Journal of Space Safety Engineering最新文献

{"title":"Design and development of a space suit mock-up for VR-based EVA research and simulation","authors":"Paolo Mangili,&nbsp;Vittorio Netti","doi":"10.1016/j.jsse.2024.05.001","DOIUrl":"10.1016/j.jsse.2024.05.001","url":null,"abstract":"<div><div>Earth-based Extra-Vehicular Activity (EVA) simulation has always been the subject of study by space agencies aimed at reproducing the most accurate experience for astronauts. Challenges and limitations are many and not limited to the natural Laws; the space suit system, an integral part of the successful Extra-Vehicular Activity (EVA), must present the same conditions to the user as it would in the environment of operation. NASA is the most prominent example of a long tradition for a faithful simulation of outer space in which astronauts operate during EVAs: the Neutral Buoyancy Lab at Johnson Space Center in Houston still represents the standard when it comes to providing astronauts with a realistic experience. However, such infrastructures can be difficult to access, considering the renewed interest in space, which is advocated by new private players looking into Low Earth Orbit (LEO) access in the short to medium term. Virtual Reality (VR) provides users with new, flexible, and relatively inexpensive ways of simulating the space environment during an EVA, without the need to build large-scale pools and mock-ups of vehicles. In this paper, it'll be shown how the Sasakawa International Center for Space Architecture (SICSA) at the University of Houston is working to provide students and researchers with a Virtual Reality (VR)-based infrastructure to simulate EVAs and Space Architectures, which are also designed in-situ. An essential component to achieve realism of experience is the design and construction, done entirely in-house, of a mock-up of the latest NASA Artemis Exploration Extra Vehicular Mobility Unit (xEMU) space suit, to recreate the physical constraints that such a garment imposes on astronauts, which cannot be entirely simulated with VR. It'll be shown how this space suit replica substantially enhances the accuracy of the experience, by replicating the mechanisms of the xEMU suit, complementing the virtual experience provided at the same time.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 622-627"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141274125","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":"Collision avoidance in GEO: An operational approach to passive orbit determination for electric propulsion satellites via optical ground based observations","authors":"Antonio Vito Montalbò,&nbsp;Fabrizio Abruzzese,&nbsp;Luca Rizzo,&nbsp;Roberto Errico,&nbsp;Fabio Mannacio","doi":"10.1016/j.jsse.2024.05.008","DOIUrl":"10.1016/j.jsse.2024.05.008","url":null,"abstract":"<div><div><span>The SICRAL Joint<span><span> Management &amp; Control Centre (SJMCC) is an Italian military institution in charge of the mission control of the Italian military spacecraft and the first European full-military institute capable of independently performing spacecraft housekeeping and station keeping operations. In this context, one of the most important activities is the management of collision risks<span>. The task is accomplished by determining the orbits of secondary objects (such as neighbouring geostationary satellites) and evaluating the orbital parameters, in order to assess the necessity of a </span></span>collision avoidance<span><span><span><span> maneuver. In recent years, a new generation of satellites equipped with innovative propulsion systems<span> based on electric thrusters has introduced new challenges to the aforementioned operation. </span></span>Electric propulsion systems provide very </span>high thrust efficiency and low fuel consumption compared to </span>chemical propulsion<span>, while generically settling for lower thrust levels and longer maneuvering times. This implies that the free dynamics behaviour of the spacecraft is only confined to a short fraction of the orbital period. Consequently, the typical flight dynamics approach, based on the propagation of the obtained state vector, loses its inner value since the electric propulsion spacecraft will persist in a free dynamics regime only for a limited fraction of its orbital period. From the perspective of a mission control centre, such as SJMCC, these new satellites make it necessary to drastically adapt its orbit determination capabilities. Consequently, the main goal of the research has been to model a strategy and a tool to manage the orbit determination of electric propulsion </span></span></span></span>geostationary satellites<span>. The paper thoroughly describes an innovative concept named “Continuous Obit Determination” (COD), also presenting a possible software implementation based on open-source libraries. Evaluating the challenges that electric propulsion satellites bring to satellite control<span> centres, COD is detailed as a robust strategy able to flexibly aggregate different observational data of the secondary satellite in order to find the best fitting solution. The comparison between orbits allows the delineation of the satellite's maneuvering strategy and the selection of the most accurate orbit. Finally, the research results have been experimentally validated through observational data acquired via the “CAS telescope” managed by SJMCC for collision avoidance purposes.