Initial value correcting method for space target track improvement

Abstract

The invention relates to an initial value correcting method for space target track improvement, which relates to the space technical field. In the invention, a nonlinear spreading model of prediction error coefficient related to along-track/normal direction prediction errors is established based on the prediction error spreading regulation of a space target track; nonlinear equation sets related to the prediction error coefficient of the along-track and normal direction prediction errors are respectively established based on multiple sets of observation datum acquired in different times; the evaluation to the along-track and normal direction prediction error coefficient is completed by fitting the along-track and normal direction errors; and based on the relationship between the prediction error coefficient and the track initial value error, the track initial value correcting amount is acquired, thus realizing the correction to the track initial value. Through repeated iteration, the accuracy of the track improvement initial value is improved; the track improvement process is promoted to be reliable; and the convergence is rapid.

Description

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AI Technical Summary

Benefits of technology

This patented technology helps predict errors during flight due to factors like astrology or gravity (the movement) over time improving its effectiveness. It uses an equation called the tendency equations that describes how changes made at certain points affecting the motion of objects may lead to deviations from their original position. By analyzing these variations with respect to both geometry and velocity, it provides valuable feedback about future improvements caused by this deviation. Overall, this innovative approach allows for more accurate predictions while reducing computational complexity compared to previous methods such as linear regression analysis.

Problems solved by technology

This patented technical problem addressed in this patents relates to finding an efficient way to correct errors caused during the orbital evaluation phase after multiple measurements on one object's location. These errors can lead to incorrect calculations when trying to determine its own position within certain limits due to changes over long distances.

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