Pub Date : 2025-03-01DOI: 10.1016/j.jsse.2024.12.004
William P. Schonberg , Michael Squire
The goal of the Mars Sample Return–Capture, Containment, and Return System Project is to retrieve samples launched from the Martian surface and return them to Earth for detailed analysis. An important part of this project is the design of the system's micrometeoroid protection system, which protects the Earth Entry System and the collected samples during their journey back to Earth. As mission parameters and the micrometeoroid and orbital debris threat became better understood, the design of the micrometeoroid protection system evolved. A key element used in the shield development process is the ballistic limit equation, which is an equation that is used to determine whether or not a particular structural element or system will end up in a failed state as a result of a specified impact. As the design of the Earth Entry System and the micrometeoroid protection system evolved, a new set of ballistic limit equations was needed to better predict and assess the performance of developing shield system designs in anticipation of possible damage from micrometeoroid and orbital debris particle impacts. This paper provides a summary of how a set of initial BLEs were either extended or modified so that the resulting equations were better suited to new types of target configurations being considered, as well as how additional ballistic limit equations were developed where none previously existed.
{"title":"Iterating on a design – further developments in the evolution of the ballistic limit equations for the Mars Sample Return Project","authors":"William P. Schonberg , Michael Squire","doi":"10.1016/j.jsse.2024.12.004","DOIUrl":"10.1016/j.jsse.2024.12.004","url":null,"abstract":"<div><div>The goal of the Mars Sample Return–Capture, Containment, and Return System Project is to retrieve samples launched from the Martian surface and return them to Earth for detailed analysis. An important part of this project is the design of the system's micrometeoroid protection system, which protects the Earth Entry System and the collected samples during their journey back to Earth. As mission parameters and the micrometeoroid and orbital debris threat became better understood, the design of the micrometeoroid protection system evolved. A key element used in the shield development process is the ballistic limit equation, which is an equation that is used to determine whether or not a particular structural element or system will end up in a failed state as a result of a specified impact. As the design of the Earth Entry System and the micrometeoroid protection system evolved, a new set of ballistic limit equations was needed to better predict and assess the performance of developing shield system designs in anticipation of possible damage from micrometeoroid and orbital debris particle impacts. This paper provides a summary of how a set of initial BLEs were either extended or modified so that the resulting equations were better suited to new types of target configurations being considered, as well as how additional ballistic limit equations were developed where none previously existed.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 119-131"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169687","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.2024.12.001
Tommaso Sgobba
The International Association for the Advancement of Space Safety (IAASS) has identified safety education as a key enhancer of system safety. Space safety design criteria, methods and hazard analyses techniques are not generally taught in depth as part of typical university education; however, both manned and unmanned space programs require familiarity with modern risk-based design techniques and with hazard control approaches. The IAASS Space Safety Academy (ISSA) is being established as the center of excellence in space safety education and professional training. The ISSA mission is to make available basic multidisciplinary knowledge in the field of space safety to aerospace engineering postgraduate and undergraduate students. The key ISSA program is a 10-week in-class certificate program in space safety (1/2 Master) organized in cooperation with major academic institutions in Europe, Americas, and Asia. The ISSA will also provide remote undergraduate level courses in space safety as well as in-class and remote on site and web-based professional training courses in space safety. The article provides an overview of the certificate program and of its multidisciplinary structure.
