Method for determining strictly-regressive orbit of near-earth satellite

Abstract

A method for determining strictly-regressive orbit of a near-earth satellite is disclosed. The method comprises: on the basis that an orbit element prediction value of a regressive orbit in a low-order gravity potential field, combining an orbit semi-major axis a and an orbit inclination angle i, performing repeated iteration correction on the orbit semi-major axis a and the orbit inclination angle i according to the relationship of the orbit semi-major axis a and the orbit inclination angle i with the longitude and latitude of a sub-satellite point and based on an orbit recursion module of a high-order gravity potential filed module, combining an eccentricity ratio e and a perigee argument omega, and performing repeated irritation correction on the eccentricity ratio e and the perigee argument omega by employing an average process according to the characteristics of a vector limit cycle of the eccentricity ratio until the regression precision of an ascending node satisfies a preset value. The method determines the strictly-regressive orbit of the near-earth satellite based on high-precision orbit dynamics, the determined orbit possesses relatively high regression precision for a space target point, and compared with a conventional method based on a low-order gravity potential field, the high-precision orbit dynamics is relatively close to reality and possesses relatively high application value.

Description

technical field [0001] The invention belongs to the technical field of spacecraft orbital dynamics, and in particular relates to a method for determining the strict return orbit of a near-earth satellite Background technique [0002] The strict return to orbit requires that after a strict return cycle, the satellite can revisit the space target point with high precision. In order to realize the strict return of the orbit, the designed orbit products need to meet the characteristics of the sun-synchronous return orbit and the frozen orbit. Among them, the optimized design based on the characteristics of the sun-synchronous return orbit can realize the revisit of the sub-satellite point; the optimized design based on the characteristics of the frozen orbit can realize the stability of the arch line in the orbital plane, so as to ensure the orbital height of the sub-satellite point revisit consistency. [0003] The traditional regression orbit determination method is based on...

AI Technical Summary

Problems solved by technology

[0003] The traditional regression orbit determination method is based on the low-order gravitational potential field, and its main defect is that the regression accuracy is not high, generally around 10km

Images