Pub Date : 2023-03-04DOI: 10.1109/AERO55745.2023.10115821
Edward A. S. Hanlon, O. Yakimenko
The United States military recognizes the threat of adversary anti-satellite weapons and has aggressively pursued new system architectures to minimize their potency. Hardening and removing military targets will shift the anti-satellite threat to equally important commercial satellites. Much like commercial shipping in World War II, civilian spacecraft require protection from the same attacks military space architectures are being fortified against. This paper uses Model-based Systems Engineering to explore defensive architectures' ability to protect commercial satellites against both co-orbital and ground launched kinetic attacks. It focuses on a comprehensive analysis of space domain awareness, evasive maneuvers, devices, and co-orbital ‘escort’ spacecraft, to provide a framework for designers and engineers to evaluate and improve spacecraft survivability. Ultimately, it highlights the value of early, decisive action; the efficacy of evasive maneuvers at thwarting series attacks; and the impact of high quality space domain awareness data.
{"title":"Hardening Civilian Spacecraft Against Kinetic Attack through Model-Based Systems Engineering","authors":"Edward A. S. Hanlon, O. Yakimenko","doi":"10.1109/AERO55745.2023.10115821","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115821","url":null,"abstract":"The United States military recognizes the threat of adversary anti-satellite weapons and has aggressively pursued new system architectures to minimize their potency. Hardening and removing military targets will shift the anti-satellite threat to equally important commercial satellites. Much like commercial shipping in World War II, civilian spacecraft require protection from the same attacks military space architectures are being fortified against. This paper uses Model-based Systems Engineering to explore defensive architectures' ability to protect commercial satellites against both co-orbital and ground launched kinetic attacks. It focuses on a comprehensive analysis of space domain awareness, evasive maneuvers, devices, and co-orbital ‘escort’ spacecraft, to provide a framework for designers and engineers to evaluate and improve spacecraft survivability. Ultimately, it highlights the value of early, decisive action; the efficacy of evasive maneuvers at thwarting series attacks; and the impact of high quality space domain awareness data.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133772972","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115737
Behzad Koosha, Rob Singh, C. Sanders, J. Spicer, Ta Ratana, Robert Conrad
In Fall 2021, SpaceLink Corporation was selected by the Center for the Advancement of Science in Space (CASIS), manager of the International Space Station (ISS) U.S. National Laboratory, for a demonstration of its end-to-end space data relay service. SpaceLink will provide secure, continuous communications between terrestrial operators and an optical terminal on the ISS, enabling real-time, high-throughput connectivity for the onboard crew, systems, and various science experiments. In a highly competitive process, made available for companies and research teams to propose technology development concepts operating in Low Earth Orbit (LEO), CASIS selected the SpaceLink concept. With this selection, SpaceLink will advance its flight project in collaboration with the ISS National Laboratory. The SpaceLink relay network will succeed and exceed NASA's Tracking and Data Relay Satellite System (TDRSS) with unprecedented capacity that leverages the latest optical communications technology advances. Demand for high-throughput, continuous orbital connectivity continues to grow with the ongoing proliferation of LEO satellites. SpaceLink's network is designed to help close the business case for Earth observation companies, commercial space stations, satellite services, launch vehicles, and space tugs. It also meets the requirements of the U.S. Government and close allies that are leveraging real-time, secure communications solutions. The SpaceLink ISS demonstration will validate a 10 Gigabit per second (Gbps) optical terminal communication link for real-time voice, video, and data relay for the ISS. Axiom Space, SpaceLink's implementation partner, will leverage its expertise in working with NASA and the ISS National Laboratory to support the SpaceLink payload mission integration, launch, and operations. Axiom will support SpaceLink as a liaison with NASA and will lead safety reviews to ensure SpaceLink hardware meets all ISS requirements. The SpaceLink-ISS Connectivity End to End Demonstration (SLICED) will demonstrate the highest data rates that can be achieved between SpaceLink relay spacecraft in Medium Earth Orbit (MEO) and the ISS, an example user satellite in LEO. The demonstration will include MEO-LEO edge case geometries where the relative range rates between the satellites are the highest and required contact acquisition times are shortest. SpaceLink's real-time gigabit user data rates are possible via optical inter-satellite communications between spacecraft, as well as high-bandwidth QN-band communications between SpaceLink's relay spacecraft and terrestrial gateways. SpaceLink has designed an innovative system architecture, implementing high-security services and continuous availability so that satellite data is available in real time when it matters the most. This study will discuss the technical foundation behind SpaceLink's ISS demonstration infrastructure.
