Journal of Space Safety Engineering最新文献

{"title":"Introducing Space Debris: Update to the State of the Art","authors":"José Pedro Ferreira , Daniel Moomey , Chris L. Ostrom","doi":"10.1016/j.jsse.2024.09.001","DOIUrl":"10.1016/j.jsse.2024.09.001","url":null,"abstract":"","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 3","pages":"Page 387"},"PeriodicalIF":1.0,"publicationDate":"2024-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142571637","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":"Establishing requirements for lunar and cislunar orbital debris tracking","authors":"Brad F. Barakat,&nbsp;Michael T. Kezirian","doi":"10.1016/j.jsse.2024.08.006","DOIUrl":"10.1016/j.jsse.2024.08.006","url":null,"abstract":"<div><div>There is a need to formally coordinate lunar and cislunar space traffic management to mitigate the risk of collisions with micrometeoroids and orbital debris in this space domain. To control this hazard, it will be critical to develop a high-fidelity orbital debris catalog. This catalog will be maintained by monitoring and propagating the trajectory of objects. The need to perform a debris avoidance maneuver for collision avoidance will depend on the fidelity of the propagated debris trajectory. A larger uncertainty (magnitude as a function of time) will require a larger maneuver and a higher likelihood of the need to perform this maneuver. This study assesses debris avoidance maneuvers and corresponding corrective actions to recover the desired mission trajectory as a way to evaluate the desired capability of tracking of objects in lunar and cislunar orbit. The baseline Earth-to-Moon trajectory was that of the Artemis I mission. Typical conjunction assessments were postulated at 100,000 km from Earth's center (approximately a quarter of the way to the moon) and at lunar orbit insertion (LOI). For these two cases, the required debris avoidance maneuver (and hence impact to the mission) is tied to the uncertainty in orbital debris tracking. The study provides a methodology and baseline inputs to establish future requirements of debris tracking in lunar and cislunar orbits. It also reinforces the importance of long-term sustainability for lunar missions, specifically preventing the generation of orbital debris.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 3","pages":"Pages 446-453"},"PeriodicalIF":1.0,"publicationDate":"2024-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142571560","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":"Serendipitous detection of orbital debris by the International Liquid Mirror Telescope","authors":"Paul Hickson ,&nbsp;Bhavya Ailawadhi ,&nbsp;Arun S ,&nbsp;Monalisa Dubey ,&nbsp;Naveen Dukiya ,&nbsp;Sara Filali ,&nbsp;Brajesh Kumar ,&nbsp;Kuntal Misra ,&nbsp;Vibhore Negi ,&nbsp;Kumar Pranshu ,&nbsp;Jean Surdej ,&nbsp;Saakshi Turakhia","doi":"10.1016/j.jsse.2024.05.003","DOIUrl":"10.1016/j.jsse.2024.05.003","url":null,"abstract":"<div><div>The International Liquid Mirror Telescope is a 4-m zenith-pointing optical telescope that employs a rotating liquid primary mirror. Located in the Indian Himalayas, it began operations in October 2022. The telescope is equipped with a CCD camera that has a 22 x 22 arcmin field of view and employs time-delay integration readout to compensate for the Earth’s rotation. While its primary purpose is to conduct astronomical survey observations using broad-band filters, the telescope is also sensitive to objects in Earth orbit that pass through its field of view, leaving detectable streaks. We have examined all images obtained during the first year of observations and determined the transit times and position angles of all detected objects. These were compared with publicly available two-line elements, propagated to the time of observation, in order to identify cataloged objects. A total of 301 streaks were found in 1838 images. Of these, 64% were identified with cataloged objects. Most of the identified objects are in low-Earth orbit, in the altitude range of 400–1600 km. The apparent magnitudes of the identified objects range from 3.6 to 15.1 in the V band. It was also possible to infer angular rates, apparent magnitudes and altitudes for 29% of the unidentified objects. The V-band magnitudes range from 6.4 to 19.5 and the estimated altitudes range from 285 to over 300,000 km.