Method for designing eccentricity ratio prebias of critical inclination nearly-circular orbit

Abstract

The invention provides a method for designing eccentricity ratio prebias of a critical inclination nearly-circular orbit, and belongs to the technical field of satellite orbits. The method comprises the steps that firstly, the mean elements of the six parameters of the eccentricity ratio, the argument of perigee, the mean anomaly, the ascending node right ascension, the orbit semi-major axis and the orbit inclination are transformed into instant elements; then, the instant elements are substituted into STK satellite simulation software for orbit calculation, and the instant elements of the six parameters in the tail period of the service life are obtained; the instant elements are transformed into the mean elements, the mean element prebias amount of the eccentricity ratio is designed to be half of the mean element of the eccentricity ratio in the tail period of the service life at last, and the mean element of the argument of perigee is designed to be 180 degrees. The eccentricity ratio of the tail period of the service life can be reduced by half to overcome the defect that the eccentricity ratio of the nearly-circular orbit of the critical inclination is gradually enlarged.

Description

technical field [0001] The invention relates to the technical field of satellite orbits, in particular to an eccentricity pre-bias design method for a near-circular orbit with a critical inclination angle. Background technique [0002] During the satellite's in-orbit flight, the earth's aspheric perturbation will bring about long-term changes in the orbit; during the satellite's lifetime, in order to prevent the number of orbital elements from exceeding the threshold, it is necessary to impose necessary controls to suppress it. Commonly used control strategies include: 1) Perform multiple controls based on the real-time measurement value of the number of roots, which can be used for tasks with relatively long life or high orbital stability requirements; 2) Pre-bias design for a certain number of roots Instead of making adjustments during the entire lifetime, this strategy can be adopted for tasks that do not live too long or allow a large range of variation. [0003] For th...

AI Technical Summary

Problems solved by technology

The critical inclination orbits launched in the past are mainly large elliptical orbits. For example, the eccentricity of the Molniya orbit in the former Soviet Union has reached more than 0.5 and remains unchanged, so no pre-bias design is required; while the critical inclination near-circular orbits launched in the past are all returnable satellites Mainly, its on-orbit life is short, and it does not carry out pre-bias design

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