Journal of Space Safety Engineering最新文献

{"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":"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":"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}

{"title":"Development of a Lox/Methane intact impact yield curve for a new launch vehicle","authors":"Andrew Berkowitz ,&nbsp;Simon Titulaer","doi":"10.1016/j.jsse.2024.11.005","DOIUrl":"10.1016/j.jsse.2024.11.005","url":null,"abstract":"<div><div>Intact impact yield curves are a key flight safety analysis input to assess the risk from explosive blast and Distant Focusing Overpressure (DFO) effects. Many new launch vehicles are utilizing Liquid Oxygen and Liquid Methane (LOX/Methane) as their propellants, a combination that does not have a historical yield curve. This paper describes SpaceX's work to develop a new LOX/Methane yield curve; unlike traditional yield curves, this work includes characterizing the effects of the launch vehicle's design and its breakup behavior. SpaceX expanded on the work of Blackwood et al. [1] to evaluate the theoretical explosive potential of an impacting launch vehicle. The theoretical model was then tested in a subscale test campaign like Project PYRO and HOVI, consisting of over 40 drop tests. The theoretical model, testing data, and launch vehicle design can be used to generate a conservative LOX/Methane yield curve for a new launch vehicle.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 590-604"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143159098","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":"An effect of Fe atom clusters doped CNTs on resistivity of PTFE dielectrics","authors":"Sayavur I. Bakhtiyarov ,&nbsp;Elguja R. Kutelia ,&nbsp;David Gventsadze ,&nbsp;Ayten S. Bakhtiyarova ,&nbsp;Stephen M. White","doi":"10.1016/j.jsse.2024.09.003","DOIUrl":"10.1016/j.jsse.2024.09.003","url":null,"abstract":"<div><div>Polymers are of interest for use on spacecraft surfaces as dielectrics and electrical insulators, and polytetrafluoroethylene (PTFE) is a polymer with mechanical advantages, but low conductivity. Fe-doped carbon nanotubes (CNT) can be added to the polymer matrix and may improve their electrical properties. This work measures the volume and surface resistivity for PTFE and PTFE + Fe-doped CNT test specimens using the Keithley 6517B Electrometer/High Resistance Meter system, by determining current levels through the samples as a function of applied voltage. The system noise current was measured and averaged to be 4.83×10⁻¹⁵ Amps. The results obtained show that both volume and surface resistivities of pristine PTFE increase with increasing voltage. The volume resistivity is higher if compared to the surface resistivity at the same voltage. The conductivities of PTFE + Fe doped CNTs composites are higher as compared to the pristine PTFE, which can be contributed to the Fe-doped CNTs. The conductivity of the PTFE + Fe doped CNTs composite material increases with the concentration of the Fe-doped CNTs.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 614-621"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143159099","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":"Handling of external risks, including launch and re-entry events, in the aviation and maritime sector","authors":"Tobias Rabus","doi":"10.1016/j.jsse.2024.04.003","DOIUrl":"10.1016/j.jsse.2024.04.003","url":null,"abstract":"<div><div>An important part of a flight safety analysis for launch and re-entry events is to ensure safety to air and sea traffic, and maritime infrastructure. Thus, hazard areas are defined based on a risk assessment and risk criteria. Traffic impact depends on size and duration of those areas. Current risk criteria for air and sea traffic as well as maritime infrastructure are reviewed in this paper. Furthermore, this paper will take a closer look on other external risk factors in the aviation or maritime sector. The paper analyses their influence on aviation and maritime operations together with its associated safety measures and compares them with the risk posed by space vehicles. Understanding these relationships can support the conduct of safe space operations and efficient integration of space activities.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 673-680"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141141975","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":"Detoxification of contaminated soils from hydrocarbon rocket fuel used in «Soyuz» launch vehicles using the bioremediation method","authors":"Yerlan Bekeshev ,&nbsp;Zhazira Zhumabekova ,&nbsp;Meirbek Moldabekov","doi":"10.1016/j.jsse.2024.07.004","DOIUrl":"10.1016/j.jsse.2024.07.004","url":null,"abstract":"<div><div>Rocket and space activities are developing worldwide, but environmental concerns are overlooked in pursuing new technologies. The Republic of Kazakhstan's \"Baikonur\" Cosmodrome routinely launches rockets in emergencies, causing toxic fuel to spill onto and contaminate the soil. This study examines the effect of T-1 kerosene, a hydrocarbon rocket fuel of toxic hazard class 4, on the soil microbial community from the aeration zone in laboratory conditions. In three different soil samples, 15 g/kg, 30 g/kg, and 50 g/kg of T-1 kerosene were tested according to their utilization by microbes throughout three, ten, and thirty days.</div><div>Based on scientific research, several strains of microorganisms were able to utilize T-1 kerosene rocket fuel, such as <em>Acinetobacter calcoaceticum</em>-18, <em>Bacillus</em> sp.-20, <em>Micrococcus roseus-</em>25, and <em>Candida</em> sp.-12/5, purifying it from 70 to 90 %. According to a study conducted after 30 days of microbiological detoxification of calcisols (loamic) (site 196) and dystric arenosols (site 31), with an initial load of 50 g/kg of T-1 kerosene, the concentration was determined. Microorganisms that produce 5 + 20 (99.83 %) and 18+20+25+12/5 (99.80 %) oil products are well utilized. During decontamination of soils contaminated with hydrocarbons was found to be present in the soil after 60 days when microorganism № 20 was used at 9.3 mg/kg, and the association of microorganism 5 + 25 at 8.88 mg/kg. The article describes the developed technology for soil detoxification using the microbiological method.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 4","pages":"Pages 605-613"},"PeriodicalIF":1.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141851777","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":"Using WACCM-X neutral densities for orbital propagation: Challenges and solutions","authors":"Matthew K. Brown,&nbsp;Sean Elvidge","doi":"10.1016/j.jsse.2024.04.012","DOIUrl":"10.1016/j.jsse.2024.04.012","url":null,"abstract":"<div><div>Atmospheric drag is a major perturbation in Low Earth Orbit (LEO). The neutral density obtained from atmospheric models is a major source of uncertainty in drag calculations and therefore orbital propagation in LEO. Many atmospheric models are available, with fast empirical models most commonly used. We explore the challenges and benefits of using numerical models, specifically the Whole Atmosphere Community Climate Model with thermosphere and ionosphere extension (WACCM-X) as part of the Community Earth System Model (CESM). Numerical models provide higher resolution of thermospheric structures, along with more accurate neutral density forecasts through assimilative models such as the Advanced Ensemble electron Density Assimilation System (AENeAS). Solutions are presented to overcome the challenges of using numerical models for neutral densities.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 3","pages":"Pages 411-416"},"PeriodicalIF":1.0,"publicationDate":"2024-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142571585","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}