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        <title>Frontiers in Space Technologies | Space Debris section | New and Recent Articles</title>
        <link>https://www.frontiersin.org/journals/space-technologies/sections/space-debris</link>
        <description>RSS Feed for Space Debris section in the Frontiers in Space Technologies journal | New and Recent Articles</description>
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        <pubDate>2026-05-13T09:03:36.604+00:00</pubDate>
        <ttl>60</ttl>
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        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2026.1777020</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2026.1777020</link>
        <title><![CDATA[Conceptualizing thresholds for effective active debris removal in Low Earth Orbit]]></title>
        <pubdate>2026-02-25T00:00:00Z</pubdate>
        <category>Brief Research Report</category>
        <author>Sofia Yang</author>
        <description><![CDATA[The rapid growth of orbital debris in the Low Earth Orbit (LEO) poses an escalating risk to space operations, with existing mitigation proving insufficient to prevent long-term instability. This study models debris population dynamics in the 500–600 km LEO under current FCC 5-year deorbit rules and varying levels of Active Debris Removal (ADR). Using publicly available orbital catalogs and a collision-risk proxy based on object density, cross-section, and relative velocity, simulations depict debris growth and collision risk trajectories under a 30-year period and various scenarios. Results indicate that removal of ∼60 large objects (>10 cm) per year is the threshold at which debris growth becomes negative and collision risk declines. This value is scenario-dependent and is presented as an illustrative threshold under controlled assumptions rather than a robust or universal quantitative value. The primary contribution of this study is to demonstrate the existence of a minimum viable ADR regime, which can provide conceptual guidance for debris mitigation policy.]]></description>
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        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2023.1309940</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2023.1309940</link>
        <title><![CDATA[Kessler’s syndrome: a challenge to humanity]]></title>
        <pubdate>2023-11-28T00:00:00Z</pubdate>
        <category>Hypothesis and Theory</category>
        <author>Amrith Mariappan</author><author>John L. Crassidis</author>
        <description><![CDATA[Kessler’s Syndrome is a global phenomenon characterized by the presence of tens of millions of debris pieces of various sizes that disrupt satellite operations. This article delves into the potential outcomes of a Kessler’s Syndrome occurrence and its implications on satellite operations. The potential threats posed by this scenario are discussed, including the implications of minimal to no satellite function on human impacts, including crashes and minimized or disrupted functions in essential utility services, as these sectors heavily rely on satellites. In addition, we discuss how the loss of satellite communications could gradually or rapidly affect global affairs. As humans are a dominant force on Earth, their endangerment would reverberate throughout the ecological system, potentially leading to the demise of other species. It is crucial for policymakers and relevant stakeholders to recognize these implications and work towards safeguarding satellite communication to mitigate potential negative outcomes for humanity’s wellbeing and progress. The recycling of space debris emerges as a promising and long-term sustainable solution to the mitigation of space debris. By repurposing decommissioned satellites and debris into useful materials to support other space missions, this recycling strategy presents a win-win scenario, promoting environmental sustainability and resource efficiency in space exploration.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2023.1162915</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2023.1162915</link>
        <title><![CDATA[Deep space debris—Detection of potentially hazardous asteroids and objects from the southern hemisphere]]></title>
        <pubdate>2023-05-23T00:00:00Z</pubdate>
        <category>Perspective</category>
        <author>Ed Kruzins</author><author>Lance Benner</author><author>Russell Boyce</author><author>Melrose Brown</author><author>David Coward</author><author>Sam Darwell</author><author>Phil Edwards</author><author>Lauren Elizabeth-Glina</author><author>Jon Giorgini</author><author>Shinji Horiuchi</author><author>Andrew Lambert</author><author>Joseph Lazio</author><author>Guifre Molera Calves</author><author>John Moore</author><author>Edwin Peters</author><author>Chris Phillips</author><author>Jamie Stevens</author><author>Arie Verveer</author>
