Journal of Space Safety Engineering最新文献

{"title":"Assessments of the impacts of orbital fragmentations using the Near-Earth Orbital Debris Environment Evolutionary Model (NEODEEM)","authors":"Ryusuke Harada ,&nbsp;Satomi Kawamoto ,&nbsp;Toshiya Hanada","doi":"10.1016/j.jsse.2024.07.008","DOIUrl":"10.1016/j.jsse.2024.07.008","url":null,"abstract":"<div><div>This study evaluates the environmental impacts of orbital fragmentation such as an anti-satellite test, collision between two objects, and explosion. A debris environment evolutionary model named NEODEEM, jointly developed by Kyushu University and JAXA, is used to predict future populations and calculate collision probabilities after a fragmentation. This study focuses on characteristics of the fragmented objects, such as altitude, mass, and whether they belong to a Large Constellation (LC). When a fragmentation occurs at higher altitudes, the new fragments will remain in orbit for a long time. Due to this accumulation, the fragments will not only keep the number of objects and probability of collision higher but also cause the risk of secondary collisions between fragments and background objects. When a collision occurs inside an LC at a lower altitude, the impacts will be short-term because most of fragments decay quickly. However, the number of conjunctions, i.e., operational roads, will increase rapidly because many satellites are operated at the same altitude. This study also discusses a collision probability to an LC taking into account the small size of fragments larger than 1 cm.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 3","pages":"Pages 395-402"},"PeriodicalIF":1.0,"publicationDate":"2024-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142571638","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":"AstroLibrary: A library for real-time conjunction assessment and optimal collision avoidance","authors":"Shawn SH Choi ,&nbsp;Peter JH Ryu ,&nbsp;Kyuil Sim ,&nbsp;Jaedong Seong ,&nbsp;Jae Wook Song ,&nbsp;Misoon Mah ,&nbsp;Douglas DS Kim","doi":"10.1016/j.jsse.2024.07.003","DOIUrl":"10.1016/j.jsse.2024.07.003","url":null,"abstract":"<div><div>Geospace is crowded due to the proliferation of satellites and space debris and will become more crowded with the increasing deployment of new space missions. This trend is rapidly increasing the probability of collisions between space objects. Space objects fly at extreme speeds; hence, the consequences of collisions are catastrophic. However, accurate and efficient conjunction assessment (CA) and collision avoidance (COLA) have long been challenging, even with the current space catalogues of O(10⁴) size. As the space catalogue size increases owing to the increased number of new satellites, improved sensor capabilities, and Kessler syndrome, the situation will worsen unless a paradigm-transforming computational method is devised. Here, we present the SpaceMap method, which can perform real-time CA and near-real-time COLA for O(10⁶) or more objects, provided that the spatiotemporal proximity amongst satellites is represented in a Voronoi diagram. As the most concise and efficient data structure for spatiotemporal reasoning amongst moving objects, Voronoi diagrams play a key role in the mathematical and computational basis for a new genre of artificial intelligence (AI) called space–time AI, which can find the best solutions to CA/COLA and other space decision-making problems in longer timeline windows. The algorithms are implemented in C++ and are available on GitHub as AstroLibrary, which has RESTful APIs and Python packages that can be called from application programs. Using this library, anyone with elementary programming skills can easily develop efficient applications for challenging spatiotemporal problems.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 3","pages":"Pages 462-468"},"PeriodicalIF":1.0,"publicationDate":"2024-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141712222","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":"Evaluation of low earth orbit post-mission disposal measures","authors":"Hugh G. Lewis,&nbsp;Vyara Yazadzhiyan","doi":"10.1016/j.jsse.2024.03.008","DOIUrl":"10.1016/j.jsse.2024.03.008","url":null,"abstract":"<div><div>The substantial benefits arising from the widespread adoption of post-mission disposal in low Earth orbit (LEO) are reflected in a reduced orbital debris population and a reduced frequency of collisions. The benefits are generally seen at higher altitudes whereas some drawbacks in the form of enhanced collision risks have been predicted for lower altitudes. These drawbacks are generally expected to reduce as the post-mission disposal lifetime decreases, as less time at lower altitudes reduces collision probability. This is the rationale used by the Federal Communications Commission (FCC) for