{"title":"Developing the IAASS Space Safety Academy","authors":"Tommaso Sgobba","doi":"10.1016/j.jsse.2024.12.001","DOIUrl":"10.1016/j.jsse.2024.12.001","url":null,"abstract":"<div><div>The International Association for the Advancement of Space Safety (IAASS) has identified safety education as a key enhancer of system safety. Space safety design criteria, methods and hazard analyses techniques are not generally taught in depth as part of typical university education; however, both manned and unmanned space programs require familiarity with modern risk-based design techniques and with hazard control approaches. The IAASS Space Safety Academy (ISSA) is being established as the center of excellence in space safety education and professional training. The ISSA mission is to make available basic multidisciplinary knowledge in the field of space safety to aerospace engineering postgraduate and undergraduate students. The key ISSA program is a 10-week in-class certificate program in space safety (1/2 Master) organized in cooperation with major academic institutions in Europe, Americas, and Asia. The ISSA will also provide remote undergraduate level courses in space safety as well as in-class and remote on site and web-based professional training courses in space safety. The article provides an overview of the certificate program and of its multidisciplinary structure.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 41-46"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169867","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.2024.09.002
Dora Babocs , Angela Preda , Rowena Christiansen
Compared to lunar missions, Mars missions will pose additional challenges. This includes a longer duration (currently anticipated to take around three years for a return mission), and a hazardous Martian environment with 0.38 Earth gravity, a thin atmosphere, and a weak magnetosphere. These factors contribute to extreme weather conditions, and significant exposure to space radiation. Evacuation to Earth for medical treatment will be impractical, rendering the capability to provide surgical interventions absolutely necessary. This paper is part of an ongoing scoping review of relevant published scientific literature to identify medical conditions that might require operative or non-operative surgical solutions during long-duration spaceflight. In the context of potential future Mars missions, onboard acute conditions, or newly developed chronic diseases (Type 1), and Mars surface/environment-related surgical conditions (Type 2), provide relevant considerations for future mission planning and crew safety. (Type 1) During long-duration spaceflight, exposure to space radiation and microgravity affects every organ system. This may result in a broad range of medical events requiring diverse operative or non-operative surgical interventions. The likelihood of acute life-threatening events (Type 1a.) is increased, and newly developed chronic diseases (Type 1b.) may also occur. If asymptomatic, but untreated, secondary sudden surgical emergencies may result. On reaching Mars (Type 2), reintroduction of partial gravity (0.38 G), flight-related reduced bone mineral density and potential changes in muscle mass, might lead to increased risk of lumbar disc herniations and traumatic injuries such as fractures. Without adequate space radiation shielding, surface conditions will likely increase the risk for development of malignancies and eye diseases such as cataracts. Communication delays (as long as 24 min each way) will require any immediate medical emergency to be managed in-situ by the expeditioners. Remotely operated robotic surgery is not currently feasible, as any communication lag >100 ms will cause a perceptible delay, potentially affecting surgical outcomes. The provision of healthcare for Mars missions will face unique challenges in terms of both a hostile and extreme environment, and a remote and isolated location without real-time Earth communication. The medical team will need to be equipped to manage a very wide range of health conditions, including low acuity, chronic, and high acuity life-threatening issues, with some potentially requiring surgical intervention. Issues for the treating team include appropriate skill sets and access to medical guidance, facilities, equipment and supplies, and available pharmaceuticals. These significant challenges underlie the importance of adequate anticipation, preparation and planning for the healthcare needs of Mars explorers.
{"title":"Reaching Mars: Medical risks and potential surgical conditions in the Martian environment and during long-duration spaceflight","authors":"Dora Babocs , Angela Preda , Rowena Christiansen","doi":"10.1016/j.jsse.2024.09.002","DOIUrl":"10.1016/j.jsse.2024.09.002","url":null,"abstract":"<div><div>Compared to lunar missions, Mars missions will pose additional challenges. This includes a longer duration (currently anticipated to take around three years for a return mission), and a hazardous Martian environment with 0.38 Earth gravity, a thin atmosphere, and a weak magnetosphere. These factors contribute to extreme weather conditions, and significant exposure to space radiation. Evacuation to Earth for medical treatment will be impractical, rendering the capability to provide surgical interventions absolutely necessary. This paper is part of an ongoing scoping review of relevant published scientific literature to identify medical conditions that might require operative or non-operative surgical solutions during long-duration spaceflight. In the context of potential future Mars missions, onboard acute conditions, or newly developed chronic diseases (Type 1), and Mars surface/environment-related surgical conditions (Type 2), provide relevant considerations for future mission planning and crew safety. (Type 1) During long-duration spaceflight, exposure to space radiation and microgravity affects every organ system. This may result in a broad range of medical events requiring diverse operative