        <description><![CDATA[Space debris are composed of both natural and human made objects, some in near Earth orbits while others are passing through deep space. Asteroids may represent one form of near Earth and deep space debris. In this article we report on a set of asteroid observations from the southern hemisphere. We indicate that Apollo and Aten class asteroids represent another form of deep space debris of a potentially hazardous nature to orbiting spacecraft and/or Earth based locations. We also show some of the operational challenges, types of facilities and the importance of geographic diversity, that is, necessary for detecting, observing and characterising asteroids, especially PHA’s. For many years, space agencies and institutions have observed and monitored near Earth asteroids and objects (NEO’s) using high gain radio frequency antennas and optical telescopes in the northern hemisphere (GSSR, Arecibo, Catalina, Pan-STARRS, Atlas and Linear) 1) However a regular operational system to monitor the southern skies does not have the same level of maturity and is where a percentage of asteroids and various human made objects are not detected until they pass into northern skies. To fill that gap the Southern Hemisphere Asteroid Radar Program (SHARP) 2) located in Australia uses available antenna time on either a 70 or 34 m beam waveguide antenna located at the Canberra Deep Space Communication Complex (CDSCC) to transmit a Doppler compensated continuous radio wave at 2.114 GHz (14.2 cm) and 7.15945 GHz (4.2 cm) toward the NEO and receive its echoes at the 64 m Parkes or 6 m × 22 m Australia Telescope Compact Array (ATCA) antennas at Narrabri in Australia. This mode of NEO observation is termed a deep space bistatic radar. The southern hemisphere program has also recently been joined by the 12 m University of Tasmania antennas at Hobart (Tasmania) and Katherine (Northern Territory). Combining SHARPS bistatic radar with small optical apertures located at the University of New South Wales (UNSW) and University of Western Australia (UWA) allows combined optical/RF NEO detections. Whilst sub-metre class optical instruments have contributed independently to asteroid detection over decades, the use of coordinated small 0.3–0.5 m instruments synchronized to large asteroid radars offers an observational flexibility and adaptability when larger optical systems 3) are dedicated to other forms of professional optical astronomy. Since 2015, SHARP has illuminated and tracked over 30 NEO’s ranging in diameter from 7 to 5000 m at ranges of 0.1–18 lunar distances (LD) from Australia.]]></description>
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        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2023.1159825</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2023.1159825</link>
        <title><![CDATA[Editorial: Space environment characterization]]></title>
        <pubdate>2023-02-24T00:00:00Z</pubdate>
        <category>Editorial</category>
        <author>Waldemar Bauer</author><author>Vitali Braun</author><author>Yukihiton Kitazawa</author><author>Igor Telichev</author>
        <description></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.998064</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.998064</link>
        <title><![CDATA[A new impact assessment model to integrate space debris within the life cycle assessment-based environmental footprint of space systems]]></title>
        <pubdate>2022-11-29T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Thibaut Maury-Micolier</author><author>Alice Maury-Micolier</author><author>Arnaud Helias</author><author>Guido Sonnemann</author><author>Philippe Loubet</author>
        <description><![CDATA[By analogy to conventional environmental impacts, the potential release of debris or generation of fragments can be considered as the emission of an environmental stressor damaging the orbital ‘natural’ resource which supports space activities. Hence, it appears relevant to integrate systematically the impact of the emission of debris on the orbital resource within the life cycle impact assessment (LCIA) step to broaden the scope of life cycle assessment (LCA) for space systems. The main objective of this article is to propose a set of characterization factors to compute the impact caused by the generation of debris within the orbital environment. To do so, the proposed approach follows the methodology of emission-related characterization models in LCIA. the characterization model enables to link the emission of debris and final economic damages to space activities through a complete impact pathway including the fate of debris in downstream orbital compartments, the exposure of targeted space objects to this debris, and the economic damage in case of collision between the debris and the space object. The model is computed for different compartments of the low earth orbit (LEO) region thanks to a discretization of the orbital environment. Results show that the potential damages are the highest for orbital compartments located in the orbital bands of altitude/inclination: 550–2000 km/52–54°, 1,200–2000 km/86–88°, 400–2000 km/96–100°, because of the downstream location of Starlink constellation, OneWeb constellation, and earth observation satellites, respectively. The proposed set of CFs can be used in the LCA of different space systems in order to include impacts and damages related to space debris, along with other environmental impacts. This original development fully in line with the standardized LCIA framework would have potential for further integration into harmonised sector-specific rules for the European space sector such as product environmental footprint category rules (PEFCR).]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.867853</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.867853</link>