{"title":"SpaceLink-ISS Connectivity End-to-End Demonstration (SLICED)","authors":"Behzad Koosha, Rob Singh, C. Sanders, J. Spicer, Ta Ratana, Robert Conrad","doi":"10.1109/AERO55745.2023.10115737","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115737","url":null,"abstract":"In Fall 2021, SpaceLink Corporation was selected by the Center for the Advancement of Science in Space (CASIS), manager of the International Space Station (ISS) U.S. National Laboratory, for a demonstration of its end-to-end space data relay service. SpaceLink will provide secure, continuous communications between terrestrial operators and an optical terminal on the ISS, enabling real-time, high-throughput connectivity for the onboard crew, systems, and various science experiments. In a highly competitive process, made available for companies and research teams to propose technology development concepts operating in Low Earth Orbit (LEO), CASIS selected the SpaceLink concept. With this selection, SpaceLink will advance its flight project in collaboration with the ISS National Laboratory. The SpaceLink relay network will succeed and exceed NASA's Tracking and Data Relay Satellite System (TDRSS) with unprecedented capacity that leverages the latest optical communications technology advances. Demand for high-throughput, continuous orbital connectivity continues to grow with the ongoing proliferation of LEO satellites. SpaceLink's network is designed to help close the business case for Earth observation companies, commercial space stations, satellite services, launch vehicles, and space tugs. It also meets the requirements of the U.S. Government and close allies that are leveraging real-time, secure communications solutions. The SpaceLink ISS demonstration will validate a 10 Gigabit per second (Gbps) optical terminal communication link for real-time voice, video, and data relay for the ISS. Axiom Space, SpaceLink's implementation partner, will leverage its expertise in working with NASA and the ISS National Laboratory to support the SpaceLink payload mission integration, launch, and operations. Axiom will support SpaceLink as a liaison with NASA and will lead safety reviews to ensure SpaceLink hardware meets all ISS requirements. The SpaceLink-ISS Connectivity End to End Demonstration (SLICED) will demonstrate the highest data rates that can be achieved between SpaceLink relay spacecraft in Medium Earth Orbit (MEO) and the ISS, an example user satellite in LEO. The demonstration will include MEO-LEO edge case geometries where the relative range rates between the satellites are the highest and required contact acquisition times are shortest. SpaceLink's real-time gigabit user data rates are possible via optical inter-satellite communications between spacecraft, as well as high-bandwidth QN-band communications between SpaceLink's relay spacecraft and terrestrial gateways. SpaceLink has designed an innovative system architecture, implementing high-security services and continuous availability so that satellite data is available in real time when it matters the most. This study will discuss the technical foundation behind SpaceLink's ISS demonstration infrastructure.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"364 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115184042","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115690
Nicholas Hennigan, Jonathan Reynolds, Kevin Hefner, Kyle Guerre, A. Stoica
This paper presents subsystem prototypes and tests of a novel design architecture to autonomously inflate and launch high altitude balloons (HABs). Three core subsystems were previously tested at reduced scale utilizing a 350-gram balloon; this paper test these subsystems at full scale, in the field, utilizing a full-scale, 1500-gram balloon. A first subsystem, the Balloon Capsule is a rigid container that utilizes a novel packing technique, allowing a latex balloon to be safely transported. Internal geometry of the capsule passively controls slack of the balloon during inflation. A second subsystem, the Helium Engagement and Locking System (HEL), oversees connecting the helium supply, locking the balloon in place, sensing lift values, and launching the balloon. A third subsystem, the Balloon Inflation Barrier (BiB), supports the balloon during inflation and prevents excessive deflection during high winds. Results from full scale compressed air testing showcased a need for a neoprene based internal retention mesh for the Balloon Capsule. Both the HEL and BiB performed satisfactorily. Helium tests concluded the Balloon Capsule performed as designed in light winds and failed at medium winds due to the excessive unreeling of balloon slack. The HEL system was actuated manually and successfully locked, inflated, and released a full scale 1500- gram balloon with lift values exceeding 2.26 kg. The BiB performed as expected when balloons were fully inflated, however, during inflation, BiB's failed at high winds due to structure buckling and excessive balloon slack. The full scale autolauncher prototype weighs less than 11 kg and is 1.2 m long, 1.2 m wide, and 1.1 m tall. This design allows one person to inflate and launch a balloon in under 30 mins. Critical elements of future work include the refinement of BiB structure, the automation of the HEL system, and implementation of the helium gas control logic; and the design of balloon payload storage system.