or non-operative surgical interventions. The likelihood of acute life-threatening events (Type 1a.) is increased, and newly developed chronic diseases (Type 1b.) may also occur. If asymptomatic, but untreated, secondary sudden surgical emergencies may result. On reaching Mars (Type 2), reintroduction of partial gravity (0.38 G), flight-related reduced bone mineral density and potential changes in muscle mass, might lead to increased risk of lumbar disc herniations and traumatic injuries such as fractures. Without adequate space radiation shielding, surface conditions will likely increase the risk for development of malignancies and eye diseases such as cataracts. Communication delays (as long as 24 min each way) will require any immediate medical emergency to be managed in-situ by the expeditioners. Remotely operated robotic surgery is not currently feasible, as any communication lag >100 ms will cause a perceptible delay, potentially affecting surgical outcomes. The provision of healthcare for Mars missions will face unique challenges in terms of both a hostile and extreme environment, and a remote and isolated location without real-time Earth communication. The medical team will need to be equipped to manage a very wide range of health conditions, including low acuity, chronic, and high acuity life-threatening issues, with some potentially requiring surgical intervention. Issues for the treating team include appropriate skill sets and access to medical guidance, facilities, equipment and supplies, and available pharmaceuticals. These significant challenges underlie the importance of adequate anticipation, preparation and planning for the healthcare needs of Mars explorers.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 239-245"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169574","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.2025.02.008
Ryui Hara, Yasuhiro Yoshimura, Toshiya Hanada
The rapid growth of resident space objects in Earth’s orbit has intensified the need for advanced space situational awareness and space domain awareness to manage satellite traffic and prevent collisions. Attitude estimation is critical for accurate state propagation, as non-gravitational forces like solar radiation pressure and atmospheric drag depend on the object’s attitude. This study explores using light curves, time variation of an object’s brightness, to estimate a space object’s attitude. Light curve inversion, traditionally used in astronomy, faces challenges when applied to resident space objects due to their non-convex shapes and specular reflections. Conventional methods for attitude estimation often assume known shape and surface parameters, which are usually unknown for space debris generated by a collision or breakup. To address this issue, this study proposes the estimation method combining Gaussian process regression with the unscented Kalman filter. This study uses Gaussian process regression for a non-parametric observation model, enhancing robustness against unknown surface parameters. Numerical examples consider a box-wing object in a geosynchronous orbit and demonstrate that the proposed method has better estimation accuracy than a conventional unscented Kalman filter. The numerical simulation results also represent the attitude estimation robust against uncertainties in surface properties, contributing to practical scenarios in space situational awareness and space domain awareness where the object parameters are unknown.
{"title":"Attitude estimation from photometric data using Gaussian process regression","authors":"Ryui Hara, Yasuhiro Yoshimura, Toshiya Hanada","doi":"10.1016/j.jsse.2025.02.008","DOIUrl":"10.1016/j.jsse.2025.02.008","url":null,"abstract":"<div><div>The rapid growth of resident space objects in Earth’s orbit has intensified the need for advanced space situational awareness and space domain awareness to manage satellite traffic and prevent collisions. Attitude estimation is critical for accurate state propagation, as non-gravitational forces like solar radiation pressure and atmospheric drag depend on the object’s attitude. This study explores using light curves, time variation of an object’s brightness, to estimate a space object’s attitude. Light curve inversion, traditionally used in astronomy, faces challenges when applied to resident space objects due to their non-convex shapes and specular reflections. Conventional methods for attitude estimation often assume known shape and surface parameters, which are usually unknown for space debris generated by a collision or breakup. To address this issue, this study proposes the estimation method combining Gaussian process regression with the unscented Kalman filter. This study uses Gaussian process regression for a non-parametric observation model, enhancing robustness against unknown surface parameters. Numerical examples consider a box-wing object in a geosynchronous orbit and demonstrate that the proposed method has better estimation accuracy than a conventional unscented Kalman filter. The numerical simulation results also represent the attitude estimation robust against uncertainties in surface properties, contributing to practical scenarios in space situational awareness and space domain awareness where the object parameters are unknown.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 227-238"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169696","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.2025.03.001
Paul Kirkpatrick
The International Association for the Advancement of Space Safety (IAASS) offers a myriad of courses to educate the space community on safety engineering concepts and accepted best practices. Space safety concepts and methodologies are critical for the safety of occupants and the uninvolved public, alike, yet are not standard contents in academic programs for space science. The IAASS considers the education of the workforce among its core goals and fulfills that mission through the IAASS training academy.
