<abstract xmlns="http://www.w3.org/1999/xhtml">

In this paper, the results of the orbit determination of two Chinese rocket bodies from low earth orbit (LEO) regime based on the picosecond laser measurements provided by one laser sensor are presented. A new approach was implemented that involved using a set of single laser measurements known as full-rate measurements instead of normal points. The computation strategy was applied using three different scenarios, and several key parameters such as root mean square (RMS), RMS of position (RMSPOS), RMS of velocity (RMSVEL), and alert time were determined. The results obtained indicate that the most optimal solution is to use short orbital arcs that are 24 h long. In this case, the average RMSPOS is approximately 345–530 m, the average RMSVEL is approximately 1 m/s, and the average arc RMS is approximately 3.7–7.0 cm. The determined alert time parameter, which refers to the time during which the laser observation of a given object should be repeated, is on average approximately 19.5 h.
If longer orbital arcs, such as 2 days or more, are used, RMSPOS and RMSVEL actually reach the level of single centimeters and single millimeters per second, respectively. However, the arc RMS increases significantly to at least decimeters and even above 1 m in some cases. This suggests that the long arc approach is not a favorable solution.
In addition, an interesting discovery has been presented that some Chinese launchers are equipped likely with the laser retroreflectors that can easily reflect the laser beam.
</abstract>

In this paper, the results of the orbit determination of two Chinese rocket bodies from low earth orbit (LEO) regime based on the picosecond laser measurements provided by one laser sensor are presented. A new approach was implemented that involved using a set of single laser measurements known as full-rate measurements instead of normal points. The computation strategy was applied using three different scenarios, and several key parameters such as root mean square (RMS), RMS of position (RMSPOS), RMS of velocity (RMSVEL), and alert time were determined. The results obtained indicate that the most optimal solution is to use short orbital arcs that are 24 h long. In this case, the average RMSPOS is approximately 345–530 m, the average RMSVEL is approximately 1 m/s, and the average arc RMS is approximately 3.7–7.0 cm. The determined alert time parameter, which refers to the time during which the laser observation of a given object should be repeated, is on average approximately 19.5 h.
If longer orbital arcs, such as 2 days or more, are used, RMSPOS and RMSVEL actually reach the level of single centimeters and single millimeters per second, respectively. However, the arc RMS increases significantly to at least decimeters and even above 1 m in some cases. This suggests that the long arc approach is not a favorable solution.
In addition, an interesting discovery has been presented that some Chinese launchers are equipped likely with the laser retroreflectors that can easily reflect the laser beam.

Orbit Determination of Chinese Rocket Bodies from the Picosecond Full-Rate Laser Measurements

Artificial Satellites

This work is licensed under the Creative Commons Attribution 4.0 International License.

In this paper, the results of the orbit determination of two Chinese rocket bodies from low earth orbit (LEO) regime based on the picosecond laser measurements...

Orbit Determination of Chinese Rocket Bodies from the Picosecond Full-Rate Laser Measurements

Online veröffentlicht: 19. Jan. 2024

Seitenbereich: 256 - 277

Eingereicht: 27. Okt. 2023

Akzeptiert: 24. Nov. 2023

DOI: https://doi.org/10.2478/arsa-2023-0010

Schlüsselwörter
space debris, rocket bodies, LEO, full-rate laser ranging, orbit determination

© 2023 Paweł Lejba, published by Sciendo

This work is licensed under the Creative Commons Attribution 4.0 International License.

Orbit Determination of Chinese Rocket Bodies from the Picosecond Full-Rate Laser Measurements

Online veröffentlicht: 19. Jan. 2024

Seitenbereich: 256 - 277

Eingereicht: 27. Okt. 2023

Akzeptiert: 24. Nov. 2023

DOI: https://doi.org/10.2478/arsa-2023-0010

Schlüsselwörterspace debris, rocket bodies, LEO, full-rate laser ranging, orbit determination

© 2023 Paweł Lejba, published by Sciendo

This work is licensed under the Creative Commons Attribution 4.0 International License.

Schlüsselwörter
space debris, rocket bodies, LEO, full-rate laser ranging, orbit determination