</span></span></div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 730-738"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141397834","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":"Collision probability evaluation of SRM slag during orbital lifetime","authors":"Kenichi Sato ,&nbsp;Kumi Nitta ,&nbsp;Toru Yoshihara ,&nbsp;Ryuusuke Harada ,&nbsp;Satomi Kawamoto ,&nbsp;Hirohide Ikeda ,&nbsp;Masahiro Kinoshita ,&nbsp;Kyoichi Ui ,&nbsp;Yoshiki Matsuura","doi":"10.1016/j.jsse.2024.09.004","DOIUrl":"10.1016/j.jsse.2024.09.004","url":null,"abstract":"<div><div>At the end of combustion, a solid rocket motor (SRM) in orbit emits combustion products with relatively large particle sizes (slag). ISO 24113:2023 “Space debris mitigation requirements” defines criteria to limit debris emission 1 mm or larger in the LEO protected region. JAXA's “Space debris mitigation standard,” JMR-003E, sets out the same requirements. Hence, JAXA has begun an improvement study on SRM slag emissions as it develops the next generation of SRMs to conserve the orbital environment by significantly reducing SRM slag larger than 1 mm. However, ensuring the complete prevention of larger SRM slag emission is technically challenging. Thus, we are alternatively working to establish a risk evaluation method and criteria based on the collision probability (Pc) of SRM slag during its orbital lifetime. Based on ground firing tests, this study estimated the number and particle size of SRM slag in orbit emitted during the Epsilon and Epsilon S launch missions. The Pc per mission during the orbital lifetime was calculated and provisionally set to 10^–3 for currently operational spacecraft. This paper discusses its acceptability to JAXA.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 779-785"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143159212","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":"Investigating and defining radiation dose risk factors, derived from terrestrial risk assessments, for probabilistic risk assessments for radiation exposure during very high altitude ‘near space’ flights for varying space weather conditions","authors":"C.T. Rees ,&nbsp;K.A. Ryden ,&nbsp;T. Woodcock ,&nbsp;M. Brito","doi":"10.1016/j.jsse.2024.07.002","DOIUrl":"10.1016/j.jsse.2024.07.002","url":null,"abstract":"<div><div>Current space tourism ventures focus on three specific areas: long duration very high-altitude flights; also referred to as ‘near space’ flights, sub-orbital flights and visits to Low Earth Orbit (LEO). In the forthcoming decades, space travel is expected to become as commonplace as transatlantic flights. Consequently, it becomes crucial to consider the potential health implications of cosmic radiation exposure during these commercial ventures, particularly in light of sudden changes in space weather, such as ground-level enhancements (GLEs) or solar particle events (SPEs), which can have profound effects on the well-being of crew members and passengers.</div><div>This paper focuses on the exposure environment and associated risk assessment for very high altitude ‘near space’ flights to the stratosphere. The current probabilistic risk assessment of the hazards for such flights is severely constrained, as the necessary dose risk factor for potential radiation exposure remains undefined for prospective space tourists. Here we examine the existing terrestrial approach to deterministic and probabilistic risk assessment for radiation exposure, specifically within the civil nuclear industry, and its applicability to ‘near space’ very high-altitude flights.</div><div>We propose a revised probabilistic risk assessment methodology, including a bespoke dose risk factor, for ‘near space’ flights. Furthermore, we delve into the distinctive exposure events associated with ‘near space’ flights, explore the impact of potential variations in space weather on radiation exposure, and evaluate potential dose risk factors for utilization in probabilistic risk calculations for flight participants.</div><div><strong>Plain Language Summary:</strong> An investigation into the acceptability and probability of risks associated with potential radiation exposure from flying to ‘near space’ within newly designed craft at very high altitude in the upper atmosphere above the Earth. Comparing and assessing the applicability of terrestrial nuclear industry risk assessment methodology to space tourism and the associated radiation risks.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 564-572"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141695533","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":"SPACE and the return of Rome","authors":"Jonathan Sinclair ,&nbsp;Daniel Patton","doi":"10.1016/j.jsse.2024.08.004","DOIUrl":"10.1016/j.jsse.2024.08.004","url":null,"abstract":"<div><div>Rapid development and increased human impact in outer space has necessitated space sustainability strategies. To protect the continued use of outer space and celestial bodies, policy makers and scholars have proposed and attempted to manage the domain through a variety of mechanisms e.g. treaty formulation, cooperative engagement/assertion, adherence to the Common Heritage of Mankind principle (CHM) and International Law. However, despite nearly 65 years of space activity, questions about how the domain is defined and how sovereignty is applied remain, with commonly used terms being controversial and imprecise. By examining fundamental concepts and early legal principles applied to modern shared resources, we can better understand both the essential attributes and development of the space domain. We assert that the principles of <em>res nullius</em> and <em>res communis</em> can be used to both define shared resource domains and measure their operational development. We understand these principles not as distinct categories, but as a continuum, upon which all shared resource domains lie, thus presenting an alternative framework for describing the shared domain.