{"title":"Professional technical training: Educating the professional community on space safety best practices","authors":"Paul Kirkpatrick","doi":"10.1016/j.jsse.2025.03.001","DOIUrl":"10.1016/j.jsse.2025.03.001","url":null,"abstract":"<div><div>The International Association for the Advancement of Space Safety (IAASS) offers a myriad of courses to educate the space community on safety engineering concepts and accepted best practices. Space safety concepts and methodologies are critical for the safety of occupants and the uninvolved public, alike, yet are not standard contents in academic programs for space science. The IAASS considers the education of the workforce among its core goals and fulfills that mission through the IAASS training academy.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 37-40"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169857","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}
JAXA develops the Object Re-entry Survival Analysis Tool - Japan (ORSAT-J), which is a tool to assess the survivability and risk to the ground of objects re-entering from low Earth orbit. This tool is derived from NASA's ORSAT ver. 4.
ORSAT-J can calculate the temperature of an entering object during its entry into a celestial body with respect to the elapsed time. Therefore, in terms of planetary protection, it could be used to evaluate whether aerodynamic heating during celestial entry is sufficient for sterilization in the event of an Earth-derived spacecraft entering into a celestial body due to an accidental event. JAXA plans some Martian biosphere exploration missions such as the MMX mission, and is aiming to build a tool that can easily analyse the aerodynamic heating during Mars entry.
In this paper, we collected and evaluated the information such as celestial geometry, gravity model, atmospheric model, radiative heating, etc. necessary to perform a Mars entry heating analysis with ORSAT-J. These were applied to the code and compared with the measured data of Schiaparelli of the ExoMars Program. The novelty of this paper is that it introduces a comprehensive analysis method for Mars entry, including trajectory and heating simulations, into a simplified survivability analysis tool for the on-ground risk of re-entry into Earth.
{"title":"Application of Re-entry survivability analysis tool to mars planetary protection","authors":"Kenichi Sato , Tsutomu Matsumoto , Takashi Ozawa , Toru Yoshihara , Kazuko Hagiwara , Satoshi Kobayashi","doi":"10.1016/j.jsse.2025.02.005","DOIUrl":"10.1016/j.jsse.2025.02.005","url":null,"abstract":"<div><div>JAXA develops the Object <em>Re</em>-entry Survival Analysis Tool - Japan (ORSAT-J), which is a tool to assess the survivability and risk to the ground of objects re-entering from low Earth orbit. This tool is derived from NASA's ORSAT ver. 4.</div><div>ORSAT-J can calculate the temperature of an entering object during its entry into a celestial body with respect to the elapsed time. Therefore, in terms of planetary protection, it could be used to evaluate whether aerodynamic heating during celestial entry is sufficient for sterilization in the event of an Earth-derived spacecraft entering into a celestial body due to an accidental event. JAXA plans some Martian biosphere exploration missions such as the MMX mission, and is aiming to build a tool that can easily analyse the aerodynamic heating during Mars entry.</div><div>In this paper, we collected and evaluated the information such as celestial geometry, gravity model, atmospheric model, radiative heating, etc. necessary to perform a Mars entry heating analysis with ORSAT-J. These were applied to the code and compared with the measured data of Schiaparelli of the ExoMars Program. The novelty of this paper is that it introduces a comprehensive analysis method for Mars entry, including trajectory and heating simulations, into a simplified survivability analysis tool for the on-ground risk of re-entry into Earth.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 206-216"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169859","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.2024.07.007
Mike Gruntman
The Department of Astronautical Engineering at the University of Southern California (USC) focuses on space engineering education. It is a unique space-engineering program in the United States where such studies usually constitute parts of aerospace departments. In addition to full-time on-campus students, its flagship Master of Science in Astronautical Engineering degree program reaches working professionals online through distance education. The growth of this space-focused graduate degree program led to the establishment of a new independent department at USC twenty years ago in 2004. Since its founding, this Department of Astronautical Engineering awarded nearly one thousand Master's degrees to students from across the United States, Canada, and selected locations abroad. The article describes the origin, rationale, focus, structure, coursework, and reach of USC's Master of Science in Astronautical Engineering program. It concludes with the lessons learned in program development which contributed to its success.
