Journal of Space Safety Engineering最新文献

{"title":"Investigation of acoustic effect on liquid residue ejection from the closed vessel with a drain valve","authors":"Valeriy Trushlyakov,&nbsp;Vladislav Urbansky","doi":"10.1016/j.jsse.2024.11.003","DOIUrl":"10.1016/j.jsse.2024.11.003","url":null,"abstract":"<div><div>The concept, schematic solution, and methodology for liquid residue passivation using additional acoustic impact based on a gas jet emitter when introducing gas into a closed vessel (CV) containing liquid residue have been developed. A methodology for numerical modeling of the process of liquid droplet entrainment from the CV using the Ansys Fluent software package has been developed, based on gas supply into the tank. The method consists of two interrelated physical-mathematical models (PMM): 1) PMM of gas introduction into CV taking into account additional acoustic impact and creation of two-phase flow structure with subsequent entrainment of liquid droplets through the drain valve into the environment; 2) PMM of acoustic cavitation occurrence in the liquid volume taking into account the assessment of vapor occurrence inside the liquid with subsequent use of these results as initial conditions in PMM on formation of two-phase gas flow. The influence of additional acoustic impact during gas introduction into the CV on the ejection of liquid residue was evaluated. The results showed that accounting for acoustic cavitation increases the entrainment of liquid droplets by approximately 40 %.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 66-75"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169682","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":"Analysis 2023 Storms based on different time scales (Dst, Kp & Sym/H)","authors":"Pawan Kumar ,&nbsp;Mahender Pal ,&nbsp;A.P. Mishra ,&nbsp;Sham Singh","doi":"10.1016/j.jsse.2024.12.002","DOIUrl":"10.1016/j.jsse.2024.12.002","url":null,"abstract":"<div><div>We use numerous plasma parameters with geomagnetic indices with different time scales for the solar wind (SW) during the corresponding periods. Using Kp 3 h data, Dst index hourly data, the symmetric disturbance field (SYM-H) minute resolution data, and solar plasma measurements from multiple satellites, examine the chain of significant events that occurred in year 2023. The Empirical methods and statistical correlation technique examines the relationship between SW parameters and geomagnetic indices during major geomagnetic storms in 2023. Statical analysis of geomagnetic provisional activity Sym/H has better results than the disturbance storm time (Dst) index during various main phases of geomagnetic activity. The correlation (Cr) between SW characteristics with Dst, Kp, and SYM/H have different values, defining the link of disturbance in space weather. This research provides valuable insights for enhancing space weather forecasting of solar-terrestrial interactions.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 94-104"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169685","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":"Radiant flux reflectivity model of nanocomposite dielectric materials","authors":"Sayavur I. Bakhtiyarov ,&nbsp;Mostafa Hassanalian ,&nbsp;Ayten S. Bakhtiyarova ,&nbsp;Stephen M. White","doi":"10.1016/j.jsse.2024.12.003","DOIUrl":"10.1016/j.jsse.2024.12.003","url":null,"abstract":"<div><div>A radiant-flux reflectivity model is developed to estimate the reflectance of the radiant flux in nanocomposite dielectric materials. The model considers reflectance, transmittance and absorbance in all components of the composite material. The model is applied to pristine PTFE and to a PFTE-based nanocomposite. The results are compared to the experimental data available in the literature. The simulation results show that the variation of the reflectance simulated for pristine PTFE samples of different thicknesses increases with increasing wavelength and decreases with increasing sample thickness. A comparison of the simulation results with the experimental data obtained by different researchers showed a qualitative agreement between the simulations and the experimental data.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 105-118"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169686","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":"Continuous in-situ and remote sun observation for space weather monitoring and mitigation of infrastructure threats through an optimized heliocentric satellite constellation","authors":"Leonidas Askianakis","doi":"10.1016/j.jsse.2025.02.002","DOIUrl":"10.1016/j.jsse.2025.02.002","url":null,"abstract":"<div><div>Although vital for life on Earth, solar activity poses questions and increasing threats to humanity due to the Sun's unknown dynamics, intensified by our dependence on terrestrial and space-based infrastructure. This situation is compounded by significant gaps in our understanding of space weather phenomena, the Sun's magnetic field, and the need for rapid responses to unpredicted solar events. To address these issues, an optimized heliocentric satellite constellation is proposed that leverages satellites in an Elliptical Walker Constellation. This system offers – among others - equally distributed arguments of periapsis separations and cross-coupled true anomalies with respect to the Sun-centric coordinate frame. In this paper it is also demonstrated that this strategic multi-spacecraft configuration makes it possible to distinguish spatial and temporal changes in solar wind phenomena, reconstruct, in 3D, Coronal Mass Ejections (CMEs), predict which space or ground-based infrastructure and when it will be affected by CMEs, maintain continuous coverage of the critical Sun-Earth line throughout the mission's duration, and protect future missions by providing simultaneously in-situ and remote measurements from small and cost-effective satellites.