Navigation satellite orbit determination and improvement non-singular point technology under nonconservative force effects

Abstract

The invention relates to a navigation satellite orbit determination and improvement non-singular point technology under nonconservative force effects. The technology is characterized by comprising obtaining a theoretical expression of a nonconservative force perturbation through a Gauss equation, forming a theoretical expression of a disturbed orbit without singular points according to a Gauss-Xu equation, and performing theoretical fitting according to observation to as to determine a navigational satellite orbit or improve the orbit. Since the orbits of beidou navigation satellites are all near-circular or near equator, and the singular points exist in all classic orbit theories, orbit determination or orbit improvement fails. The technology provided by the invention can be applied to the orbit determination or improvement of the beidou navigation satellite orbits, and no singular points exist. Besides, the technology is simple, computational complexity is reduced, and the technology is suitable for satellite automatic orbit determination. Since a satellite perturbative force comprises two kinds, i.e., a potential force and a nonconservative force, the invention, together with the invention with an invention right registry number 201310545077.2, i.e., a navigation satellite orbit determination and improvement non-singular point technology under the potential force, forms a complete non-singular point orbit determination and improvement technology through combination application.

Description

Technical field [0001] The invention relates to a method and technology for determining and improving satellite orbits under non-conservative forces by using the theory and technology of no singularity, relates to the technical field of satellite navigation and positioning, and relates to the field of navigation satellite measurement orbit determination, and belongs to geodesy The subject of satellite navigation and positioning belongs to the subject of astrometry and celestial mechanics. Background technique [0002] The key issue in determining and improving the orbit of navigation satellites under non-conservative forces lies in the application of satellite motion equations. [0003] At present, there are two types of equations that mainly describe the motion of navigation satellites: 1) The equation of motion in a rectangular coordinate system. This method cannot obtain a theoretical solution, that is, a theoretical orbit description. Therefore, it can only be solved by numeric...

AI Technical Summary

Problems solved by technology

[0003] At present, there are two types of equations that mainly describe the motion of navigation satellites: 1) The equation of motion in the Cartesian coordinate system. This method cannot obtain a theoretical solution, that is, a theoretical orbit description, so it can only be solved by numerical integration, which requires an integrator and a larger Computing power, difficult to real-time, unable to conduct qualitative analysis of motion, unable to apply on-board orbit determination

2) The Gaussian equation under the Kepler variable, the theoretical description of the satellite orbit can be obtained by applying this equation, the orbit determination and orbit improvement become a fitting adjustment filter, the amount of calculation is greatly reduced, and it is suitable for the application of self-orbit determination on the satellite , can be real-time, but there is a singularity problem in the orbital theory description

[0005] The above-mentioned existing theoretical methods and technologies either have a large amount of calculation, require an integrator, are difficult to real-time, and cannot be qualitatively analyzed, or have singularity problems, which cannot be used for self-orbit determination on real-time navigation satellites

Images