Simple orbit extrapolation method on satellite

Abstract

The invention discloses a simple orbit extrapolation method on a satellite. The method comprises the following steps of determining the type of orbit elements according to the orbit determination result of a measurement and control system and with the combination of the orbit inclination angle and the eccentricity ratio characteristics; 2, performing orbit extrapolation by using the measurement and control system and taking the orbit determination result as an input, and outputting satellite positions and velocity vectors obtained through extrapolation according to the type of the orbit elements to obtain respective change sequences of the six orbit elements; determining the orbit fitting coefficients according to the respective change sequences of the orbit elements; and transmitting theground orbit fitting coefficients, the type of the orbit elements and the epoch t<0> to the satellite through a remote control instruction, and realizing simple orbit extrapolation on the satellite according to the calculated orbit elements at the time after the epoch t<0> on the satellite. The method greatly reduces the calculation amount on the satellite, reduces the complexity of an orbit extrapolation model, achieves the moderate orbit precision and meets the precision requirement.

Description

technical field [0001] The invention relates to a simple orbit extrapolation method on a satellite, belonging to the technical field of orbit calculation. Background technique [0002] With the improvement of aerospace technology, the functions of spacecraft are becoming more and more complex, and the autonomy of spacecraft is gradually improving, gradually getting rid of the dependence on ground control. Autonomous orbit extrapolation of spacecraft is an important basis for realizing many autonomous functions, such as attitude determination and antenna pointing control. [0003] At present, there are generally the following methods to realize the function of autonomous orbit extrapolation on the star: [0004] a) The flat root number of the satellite orbit at the epoch time is injected from the ground, and the traditional analytical method is used on the satellite to extrapolate, which often includes long-term items, long-period items, and short-period items. There are ma...

AI Technical Summary

Problems solved by technology

[0006] The analytical method contains a large number of items and the form is complex, but the accuracy is not high. It is easy to cause incompatibility with the measurement and control system due to the form of the flat root number during injection, which will bring artificial deviations and errors. Writing software is also a lot of work and prone to subtle errors

Although the numerical method has high precision, the calculation is complex, requires high computer capabilities, and takes up a lot of resources during calculation.

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