Journal of Space Safety Engineering最新文献

{"title":"Continuous in-situ and remote sun observation for space weather monitoring and mitigation of infrastructure threats through an optimized heliocentric satellite constellation","authors":"Leonidas Askianakis","doi":"10.1016/j.jsse.2025.02.002","DOIUrl":"10.1016/j.jsse.2025.02.002","url":null,"abstract":"<div><div>Although vital for life on Earth, solar activity poses questions and increasing threats to humanity due to the Sun's unknown dynamics, intensified by our dependence on terrestrial and space-based infrastructure. This situation is compounded by significant gaps in our understanding of space weather phenomena, the Sun's magnetic field, and the need for rapid responses to unpredicted solar events. To address these issues, an optimized heliocentric satellite constellation is proposed that leverages satellites in an Elliptical Walker Constellation. This system offers – among others - equally distributed arguments of periapsis separations and cross-coupled true anomalies with respect to the Sun-centric coordinate frame. In this paper it is also demonstrated that this strategic multi-spacecraft configuration makes it possible to distinguish spatial and temporal changes in solar wind phenomena, reconstruct, in 3D, Coronal Mass Ejections (CMEs), predict which space or ground-based infrastructure and when it will be affected by CMEs, maintain continuous coverage of the critical Sun-Earth line throughout the mission's duration, and protect future missions by providing simultaneously in-situ and remote measurements from small and cost-effective satellites.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 149-159"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169689","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":"International Space Settlement Design Competition - An Experience","authors":"J. Clayton Gafford","doi":"10.1016/j.jsse.2025.02.001","DOIUrl":"10.1016/j.jsse.2025.02.001","url":null,"abstract":"<div><div>A high school Space Settlement Design Competition held continuously for over 40 years exposes a group of student competitors to simulated real world industry proposal activity. This competition provides an opportunity for high school students interested in space to learn about both space exploration and system engineering. ISSDC provides students an opportunity to learn these concepts as well as offering opportunities for individuals to focus on their own specific interests and to the level of involvement that they select. Student competitors form fictitious companies and establish a company organizational structure that include a president, vice presidents, department directors and department team members. The companies also have an industry professional join as a Chief Executive Officer (CEO) who guides the students through the competition proposal. The result of the competition is that student competitors, CEOs, and other volunteers gain a lifelong experience that guides and enriches them through their educational and professional careers.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 28-36"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169866","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":"AF advertisement","authors":"","doi":"10.1016/S2468-8967(25)00053-9","DOIUrl":"10.1016/S2468-8967(25)00053-9","url":null,"abstract":"","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Page ii"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169693","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":"Efficient disposal of low lunar orbiters on the lunar surface","authors":"Nathan R. Boone,&nbsp;Robert A. Bettinger","doi":"10.1016/j.jsse.2024.09.005","DOIUrl":"10.1016/j.jsse.2024.09.005","url":null,"abstract":"<div><div>Realistic numerical simulations are conducted to explore safe and efficient strategies for End-of-Life lunar spacecraft disposal on the lunar surface. Disposal from three different near-polar, low-altitude, and near-circular orbit types was analyzed to determine if impact locations that minimize the risk to protected regions of the lunar surface can be achieved consistently for low fuel costs using the Moon’s non-spherical gravity field. A total of 300,000 objects were propagated following retrograde disposal burns using a high-fidelity lunar trajectory model, and the disposal burn locations and magnitudes were compared against the resulting likelihoods of decay and lunar surface impact locations. The results identified disposal strategies that could achieve impact in safe locations for 10 m/s of <span><math><mrow><mstyle><mi>Δ</mi></mstyle><mi>V</mi></mrow></math></span> or less for all orbit types, much lower than the <span><math><mrow><mstyle><mi>Δ</mi></mstyle><mi>V</mi></mrow></math></span> cost to lower the perilune entirely to the lunar surface. A similar simulation-based methodology could be applied to operational lunar satellites to identify disposal strategies based on specific mission conditions. The results of this study support the development of safe and efficient End-of-Life disposal strategies that minimize the accumulation of debris in lunar orbit and extend the operational lifetimes of lunar missions.