Geosynchronous transfer section orbit element high-precision fitting method

Abstract

The invention discloses a geosynchronous transfer section orbit element high-precision fitting method, which is specifically implemented according to the following steps: 1, determining a step length in an orbit fitting time interval and calculating k groups of orbit data; 2, calculating an orbit average semi-major axis and an average orbit angular velocity n; 3, writing a forecasting equation according to the k groups of orbit data, the average semi-major axis of the orbit and the average angular velocity n of the orbit; 4, listing a system state equation and a state transition matrix phi; 5, carrying out SVD singular value decomposition on the state transition matrix phi; 6, calculating an orbit coefficient fitting matrix P; and 7, substituting the calculated orbit coefficient fitting matrix P into the forecasting equation in the step 3 to realize orbit forecasting. According to the geosynchronous transfer section orbit element high-precision fitting method, a primary function fitting method is adopted, complex calculation work is completed on the ground, and high-precision orbit forecasting is achieved.

Description

technical field [0001] The invention belongs to the technical field of spacecraft measurement and control methods, and relates to a high-precision fitting method for orbit elements of a geosynchronous transfer section. Background technique [0002] According to the geosynchronous satellite configuration requirements, in the transfer orbit segment, the star sensor is used as the main solution to realize the attitude control tasks such as satellite pointing to the ground and ignition attitude establishment. The star sensor outputs the attitude information of the satellite relative to the earth-centered inertial system (usually J2000), and it is necessary to combine the orbit information to determine the current three-axis attitude of the satellite relative to the orbital system. [0003] In the geosynchronous satellite transfer orbit section, when the orbit altitude is greater than 20,000km, the satellite needs orbit information for attitude control tasks such as pointing to t...

AI Technical Summary

Problems solved by technology

[0005]During the transfer section, due to the influence of large eccentricity, the expression of the basis function of the satellite position and velocity expansion is extremely complicated, and there is a strong coupling relationship between the parameters , so it is not appropriate to use the position and velocity as the parameters of the on-board orbit prediction model for the transfer segment

[0006]In the past, the calculation methods of orbital elements used on stars were basically extrapolated by the method of dynamic integration. The dynamic model used is relatively simple, which makes the extrapolation of orbital elements unable to meet the high-precision requirements

Images