-board orbit prediction method that takes into account both satellite orbit accuracy and orbit calculation running time. Background technique [0002] Orbit prediction refers to predicting the position and velocity of the satellite in the future according to the kinematic differential equation of the satellite on the premise of knowing the current state of the satellite. Orbit prediction plays an important role in satellite navigation, satellite measurement and control mission planning, etc. At present, the orbit calculation of low-orbit satellites in my country generally uses the quasi-average root method that considers the main harmonic items of the earth's non-gravitational field. At the same time, the long-term effect of the semi-major axis caused by the influence of atmospheric perturbation is considered in the injection parameters. This method It has bee...

AI Technical Summary

Problems solved by technology

As mentioned above, although the precise algorithm has high orbit prediction accuracy, it needs to occupy the total rudder computing resources and the running time is slow; the simplified algorithm has less running time, but the prediction accuracy is not as satisfactory

Therefore, neither of the above two orbit calculation methods can be directly applied to orbit calculations on satellites

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