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 691-696"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143158618","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 systems approach for characterizing human deep space mission anomaly response capabilities and functional constraints","authors":"Patrick K. Pischulti,&nbsp;David M. Klaus","doi":"10.1016/j.jsse.2024.06.007","DOIUrl":"10.1016/j.jsse.2024.06.007","url":null,"abstract":"<div><div><span>Human exploration of Mars and beyond will demand unprecedented levels of onboard self-sufficiency due to the exceedingly far distances from Earth and lengthy mission durations. This paradigm shift will require the development of novel anomaly response architectures to protect future crews adequately from anomalies and failures. In this paper we outline and demonstrate a process to identify and evaluate key factors that affect the anomaly response process for deep space<span> operations. It builds on established frameworks, illustrating how incredibly complex and interdependent this activity is. Relevant factors of the current state-of-the-art anomaly response were established through a literature review in combination with an established taxonomy process. These factors were then assessed for their Earth-reliance specific attributes through a case study. In this paper we have identified over 120 relevant anomaly response factors and developed a process that allows for identifying system capabilities that need to be integrated into future habitat designs to provide a minimum level self-sufficiency to protect crews from catastrophic outcomes stemming from communications delays and compounding co-dependency of factors. While this process was demonstrated using notional </span></span>Mars mission constraints and evaluated against current ISS processes as the baseline, the outlined approach can be adapted for anomaly response designs that require different forms of system autonomy by modifying the relevant mission constraints and operational capability attributes accordingly.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 550-563"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141842800","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":"Study and evaluation of tether-net parameters for space debris capture using modified capture quality index","authors":"Andry Renaldy Pandie","doi":"10.1016/j.jsse.2024.07.005","DOIUrl":"10.1016/j.jsse.2024.07.005","url":null,"abstract":"<div><div>The increasing volume of space debris presents a significant threat to spacecraft safety and the long-term viability of space missions. Among the proposed methods for capturing and removing small space debris at low relative velocities, the tether-net method emerges as particularly promising. Identifying and evaluating the parameters influencing the capture process through simulations is imperative to ensure the effective capture of debris by the net and to assess its efficiency. Therefore this study investigates the influence and effectiveness of various parameter combinations through simulations. The study examines the effects of parameters such as net and space debris masses, shooting speed of the corner mass (CM), CM ejection angle, and activation or deactivation of the net mouth closure mechanism on the space debris-capturing capacity. The capture effectiveness evaluation was conducted utilizing the modified capture quality index (<span><math><mrow><mi>M</mi><mi>C</mi><mi>Q</mi><mi>I</mi></mrow></math></span>). During simulations where the closure mechanism was not activated, the net opened upon debris contact, resulting in expulsion and decreased <span><math><mrow><mi>M</mi><mi>C</mi><mi>Q</mi><mi>I</mi></mrow></math></span>. Conversely, activation of the closure mechanism enhanced the probability of capturing space debris. Within the “wrap” category, parameter combinations of medium CM ejection angles, extended initial distances, and high shooting speeds yielded the highest capture quality for debris capture, as confirmed by the <span><math><mrow><mi>M</mi><mi>C</mi><mi>Q</mi><mi>I</mi></mrow></math></span>. Conversely, a larger CM ejection angle and other parameters reduced the likelihood of debris capture, indicating an inverse relationship between the ejection angle and the initial distance between the net and the debris.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 750-766"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143159090","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":"Integrated NASA and Private Astronaut Crews Readiness Needs Assessment: Summary report of a NASA-sponsored technical interchange meeting","authors":"Lauren Blackwell Landon","doi":"10.1016/j.jsse.2024.08.011","DOIUrl":"10.1016/j.jsse.2024.08.011","url":null,"abstract":"<div><div>NASA facilitated a Technical Interchange Meeting to assess NASA readiness to host and integrate crews of NASA and private astronauts on the International Space Station. Experts from NASA research, operations, and other government organizations identified research gaps and countermeasure needs to enhance current efforts and protect crew health and safety.