its new 5-year rule. To investigate the potential benefits and drawbacks, the DAMAGE computational model was used to investigate the effects of a variety of LEO post-mission disposal rules, including the new 5-year rule, within scenarios involving the deployment of large constellations of satellites. The results suggest substantial reductions in conjunction rates overall, as the post-mission residual orbital lifetime decreases, but indicate an increasing frequency of conjunctions and a corresponding need for risk mitigation maneuvers at low altitudes. The results reinforce the recommendation that disposal must be completed as soon as practicable following end of mission. Additionally, the results highlight the need for careful consideration and further research into post-mission disposal where a residual orbital lifetime is permitted.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 3","pages":"Pages 526-531"},"PeriodicalIF":1.0,"publicationDate":"2024-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142571487","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 economic indicator of the orbital debris environment","authors":"","doi":"10.1016/j.jsse.2024.04.014","DOIUrl":"10.1016/j.jsse.2024.04.014","url":null,"abstract":"<div><div>The continued growth of orbital debris increases potential losses faced by commercial operators in Earth's orbits. Yet, there is no commonly accepted measure that describes the orbital debris environment from an <em>economic</em> perspective. This study begins to fill that gap by developing an Orbital Debris Economic Loss Index (ODELI) that measures and tracks the changes in the expected negative economic impact of orbital debris on satellite operators, both in aggregate and in specific orbits. Such information is valuable to the stakeholders, such as policymakers, commercial operators, and the public, in communicating valuable information about the economic state of the orbital debris environment.</div><div>We illustrate the calculation of the index utilizing the data from 2012 to 2022. The analysis is based on the publicly available data and the Meteoroid and Space Debris Terrestrial Environment Reference (MASTER) orbital debris environment model. Our analysis suggests that the aggregate expected economic damage to Earth's orbits is increasing at a slower rate than the growth rate of the number of satellites or trackable pieces of debris objects. The slower rate of growth in ODELI indices from 2012 to 2022 is explained by a decrease in the average mass of satellites, a reduction in the real cost of placing satellites in orbit, and a commercial preference to launch satellites into orbits with lower debris density.</div><div>The estimates of annual expected economic losses from debris collisions increased from $86 million to $107 million from 2012 to 2022, and the losses are concentrated in the low-Earth orbit (LEO). However, LEO had the smallest rate of increase in ODELI compared to other orbits. Medium-Earth orbit (MEO), which has the smallest contribution to the combined expected economic losses from debris on the Earth's orbits, experienced the fastest rate of increase in ODELI during the same period.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 3","pages":"Pages 539-545"},"PeriodicalIF":1.0,"publicationDate":"2024-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141053161","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":"Post mission disposal of Megha-Tropiques-1 through controlled atmospheric Re-entry to be published in: The journal of space safety engineering","authors":"","doi":"10.1016/j.jsse.2024.05.006","DOIUrl":"10.1016/j.jsse.2024.05.006","url":null,"abstract":"<div><div><span>Controlled Re-Entry Experiment of Megha-Tropiques 1 (CREEM), an immensely challenging and significant exercise, was successfully executed on 7 March 2023 by Indian Space Research organization (ISRO) as part of its ongoing efforts to improve compliance with internationally accepted space debris mitigation guidelines. In this paper, we present the overall strategy of CREEM which was primarily shaped by the stringent requirements of targeted impact within a pre-designated zone and ensuring visibility during the final de-boosting burns. We specifically address how the strategy was driven by the on-board and operational constraints, the rationale for the selection of the target region, the de-orbiting maneuver performance details, and the operational workarounds to ensure required subsystem performance. The external coordination related aspects and the </span>lessons learnt are also presented.