{"title":"Master of Science in Astronautical Engineering degree at the University of Southern California for the space industry","authors":"Mike Gruntman","doi":"10.1016/j.jsse.2024.07.007","DOIUrl":"10.1016/j.jsse.2024.07.007","url":null,"abstract":"<div><div>The Department of Astronautical Engineering at the University of Southern California (USC) focuses on space engineering education. It is a unique space-engineering program in the United States where such studies usually constitute parts of aerospace departments. In addition to full-time on-campus students, its flagship Master of Science in Astronautical Engineering degree program reaches working professionals online through distance education. The growth of this space-focused graduate degree program led to the establishment of a new independent department at USC twenty years ago in 2004. Since its founding, this Department of Astronautical Engineering awarded nearly one thousand Master's degrees to students from across the United States, Canada, and selected locations abroad. The article describes the origin, rationale, focus, structure, coursework, and reach of USC's Master of Science in Astronautical Engineering program. It concludes with the lessons learned in program development which contributed to its success.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 1-11"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169863","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.2025.02.003
F. Pasciuti, G. Acampa, M. Cinque, W. Dai, G.T. Kuthukallumkal, A. Scolaro, R. Armellini
Current trends in the Space Industry show that launcher providers are moving towards the automatization of Flight Termination Systems (AFTS). Nevertheless, nowadays a problem arises when trying to conceive an AFTS which can be compliant with all the relevant international safety regulations.
A previous study [12], starting from differences existing among those legislations that more explicitly refer to Flight Termination Systems, has identified and highlighted the key needs and concepts an AFTS should fulfill.
Therefore, starting from the proposed regulatory guideline, a further step is moved hereinafter for building up a set of generic (not mission dependent) requirements matching with the above-mentioned needs and concepts.
The resulting requirements here proposed are meant to be set as a starting point for the agreement, among industries and safety authorities, on a common specification for developing an AFTS suitable to all launch sites, with greater range of mission trajectories and cadences allowed.
{"title":"Autonomous flight termination system: A proposal for an international regulatory frame and set of requirements","authors":"F. Pasciuti, G. Acampa, M. Cinque, W. Dai, G.T. Kuthukallumkal, A. Scolaro, R. Armellini","doi":"10.1016/j.jsse.2025.02.003","DOIUrl":"10.1016/j.jsse.2025.02.003","url":null,"abstract":"<div><div>Current trends in the Space Industry show that launcher providers are moving towards the automatization of Flight Termination Systems (AFTS). Nevertheless, nowadays a problem arises when trying to conceive an AFTS which can be compliant with all the relevant international safety regulations.</div><div>A previous study [<span><span>12</span></span>], starting from differences existing among those legislations that more explicitly refer to Flight Termination Systems, has identified and highlighted the key needs and concepts an AFTS should fulfill.</div><div>Therefore, starting from the proposed regulatory guideline, a further step is moved hereinafter for building up a set of generic (not mission dependent) requirements matching with the above-mentioned needs and concepts.</div><div>The resulting requirements here proposed are meant to be set as a starting point for the agreement, among industries and safety authorities, on a common specification for developing an AFTS suitable to all launch sites, with greater range of mission trajectories and cadences allowed.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 76-82"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169683","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.2024.11.004
Kenneth Iluore , Jianyong Lu , Kesyton Oyamenda Ozegin
Predictions of the ionosphere are essential for detecting anomalies in space weather conditions. Deep learning technologies applied to ionospheric forecasting have emerged as an exciting field of focus for researchers. This paper presents the forecasting of GPS-VTEC using multilayer perceptron (MLP) and the deep learning model: long short-term memory (LSTM), gated recurrent unit (GRU), and a hybrid model composed of LSTM and a convolutional neural network (CNN). The MLP and the deep learning model are constructed with the GPS-vertical total electron content (GPS-VTEC) time series data estimated over a mid-latitude HUGE Station () located in Germany. Factors that influence the variations of GPS-VTEC are identified and used as the input parameters for the deep learning model. The factors are seasonal variation, diurnal variation, magnetic activity, and solar activity. The training is carried out using the data obtained from the years 2010–2014, while the prediction performance of the model is evaluated using the data from the year 2015 (high solar activity). The hybrid LSTM-CNN model performs better than the MLP and the other deep learning model, with a root mean square error (RMSE) of 3.046 total electron content unit (TECU) and a correlation coefficient (R) of 0.896 and is able to capture the diurnal variations of the GPS-VTEC. In addition, the prediction performance of the MLP and the deep learning model is compared with that of IRI-Plas 2017 and NeQuick-2 in capturing the seasonal variation of GPS-VTEC, and it is observed that the IRI-Plas 2017 model provides more accurate predictions than the MLP, the deep learning model, and the NeQuick-2 model during March 2015. However, on average, the deep learning model, the MLP, and the NeQuick-2 model capture the seasonal variations more accurately than the IRI-Plas 2017 at this GPS station.
