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A Reentry Prediction Method for Small Ellipse Targets in Sparse Data

A sparse data, numerical method technology, applied in design optimization/simulation, offensive equipment, projectiles, etc., can solve problems such as difficulty in judging orbit accuracy, large residual error of measurement elements, and difficulty in selecting initial values ​​of ballistic coefficients.

Active Publication Date: 2022-07-01
中国人民解放军32035部队
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Problems solved by technology

Compared with near-circular targets, the reentry prediction of small elliptical targets is more difficult due to the change of atmospheric drag coefficient with height. The difference may be large, and it is difficult to judge the accuracy of the trajectory determination results. However, the strategy of solving multiple ballistic coefficients in segments can obtain more accurate target orbits, but it is difficult to choose the initial value of the ballistic coefficient when re-entry prediction

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  • A Reentry Prediction Method for Small Ellipse Targets in Sparse Data
  • A Reentry Prediction Method for Small Ellipse Targets in Sparse Data
  • A Reentry Prediction Method for Small Ellipse Targets in Sparse Data

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Embodiment Construction

[0034] The present invention will be further described below in conjunction with the accompanying drawings:

[0035] The present invention comprises the following steps:

[0036] Step 1: Process the N-circle data collected in the past several days (usually 5 days), and use the numerical method to determine the orbit of the single-circle data respectively, and obtain the corresponding close root number (σ). 1 ,σ 2 ,…,σ N ); remove the short period term in the close root number, and calculate the corresponding square root number

[0037] Step 2: Use the Kepler square root as the root system, use the semi-numerical method for orbital integration, and use the least squares method to fit the ballistic coefficient of the re-entry target; the perturbation items considered in the integration include the earth's aspherical J 2 item, J 3 term, atmospheric drag; the integral model is as follows:

[0038]

[0039]

[0040]

[0041]

[0042]

[0043] Among them, ρ is ...

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Abstract

The invention discloses a re-entry prediction method for a small elliptical target under the condition of sparse data, which processes N-circle data collected in the past 5 days, uses a numerical method to determine the orbit of the single-circle data respectively, and uses the Kepler square root as the root. Compared with the prior art, the present invention proposes a numerical system based on the characteristics of sparse data and small elliptical orbits, and uses the semi-numerical method for orbit integration, and uses the least squares method to fit the ballistic coefficient of the re-entry target. A reentry forecasting method combining the method with the semi-numerical method. It effectively solves the problems that the residual error of joint orbit determination of multi-turn data is too large or does not converge in the case of sparse data, and it is difficult to determine the ballistic coefficient of orbit determination of single-turn data.

Description

technical field [0001] The invention relates to the field of aerospace measurement and control, in particular to a re-entry prediction method for small elliptical targets under the condition of sparse data. Background technique [0002] Massive space targets will not be completely burned during the re-entry process, and 10-40% of the debris still returns to the earth's surface, posing a great threat to life groups, building facilities, and ecological environment on the surface. known as a dangerous reentry target. Atmospheric drag is the main non-conservative perturbation force for the re-entry space target. Accurate space target surface-to-mass ratio and reasonable atmospheric drag characteristic modeling are the keys to accurately calculate the atmospheric drag acceleration and predict the re-entry time. The atmospheric drag coefficient is closely related to the shape, surface material, atmospheric composition and temperature of the space target. The atmospheric drag coef...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/28F42B15/01
CPCF42B15/01G06F30/20
Inventor 张炜崔文祝开建游经纬田鑫张育卫刘兴滕星全
Owner 中国人民解放军32035部队
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