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Calculation method of initial orbit for perturbation compensation of ultra-sparse radar data

A radar data and calculation method technology, applied in calculation, electrical digital data processing, special data processing applications, etc., can solve the problems of large measurement time span, sparse points, inapplicability, etc., and achieve the effect of meeting the requirements of initial orbit accuracy

Inactive Publication Date: 2018-04-13
CHINA XIAN SATELLITE CONTROL CENT
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Problems solved by technology

Due to the large measurement time span and the sparse number of points, the traditional initial orbit calculation method is no longer applicable

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  • Calculation method of initial orbit for perturbation compensation of ultra-sparse radar data
  • Calculation method of initial orbit for perturbation compensation of ultra-sparse radar data
  • Calculation method of initial orbit for perturbation compensation of ultra-sparse radar data

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Embodiment Construction

[0026] The present invention will be further described below in conjunction with the examples, and the present invention includes but not limited to the following examples.

[0027] According to the measurement data information, the present invention establishes the time transfer equation, integrates the idea of ​​orbit selection, and calculates the solution of the equation in the case of multi-turn transfer (the time difference between two measurement points is greater than 1 orbit period) in the sense of two bodies. On this basis , considering the perturbation compensation with a certain precision, the solution of the time transfer equation is modified and iterated until the initial orbital elements satisfying the analytical perturbation conditions are obtained.

[0028] The present invention specifically comprises the steps:

[0029] Step 1: Initialize the state quantity.

[0030] Given starting position r 1 , the target position r 2 , r 1 The corresponding measurement ...

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Abstract

The invention provides a supersparsity radar data perturbation compensation initial orbit calculation method. According to the measuring data information, a time migration equation is built; an orbit optimum selection idea is fused; the equation solution under the condition of multi-circle transfer is calculated under the disome meaning; on the basis, the perturbation compensation at the certain precision is considered; the solution of the time migration equation is subjected to correction and iteration until the initial orbit number meeting the perturbation removing condition is obtained. The method provided by the invention effectively solves the problem of long time interval of one-ascending and one-descending two-point data and inapplicability of a conventional initial orbit calculation method; the requirements of the orbit improvement on the initial orbit precision are met; the blank in the high-precision initial orbit determination aspect under the large-time span condition of the supersparsity radar data in China is filled.

Description

technical field [0001] The invention belongs to the field of aerospace measurement and control, and relates to a method for determining an initial orbit. Background technique [0002] Ultra-sparse radar data refers to the measurement data that the measurement equipment obtains a very small number of sampling points per circle for a single space target. For example, the NAVSPASUR space fence system in the United States has only a very short measurement arc (1 to 2 points). When the target passes through the beam of the observation equipment twice in different directions (one up and one down or one down and one up), the time interval of the two remaining position vectors generally differs by several hours. Ultra-sparse data is characterized by very few measurement points (for low-orbit targets, there may be only 4 to 6 points of data per day), and the data time span is large (more than several hours). Due to the large measurement time span and the sparse number of points, th...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F19/00
CPCG16Z99/00
Inventor 何雨帆张淑琴张荣之郭海张育卫杨涛李宁杜凯
Owner CHINA XIAN SATELLITE CONTROL CENT
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