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Aerospace
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Innovative Methods for Satellite and Space Debris Identification and Motion...
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Innovative Methods for Satellite and Space Debris Identification and Motion Reconstruction

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Astronautics & Space Science".

Deadline for manuscript submissions: closed (28 February 2025) | Viewed by 5062

Special Issue Editors

Dr. Leonardo Parisi

E-Mail Website
Guest Editor
Institute of Complex System (ICS), National Council of Research (CNR), UOS Sapienza, 00185 Rome, Italy
Interests: space debris; satellite and debris tracking system; optical observations; stereometry; object segmentation; object detection; computer vision
Dr. Paolo Marzioli

E-Mail Website
Guest Editor
Department of Mechanical and Aerospace Engineering, Sapienza University of Rome, via Eudossiana 18, 00184, Rome, Italy
Interests: CubeSats; small satellites; satellites system engineering; satellite constellations; in-orbit experiments; satellite navigation; space system development and operations; space traffic management; space debris
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

The rapid advancement of space exploration and exploitation and satellite technology has led to an increasing number of in-orbit objects. This growth in space debris poses significant challenges regarding the safety and sustainability of future space missions. To address this critical issue, we are inviting researchers and experts in the field to contribute their original research to a Special Issue on "Innovative Methods for Satellite and Space Debris Identification and Motion Reconstruction".

This Special Issue aims to bring together cutting-edge research on the development of novel techniques and methodologies for the identification and motion reconstruction of satellites and space debris. We encourage submissions that explore a wide range of innovative approaches, including, but not limited to:

  • Sensor fusion and data integration techniques for space debris tracking and identification;
  • Machine learning and artificial intelligence algorithms for automated detection and classification of satellites and debris;
  • Advanced image processing and computer vision techniques for satellite imagery analysis;
  • Radar and lidar-based methods for space debris detection and tracking;
  • Multi-sensor data fusion for accurate motion estimation and trajectory prediction of space objects.
  • Statistical modeling and optimization techniques for space debris population analysis;
  • Innovative sensor technologies and platforms for space situational awareness;
  • Modeling and tracking of novel mission profiles (e.g., SSTO, suborbital spaceplanes, mega-constellations, and higher-orbit exploitation);
  • Mitigation techniques for space debris density and population;
  • Uncertainty quantification and error propagation in space debris tracking and motion reconstruction.

Authors are encouraged to present original research articles that provide a comprehensive overview of the state of the art in this rapidly evolving field.

Dr. Leonardo Parisi
Dr. Paolo Marzioli
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • satellite
  • space debris
  • identification
  • motion
  • tracking
  • orbit determination
  • attitude

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Further information on MDPI's Special Issue policies can be found here.

Published Papers (4 papers)