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 662-672"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143159116","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":"Lunar distress communications: Interoperability, frequencies, and harmful interference, which normative model for the artemis accords?","authors":"Guillaume Loonis Quélen","doi":"10.1016/j.jsse.2024.07.001","DOIUrl":"10.1016/j.jsse.2024.07.001","url":null,"abstract":"<div><div>A new space era begins with the Artemis Accords. These will allow the return of humans to the Moon. The starting point of this historic period was marked by the signing of this international agreement on October 13, 2020. Eight States are at the origin of these accords: the United States of America<span><span><span>, Australia, Canada, Italy, Japan, Luxembourg, the United Arab Emirates, and the United Kingdom. Since then, thirteen other governments – including France – have joined this international space program led by NASA. Artemis will require the implementation of a new communication architecture called “LunaNet”, encompassing the </span>search and rescue<span> service known as “LunaSAR”. Therefore, like on Earth, on the Moon, search and rescue of people in distress will require the interoperability of international communications. From a legal point of view, the Artemis Accords are based on existing space law, particularly the 1967 Outer Space Treaty. According to this, Lunar missions shall be conducted for peaceful purposes. Transparency in the implementation of international partnerships is another key principle of this space program. From this, at the operational level, interoperability of the systems based on existing or future standards naturally follows. Beyond the technical or commercial aspects, what takes precedence over all other considerations is the safety of the astronauts working for the completion of the Artemis program. Thus, generally, the possible assistance brought to the astronauts in distress is foreseen in the United Nations treaties and principles on outer space. Regarding the implementation of the Artemis program, personnel will operate on board a spacecraft, a space station, or from the surface of the Moon. This is why NASA plans to implement the Astronaut's Lunar Lifeline, known as Lunar Search and Rescue or LunaSAR. Integrated with the LunaNet system, this system will assist workers in distress. In this study, therefore, we will focus on standards for communications interoperability, in the context of search and rescue of persons in distress. To do so, we will examine the Artemis program through the lens of satellite-assisted Earth search and rescue principles and techniques. In particular, we will focus on the COSPAS-SARSAT alerting service and the International Aeronautical and Maritime Search and Rescue (IAMSAR) Manual. In this context, issues such as, for example, the implementation of the Treaty on Principles Governing the Activities of States in the Exploration and Use of Outer Space, including the Moon and Other Celestial Bodies of 1967, the Agreement on the Rescue of Astronauts, the Return of Astronauts and the Return of Objects Launched into Outer Space of 1968 and the Agreement Governing the Activities of States on the Moon and Other Celestial Bodies of 1979 as well as the protection of SAR frequencies and potential </span></span>harmful interference will be addressed.</span></div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 681-690"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141695042","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":"Statistical reliability estimation of space launch vehicles: 2000–2022","authors":"Brooke N. Wagenblast,&nbsp;Robert A. Bettinger","doi":"10.1016/j.jsse.2024.10.001","DOIUrl":"10.1016/j.jsse.2024.10.001","url":null,"abstract":"<div><div>This research examines the reliability of space launch vehicles (SLVs) performing commercial, civil, and military space lift missions through trend analysis and a variety of statistical methods. Data sets obtained from the Seradata database are analyzed for trends by examining data subsets including launch date, sector (commercial, civil or military), launch country, intended mission orbit, SLV family, and failed subsystem. Evolving, time-dependent first-level Bayesian success rate analysis is performed to assess SLV reliability and performance trends on 1873 launches occurring during the period 1 January 2000 to 31 December 2022. It was determined that even with a near-exponential increase in launch events in the 2020s, the number of failures is less than 6% each year, with the average success rate being 95% annually. Overall, 56% of launches were sent into low Earth orbit (LEO) and 32% were sent into geosynchronous Earth orbit (GEO) or geostationary Earth orbit (GSO). Although SLVs servicing missions to these orbital regimes featured success rates above 92%, LEO launches accounted for approximately 73% of total launch failures, while GEO-GSO launches accounted for 18% of failures. Specifically looking at U.S. and Russian SLV families, the main subsystem responsible for failure was propulsion, which accounted for 72.3% of 47 reported launch failures. First-level and second-level (using method of moments) Bayesian techniques were performed on 37 launch vehicle families and it was found that vehicles with a high accrual of launches performed with a higher reliability than vehicles with a low number of launches, resulting in first-level success rates of greater than 90%.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 573-589"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143159117","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}