Pub Date : 2025-03-01DOI: 10.1016/j.jsse.2025.02.009
Gernot Grömer , Vitali Braun , Xanthi Oikonomidou , Wolfgang Ebner , Theresa Mayer , Willibald Stumptner , Stefan Amberger , Christian Federspiel , Bernhard Niedermayer , Peter Schüller
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.
{"title":"Sub-cm space debris in LEO: A comparison between the ESA MASTER model and ADLER in-situ data","authors":"Gernot Grömer , Vitali Braun , Xanthi Oikonomidou , Wolfgang Ebner , Theresa Mayer , Willibald Stumptner , Stefan Amberger , Christian Federspiel , Bernhard Niedermayer , 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}
Pub Date : 2025-03-01DOI: 10.1016/j.jsse.2024.09.005
Nathan R. Boone, Robert A. Bettinger
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 or less for all orbit types, much lower than the 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.
{"title":"Efficient disposal of low lunar orbiters on the lunar surface","authors":"Nathan R. Boone, 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}
Pub Date : 2025-03-01DOI: 10.1016/j.jsse.2025.01.002
S.V. Fedorov, I.A. Bolotina, P.V. Merzlyakova
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.
{"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, I.A. Bolotina, 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}
Pub Date : 2025-03-01DOI: 10.1016/j.jsse.2024.11.002
F. Lumpe , M. Seidl
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.
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.
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.
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).
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.
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.
{"title":"Benefits of using functional safety in commercial space applications","authors":"F. Lumpe , 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}
Pub Date : 2025-03-01DOI: 10.1016/S2468-8967(25)00045-X
{"title":"Editorial Board and Society Advert","authors":"","doi":"10.1016/S2468-8967(25)00045-X","DOIUrl":"10.1016/S2468-8967(25)00045-X","url":null,"abstract":"","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Page IFC"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169860","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}
Pub Date : 2025-03-01DOI: 10.1016/j.jsse.2025.02.004
Liz Bosch , Radu Babiceanu
There is a significant number of discussions lately, at both government agencies and private industry, about sending crewed missions further into space. Sending astronauts back to the Moon and, for the first time, to Mars seems to make space enthusiasts around the world excited given the noteworthy tests and preparations going on in the last few years. The decision to launch crewed missions into space depends primarily on three aspects: technology, budget, and mission risk. Even when the first two aspects are addressed, the third question still remains: is it safe enough? Generally, Safety and Mission Assurance (S&MA) for space systems is taught in space systems programs from an operations standpoint. There are very few to no courses across the USA that address space S&MA from the design engineering perspective. There is also limited teaching of ethics-based safety culture in the engineering programs offered across the country. The resultant gap between graduates’ knowledge of space S&MA and the needed skills to conduct design engineering of space systems is, at the moment, mostly filled by the space agencies and private space industry. The graduate course framework presented in this paper is built on a student-centered approach through customized case-study experiences that promotes understanding and motivation, which are significant aspects of making risk-based decisions with considerations to safeguarding human lives. By exploring the root causes of human space flight close calls, incidents, and mishaps, students can envision themselves in the space operational environment and can become aware of how design engineering, safety culture, and ethics act through a combined feedforward and feedback mechanism to ensure reliable and safe operations. Then, connecting back to the theoretical course material creates the student's understanding and motivation once they act as decision-makers after graduation. The proposed case study-based course framework also promotes critical thinking and problem-solving for the safety engineering aspects of the design of space systems. Understanding and motivation, together with critical-thinking and problem-solving is expected to prove the efficacy of case-study-based instruction and support instilling student ethical decision making, with its component parts of integrity, accountability, and responsibility.
