Satellite-borne space target orbit smoothing method

Abstract

The embodiment of the invention discloses a satellite-borne space target orbit smoothing method. The method comprises the following steps: S000, importing space target orbit parameters at a sampling moment; S001, judging whether the orbit parameter is the number of orbits or not, if so, skipping to S004, and otherwise, skipping to S003; S003, converting the orbit parameter into a sampling time space target orbit element; S004, converting the number of space target orbits at the sampling time to the number of square roots; S005, forecasting orbital elements by an analytical method; S006, calculating an error between the sampling time orbital element and the analysis prediction orbital element, generating fitting data, and fitting the error by using a second-order Fourier series; S007, generating a smoothing result of the orbital elements of the space target at any moment by using a second-order Fourier series fitting model; S008, calculating the position and the speed of the space target at any moment; and S009, subtracting the position and the speed of the space target at any moment from the position and the speed under the time sequence corresponding to the test data to obtain an orbit smoothing error.

Description

technical field [0001] The present invention relates to the field of satellites. More specifically, it relates to a method for smoothing orbits of space objects on board. Background technique [0002] The orbit prediction of space objects is the prerequisite for the realization of space missions. Improving the accuracy of orbit prediction has important practical significance for orbit design, tracking and monitoring, GNSS navigation and positioning and other fields. [0003] When a space object is in orbit, it is not only affected by the gravitational force of the center of the earth, but also affected by various complex perturbations such as the earth's non-spherical shape, atmosphere, other celestial bodies, and solar light pressure. In order to predict and smooth the trajectory of space targets with high precision, three types of calculation methods can generally be used: analytical method (general perturbation method), numerical method (special perturbation method) and ...

AI Technical Summary

Problems solved by technology

STK has a high-precision orbit prediction model HPOP, which uses a set of high-fidelity mechanical models, and can choose a variety of different integration methods. The orbit prediction accuracy is very high, but its efficiency is not ideal for predicting dense ephemeris

Without considering the calculation efficiency, STK is indeed a very good satellite orbit simulation tool, but its poor scalability also limits its further application, which is also a common feature of many mature software

[0008] Although the ground measurement and control center can predict high-precision orbit data in the next 24 hours in advance at one time, it is limited by the bandwidth of measurement and control data transmission and the storage capacity of the on-board computer. The orbit prediction data is not the preferred solution, and the real-time orbit prediction must be performed on the spaceborne computer; on the other hand, in order to predict the orbit of the space target with high precision, it is generally necessary to establish the complex dynamics of the space target in orbit model, and numerically integrate the dynamic model, which puts high demands on the on-board computer, and cannot guarantee real-time

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