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 3","pages":"Pages 469-475"},"PeriodicalIF":1.0,"publicationDate":"2024-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141392282","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":"An approach to shape parameterization using laboratory hypervelocity impact experiments","authors":"John H. Seago ,&nbsp;Heather Cowardin ,&nbsp;Phillip Anz-Meador ,&nbsp;Alyssa Manis ,&nbsp;Joshua Miller ,&nbsp;Eric Christiansen","doi":"10.1016/j.jsse.2024.05.004","DOIUrl":"10.1016/j.jsse.2024.05.004","url":null,"abstract":"<div><div><span>NASA's Orbital Debris Program Office relies on laboratory-based impact tests to supplement the measurement data of on-orbit events that define the orbital debris environment. These experiments deliver information that is essential to interpreting the radar and optical measurements of orbital fragmentation events into useful metrics, such as characteristic size, and to providing a better understanding of the distributions of fragment populations in terms of their masses, material constituents, fragment densities, cross-sectional areas, area-to-mass ratios, shapes, </span><em>etc</em><span>. The Satellite Orbital Debris Characterization Impact Test was a notable laboratory impact experiment conducted in 1992 using a surplus U.S.<span> Navy Transit navigation satellite of the 1960s. The data from this ground-based experiment were combined with on-orbit measurements to develop the NASA Standard Satellite Breakup Model (SSBM). To account for advancements in satellite design and construction since, a new impact test series – DebriSat – was conducted in 2014. This test utilized a high-fidelity mock-up spacecraft that better represents the materials and construction techniques used to design and manufacture modern spacecraft. Together, these tests offer valuable data to model an orbital debris environment composed of legacy and modern spacecraft. This paper presents an overview of the two laboratory impact tests, comparing their fragment parameter distributions with each other and with relevant distributions from the NASA SSBM. The categorization and descriptions of fragment shapes are of significant interest for future work, yet there are marked differences in the definitions of shape categories, categorizations of constituent materials, and the measurement techniques employed to populate these two datasets. New rubrics simplify and equate the categorizations between datasets to aid comparative analyses and to facilitate the potential use of both datasets in tandem with future environmental debris models. A preferred approach to classifying shape across disparate datasets uses the characteristic-length dimensions, and a simplified shape classification based on physical, solid-body dimensions, to mathematically construct an encapsulating right-circular cylinder that represents the fragment. The ratio of cylinder length-to-diameter (</span></span><em>L:D</em><span>) then provides a single continuum value for shape that is strongly correlated with its designated shape and size. This metric can then be used to further assess the distribution of shape with populations of other fragment characteristics within these datasets. The shape parameterization using the </span><em>L:D</em> ratios of right-circular cylinders is discussed.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 3","pages":"Pages 518-525"},"PeriodicalIF":1.0,"publicationDate":"2024-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141695560","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":"Investigation of near-rectilinear halo orbit search and rescue using staging L1/L2 Lyapunov and distant retrograde orbit families","authors":"Thomas J. Fay,&nbsp;Adam P. Wilmer,&nbsp;Robert A. Bettinger","doi":"10.1016/j.jsse.2024.04.009","DOIUrl":"https://doi.org/10.1016/j.jsse.2024.04.009","url":null,"abstract":"<div><p>Cislunar space is a region of growing interest with nations investing resources to cultivate long presence habitations on the lunar surface. With this increased attention and expansion of missions, both crewed and uncrewed, the likelihood of a mishap or a spacecraft becoming impaired and unable to continue its mission will also increase. The present research adds to the field of cislunar mission operations and trajectory analysis by investigating search and rescue (SAR) operations via rendezvous and proximity operations (RPO) with an impaired notional spacecraft located in a Near-Rectlinear Halo Orbit (NRHO). This research compares the response times of rescuer spacecraft located in sample distant retrograde orbits (DROs) and <span><math><msub><mi>L</mi><mn>1</mn></msub></math></span>/<span><math><msub><mi>L</mi><mn>2</mn></msub></math></span> Lyapunov orbits for the timely far rendezvous with the impaired spacecraft located in the NRHO. This will simulate a variety of far rendezvous whereby the impaired spacecraft’s location within the NRHO and the rescuer spacecraft in the <span><math><msub><mi>L</mi><mn>1</mn></msub></math></span>/<span><math><msub><mi>L</mi><mn>2</mn></msub></math></span> Lyapunov