{"title":"Space systems safety and mission assurance case study-based graduate education","authors":"Liz Bosch , Radu Babiceanu","doi":"10.1016/j.jsse.2025.02.004","DOIUrl":"10.1016/j.jsse.2025.02.004","url":null,"abstract":"<div><div>There is a significant number of discussions lately, at both government agencies and private industry, about sending crewed missions further into space. Sending astronauts back to the Moon and, for the first time, to Mars seems to make space enthusiasts around the world excited given the noteworthy tests and preparations going on in the last few years. The decision to launch crewed missions into space depends primarily on three aspects: technology, budget, and mission risk. Even when the first two aspects are addressed, the third question still remains: is it safe enough? Generally, Safety and Mission Assurance (S&MA) for space systems is taught in space systems programs from an operations standpoint. There are very few to no courses across the USA that address space S&MA from the design engineering perspective. There is also limited teaching of ethics-based safety culture in the engineering programs offered across the country. The resultant gap between graduates’ knowledge of space S&MA and the needed skills to conduct design engineering of space systems is, at the moment, mostly filled by the space agencies and private space industry. The graduate course framework presented in this paper is built on a student-centered approach through customized case-study experiences that promotes understanding and motivation, which are significant aspects of making risk-based decisions with considerations to safeguarding human lives. By exploring the root causes of human space flight close calls, incidents, and mishaps, students can envision themselves in the space operational environment and can become aware of how design engineering, safety culture, and ethics act through a combined feedforward and feedback mechanism to ensure reliable and safe operations. Then, connecting back to the theoretical course material creates the student's understanding and motivation once they act as decision-makers after graduation. The proposed case study-based course framework also promotes critical thinking and problem-solving for the safety engineering aspects of the design of space systems. Understanding and motivation, together with critical-thinking and problem-solving is expected to prove the efficacy of case-study-based instruction and support instilling student ethical decision making, with its component parts of integrity, accountability, and responsibility.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 12-16"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169864","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}
Pub Date : 2025-03-01DOI: 10.1016/j.jsse.2025.03.002
Dr. L. Dale Thomas , Samantha Rawlins , Shreyas Lakshmipuram Raghu , Alexander Aueron
The development methodology employed in the United States’ Rover NERVA program is reviewed as the basis for the Reliability-Driven Design and Test (ReDDT) methodology described herein. Postulated as perhaps the first full programmatic implementation of probabilistic design, the NERVA foundational methodology appears to have never been adopted elsewhere following program cancelation. Nevertheless, much of the framework developed during NERVA remains applicable, and the ReDDT approach described in this work is based upon their approach. The ReDDT approach builds on the NERVA method by introducing a qualitative failure mode analysis to identify which tests are most useful and maximize program efficiency. The qualitative analysis is supported by uncertainty analysis, which is applied to identify the drivers of the system's technical uncertainty and thereby drivers of safety and reliability. The ReDDT approach is distinct from existing reliability-based methodologies including Reliability Based Design Optimization (RBDO) and Design for Reliability (DfR) in that ReDDT focuses on concurrent and synergistic system design, integration, and test planning. ReDDT has been developed for NASA's current Space Nuclear Propulsion effort, but it has broader applicability to nuclear power systems and complex aerospace system developments and upgrades in general. The ReDDT methodology has the goal of transforming the relationship of the design effort to the integration and test effort within a system development from one of test-fail-fix to model-test-evaluate.
{"title":"A Reliability-Driven Design and Test (ReDDT) methodology for space nuclear power and propulsion systems","authors":"Dr. L. Dale Thomas , Samantha Rawlins , Shreyas Lakshmipuram Raghu , Alexander Aueron","doi":"10.1016/j.jsse.2025.03.002","DOIUrl":"10.1016/j.jsse.2025.03.002","url":null,"abstract":"<div><div>The development methodology employed in the United States’ Rover NERVA program is reviewed as the basis for the Reliability-Driven Design and Test (ReDDT) methodology described herein. Postulated as perhaps the first full programmatic implementation of probabilistic design, the NERVA foundational methodology appears to have never been adopted elsewhere following program cancelation. Nevertheless, much of the framework developed during NERVA remains applicable, and the ReDDT approach described in this work is based upon their approach. The ReDDT approach builds on the NERVA method by introducing a qualitative failure mode analysis to identify which tests are most useful and maximize program efficiency. The qualitative analysis is supported by uncertainty analysis, which is applied to identify the drivers of the system's technical uncertainty and thereby drivers of safety and reliability. The ReDDT approach is distinct from existing reliability-based methodologies including Reliability Based Design Optimization (RBDO) and Design for Reliability (DfR) in that ReDDT focuses on concurrent and synergistic system design, integration, and test planning. ReDDT has been developed for NASA's current Space Nuclear Propulsion effort, but it has broader applicability to nuclear power systems and complex aerospace system developments and upgrades in general. The ReDDT methodology has the goal of transforming the relationship of the design effort to the integration and test effort within a system development from one of test-fail-fix to model-test-evaluate.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 53-65"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169868","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}
Pub Date : 2025-03-01DOI: 10.1016/S2468-8967(25)00052-7
{"title":"Front page with the caption related to the front cover","authors":"","doi":"10.1016/S2468-8967(25)00052-7","DOIUrl":"10.1016/S2468-8967(25)00052-7","url":null,"abstract":"","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Page i"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169862","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}
Pub Date : 2025-03-01DOI: 10.1016/j.jsse.2025.04.003
Raafat George Saadé, Liu Hao, Taro Kuusiholma
In the coming 20 years, advancements in aerospace technology will transform the aviation industry, spurred by environmental concerns and worldwide developments. The emergence of Higher Airspace Operations (HAO) will create new possibilities in fields such as telecommunications, Earth observation, and hypersonic transportation, employing trans-atmospheric vehicles and High-Altitude Platform Stations. Simultaneously, the low-altitude sector is experiencing growth through advanced air mobility (AAM), including unmanned aerial vehicles (UAV) and air taxis. China is spearheading this "low-altitude economy" initiative, with projections suggesting that urban air mobility could surpass a trillion-dollar valuation by 2040. The expansion in both high- and low-altitude domains signals significant technological progress and economic benefits on a global scale. All these advancements present significant challenges to operations, management, and governance of air and space, most importantly as they relate to safety. In response, the Beijing Institute of Technology's School of Global Governance (SGG) was established to address China's evolving global role, its increasing involvement in the United Nations, and the lack of integrated management and governance content in aerospace-related graduate programs. The school has developed four primary focus areas: air and space, the digital economy and AI, the environment and sustainability, and governance. The SGG aims to maintain a significant proportion of international faculty members. The school emphasizes an internationalized curriculum to equip students with the multifaceted and interdisciplinary nature of air and space studies. By offering a global governance degree in business management, public administration, or legal focus, students have the flexibility to tailor their thesis or dissertation to their career goals. The SGG forged numerous international partnerships through Memorandums of Understanding (MoUs), providing students with internship opportunities. The school's educational approach is grounded in Self-Directed Learning principles, fostering skills for lifelong learning in its students.