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Research

29 pages, 16669 KiB  
Article
Spin Period Evolution of Decommissioned GLONASS Satellites
by Abdul Rachman, Alessandro Vananti and Thomas Schildknecht
Aerospace 2025, 12(4), 283; https://doi.org/10.3390/aerospace12040283 - 27 Mar 2025
Viewed by 244
Abstract
Light curve analysis of defunct satellites is critical for characterizing their rotational motion. An accurate understanding of this aspect will benefit active debris removal and on-orbit servicing missions as part of the solution to the space debris issue. In this study, we explored [...] Read more.
Light curve analysis of defunct satellites is critical for characterizing their rotational motion. An accurate understanding of this aspect will benefit active debris removal and on-orbit servicing missions as part of the solution to the space debris issue. In this study, we explored the attitude behavior of inactive GLONASS satellites, specifically a repeating pattern observed in their spin period evolution. We utilized a large amount of data available in the light curve database maintained by the Astronomical Institute of the University of Bern (AIUB). The morphology of the inactive GLONASS light curves typically features four peaks in two pairs and is presumably attributed to the presence of four evenly distributed thermal control flaps or radiators on the satellite bus. The analysis of the periods extracted from the light curves shows that nearly all of the inactive GLONASS satellites are rotating and exhibit a periodic oscillating pattern in their spin period evolution with an increasing or decreasing secular trend. Through modeling and simulation, we found that the periodic pattern is likely a result of canted solar panels that provide an asymmetry in the satellite model and enable a wind wheel or fan-like mechanism to operate. The secular trend is a consequence of differing values of the specular reflection coefficients of the front and back sides of the solar panels. Assuming an empirical model describing the spin period evolution of 18 selected objects, we found significant variations in the average spin period and amplitude of the oscillations, which range from 8.11 s to 469.58 s and 1.10 s to 513.24 s, respectively. However, the average oscillation period remains relatively constant at around 1 year. Notably, the average spin period correlates well with the average amplitude. The empirical model can be used to extrapolate the spin period in the future, assuming that the oscillating pattern is preserved and roughly shows a linear trend. Full article
(This article belongs to the Special Issue Innovative Methods for Satellite and Space Debris Identification and Motion Reconstruction)
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18 pages, 6971 KiB  
Article
A Parametrical Study on Hypervelocity Impact of Orbital Debris
by Ali Eken and Seher Eken
Aerospace 2024, 11(10), 819; https://doi.org/10.3390/aerospace11100819 - 7 Oct 2024
Viewed by 1018
Abstract
A numerical method has been presented to simulate hypervelocity impacts on metal targets. The target is a rectangular prism and is positioned at various inclined angles relative to the impact direction, while four different projectiles such as square prism, triangular prism, truncated cone, [...] Read more.
A numerical method has been presented to simulate hypervelocity impacts on metal targets. The target is a rectangular prism and is positioned at various inclined angles relative to the impact direction, while four different projectiles such as square prism, triangular prism, truncated cone, and ogival shape are chosen. This numerical model employs an open-source code, MPM3D-F90, which is based on the Material Point Method. In order to enhance flexibility of the code for defining projectiles and target bodies in the material domain, a preprocessor is developed to create a variety of geometrical shapes for a given volume. In addition to supplementing and defining various geometrical bodies, this tool also simplifies the preprocessing process to create the user’s specific preferences for the problem. To demonstrate the utility of the preprocessor tool and investigate the influence of geometry on hypervelocity impacts, simulations are conducted using various projectile and target configurations. The analysis results reveal that the structure of the debris cloud formations, scattering behavior of the ejected particle from both front and rear faces, and penetration depth measures are significantly influenced by the projectile shape and impact angles. Full article
(This article belongs to the Special Issue Innovative Methods for Satellite and Space Debris Identification and Motion Reconstruction)
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21 pages, 9367 KiB  
Article
Design of Low-Cost Simulation Space Micro Debris Launch Device
by Renjie Yang, Kai Tang, Xuqiang Lang, Cheng He, Yu Liu and Yue Liu
Aerospace 2024, 11(7), 577; https://doi.org/10.3390/aerospace11070577 - 15 Jul 2024
Viewed by 1113
Abstract
The high cost and low emission frequency of microparticle launchers have resulted in a long lead time for the development of detectors for micro-debris in space. In this paper, two low-cost, high-emission-frequency, small-size, millimeter-sized particle launchers are designed using the principles of gas [...] Read more.
The high cost and low emission frequency of microparticle launchers have resulted in a long lead time for the development of detectors for micro-debris in space. In this paper, two low-cost, high-emission-frequency, small-size, millimeter-sized particle launchers are designed using the principles of gas expansion and surge propulsion by a high-speed air stream. Electrostatic detection is utilized to determine the emission velocity of the microbeads and their deviation from a specific position on the flight trajectory. The emission rate and accuracy of both methods were experimentally evaluated, along with the deviation of the detection system. Both devices emitted microbeads to simulate micro-debris, providing experimental data for the development of a space debris detector and establishing research conditions for studying the impact of micro-debris. Full article
(This article belongs to the Special Issue Innovative Methods for Satellite and Space Debris Identification and Motion Reconstruction)
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17 pages, 7879 KiB  
Article
A Dual Perspective on Geostationary Satellite Monitoring Using DSLR RGB and sCMOS Sloan Filters
by Lorenzo Mariani, Lorenzo Cimino, Matteo Rossetti, Mascia Bucciarelli, Shariar Hadji Hossein, Simone Varanese, Gaetano Zarcone, Marco Castronuovo, Alessandra Di Cecco, Paolo Marzioli and Fabrizio Piergentili
Aerospace 2023, 10(12), 1026; https://doi.org/10.3390/aerospace10121026 - 12 Dec 2023
Viewed by 1741
Abstract
This paper outlines a multi-system approach for ground-based optical observations and the characterization of satellites in geostationary orbit. This multi-system approach is based on an in-depth analysis of the key factors to consider for light curve analysis of Earth’s orbiting satellites. Light curves [...] Read more.
This paper outlines a multi-system approach for ground-based optical observations and the characterization of satellites in geostationary orbit. This multi-system approach is based on an in-depth analysis of the key factors to consider for light curve analysis of Earth’s orbiting satellites. Light curves have been observed in different spectral bands using two different systems. The first system is specialized for astronomical observations and consists of a telescope equipped with an sCMOS camera and Sloan photometric filters. In contrast, the second system is a more cost-effective solution designed for professional non-astronomical applications, incorporating DSLR cameras equipped with RGB channels associated with a Bayer mask and photographic lenses. This comparative analysis aims to highlight the differences and advantages provided by each system, stressing their respective performance characteristics. The observed light curves will be presented as a function of the phase angle, which depends on the relative positions of the observer, the object, and the Sun. This angle plays an important role in optimizing the visibility of Earth’s orbiting satellites. Finally, multiband observations of different satellites will be compared to seek an associated spectral signature, which may allow the identification of structurally similar objects through optical observations. Full article
(This article belongs to the Special Issue Innovative Methods for Satellite and Space Debris Identification and Motion Reconstruction)
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