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 195-205"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169861","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":"Sub-cm space debris in LEO: A comparison between the ESA MASTER model and ADLER in-situ data","authors":"Gernot Grömer ,&nbsp;Vitali Braun ,&nbsp;Xanthi Oikonomidou ,&nbsp;Wolfgang Ebner ,&nbsp;Theresa Mayer ,&nbsp;Willibald Stumptner ,&nbsp;Stefan Amberger ,&nbsp;Christian Federspiel ,&nbsp;Bernhard Niedermayer ,&nbsp;Peter Schüller","doi":"10.1016/j.jsse.2025.02.009","DOIUrl":"10.1016/j.jsse.2025.02.009","url":null,"abstract":"<div><div>Modeling the Space debris and Meteoroid (SD/M) environment in Low Earth orbit is particularly challenging when it comes to sub-cm sized particles that are below the detection thresholds of ground based observations. The MASTER model of ESA is used to establish a reference for risk assessments and mission planning. However, given the significant increase in satellite operations in the last decade, the lack of recent in-situ data for calibrating the models is evident. The ADLER-1 mission, operating for 512 days at an altitude of 480 km, was an in-orbit demonstrator for deploying a piezoelectric sensor array as well as a continuous wave miniature radar to obtain pilot data. The APID-1 instrument onboard ADLER-1 yielded 117 impact events for a period of ca 400 days, which were compared to the MASTER simulations. There is evidence for detecting debris from a rocket motor firing of an ISS supply flight.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 160-174"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169690","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":"Producing compact copper elements in the velocity range of 5–9.5 km/s using shaped charges with modified combined hemisphere-cylinder liners","authors":"S.V. Fedorov,&nbsp;I.A. Bolotina,&nbsp;P.V. Merzlyakova","doi":"10.1016/j.jsse.2025.01.002","DOIUrl":"10.1016/j.jsse.2025.01.002","url":null,"abstract":"<div><div>To test the protective shields of spacecraft for resistance to meteoroids and space debris fragments, it is necessary to develop methods for accelerating solid particles to high velocities. The currently used shaped charges with a combined hemisphere-cylinder liner make it possible to produce compact steel elements with velocities at the level of 6 km/s. Based on numerical modeling within framework of a two-dimensional axisymmetric problem of continuum mechanics, the possibilities of modifying hemisphere-cylinder liner to expand the range of velocities of the resulting compact elements are considered. Modeling was carried out with respect to a shaped charge with a diameter of 100 mm and a copper liner. The jet-forming part of the liner was given a degressive (decreasing from the top to the base) thickness with a hemispherical or semi-ellipsoidal shape of its outer surface and a semi-ellipsoidal or semi-superellipsoidal shape of the inner surface. By numerical calculations, the geometric parameters of the combined liners were selected, which make it possible to form compact elements with velocities in the range from 5 to 9.5 km/s at the maximum possible value of element mass. The mass of the element at a velocity of about 9.5 km/s was about 5 g.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 132-148"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169688","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":"Benefits of using functional safety in commercial space applications","authors":"F. Lumpe ,&nbsp;M. Seidl","doi":"10.1016/j.jsse.2024.11.002","DOIUrl":"10.1016/j.jsse.2024.11.002","url":null,"abstract":"<div><div>According to IEC61508 functional safety is relevant whenever a product or system contains electrical, electronic or programmable electronic elements that perform safety-critical functions. It is used in many areas of technology such as, process industry (e.g., energy sector), automotive (transport sector), mechanical engineering, or aviation. This article will compare the approaches and concepts of Functional Safety based on IEC61508 and ISO26262 with the RAMS (Reliability, availability, maintainability and safety) approaches of the space industry, in particular with the Fault Detection Isolation and Recovery (FDIR) approach.</div><div>The paper will provide an insight into the possibilities of minimizing risk at the component level, especially for complex integrated circuits. Traditionally, the space industry has focused on qualifying the components used for the extreme environmental parameters and the typically very long duration of use in space. However, as ICs (Integrated Circuit) have become very complex, there is significantly increased risk of systematic failures that can occur during the development of the component itself and also by the designer using it for development the actual circuit board assembly.</div><div>In addition, the cost of components is a major factor in the development of satellite constellations due to higher volumes, so a trade-off between qualification and affordability must be found.</div><div>The presentation will show how systematic faults in other market sectors can be avoided as far as possible and how so-called random faults can be detected as quickly as possible and their effects ideally eliminated or at least minimized with the help of appropriate performance features of the semiconductor products, such as ECC (Error Correction Code), lock-step, or BIST (Built-in Self Test).</div><div>The successful mission of the Mars Rotorcraft Ingenuity from JPL (NASA) provides an insight into the practical application of a functional safety concept in a space application.