and DRO orbit families are varied. A series of minimum time optimal control problems are posed using the circular restricted three-body problem (CR3BP) dynamics, and pseudospectral methods are used to find solutions given an example maximum <span><math><mrow><mstyle><mi>Δ</mi></mstyle><mi>V</mi></mrow></math></span> constraint of 3 km/s. The results reinforces our intuition that rendezvous time of flight (TOF) between orbits within the <span><math><msub><mi>L</mi><mn>1</mn></msub></math></span>, <span><math><msub><mi>L</mi><mn>2</mn></msub></math></span>, and DRO families and the targeted NRHO correlate with proximity to the NRHO, with the shortest far rendezvous times in each family found to be approximately 6 hours, 4.5 hours, and 10 hours respectively. The results further show that a constellation of two rescue spacecraft could be positioned within the three orbit families to achieve far rendezvous with the chosen NRHO in under one day.</p></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 2","pages":"Pages 165-173"},"PeriodicalIF":0.0,"publicationDate":"2024-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141294580","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":"Commercial spaceflight: Regulatory framework assessment and safety perspectives","authors":"G. Buzzo,&nbsp;L. Travascio,&nbsp;A. Vozella","doi":"10.1016/j.jsse.2024.04.004","DOIUrl":"10.1016/j.jsse.2024.04.004","url":null,"abstract":"<div><p>Recent years are witnessing the rapid technological development in airspace domain, actually paving the way to the development of a commercial space market. Until the recent past, space operations have been essentially performed by research centers or military agencies, in usually segregated areas to ensure third parties’ safety, governed by launch base regulations and organized in an unscheduled manner. However, with the entry of private companies into the space domain, a new market niche is being created: that of commercial space transportation. For example, a promising area is the one related to operations performed by commercial suborbital flights, whether aimed at space tourism or simply transporting things and/or passengers from one point to another on the Earth's surface. The traffic volumes are supposed to increase in next years and segregating airspace does not represent a sustainable solution for the future.</p><p>The present paper will first assess the state of the art of the regulatory framework currently applicable to operators in order to obtain authorization to perform space missions for commercial use, then propose a comparison between the United State of America and European regulatory frameworks. Main challenges related to regulatory aspects will be identified and perspectives on possible higher airspace operations integration in the medium-long term will be derived. Finally, safety considerations deriving from a seamless accommodation of higher airspace operations in current Air Traffic Management will be derived for the medium-long term. In conclusion, this work reveals that neither the United States nor Europe has formally approved a legal framework establishing certification procedures for sub-orbital space transport systems. Currently, the US legislation is the most applicable as it has comprehensive rules to allow operators to obtain flight authorization ensuring compliance with requirements through a compliance matrix periodically updated.</p></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 2","pages":"Pages 326-334"},"PeriodicalIF":0.0,"publicationDate":"2024-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140777074","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":"Antarctic station Vostok as an analogue of a future lunar base: physiological reactions of the human cardiorespiratory system during a year-long exposure to the conditions of hypobaric hypoxia, isolation and hypokinesia","authors":"Nikolay Osetskiy,&nbsp;Olga Manko,&nbsp;Anton Artamonov,&nbsp;Eugeniy Ilyin ,&nbsp;Oleg Orlov","doi":"10.1016/j.jsse.2024.03.003","DOIUrl":"10.1016/j.jsse.2024.03.003","url":null,"abstract":"<div><p>A number of physiological investigations focused on human cardiorespiratory system have been conducted at Vostok station in Central Antarctica during the wintering of 2019.</p><p>During the one-year expedition at the Vostok station, the cardiorespiratory system gradually adapted to the unusual conditions of life and work in the isolated, confined and extreme (ICE) environment of Central Antarctica.</p><p>We hypothesized that during a long stay in the conditions of the Central Antarctica the adaptation strategy to physical environmental conditions for representatives of two age groups will differ, which will be evident from the dynamics of indicators of the functioning of the cardiovascular system and when assessing the autonomic nervous system status.