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 149-159"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169689","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"International Space Settlement Design Competition - An Experience","authors":"J. Clayton Gafford","doi":"10.1016/j.jsse.2025.02.001","DOIUrl":"10.1016/j.jsse.2025.02.001","url":null,"abstract":"<div><div>A high school Space Settlement Design Competition held continuously for over 40 years exposes a group of student competitors to simulated real world industry proposal activity. This competition provides an opportunity for high school students interested in space to learn about both space exploration and system engineering. ISSDC provides students an opportunity to learn these concepts as well as offering opportunities for individuals to focus on their own specific interests and to the level of involvement that they select. Student competitors form fictitious companies and establish a company organizational structure that include a president, vice presidents, department directors and department team members. The companies also have an industry professional join as a Chief Executive Officer (CEO) who guides the students through the competition proposal. The result of the competition is that student competitors, CEOs, and other volunteers gain a lifelong experience that guides and enriches them through their educational and professional careers.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 28-36"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169866","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"AF advertisement","authors":"","doi":"10.1016/S2468-8967(25)00053-9","DOIUrl":"10.1016/S2468-8967(25)00053-9","url":null,"abstract":"","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Page ii"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169693","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Sub-cm space debris in LEO: A comparison between the ESA MASTER model and ADLER in-situ data","authors":"Gernot Grömer ,&nbsp;Vitali Braun ,&nbsp;Xanthi Oikonomidou ,&nbsp;Wolfgang Ebner ,&nbsp;Theresa Mayer ,&nbsp;Willibald Stumptner ,&nbsp;Stefan Amberger ,&nbsp;Christian Federspiel ,&nbsp;Bernhard Niedermayer ,&nbsp;Peter Schüller","doi":"10.1016/j.jsse.2025.02.009","DOIUrl":"10.1016/j.jsse.2025.02.009","url":null,"abstract":"<div><div>Modeling the Space debris and Meteoroid (SD/M) environment in Low Earth orbit is particularly challenging when it comes to sub-cm sized particles that are below the detection thresholds of ground based observations. The MASTER model of ESA is used to establish a reference for risk assessments and mission planning. However, given the significant increase in satellite operations in the last decade, the lack of recent in-situ data for calibrating the models is evident. The ADLER-1 mission, operating for 512 days at an altitude of 480 km, was an in-orbit demonstrator for deploying a piezoelectric sensor array as well as a continuous wave miniature radar to obtain pilot data. The APID-1 instrument onboard ADLER-1 yielded 117 impact events for a period of ca 400 days, which were compared to the MASTER simulations. There is evidence for detecting debris from a rocket motor firing of an ISS supply flight.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 160-174"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169690","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Efficient disposal of low lunar orbiters on the lunar surface","authors":"Nathan R. Boone,&nbsp;Robert A. Bettinger","doi":"10.1016/j.jsse.2024.09.005","DOIUrl":"10.1016/j.jsse.2024.09.005","url":null,"abstract":"<div><div>Realistic numerical simulations are conducted to explore safe and efficient strategies for End-of-Life lunar spacecraft disposal on the lunar surface. Disposal from three different near-polar, low-altitude, and near-circular orbit types was analyzed to determine if impact locations that minimize the risk to protected regions of the lunar surface can be achieved consistently for low fuel costs using the Moon’s non-spherical gravity field. A total of 300,000 objects were propagated following retrograde disposal burns using a high-fidelity lunar trajectory model, and the disposal burn locations and magnitudes were compared against the resulting likelihoods of decay and lunar surface impact locations. The results identified disposal strategies that could achieve impact in safe locations for 10 m/s of <span><math><mrow><mstyle><mi>Δ</mi></mstyle><mi>V</mi></mrow></math></span> or less for all orbit types, much lower than the <span><math><mrow><mstyle><mi>Δ</mi></mstyle><mi>V</mi></mrow></math></span> cost to lower the perilune entirely to the lunar surface. A similar simulation-based methodology could be applied to operational lunar satellites to identify disposal strategies based on specific mission conditions. The results of this study support the development of safe and efficient End-of-Life disposal strategies that minimize the accumulation of debris in lunar orbit and extend the operational lifetimes of lunar missions.