</div><div>This paper is intended as a suggestion on how to make the best use of existing features of semiconductor products developed for functional safety in other market sectors also for space applications.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 187-194"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169692","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":"Editorial Board and Society Advert","authors":"","doi":"10.1016/S2468-8967(25)00045-X","DOIUrl":"10.1016/S2468-8967(25)00045-X","url":null,"abstract":"","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Page IFC"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169860","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":"Space systems safety and mission assurance case study-based graduate education","authors":"Liz Bosch ,&nbsp;Radu Babiceanu","doi":"10.1016/j.jsse.2025.02.004","DOIUrl":"10.1016/j.jsse.2025.02.004","url":null,"abstract":"<div><div>There is a significant number of discussions lately, at both government agencies and private industry, about sending crewed missions further into space. Sending astronauts back to the Moon and, for the first time, to Mars seems to make space enthusiasts around the world excited given the noteworthy tests and preparations going on in the last few years. The decision to launch crewed missions into space depends primarily on three aspects: technology, budget, and mission risk. Even when the first two aspects are addressed, the third question still remains: is it safe enough? Generally, Safety and Mission Assurance (S&amp;MA) for space systems is taught in space systems programs from an operations standpoint. There are very few to no courses across the USA that address space S&amp;MA from the design engineering perspective. There is also limited teaching of ethics-based safety culture in the engineering programs offered across the country. The resultant gap between graduates’ knowledge of space S&amp;MA and the needed skills to conduct design engineering of space systems is, at the moment, mostly filled by the space agencies and private space industry. The graduate course framework presented in this paper is built on a student-centered approach through customized case-study experiences that promotes understanding and motivation, which are significant aspects of making risk-based decisions with considerations to safeguarding human lives. By exploring the root causes of human space flight close calls, incidents, and mishaps, students can envision themselves in the space operational environment and can become aware of how design engineering, safety culture, and ethics act through a combined feedforward and feedback mechanism to ensure reliable and safe operations. Then, connecting back to the theoretical course material creates the student's understanding and motivation once they act as decision-makers after graduation. The proposed case study-based course framework also promotes critical thinking and problem-solving for the safety engineering aspects of the design of space systems. Understanding and motivation, together with critical-thinking and problem-solving is expected to prove the efficacy of case-study-based instruction and support instilling student ethical decision making, with its component parts of integrity, accountability, and responsibility.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 12-16"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169864","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 Reliability-Driven Design and Test (ReDDT) methodology for space nuclear power and propulsion systems","authors":"Dr. L. Dale Thomas ,&nbsp;Samantha Rawlins ,&nbsp;Shreyas Lakshmipuram Raghu ,&nbsp;Alexander Aueron","doi":"10.1016/j.jsse.2025.03.002","DOIUrl":"10.1016/j.jsse.2025.03.002","url":null,"abstract":"<div><div>The development methodology employed in the United States’ Rover NERVA program is reviewed as the basis for the Reliability-Driven Design and Test (ReDDT) methodology described herein. Postulated as perhaps the first full programmatic implementation of probabilistic design, the NERVA foundational methodology appears to have never been adopted elsewhere following program cancelation. Nevertheless, much of the framework developed during NERVA remains applicable, and the ReDDT approach described in this work is based upon their approach. The ReDDT approach builds on the NERVA method by introducing a qualitative failure mode analysis to identify which tests are most useful and maximize program efficiency. The qualitative analysis is supported by uncertainty analysis, which is applied to identify the drivers of the system's technical uncertainty and thereby drivers of safety and reliability. The ReDDT approach is distinct from existing reliability-based methodologies including Reliability Based Design Optimization (RBDO) and Design for Reliability (DfR) in that ReDDT focuses on concurrent and synergistic system design, integration, and test planning. ReDDT has been developed for NASA's current Space Nuclear Propulsion effort, but it has broader applicability to nuclear power systems and complex aerospace system developments and upgrades in general. The ReDDT methodology has the goal of transforming the relationship of the design effort to the integration and test effort within a system development from one of test-fail-fix to model-test-evaluate.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 53-65"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169868","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}