</p><p>The level of blood oxygen saturation stabilized by the second month and was in the range of 86.0-91.0%, which corresponded to a reduced partial pressure of oxygen in the inhaled air. In terms of the respiratory system, central sleep apnea was noted in all subjects throughout the study. Quantitative analysis revealed that the average number of apneas per hour was 43, and their average duration was 25.2 seconds. The maximum apnea number was recorded at the beginning and middle of wintering, while before the end of the expedition the episodes became rarer. In all age groups there was a shortening of the PQ interval, with a tendency towards normalization by the end of wintering, while in the first age group the shortening of the interval was more significant than in the second, which apparently can be explained by a more pronounced active reaction of the sympathetic nervous system of polar explorers of the first age group.</p><p>Adaptive Potential Index (API) level remained practically unchanged throughout the wintering period in 9 out of 11 members of the expedition. The API value was predominantly in the range from 2.11 to 3.20 points, which corresponds to the level of “adaptation stress”. The autonomous nervous system (ANS) status was assessed by Kerdo Index (KI) values. KI positive dynamic was noted in 90% of cases by the 5th month of wintering. A direct correlation was found between the degree of positive shift in the KI value and the age of the participant. The gained results do not allow us to state that ANS has fully adapted to the conditions of life and work at the station. The results of this investigation demonstrate stable and positive adaptation trend to the ICE environment of Central Antarctica throughout the study period, regardless of age and wintering experience.</p></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 2","pages":"Pages 268-280"},"PeriodicalIF":0.0,"publicationDate":"2024-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140784787","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":"The planetary protection strategy of Mars Sample Return’s Earth Return Orbiter mission","authors":"Giuseppe Cataldo ,&nbsp;Lorenz Affentranger ,&nbsp;Brian G. Clement ,&nbsp;Daniel P. Glavin ,&nbsp;David W. Hughes ,&nbsp;John Hall ,&nbsp;Bruno Sarli ,&nbsp;Christine E. Szalai","doi":"10.1016/j.jsse.2024.04.013","DOIUrl":"10.1016/j.jsse.2024.04.013","url":null,"abstract":"<div><p>The Mars Sample Return campaign aims to use three flight missions and one ground element to safely bring rock cores, regolith and atmospheric samples from the surface of Mars to Earth to answer key questions about the geologic and climate history of Mars, including the potential for ancient life. Since its landing in Jezero Crater in 2021, the first mission, NASA’s Mars 2020, has collected a number of samples on the crater floor and on the delta using the Perseverance rover. Subsequent missions would recover the sealed sample tubes, launch them into Mars orbit, and transport them back to Earth. The ground element would be a high-containment facility that would isolate and protect the samples during initial sample characterization, which would include sample safety assessments and time-sensitive scientific investigations. These elements are currently in the planning and design stages of development, and represent an international effort of NASA, the European Space Agency (ESA), and many industry partners. The work presented here provides an overview of the planetary protection strategy of the third flight mission, the ESA-led Earth Return Orbiter, which hosts the NASA-provided Capture, Containment, and Return System. The orbiter would detect and capture the container with up to 30 sealed tubes previously put in Martian orbit, contain them in redundant containers to ensure that no potentially hazardous Mars particles are released, and return them to Earth through an entry vehicle. Both NASA and ESA policies comply with the United Nations’ Outer Space Treaty by planning to protect Earth’s biosphere from any potential adverse effects from material returned from solar system bodies beyond the Earth-Moon system. In the conduct of Mars Sample Return, the two agencies have mutually agreed to apply approaches consistent with their own planetary protection standards to the campaign elements they each provide.</p></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 2","pages":"Pages 374-384"},"PeriodicalIF":0.0,"publicationDate":"2024-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S2468896724000594/pdfft?md5=b2b225e29846e876797f013d9c8354a5&pid=1-s2.0-S2468896724000594-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141036384","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}