Journal of Space Safety Engineering最新文献

{"title":"Design and development of a CubeSat power control and distribution unit (PCDU) using commercial off-the-shelf components","authors":"Ahmed Mokhtar ,&nbsp;Mohamed Sameh Elkerdany ,&nbsp;Mohamed E. Hanafy ,&nbsp;Fawzy H. Amer ElTohamy ,&nbsp;Yehia Z. Elhalwagy","doi":"10.1016/j.jsse.2026.02.006","DOIUrl":"10.1016/j.jsse.2026.02.006","url":null,"abstract":"<div><div>The Electric Power Subsystem (EPS) is critical to CubeSat missions. This paper presents the design, hardware prototype, and validation of a Power Control and Distribution Unit (PCDU) for a 6U CubeSat (CTIM), emphasizing modularity and the use of Commercial Off-The-Shelf (COTS) components. We present mission-driven sizing, component trade-offs, a consolidated PCDU architecture, and experimental verification of protection, sensing, and point-of-load conversion. The design follows ECSS-relevant recommendations and includes battery sizing that explicitly accounts for conversion efficiencies and margins for ageing and degradation.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 2","pages":"Pages 267-277"},"PeriodicalIF":1.8,"publicationDate":"2026-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148314643","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Applying defense-in-depth to the design and operation of fission power systems on the lunar surface","authors":"Matthew E. Granger","doi":"10.1016/j.jsse.2026.02.011","DOIUrl":"10.1016/j.jsse.2026.02.011","url":null,"abstract":"<div><div>Compact, reliable Fission Surface Power (FSP) reactor systems are essential to meeting the electrical power demands required for sustained human presence and operations on the Moon. Multiple nations are making plans to deploy and operate such systems in close proximity on the lunar surface, particularly at the South Pole, but the risks these systems pose will be shared internationally and thus require a common, internationally-accepted approach and expectations for safety. This paper synthesizes a Defense-in-Depth (DiD) safety framework tailored to the unique considerations specific to FSP systems on the lunar surface. The recommended approach draws from terrestrial nuclear power safety standards and international space nuclear system principles, and are performance-based to enable the wide-range of FSP systems currently being considered and developed.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 2","pages":"Pages 391-395"},"PeriodicalIF":1.8,"publicationDate":"2026-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148261392","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Debris generation from CFRP fragmentation derived from DebriSat experiment","authors":"Tabitha Patrick,&nbsp;Gabriella Araujo,&nbsp;Aimee Dew,&nbsp;Allen Martinez,&nbsp;Bogachan Ondes,&nbsp;Norman Fitz-Coy","doi":"10.1016/j.jsse.2026.04.004","DOIUrl":"10.1016/j.jsse.2026.04.004","url":null,"abstract":"<div><div>Understanding the fragmentation of modern spacecraft materials is critical for accurate orbital debris modelling. The DebriSat laboratory hypervelocity impact experiment was designed to provide representative data on these materials, with carbon-fibre reinforced polymer (CFRP) as the focus of this study due to its increased use in satellites and its disproportionately high fragment count. Analysis of DebriSat fragmentation data demonstrates that CFRP is the dominant contributor to fragment count despite its relatively small contribution to mass. The current estimate of the collected fragments greater than 2 mm is more than 325,000. As of February 19, 2025, over 220,000 fragments had been recorded in the Debris Characterization System (DCS). Of these, 126,642 had been assessed for material type(s), shape, and other basic characteristics, with 78,749 identified as primarily CFRP, representing 62.2% of the assessed population. Within the measured subset of fragments with dimensional data from imaging (65,582 fragments), 38,967 were identified as CFRP, corresponding to 59.4% of that dataset. This value is within 3% of the overall assessed percentage, showing that the CFRP fragment count is closely represented in the measured dataset used for size and shape distribution analyses. Results show that CFRP fragments are strongly skewed toward the sub-centimetre regime, with 63.1% falling in the 2–10 mm range. CFRP also overwhelmingly produces needle and plate geometries, reflecting its brittle, layered fracture behaviour. Although CFRP accounts for about 62.2% of the total fragment count within the assessed population, it contributes only 3.28% of the measured mass within the massed population. This disproportionate behaviour underscores the need to incorporate CFRP fragmentation into updated breakup models to ensure accurate orbital debris risk assessments.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 2","pages":"Pages 384-390"},"PeriodicalIF":1.8,"publicationDate":"2026-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148571030","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Enhanced methodology for assessing the reliability of the satellite attitude control subsystem during failure scenarios","authors":"Jamila Hamzei ,&nbsp;Mahdi Fakoor ,&nbsp;Peyman Nikpey","doi":"10.1016/j.jsse.2026.02.010","DOIUrl":"10.1016/j.jsse.2026.02.010","url":null,"abstract":"<div><div>This study investigates the reliability of the attitude control subsystem (ACS) in a flexible spacecraft under various operational conditions. The research follows a structured four-phase approach. First, the optimal configuration of reaction wheels as actuators, in combination with thrusters, is determined, considering both pyramidal and tetrahedral arrangements. Next, two control methods i.e. proportional-derivative (PD) control and sliding mode control (SMC), are designed and selected to manage the ACS. This combination of phases results in four distinct system scenarios that encompass a range of operational contexts. The effectiveness of the actuators under various random conditions will be assessed through comprehensive simulations of potential actuator malfunctions, illustrating uncertainties using Monte Carlo simulation techniques. Extensive simulations conducted in these phases lead to the development of an optimized algorithm capable of predicting ACS performance, taking into account factors such as configuration type, control method, and actuator failure rates. Additionally, a reliability block diagram for the four scenarios is constructed using a novel event tree method to calculate system reliability and address the inherent complexity of the study. An analysis of a substantial production dataset allows us to optimize the deployment of actuators, particularly those lacking prior space heritage, for effective use in spacecraft operations.