Initial Orbit Determination of a Space Object from Limited Angular Optical Measurements
Currently, the problem of initial orbit determination for space objects based on angular coordinate measurements (right ascension and declination) under limited data conditions is of significant practical value. The aim of this work was to develop a non-iterative estimation method for the slant rang...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Belarusian National Technical University
2025-07-01
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| Series: | Приборы и методы измерений |
| Subjects: | |
| Online Access: | https://pimi.bntu.by/jour/article/view/958 |
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| Summary: | Currently, the problem of initial orbit determination for space objects based on angular coordinate measurements (right ascension and declination) under limited data conditions is of significant practical value. The aim of this work was to develop a non-iterative estimation method for the slant range vector of an unknown space object relative to an observation site under conditions of limited angular optical measurement data, enabling near-real-time determination of orbital parameters (semi-major axis, inclination, eccentricity, longitude of the ascending node, and argument of latitude). This is particularly relevant for operational orbit determination of unknown space objects to prevent hazardous close approaches and potential collisions, especially given the increasing number of satellite launches and the growing density of space debris in low Earth orbit. A method for initial orbit determination (in the absence of prior orbital data) of an unknown space object is presented, based on angular optical measurements over a short observation arc (< 0.5°) in two detection regions. The proposed method allows for the estimation of the slant range vector of an unknown space object relative to the observation site using angular measurement data and computed values of the velocity projection onto the frame plane of a reference satellite (with known orbital parameters). To estimate the velocity projection onto the frame plane, a method for detecting space objects in optical surveillance system video data is employed. Experimental optical observations of the detected SL-12/RB rocket stage were performed, including angular measurements and orbital parameter calculations. The absolute errors in determining the semi-major axis of the SL-12/RB rocket stage did not exceed 19.71 km. The absolute errors in orbital inclination i, longitude of the ascending node Ω, and argument of latitude u were 0.033°, 0.083°, and 0.046°, respectively. |
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| ISSN: | 2220-9506 2414-0473 |