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 195-205"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169861","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Producing compact copper elements in the velocity range of 5–9.5 km/s using shaped charges with modified combined hemisphere-cylinder liners","authors":"S.V. Fedorov,&nbsp;I.A. Bolotina,&nbsp;P.V. Merzlyakova","doi":"10.1016/j.jsse.2025.01.002","DOIUrl":"10.1016/j.jsse.2025.01.002","url":null,"abstract":"<div><div>To test the protective shields of spacecraft for resistance to meteoroids and space debris fragments, it is necessary to develop methods for accelerating solid particles to high velocities. The currently used shaped charges with a combined hemisphere-cylinder liner make it possible to produce compact steel elements with velocities at the level of 6 km/s. Based on numerical modeling within framework of a two-dimensional axisymmetric problem of continuum mechanics, the possibilities of modifying hemisphere-cylinder liner to expand the range of velocities of the resulting compact elements are considered. Modeling was carried out with respect to a shaped charge with a diameter of 100 mm and a copper liner. The jet-forming part of the liner was given a degressive (decreasing from the top to the base) thickness with a hemispherical or semi-ellipsoidal shape of its outer surface and a semi-ellipsoidal or semi-superellipsoidal shape of the inner surface. By numerical calculations, the geometric parameters of the combined liners were selected, which make it possible to form compact elements with velocities in the range from 5 to 9.5 km/s at the maximum possible value of element mass. The mass of the element at a velocity of about 9.5 km/s was about 5 g.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 132-148"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169688","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Benefits of using functional safety in commercial space applications","authors":"F. Lumpe ,&nbsp;M. Seidl","doi":"10.1016/j.jsse.2024.11.002","DOIUrl":"10.1016/j.jsse.2024.11.002","url":null,"abstract":"<div><div>According to IEC61508 functional safety is relevant whenever a product or system contains electrical, electronic or programmable electronic elements that perform safety-critical functions. It is used in many areas of technology such as, process industry (e.g., energy sector), automotive (transport sector), mechanical engineering, or aviation. This article will compare the approaches and concepts of Functional Safety based on IEC61508 and ISO26262 with the RAMS (Reliability, availability, maintainability and safety) approaches of the space industry, in particular with the Fault Detection Isolation and Recovery (FDIR) approach.</div><div>The paper will provide an insight into the possibilities of minimizing risk at the component level, especially for complex integrated circuits. Traditionally, the space industry has focused on qualifying the components used for the extreme environmental parameters and the typically very long duration of use in space. However, as ICs (Integrated Circuit) have become very complex, there is significantly increased risk of systematic failures that can occur during the development of the component itself and also by the designer using it for development the actual circuit board assembly.</div><div>In addition, the cost of components is a major factor in the development of satellite constellations due to higher volumes, so a trade-off between qualification and affordability must be found.</div><div>The presentation will show how systematic faults in other market sectors can be avoided as far as possible and how so-called random faults can be detected as quickly as possible and their effects ideally eliminated or at least minimized with the help of appropriate performance features of the semiconductor products, such as ECC (Error Correction Code), lock-step, or BIST (Built-in Self Test).</div><div>The successful mission of the Mars Rotorcraft Ingenuity from JPL (NASA) provides an insight into the practical application of a functional safety concept in a space application.</div><div>This paper is intended as a suggestion on how to make the best use of existing features of semiconductor products developed for functional safety in other market sectors also for space applications.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 187-194"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169692","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}