DETERMINATION OF AES ORBIT ELEMENTS USING MIXED DATA

Автор(и)

  • S. Ja. Kolesnik Odessa Astronomical Observatory, Odessa National University T.G.Shevchenko Park, Odessa 65014, Ukraine, Україна
  • S. L. Strakhova Odessa Astronomical Observatory, Odessa National University, Україна

DOI:

https://doi.org/10.18524/1810-4215.2007.20.93667

Ключові слова:

artificial Earth satellites, orbit elements.

Анотація

An algorithm is worked out and a program is compiled for a determination of AES (artificial Earth satellite) orbit elements using both goniometrical and range-finder observations of different precision. The observations of one or several passages carried out from one or several stations can be used. A number of observational stations and a number of observations are not limited in principle. When solving this task the AES ephemerides on the moments of observations are calculated for different sets of orbit elements. A parameter F is considered which is a function of orbit elements. The parameter presents a square-mean deviation of AES ephemeris position on the moments {ti} from its observed one. The determination of real orbit elements comes to minimizing of parameter F by orbit elements using a method of deformed polyhedron. When calculating the ephemeris the amendments for 2-d, 3-d, 4-th geopotential zone harmonics are considered.

Посилання

Дубошин Г.Н.: 1968, Небесная механика. Основные задачи и методы, М., Наука.

Эскобал П.: 1970, Методы определения орбит, М., Мир.

Химмельблау Д.: 1975, Прикладное линейное программирование, М., Мир.

Калиткин Н.Н.: 1978, Численные методы, М., Наука.

Жонголович И.Д.: 1960, Бюлл. Института Теор. Астрономии, VII, N 10(93), 743.

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Опубліковано

2017-03-15

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