Calculation method of subsatellite points and photographic point trajectory self-intersection points of near-earth regression orbit satellite

Abstract

The invention discloses a calculation method of subsatellite points and photographic point trajectory self-intersection points of a near-earth regression orbit satellite. Based on an orbital perturbation model of the earth oblateness (J2), the mean influence of the earth oblateness on the long-term perturbation of the right ascension of the ascending node, the perigee argument and the aplanatic angle is utilized, so that the mean drift period and the orbital intersection period of the satellite orbital plane relative to the earth resonate, and revisit regression of the orbital relative to thesubsatellite point and the photographic point trajectory of the earth surface is formed. After the orbit inclination angle, the eccentricity ratio, the regression days and the period number are given,the orbit semi-major axis can be solved, then the longitude of the sub-satellite point trajectory self-intersection point is analyzed and solved, the latitude of the self-intersection point under thecorresponding precision is screened out through numerical screening, and the distribution situation of the sub-satellite point trajectory self-intersection point in one regression period can be obtained. The invention provides a practical near-earth regression orbit sub-satellite point trajectory self-intersection point calculation method, and the method has important application value in near-earth surveying and mapping, remote sensing, reconnaissance, InSAR and other regression orbit satellite measurement tasks.

Description

technical field [0001] The invention belongs to the technical field of remote sensing satellites, and in particular relates to a method for calculating the self-intersection point of sub-satellite points and photographic point tracks of low-Earth return orbit satellites. Background technique [0002] According to mission requirements, remote sensing satellites often need to make repeated observations of specific areas within a certain period of time to complete tasks such as ground imaging and 3D terrain modeling, and regular revisit and regression detection is required for key areas of concern. The low-Earth return orbit is generally used to realize this function, which has the advantages of low cost, good imaging effect, short revisit time, dense sub-satellite points, and wide detection range. [0003] Due to the perturbation of the Earth's non-spherical gravitational force (especially the J 2 item) is more obvious, it will cause a large drift of the satellite orbit in th...

AI Technical Summary

Problems solved by technology

[0004] Traditional near-Earth satellites often use sun-synchronous orbits for earth observation. Although regular revisit observations of designated points on the ground are realized, there are still observation areas and satellite observation angles that are relatively fixed, and adjacent observation time intervals are relatively long (once a day) ), large amount of calculation, easy to lose and other disadvantages

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