Orbit parameter exception cleaning method based on extension minimization estimation

A technology for orbital parameters and cleaning methods, applied in the field of orbital parameter anomaly cleaning, which can solve the problems of lack of theoretical support, data "islands, inapplicability, etc."

Active Publication Date: 2021-06-01
ZIJINSHAN ASTRONOMICAL OBSERVATORY CHINESE ACAD OF SCI +1
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Problems solved by technology

However, there are such problems in practical applications: if there is a problem with the orbital parameters after it is released, it will be corrected later, and the orbital parameters with problems still exist in the catalog library; the orbital parameters of some targets are sparse, resulting in the existence of data "islands"; Some unknown events in the process of orbit determination caused abnormalities in the final orbital parameters, etc.
Because the a priori threshold for judging anomalies needs to be obtained by simulation, there are three significant problems in this technology: ① lack of theoretical support, which leads to unreasonable phenomena in judging anomalies; ② it cannot be applied to all objects in the space object catalog library, and its applicability is poor; ③The cleaning process of orbital parameters is cumbersome and inconsistent

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  • Orbit parameter exception cleaning method based on extension minimization estimation
  • Orbit parameter exception cleaning method based on extension minimization estimation
  • Orbit parameter exception cleaning method based on extension minimization estimation

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Experimental program
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no. 1 Embodiment

[0077] Based on the TLE data in the US NORAD cataloging database, aiming at the anomalies in the target 13025 time series, discuss the impact of the three combinations of threshold setting within the window and threshold setting outside the window on anomaly cleaning: strategy 1: 3 times the standard deviation of the window threshold , 3 times the standard deviation of the threshold outside the window; strategy 2: 2 times the standard deviation of the threshold outside the window, 3 times the standard deviation of the threshold outside the window; strategy 3: 2 times the standard deviation of the threshold outside the window, 2 times the standard deviation of the threshold outside the window.

[0078] Taking the object's orbital inclination anomaly cleaning as an example, discuss the impact of three strategies:

[0079] Step 1: Download all the data of target 13025, from January 9, 1982 to November 20, 1988;

[0080] Step 2: Read the data, specify the corrected observation val...

no. 2 Embodiment

[0092] For the TLE data in the US NORAD cataloging database, aiming at the anomaly with complex changes in orbital elements in the satellite Jason-2 time series with man-made maneuvers, the influence of the combined strategy of the number of window observations and three thresholds on the anomaly cleaning is discussed. Three combinations of threshold setting and threshold setting outside the window: strategy 1: 3 times the standard deviation of the window threshold, 3 times the standard deviation of the outside threshold; strategy 2: 2 times the standard deviation of the window threshold, 3 times the standard deviation of the outside threshold; strategy3 : The window threshold is 2 times the standard deviation, and the threshold outside the window is 2 times the standard deviation.

[0093] Satellite Jason-2 has the NORAD number 33105 and is pending from January 1, 2019 to January 11, 2021. After cleaning the corrected observations, there are a total of 1820 observations remai...

no. 3 Embodiment

[0108] According to Lidtke et al. (Lidtke, A.A., Gondelach, D.J., & Armellin, R. Optimizing filtering of two-line element sets to increase re-entry prediction accuracy for GTO objects [J]. Advances in Space Research, 2018:1289-1317.) As a result, the rocket object 14287 was selected as a comparison of the cleaning algorithm. Figure 8 The cleaning effects of the two algorithms are given. The left side of the figure shows the cleaning effect of the algorithm of this application, the dotted box is the comparison area, and the box is the abnormality determined by the new algorithm; the right side of the figure is the cleaning effect of the comparison scheme disclosed by Lidtke et al., and there are significant abnormalities. Therefore, the algorithm proposed by Lidtke et al. is unreasonable for certain anomaly judgments, which affects the judgment of subsequent anomalies, and there are a large number of anomalies.

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Abstract

The invention relates to an orbit parameter exception cleaning method based on extension minimization estimation. The orbit parameter exception cleaning method comprises the following specific steps of: selecting an orbit parameter exception cleaning method, an orbit parameter exception cleaning method and an orbit parameter exception cleaning method, the method comprises the following steps of: firstly, cleaning a corrected observation value: determining a threshold value for cleaning the corrected observation value by counting a release time interval of the observation value, or assigning a prior cleaning threshold value according to existing experience, and taking an orbital period as a unit; secondly, cleaning orbit parameters: based on polynomial regression and anomaly detection in a sliding window and detection of anomaly and space events outside the sliding window, completing observation value orbit element anomaly cleaning; If the target is close to the atmosphere reentry moment, all observation values containing negative ballistic coefficients are eliminated. The method can unify the orbital parameter exception cleaning process and effectively clean the orbital parameter exceptions of all targets in the spatial data cataloguing library.

Description

technical field [0001] The invention relates to the technical field of removing a small amount of orbital parameter anomalies existing in a space object orbit data cataloging library under the framework of celestial mechanics, specifically a method for cleaning orbital parameter anomalies based on expectation maximization estimation. Background technique [0002] The space object orbit data catalog library contains a large number of historical orbit parameters of objects, which is the basis for applications such as collision warning, ballistic coefficient estimation, atmospheric reentry forecast, and space object association. However, there are such problems in practical applications: if there is a problem with the orbital parameters after it is released, it will be corrected later, and the orbital parameters with problems still exist in the catalog library; the orbital parameters of some targets are sparse, resulting in the existence of data "islands"; Some unknown events i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20
CPCG06F30/20G06F2119/14
Inventor 刘劲宏杜建丽徐劲
Owner ZIJINSHAN ASTRONOMICAL OBSERVATORY CHINESE ACAD OF SCI
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