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 2","pages":"Pages 436-447"},"PeriodicalIF":1.8,"publicationDate":"2026-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148433037","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"A coupled SPH–FEM strategy for hypervelocity impact analysis with emphasis on shock-wave transmission in Whipple shields","authors":"Tiziana Cardone,&nbsp;Chiara Bisagni","doi":"10.1016/j.jsse.2026.03.005","DOIUrl":"10.1016/j.jsse.2026.03.005","url":null,"abstract":"<div><div>The population of orbital debris in Low Earth Orbit (LEO) continues to increase steadily. This situation is driven by a combination of human space activities and collisions between objects in orbit, which are becoming increasingly unavoidable and pose a significant threat to space missions.</div><div>This work addresses debris–spacecraft collision phenomena by first investigating the hypervelocity impact of a projectile on a single plate. A coupled smoothed particle hydrodynamics (SPH) and finite element method (FEM) numerical framework, implemented in the commercial code LS-DYNA®, is developed to simulate this process and correlated with publicly available hypervelocity impact experimental data. The methodology is subsequently optimised and extended to a more complex configuration, namely a Whipple shield, which is more representative of realistic spacecraft shielding concepts against debris impacts. Validation is performed using an experimental dataset provided by Airbus Defence and Space.</div><div>Unlike conventional SPH/FEM coupling approaches that are primarily used to improve local damage modelling near the impact zone, the proposed framework is deliberately formulated to enable consistent propagation of shock waves and stress fields into the surrounding finite element domain. This enables the method to be employed not only for accurate fragmentation modelling, but as a physics-driven approach for analysing energy transport and shock propagation within spacecraft structures following hypervelocity impacts.</div><div>The developed methodology enhances insight into spacecraft structural behaviour under hypervelocity debris impacts and supports its application in the design and optimisation of future spacecraft shielding solutions.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 2","pages":"Pages 349-362"},"PeriodicalIF":1.8,"publicationDate":"2026-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148571027","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Cybersecurity internal audit framework of the European Space Agency’s navigation satellite systems","authors":"Jose Ramon Coz Fernandez,&nbsp;Davide Senatori,&nbsp;Enrique Viudes Gutierrez","doi":"10.1016/j.jsse.2026.03.007","DOIUrl":"10.1016/j.jsse.2026.03.007","url":null,"abstract":"<div><div>The Cybersecurity Internal Audit Framework (CIAF) for the European Space Agency’s Navigation Satellite Systems addresses the growing complexity and criticality of cybersecurity in space navigation. Focusing on ESA’s navigation programs, the framework integrates risk assessment, compliance analysis, and software development process standards into a multi-level audit methodology. By referencing leading international standards and applying a structured approach across ESA, prime contractors, and subcontractors, the CIAF supports continuous improvement, regulatory compliance, and the resilience of Europe’s navigation infrastructure. Its effectiveness is demonstrated through application within ESA’s GNSS programs. Overall, the paper highlights a novel ESA cybersecurity auditing framework that integrates international standards and supply chain analysis, enabling risk monitoring and mitigation in the navigation domain since 2019.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 2","pages":"Pages 448-461"},"PeriodicalIF":1.8,"publicationDate":"2026-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148274659","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Safe operation of space cold gas mini-thruster with experimental investigation of the condensation using supersonic vacuum diffuser design","authors":"Mohammad Reza Ghelichkhani","doi":"10.1016/j.jsse.2026.02.005","DOIUrl":"10.1016/j.jsse.2026.02.005","url":null,"abstract":"<div><div>Cold gas mini- thrusters with high nozzle expansion ratios are extensively employed in satellites and spacecraft due to their lightweight construction, simple design, minimal operational risks, non-toxic nature, and enhanced reliability. The presence of moisture in the working fluid—particularly air—may lead to the formation of condensation shock, negatively impacting both the safety and performance of the thruster. Accurate measurement of vacuum features typically requires high-altitude testing facilities. However, in this study, a laboratory setup featuring a supersonic diffuser was developed to measure the vacuum thrust-force changes without the need for relocation to a vacuum chamber. Utilizing this setup, the effects of supersonic condensation were assessed at an expansion ratio of 21.3. Experimental results and thermodynamics calculations confirmed the absence of condensation shock at the nozzle throat, even under a temperature drop of –20 °C. The diffuser design methodology was validated through normal shock equations, computational fluid dynamics (CFD) simulations, and supporting experimental data. The newly proposed method offers portability and cost-efficiency for the condensation analysis, eliminating the need for large vacuum chambers or advanced diagnostics such as Schlieren imaging or X-ray techniques. By enabling the analysis of supersonic condensation effects on the thrust-force, it contributes to enhanced spacecraft safety and overall performance.