        <title><![CDATA[A novel evaluation method for in situ space debris detection based on conductive traces]]></title>
        <pubdate>2022-10-21T00:00:00Z</pubdate>
        <category>Technology and Code</category>
        <author>Sebastian Fexer</author>
        <description><![CDATA[To enable the detection of micrometeoroids and small-sized space debris (MMSD) in the sub-mm range, in situ detectors aboard a spacecraft are the tool of choice. Unfortunately, only a few projects have been sent to space until today. However, knowledge of the MMSD population is important to keep the reference models up-to-date and gain more insights into factors like the amount of debris and its distribution along certain orbits. This will be crucial for the safety of current and future spaceflight missions. Present-day in situ detection systems mostly rely on impact recognition and characterization using different methods. One of them is the perforation of a special detection area during such an event. These areas consist of one or more layers provided with conductive traces. Any interruption of one of these lines can be recognized using some kind of electrical continuity testing method or the determination of the resistance. This goes along with some drawbacks, like the difficult or even impossible multi-event recognition along one line. The proposed concept relies on a reflectometric approach. In doing so, for example, pulses are being sent along a well-defined transmission line, which is a part of the detection area. Any alteration in the characteristic line impedance, for instance, due to an impact, will generate reflections back into the generator. Their evaluation can provide the location as well as the complex impedance of the perturbation.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.933988</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.933988</link>
        <title><![CDATA[MOVE-III: A CubeSat for the detection of sub-millimetre space debris and meteoroids in Low Earth Orbit]]></title>
        <pubdate>2022-10-17T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Xanthi Oikonomidou</author><author>Eleftherios Karagiannis</author><author>Dominik Still</author><author>Florian Strasser</author><author>Felix S. Firmbach</author><author>Jonathan Hettwer</author><author>Allan G. Schweinfurth</author><author>Paul Pucknus</author><author>Deniz Menekay</author><author>Tianyi You</author><author>Maximilian Vovk</author><author>Selina Weber</author><author>Zeyu Zhu</author>
        <description><![CDATA[The Munich Orbital Verification Experiment (MOVE) is a CubeSat student project housed at the Scientific Workgroup for Rocketry and Spaceflight at the Technical University of Munich. MOVE-III is the fourth CubeSat under development, and the first 6U mission of the MOVE project that will carry a dedicated scientific payload in orbit. The mission aims at acquiring in-situ observations of sub-millimetre space debris and meteoroids in Low Earth Orbit, with the objective of compiling a dataset of flux, as well as object mass and velocity measurements that can be used for the validation of the small object estimates of space debris models and support further studies related to the characterisation of the space environment. The MOVE-III CubeSat employs the MOVE-BEYOND platform and is planned to carry three Debris Density Retrieval and Analysis (DEDRA) plasma ionization sensors. The Preliminary Design Review has been completed in early 2022, with the next milestone being the Critical Design Review, planned for 2023. The paper elaborates on the scientific objectives of the mission and the expected data products, provides an overview of the detector operation principle and presents the overall system architecture, the platform configuration and the subsystem interaction. Considerations on the debris mitigation aspects of the mission are additionally discussed.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.891753</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.891753</link>
        <title><![CDATA[Analysis of upper atmospheric effects on material per onboard atomic oxygen monitor system of SLATS]]></title>
        <pubdate>2022-10-06T00:00:00Z</pubdate>
        <category>Review</category>
        <author>Yugo Kimoto</author><author>Yuta Tsuchiya</author><author>Eiji Miyazaki</author><author>Aki Goto</author><author>Kazuki Yukumatsu</author><author>Shunsuke Imamura</author>
        <description><![CDATA[JAXA has proposed an innovative idea for satellites in Low Earth Orbit (LEO). The Super-Low Altitude Test Satellite (SLATS), also known as TSUBAME, is the first Earth observation satellite to occupy a Super-Low Orbit (S-LEO) or Very Low Earth Orbit (VLEO), below 300 km. The purposes of SLATS are 1) testing the maintenance of the satellite’s altitude with its ion engine against high atmospheric drag at a super-low altitude, 2) acquiring data on atmospheric density and atomic oxygen (AO), and 3) testing optical Earth observation. SLATS was successfully launched on 23 December 2017. SLATS was then altitude-controlled for 636 days to 271.7 km using chemical thrusters, aerodynamic drag, and ion engine propulsion. SLATS finally maintained its orbit of 167.4 km for 7 days and finished its operation on 1 October 2019. All the SLATS and Atomic oxygen MOnitor (AMO) data