{"title":"Ionospheric GPS-VTEC forecasting using hybrid deep learning model (LSTM-CNN)","authors":"Kenneth Iluore , Jianyong Lu , Kesyton Oyamenda Ozegin","doi":"10.1016/j.jsse.2024.11.004","DOIUrl":"10.1016/j.jsse.2024.11.004","url":null,"abstract":"<div><div>Predictions of the ionosphere are essential for detecting anomalies in space weather conditions. Deep learning technologies applied to ionospheric forecasting have emerged as an exciting field of focus for researchers. This paper presents the forecasting of GPS-VTEC using multilayer perceptron (MLP) and the deep learning model: long short-term memory (LSTM), gated recurrent unit (GRU), and a hybrid model composed of LSTM and a convolutional neural network (CNN). The MLP and the deep learning model are constructed with the GPS-vertical total electron content (GPS-VTEC) time series data estimated over a mid-latitude HUGE Station (<span><math><mrow><msup><mrow><mn>47.834</mn></mrow><mi>o</mi></msup><mspace></mspace><mi>N</mi><mo>,</mo><mspace></mspace><msup><mrow><mn>7.596</mn></mrow><mi>o</mi></msup><mi>E</mi></mrow></math></span>) located in Germany. Factors that influence the variations of GPS-VTEC are identified and used as the input parameters for the deep learning model. The factors are seasonal variation, diurnal variation, magnetic activity, and solar activity. The training is carried out using the data obtained from the years 2010–2014, while the prediction performance of the model is evaluated using the data from the year 2015 (high solar activity). The hybrid LSTM-CNN model performs better than the MLP and the other deep learning model, with a root mean square error (RMSE) of 3.046 total electron content unit (TECU) and a correlation coefficient (<em>R</em>) of 0.896 and is able to capture the diurnal variations of the GPS-VTEC. In addition, the prediction performance of the MLP and the deep learning model is compared with that of IRI-Plas 2017 and NeQuick-2 in capturing the seasonal variation of GPS-VTEC, and it is observed that the IRI-Plas 2017 model provides more accurate predictions than the MLP, the deep learning model, and the NeQuick-2 model during March 2015. However, on average, the deep learning model, the MLP, and the NeQuick-2 model capture the seasonal variations more accurately than the IRI-Plas 2017 at this GPS station.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 83-93"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169684","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}
The grave danger posed by space debris is attracting increasing attention, and many countries are actively researching active debris removal (ADR). One of the most important challenges to an ADR mission is the need for a highly accurate, robust navigation technology for docking with non-cooperative targets. This paper proposes a LiDAR-based navigation system, in particular a point cloud processing architecture that is robust against point cloud outliers that may occur in real environments. This study selected the upper stage of an H2A rocket as an example for ADR target. The proposed method addresses technical issues specific to ADR missions, such as point cloud loss at the target’s mirror surface and LiDAR’s Field of View (FOV) limitations. The results of dynamic and static measurement testing using actual hardware showed that the proposed method is capable of stable estimation in close proximity operation.
{"title":"LiDAR-Based navigation strategies for a non-cooperative target considering rendezvous trajectory","authors":"Taisei Nishishita, Yu Nakajima, Takahiro Sasaki, Hiroyuki Okamoto, Ryo Nakamura","doi":"10.1016/j.jsse.2025.02.010","DOIUrl":"10.1016/j.jsse.2025.02.010","url":null,"abstract":"<div><div>The grave danger posed by space debris is attracting increasing attention, and many countries are actively researching active debris removal (ADR). One of the most important challenges to an ADR mission is the need for a highly accurate, robust navigation technology for docking with non-cooperative targets. This paper proposes a LiDAR-based navigation system, in particular a point cloud processing architecture that is robust against point cloud outliers that may occur in real environments. This study selected the upper stage of an H2A rocket as an example for ADR target. The proposed method addresses technical issues specific to ADR missions, such as point cloud loss at the target’s mirror surface and LiDAR’s Field of View (FOV) limitations. The results of dynamic and static measurement testing using actual hardware showed that the proposed method is capable of stable estimation in close proximity operation.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"12 1","pages":"Pages 217-226"},"PeriodicalIF":1.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169695","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}
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