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 2","pages":"Pages 316-328"},"PeriodicalIF":1.8,"publicationDate":"2026-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148571026","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Oriented Odyssey of the lunar scars: Directional distribution of lunar craters","authors":"Debashis Chatterjee ,&nbsp;Prithwish Ghosh","doi":"10.1016/j.jsse.2026.02.009","DOIUrl":"10.1016/j.jsse.2026.02.009","url":null,"abstract":"<div><div>We study the global spatial distribution of lunar impact craters using directional statistics on the sphere. Crater coordinates are mapped to unit vectors and modeled via mixtures of von Mises–Fisher (vMF) distributions. Model selection using information criteria supports a four-component vMF mixture, indicating clear multimodality in crater-density structure. A goodness-of-fit comparison finds no statistical evidence that a more general Kent model is needed for these data. Using the fitted spherical density, we construct low-density maps and identify candidate regions with comparatively reduced crater occurrence, with emphasis on polar latitudes relevant to future landing and volatile-prospecting missions. Our framework provides a reproducible, geometry-aware method for summarizing crater anisotropy and translating statistical density estimates into mission-planning layers.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 2","pages":"Pages 340-348"},"PeriodicalIF":1.8,"publicationDate":"2026-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148274658","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Spaceport selection, licensing complexity and launch operator constraints in NewSpace","authors":"Paola Breda,&nbsp;Vittorio Di Pietrantonio,&nbsp;Scott Schneider","doi":"10.1016/j.jsse.2026.02.012","DOIUrl":"10.1016/j.jsse.2026.02.012","url":null,"abstract":"<div><div>The NewSpace sector presents significant regulatory challenges as governments need to find balance between supporting technological innovation, complying to international obligations and ensuring public safety. National space laws translate commitment from international treaties into enforceable domestic regulations, aiming to ensure accountability while fostering the growth of the private sector. This paper explores two key themes, drawing from the authors’ experience with launch operators and spaceports, based on previous involvement in space licensing processes. First, the coexistence of national and regional space laws is examined through the cases of the Italian space law and the Space Industry Act 2018 in the United Kingdom. These examples highlight the collaborative efforts of governments, legal experts, and industry stakeholders in crafting regulatory frameworks for commercial operations. The emergence of a unified European space law, targeting resilience, safety, and sustainability, partially overlaps with existing national space laws, creating legal and procedural complexity. Coordination between national and European levels is essential but poses challenges for applicants facing already overlapping jurisdictions. Second, the impact of regulatory complexity on launch site selection is analysed in a wider context. From the perspective of a launch operator, factors influencing the selection of a spaceport include the intricacy of licensing procedures, requirements on safety-critical systems, liability frameworks, and stakeholder mapping within airspace, maritime, and environmental authorities. Based on practical experience, the authors identify critical trade-offs, for example the assessment of regulatory delays versus potential financial benefits. Lessons learned emphasize the importance of securing third-party liability insurance for space activities, aligning engineering and legal processes, and proactively engaging stakeholders to avoid licensing delays. The authors recommend that early applicants and operators share insights to improve regulatory processes and optimize licensing outcomes in a complex and evolving legal landscape.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 2","pages":"Pages 396-404"},"PeriodicalIF":1.8,"publicationDate":"2026-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148571035","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Microsatellite mock-up for verification of docking operations in laboratory","authors":"Francesco Branz,&nbsp;Martina Imperatrice,&nbsp;Federico Basana,&nbsp;Alex Caon,&nbsp;Luca Lion,&nbsp;Dario Delbono,&nbsp;Alessandro Francesconi","doi":"10.1016/j.jsse.2026.05.002","DOIUrl":"10.1016/j.jsse.2026.05.002","url":null,"abstract":"<div><div>This paper presents the design, characterization, and experimental validation of a microsatellite mock-up for laboratory simulation of close-proximity relative dynamics between small satellites. The mock-up is suspended on flat air bearings, allowing 2D motion on a low-friction table, effectively emulating free-fall dynamics. The relative pose control system is a key component, and assessing its performance is the main goal of this work. Relevant subsystems are described in detail, highlighting how laboratory-grade components are used to simulate satellite subsystem behavior. System parameters crucial for pose control development are experimentally evaluated, including inertial properties and propulsion system characteristics. Experimental results demonstrate the simulator’s capability to execute pose maneuvers and track desired trajectories. The simulator provides a versatile testbed for docking systems and other enabling technologies for close-proximity operations.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 2","pages":"Pages 462-470"},"PeriodicalIF":1.8,"publicationDate":"2026-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148571885","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}