was acquired during these operations. The AMO is one of the mission sensors that monitor AO and its effects on spacecraft materials. The data from the AMO contributes to the choice of materials in future S-LEO satellite design. The data obtained by the AMO are valuable in that they provide considerable knowledge on AO fluence and its effects on space materials. A precise atmospheric density model and atmospheric composition model are indispensable for predicting the trajectory or re-entry of debris in orbit. Atmospheric models such as NRLMSISE-00, JB 2008, and DTM2013 have been developed, but few studies compare these models and the actual atmospheric environment in LEO. The average atmospheric density obtained from SLATS is lower than the value predicted by the atmospheric models (NRLMSISE-00, JB 2008, and DTM 2013). Understanding the model’s accuracy will contribute to the orbit control of future S-LEO satellites and the orbit prediction and control of debris in LEO.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.933664</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.933664</link>
        <title><![CDATA[Palladium-coated kapton for use on dust detectors in low earth orbit: Performance under hypervelocity impact and atomic oxygen exposure]]></title>
        <pubdate>2022-09-28T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Aishling Dignam</author><author>Penelope J. Wozniakiewicz</author><author>Mark J. Burchell</author><author>Luke S. Alesbrook</author><author>Adrian Tighe</author><author>Agnieszka Suliga</author><author>Johanna Wessing</author><author>Anton Kearsley</author><author>John Bridges</author><author>John Holt</author><author>Stuart Howie</author><author>Libby Peatman</author><author>Dennis Fitzpatrick</author>
        <description><![CDATA[Observation of dust and debris in the near Earth environment is a field of great commercial and scientific interest, vital to maximising the operational and commercial life-cycle of satellites and reducing risk to increasing numbers of astronauts in Low Earth Orbit (LEO). To this end, monitoring and assessment of the flux of particles is of paramount importance to the space industry and wider socio-economic interests that depend upon data products/services from orbital infrastructure. We have designed a passive space dust detector to investigate the dust environment in LEO—the Orbital Dust Impact Experiment (ODIE). ODIE is designed for deployment in LEO for ∼1 year, whereupon it would be returned to Earth for analysis of impact features generated by dust particles. The design emphasises the ability to distinguish between the orbital debris (OD) relating to human space activity and the naturally occurring micrometeoroid (MM) population at millimetre to submillimetre scales. ODIE is comprised of multiple Kapton foils, which have shown great potential to effectively preserve details of the impacting particles’ size and chemistry, with residue chemistry being used to interpret an origin (OD vs. MM). LEO is a harsh environment—the highly erosive effects of atomic oxygen damage Kapton foil—requiring the use of a protective coating. Common coatings available for Kapton (e.g., Al, SiO2, etc.) are problematic for subsequent analysis and interpretation of OD vs. MM origin, being a common elemental component of MM or OD, or having X-ray emission peaks overlapping with those of elements used to distinguish MM from OD. We thus propose palladium coatings as an alternative for this application. Here we report on the performance of palladium as a protective coating for a Kapton-based passive dust detector when exposed to atomic oxygen and impact. When subjected to impact, we observe that thicker coatings suffer delamination such that a coating of <50 nm is recommended. Analysis of atomic oxygen exposed samples shows a thin 10 nm coating of palladium significantly reduces the mass loss of Kapton, while coatings of 25 nm and over perform as well as or better than other commonly used coatings.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.933340</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.933340</link>
        <title><![CDATA[Proton Spectra for the Interplanetary Space Derived From Different Environmental Models]]></title>
        <pubdate>2022-07-15T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>E. M. Klein</author><author>M. Sznajder</author><author>P. Seefeldt</author>
        <description><![CDATA[Knowledge about the space radiation environment is crucial for the design and selection of materials and components used for space applications. This environment is characterized not only by the Sun’s electromagnetic radiation but also by charged particles categorized into solar wind, solar energetic particles (SEP) and galactic cosmic rays (GCR). Especially for material engineering and qualification testing, differential and integral spectra for particle energies ranging from keVs to GeVs are required. Up to now, a wide variety of models is available, whereas it is difficult to keep the overview. Although, e.g., the European Cooperation for Space Standardization (ECSS) standard includes instructions on how to investigate particle radiation, it does not provide an overall view. This paper shall support those in need of a comprehensive overview and provide comprehensive information about proton radiation spectra that can