{"title":"Full-Scale Testing of Portable and Automatic High Altitude Balloon Launching Platform","authors":"Nicholas Hennigan, Jonathan Reynolds, Kevin Hefner, Kyle Guerre, A. Stoica","doi":"10.1109/AERO55745.2023.10115690","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115690","url":null,"abstract":"This paper presents subsystem prototypes and tests of a novel design architecture to autonomously inflate and launch high altitude balloons (HABs). Three core subsystems were previously tested at reduced scale utilizing a 350-gram balloon; this paper test these subsystems at full scale, in the field, utilizing a full-scale, 1500-gram balloon. A first subsystem, the Balloon Capsule is a rigid container that utilizes a novel packing technique, allowing a latex balloon to be safely transported. Internal geometry of the capsule passively controls slack of the balloon during inflation. A second subsystem, the Helium Engagement and Locking System (HEL), oversees connecting the helium supply, locking the balloon in place, sensing lift values, and launching the balloon. A third subsystem, the Balloon Inflation Barrier (BiB), supports the balloon during inflation and prevents excessive deflection during high winds. Results from full scale compressed air testing showcased a need for a neoprene based internal retention mesh for the Balloon Capsule. Both the HEL and BiB performed satisfactorily. Helium tests concluded the Balloon Capsule performed as designed in light winds and failed at medium winds due to the excessive unreeling of balloon slack. The HEL system was actuated manually and successfully locked, inflated, and released a full scale 1500- gram balloon with lift values exceeding 2.26 kg. The BiB performed as expected when balloons were fully inflated, however, during inflation, BiB's failed at high winds due to structure buckling and excessive balloon slack. The full scale autolauncher prototype weighs less than 11 kg and is 1.2 m long, 1.2 m wide, and 1.1 m tall. This design allows one person to inflate and launch a balloon in under 30 mins. Critical elements of future work include the refinement of BiB structure, the automation of the HEL system, and implementation of the helium gas control logic; and the design of balloon payload storage system.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"200 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115719924","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115704
K. Pham
The phenomenal growth of critical infrastructures has brought about increasing reliance on global navigation satellite systems (GNSS) for everyday positioning and timing operations. Meanwhile, due to their low power levels, GNSS signals are very susceptible to radio frequency interferences (RFIs) from intentional and unintentional sources. To address these issues, detection, localization, and elimination of interferences to GNSS are of paramount importance. This paper presents an analytical framework of GNSS environmental monitoring from the perspective of optimization problems dealing with selecting, at each epoch of time, one measurement provided by one out of many spatially distributed sensors from the area of responsibility. Specifically, RFIs are monitored using multisensory hy-bridization and cost-aware provision of observation resources. Potential benefits for selecting an optimal measurement policy during a fixed time interval, are discussed with the view to a weighted combination of prediction accuracy and accumulated observation cost being optimized. As reported from the findings, the indepth analysis of the GNSS environmental monitoring system as proposed herein, is limited to the class of linear stochastic dynamic systems and measurement subsystems.
