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Small elliptic target reentry forecasting method under sparse data condition

A sparse data and numerical method technology, applied in the direction of electrical digital data processing, special data processing applications, instruments, etc., can solve the problems of large residual error of measurement elements, difficulty in judging the accuracy of orbit, and difficulty in selecting the initial value of ballistic coefficient, etc., to achieve Solve the effect of excessive residual or non-convergence

Active Publication Date: 2019-07-09
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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  • Small elliptic target reentry forecasting method under sparse data condition
  • Small elliptic target reentry forecasting method under sparse data condition
  • Small elliptic target reentry forecasting method under sparse data condition

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Embodiment Construction

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

[0035] The present invention comprises the steps:

[0036] Step 1: Process the N-circle data collected in the past several days (generally 5 days), use the numerical method to determine the orbit of the single-circle data, 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 flat root number

[0037] Step 2: Use Kepler’s flat root number as the root number system, and 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 term considered in the integration includes the earth’s non-spherical J 2 Item, J 3 term, atmospheric resistance; the integral model is as follows:

[0038]

[0039]

[0040]

[0041]

[0042]

[0043] Among them, ρ is the atmosph...

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Abstract

The invention discloses a small elliptic target reentry forecasting method under a sparse data condition. N circles of data collected in the past 5 days are processed, a numerical method is adopted tocarry out track determination on the single circle of data, the Kepler root number is adopted as a root number system, a semi-numerical method is adopted to carry out track integration, and a least square method is adopted to fit a ballistic coefficient of a reentry target. Compared with the prior art, the invention provides a reentry forecasting method combining the numerical method and the semi-numerical method for the characteristics of the sparse data and the small elliptic orbit. The problems that under the condition of sparse data, the multi-circle data joint orbit determination residual error is too large or not convergent, and the ballistic coefficient is difficult to determine through single-circle data orbit determination are effectively solved.

Description

technical field [0001] The invention relates to the field of aerospace measurement and control, in particular to a method for reentry prediction of small ellipse targets under the condition of sparse data. Background technique [0002] Large-mass space objects will not be completely burned during the re-entry process, and 10-40% of the debris will still return to the earth's surface, which poses a great threat to the life groups, building facilities, and ecological environment on the surface. called a dangerous reentry target. Atmospheric drag is the most important non-conservative perturbation force on space targets about to re-enter. Accurate surface-to-mass ratio of space targets and reasonable modeling of atmospheric drag characteristics are the keys to accurately calculate the acceleration of atmospheric drag and predict the re-entry time. The atmospheric drag coefficient is closely related to the space target's shape, surface material, atmospheric composition, and tem...

Claims

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Application Information

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IPC IPC(8): G06F17/50F42B15/01
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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