potentially be of use for space engineering tasks ranging from mission analysis to material and component design as well as qualification testing. The publicly accessible platforms OLTARIS, SPENVIS, and OMERE were examined for available proton spectra to be used. Exemplary, the particle radiation of solar cycle 23 is considered, which comprehends the years 1996–2008. A common drawback of the available models is their restriction to the MeV-range. Particularly when materials are directly exposed to the space environment, low energetic particles, specifically, the keV-range, are of high interest, since these particle transfer all their energy to the material. Therefore, additional data sources were used in order to include the usually neglected low energy protons into the derived spectrum. The data was transferred to common set of units and eventually could be compared and merged together. This includes a comparison of the most common models, incorporating data foundation, applicability, and accessibility. As a result, extensive and continues spectra are fitted that take all different models with its different energies and fluxes into account. Each covered year is represented by a fitted spectrum including confidence level as applicable. For solar active and quite times spectra are provided.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.867236</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.867236</link>
        <title><![CDATA[Estimation of Orbital Parameters of Broken-Up Objects From In-Situ Debris Measurements]]></title>
        <pubdate>2022-04-11T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Toshiya Hanada</author><author>Koki Fujita</author><author>Yasuhiro Yoshimura</author>
        <description><![CDATA[This paper briefly introduces a new approach to estimate some orbital parameters of on-orbit satellite fragmentations (specifically, the direction of angular momentum at a specific time and the time change in direction of angular momentum) from in-situ debris measurements. This approach, as in previous studies, adopts a constraint equation derived from the fact that a piece of debris detected shares the geocentric position vector with an in-situ debris measurement satellite. However, unlike previous studies, this approach does not adopt a constraint equation that can be applied to the rate of change in right ascension of the ascending node of a broken-up object. Instead, this approach determines the inclination of a broken-up object from the maximum or minimum geocentric declination at the time of detection. Then, this approach finds out a candidate for the rate of change in right ascension of the ascending node of a broken-up object by assuming a circular orbit with a radius of the geocentric distance at the time of detection. Finally, using the constraint equation adopted, this approach estimates the right ascension of the ascending node at the time of breakup and calculates a correction for the rate of change in right ascension of the ascending node. This paper also verifies that this new approach works effectively under ideal conditions where all detections are assumed to be at the line of intersection of the two orbital planes of a broken-up object and an in-situ debris measurement satellite.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.792944</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.792944</link>
        <title><![CDATA[ET-Class: An Energy Transfer-Based Classification of Space Debris Removal Methods and Missions]]></title>
        <pubdate>2022-03-02T00:00:00Z</pubdate>
        <category>Review</category>
        <author>Barış Can Yalçın</author><author>Carol Martinez</author><author>Maxime Hubert Delisle</author><author>Gonzalo Rodriguez</author><author>James Zheng</author><author>Miguel Olivares-Mendez</author>
        <description><![CDATA[Space debris is positioned as a fatal problem for current and future space missions. Many effective space debris removal methods have been proposed in the past decade, and several techniques have been either tested on the ground or in parabolic flight experiments. Nevertheless, no uncooperative debris has been removed from any orbit until this moment. Therefore, to expand this research field and progressing the development of space debris removal technologies, this paper reviews and compares the existing technologies with past, present, and future methods and missions. Moreover, since one of the critical problems when designing space debris removal solutions is how to transfer the energy between the chaser/de-orbiting kit and target during the first interaction, this paper proposes a novel classification approach, named ET-Class (Energy Transfer Class). This classification approach provides an energy-based perspective to the space debris phenomenon by classifying how existing methods dissipate or store energy during the first contact.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2020.00002</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2020.00002</link>
        <title><![CDATA[From Space Debris to NEO, Some of the Major Challenges for the Space Sector]]></title>
        <pubdate>2020-06-16T00:00:00Z</pubdate>
        <category>Specialty Grand Challenge</category>
        <author>Guglielmo S. Aglietti</author>
        <description></description>
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