{"title":"Radio Frequency Interference Situational Awareness: A Control- Theoretic Sensor Fusion and Policy Approach","authors":"K. Pham","doi":"10.1109/AERO55745.2023.10115704","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115704","url":null,"abstract":"The phenomenal growth of critical infrastructures has brought about increasing reliance on global navigation satellite systems (GNSS) for everyday positioning and timing operations. Meanwhile, due to their low power levels, GNSS signals are very susceptible to radio frequency interferences (RFIs) from intentional and unintentional sources. To address these issues, detection, localization, and elimination of interferences to GNSS are of paramount importance. This paper presents an analytical framework of GNSS environmental monitoring from the perspective of optimization problems dealing with selecting, at each epoch of time, one measurement provided by one out of many spatially distributed sensors from the area of responsibility. Specifically, RFIs are monitored using multisensory hy-bridization and cost-aware provision of observation resources. Potential benefits for selecting an optimal measurement policy during a fixed time interval, are discussed with the view to a weighted combination of prediction accuracy and accumulated observation cost being optimized. As reported from the findings, the indepth analysis of the GNSS environmental monitoring system as proposed herein, is limited to the class of linear stochastic dynamic systems and measurement subsystems.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"98 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115786919","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115614
Willem Jordaan, G. Serfontein, Irvin Deaan Swart, Lourens Visagie, Jonathan Lun
This project involves a 2U and 1U CubeSat that are launched together. The CubeSats are initially attached using a novel docking mechanism. The CubeSats will separate after being released from the deployer followed by rendezvous and re-docking maneuvers with one another. Multiple undocking and re-docking demonstrations will be attempted, with increasing separation distance between the satellites at each iteration. Docking demonstrations will commence once the joined satel-lites have deployed from the CubeSat deployer, and both chaser and target have been fully commissioned. Both the 1U target and the 2U chaser will have a docking interface. An undocking and re-docking experiment will involve an initial satellite release by the docking adapters. Initial relative velocity will be imparted by a combination of spring force and electromagnets. An electric thruster on the 2U satellite will bring the satellites closer together, while visual-based pose estimation will provide feedback for the control system. The 1U satellite will maintain a stable attitude while the rendezvous and proximity operations are taking place. The final close approach and docking will be assisted by electromagnets built into the docking system on each satellite. The projects primary goal is to demonstrate critical technolo-gies for reconfigurable satellites and in-orbit servicing. The technologies that will be demonstrated include vision-based pose estimation and navigation, modular and dynamic reconfigurable spacecraft, and trajectory planning with electric thrusters. In addition, the project has the objective of establishing a sus-tainable CubeSat program at Stellenbosch University, through which post-graduate students can gain experience in satellite design and integration. In this paper, we include the conceptual design of the mission including the definition of the major subsystems, mass budget as well as simulations of the undock and re-dock demonstration to show the mission feasibility. Three components required for the mission have been identified that require the most additional research and development. The docking mechanism is designed to be androgynous with servo-actuated latches and a vision system for multiple separations and docking procedures. Elec-tromagnets are also added to the mechanism and the behavior is modeled for initial separation and final close-proximity control. Additionally, a practical statistical model of the proposed elec-tric thruster is constructed and used in simulation to obtain an expectation of the chasers trajectory tracking performance.
{"title":"Miniaturizing Docking and Undocking through DockSat","authors":"Willem Jordaan, G. Serfontein, Irvin Deaan Swart, Lourens Visagie, Jonathan Lun","doi":"10.1109/AERO55745.2023.10115614","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115614","url":null,"abstract":"This project involves a 2U and 1U CubeSat that are launched together. The CubeSats are initially attached using a novel docking mechanism. The CubeSats will separate after being released from the deployer followed by rendezvous and re-docking maneuvers with one another. Multiple undocking and re-docking demonstrations will be attempted, with increasing separation distance between the satellites at each iteration. Docking demonstrations will commence once the joined satel-lites have deployed from the CubeSat deployer, and both chaser and target have been fully commissioned. Both the 1U target and the 2U chaser will have a docking interface. An undocking and re-docking experiment will involve an initial satellite release by the docking adapters. Initial relative velocity will be imparted by a combination of spring force and electromagnets. An electric thruster on the 2U satellite will bring the satellites closer together, while visual-based pose estimation will provide feedback for the control system. The 1U satellite will maintain a stable attitude while the rendezvous and proximity operations are taking place. The final close approach and docking will be assisted by electromagnets built into the docking system on each satellite. The projects primary goal is to demonstrate critical technolo-gies for reconfigurable satellites and in-orbit servicing. The technologies that will be demonstrated include vision-based pose estimation and navigation, modular and dynamic reconfigurable spacecraft, and trajectory planning with electric thrusters. In addition, the project has the objective of establishing a sus-tainable CubeSat program at Stellenbosch University, through which post-graduate students can gain experience in satellite design and integration. In this paper, we include the conceptual design of the mission including the definition of the major subsystems, mass budget as well as simulations of the undock and re-dock demonstration to show the mission feasibility. Three components required for the mission have been identified that require the most additional research and development. The docking mechanism is designed to be androgynous with servo-actuated latches and a vision system for multiple separations and docking procedures. Elec-tromagnets are also added to the mechanism and the behavior is modeled for initial separation and final close-proximity control. Additionally, a practical statistical model of the proposed elec-tric thruster is constructed and used in simulation to obtain an expectation of the chasers trajectory tracking performance.