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 3","pages":"Pages 425-431"},"PeriodicalIF":1.0,"publicationDate":"2024-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142571586","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":"Infrared photometry and spectrometry of satellites and debris at UKIRT","authors":"Eric C. Pearce ,&nbsp;Harrison Krantz ,&nbsp;Adam Block ,&nbsp;Deatrick L. Foster","doi":"10.1016/j.jsse.2024.07.010","DOIUrl":"10.1016/j.jsse.2024.07.010","url":null,"abstract":"&lt;div&gt;&lt;div&gt;The characterization of deep space debris poses a significant challenge in Space Domain Awareness (SDA). Multi-color photometry and the resultant color indices offer the potential to rapidly discriminate between debris and intact space objects such as rocket bodies and satellites. These multi-color techniques can also identify anomalous members of objects in certain groups and cue higher fidelity data collections and studies. However, multi-color photometry can be difficult to interpret, as the effects of phase and rotation become conflated with the more fundamental material properties of the satellite. Additionally, the broad astronomical photometric bands may not identify key spectral features that can be diagnostic for SDA applications. With our recent observational campaign we have been able to collect 5-color photometry in the near-IR with WFCAM as well as overlapping near-IR spectra with the UKIRT 1–5 μm Imager-Spectrometer (UIST). On a small set of objects, we also have mid-IR spectrophotometry with the Mid-IR esCHELLE (Michelle) imaging spectrograph.&lt;/div&gt;&lt;div&gt;Our previous measurements with the United Kingdom Infrared Telescope (UKIRT) Wide Field Camera (WFCAM) characterized a wide range of space objects with the goal of developing techniques to rapidly discriminate between different classes of objects and to identify anomalous members of these groups. The survey has produced a comprehensive database of 5-color photometry in the Z, Y, J, H, and K bands, analogous to the bands that are anticipated to be exploited by future U.S. ground-based SDA systems. Our current data set includes:&lt;ul&gt;&lt;li&gt;&lt;span&gt;(a)&lt;/span&gt;&lt;span&gt;&lt;div&gt;United States Centaur rocket bodies (RBs),&lt;/div&gt;&lt;/span&gt;&lt;/li&gt;&lt;li&gt;&lt;span&gt;(b)&lt;/span&gt;&lt;span&gt;&lt;div&gt;Molniya communication satellites including the −1 K, 1T, −2, and −3 variants,&lt;/div&gt;&lt;/span&gt;&lt;/li&gt;&lt;li&gt;&lt;span&gt;(c)&lt;/span&gt;&lt;span&gt;&lt;div&gt;Russian FREGAT and SL-6 upper stage RBs in Molniya orbits,&lt;/div&gt;&lt;/span&gt;&lt;/li&gt;&lt;li&gt;&lt;span&gt;(d)&lt;/span&gt;&lt;span&gt;&lt;div&gt;Russian Breeze-M rocket bodies disposed of in GEO-crossing graveyard like orbits, and the Angara-5/Breeze-M mass simulator, also disposed of in a near-GEO orbit,&lt;/div&gt;&lt;/span&gt;&lt;/li&gt;&lt;li&gt;&lt;span&gt;(e)&lt;/span&gt;&lt;span&gt;&lt;div&gt;Intact payloads selected from satellites using the Boeing HS-376 buses—including four different generations of solar panel technology.&lt;/div&gt;&lt;/span&gt;&lt;/li&gt;&lt;/ul&gt;Many of the objects we have studied have significant orbital inclination or drift in the GEO belt. The interpretation of photometry of these objects is especially difficult as phase angle can no longer be considered simply as a single-dimensional quantity. During 2023, we have endeavored to expand our phase angle coverage of a handful of objects and comprehensively sample brightness and color in both components of phase angle. In this paper we present exemplary “phase-phase” diagrams demonstrating this technique and highlight some of the practical and observational difficulties in achieving comprehensive phase angle coverage and interpreti","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"11 3","pages":"Pages 432-438"},"PeriodicalIF":1.0,"publicationDate":"2024-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142571587","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":"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}