{"title":"Global governance & aerospace – The need for a management-integrated air and space education paradigm","authors":"Raafat George Saadé, Liu Hao, Taro Kuusiholma","doi":"10.1016/j.jsse.2025.04.003","DOIUrl":"10.1016/j.jsse.2025.04.003","url":null,"abstract":"<div><div>In the coming 20 years, advancements in aerospace technology will transform the aviation industry, spurred by environmental concerns and worldwide developments. The emergence of Higher Airspace Operations (HAO) will create new possibilities in fields such as telecommunications, Earth observation, and hypersonic transportation, employing trans-atmospheric vehicles and High-Altitude Platform Stations. Simultaneously, the low-altitude sector is experiencing growth through advanced air mobility (AAM), including unmanned aerial vehicles (UAV) and air taxis. China is spearheading this \"low-altitude economy\" initiative, with projections suggesting that urban air mobility could surpass a trillion-dollar valuation by 2040. The expansion in both high- and low-altitude domains signals significant technological progress and economic benefits on a global scale. All these advancements present significant challenges to operations, management, and governance of air and space, most importantly as they relate to safety. In response, the Beijing Institute of Technology's School of Global Governance (SGG) was established to address China's evolving global role, its increasing involvement in the United Nations, and the lack of integrated management and governance content in aerospace-related graduate programs. The school has developed four primary focus areas: air and space, the digital economy and AI, the environment and sustainability, and governance. The SGG aims to maintain a significant proportion of international faculty members. The school emphasizes an internationalized curriculum to equip students with the multifaceted and interdisciplinary nature of air and space studies. By offering a global governance degree in business management, public administration, or legal focus, students have the flexibility to tailor their thesis or dissertation to their career goals. The SGG forged numerous international partnerships through Memorandums of Understanding (MoUs), providing students with internship opportunities. The school's educational approach is grounded in Self-Directed Learning principles, fostering skills for lifelong learning in its students.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 17-27"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169865","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}
Pub Date : 2025-03-01DOI: 10.1016/j.jsse.2025.02.006
Jingyan Xie, Yun-Ze Li
Similar to Earth, the orbital season also exists in a low-Earth orbit, and understanding these seasonal effects is crucial for ensuring the long-term performance and safety of spacecraft. However, methods for determining the orbital season and its long-term impact on the electricity supply systems are lacking. To address this research gap, we present a method for dividing the orbital season in the low-Earth Sun-synchronous orbit throughout the year. Accurate orbital data from four satellites from 2021 to 2023 were incorporated to ensure practical relevance and generalisability. The results indicate that the seasons in the Sun-synchronous orbit can be divided into a cold season, lasting from April to October, and a hot season, lasting from November to March. The thermal environment of satellites and the performance of the electricity supply system during different orbital seasons were studied. Our findings suggest that additional thermal management measures should be implemented during the hot season, which can mitigate system failure risks and enhance operational efficiency. This research not only complements previous studies on orbital seasons but also provides valuable guidance for future spacecraft design and management, emphasizing the importance of integrating thermal considerations into mission planning to ensure safe and effective space operations.
{"title":"Orbital season and its long-term effects on the thermal and electrical safe operation of low-Earth satellites in Sun-synchronous orbit","authors":"Jingyan Xie, Yun-Ze Li","doi":"10.1016/j.jsse.2025.02.006","DOIUrl":"10.1016/j.jsse.2025.02.006","url":null,"abstract":"<div><div>Similar to Earth, the orbital season also exists in a low-Earth orbit, and understanding these seasonal effects is crucial for ensuring the long-term performance and safety of spacecraft. However, methods for determining the orbital season and its long-term impact on the electricity supply systems are lacking. To address this research gap, we present a method for dividing the orbital season in the low-Earth Sun-synchronous orbit throughout the year. Accurate orbital data from four satellites from 2021 to 2023 were incorporated to ensure practical relevance and generalisability. The results indicate that the seasons in the Sun-synchronous orbit can be divided into a cold season, lasting from April to October, and a hot season, lasting from November to March. The thermal environment of satellites and the performance of the electricity supply system during different orbital seasons were studied. Our findings suggest that additional thermal management measures should be implemented during the hot season, which can mitigate system failure risks and enhance operational efficiency. This research not only complements previous studies on orbital seasons but also provides valuable guidance for future spacecraft design and management, emphasizing the importance of integrating thermal considerations into mission planning to ensure safe and effective space operations.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 175-186"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169691","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}
扫码关注我们
求助内容：
应助结果提醒方式：
京公网安备 11010802042870号