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124579313","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115663
T. Hoffman, C. Lawler, M. Lysek, A. Murray, Pavani Peddada, M. Rokey, M. Vaquero, A. Mainzer, Jason J. Andersen, Timothy Sayer, M. Veto
The Near-Earth Object Surveyor (NEOS) is currently undergoing preliminary design activities and preparing to enter the detailed design phase of the project. NEO Surveyor is to designed to detect, categorize and characterize NEOs using infrared imaging. The NEOS project responds to National Research Council's report Defending Planet Earth: Near-Earth Object Surveys & Hazard Mitigation Strategies (2010), the U. S. National Near-Earth Object Preparedness Strategy and Action Plan (June 2018), and the objectives of NASA's Planetary Defense Coordination Office (PDCO). The project was identified as a high priority project in the recent NASA Authorization Act. The goals of the NEOS project are to: (1) identify impact hazards to the Earth posed by NEOs (both asteroids and comets) by performing a comprehensive survey of the NEO population; (2) obtain detailed physical characterization data for individual objects that are likely to pose an impact hazard; (3) characterize the entire population of potentially hazardous NEOs to inform potential mitigation strategies by assisting the determination of impact energies through accurate object size determination and physical properties. The mission will make significant progress toward the George E. Brown, Jr. NEO Survey Program objective of detecting, tracking, cataloging, and characterizing at least 90% of NEOs equal to or larger than 140 m in diameter. The project is a collaboration between NASA-JPL, the University of Arizona and industry, with Ball Aerospace notably providing the spacecraft and key instrument elements. This paper will describe the key activities and accomplishments performed by the NEOS Project during the preliminary design phase and describe how these have matured the overall mission.
{"title":"Near-Earth Object Surveyor Project Preliminary Design","authors":"T. Hoffman, C. Lawler, M. Lysek, A. Murray, Pavani Peddada, M. Rokey, M. Vaquero, A. Mainzer, Jason J. Andersen, Timothy Sayer, M. Veto","doi":"10.1109/AERO55745.2023.10115663","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115663","url":null,"abstract":"The Near-Earth Object Surveyor (NEOS) is currently undergoing preliminary design activities and preparing to enter the detailed design phase of the project. NEO Surveyor is to designed to detect, categorize and characterize NEOs using infrared imaging. The NEOS project responds to National Research Council's report Defending Planet Earth: Near-Earth Object Surveys & Hazard Mitigation Strategies (2010), the U. S. National Near-Earth Object Preparedness Strategy and Action Plan (June 2018), and the objectives of NASA's Planetary Defense Coordination Office (PDCO). The project was identified as a high priority project in the recent NASA Authorization Act. The goals of the NEOS project are to: (1) identify impact hazards to the Earth posed by NEOs (both asteroids and comets) by performing a comprehensive survey of the NEO population; (2) obtain detailed physical characterization data for individual objects that are likely to pose an impact hazard; (3) characterize the entire population of potentially hazardous NEOs to inform potential mitigation strategies by assisting the determination of impact energies through accurate object size determination and physical properties. The mission will make significant progress toward the George E. Brown, Jr. NEO Survey Program objective of detecting, tracking, cataloging, and characterizing at least 90% of NEOs equal to or larger than 140 m in diameter. The project is a collaboration between NASA-JPL, the University of Arizona and industry, with Ball Aerospace notably providing the spacecraft and key instrument elements. This paper will describe the key activities and accomplishments performed by the NEOS Project during the preliminary design phase and describe how these have matured the overall mission.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117031038","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115884
B. Donahue, M. Duggan, Terry D. Haws, Jennifer Bowman, M. Paul
The NASA Space Launch System (SLS) capabilities for launching heavy payloads with high injection velocities will enable a variety of exploration missions that would not otherwise be considered. In this paper, the Interstellar Probe mission is described and an enhanced version of the NASA SLS is presented.
{"title":"Interstellar Probe: Fifteen Years to the Interstellar Medium with An Enhanced NASA Space Launch System","authors":"B. Donahue, M. Duggan, Terry D. Haws, Jennifer Bowman, M. Paul","doi":"10.1109/AERO55745.2023.10115884","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115884","url":null,"abstract":"The NASA Space Launch System (SLS) capabilities for launching heavy payloads with high injection velocities will enable a variety of exploration missions that would not otherwise be considered. In this paper, the Interstellar Probe mission is described and an enhanced version of the NASA SLS is presented.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"62 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123459012","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115863
M. A. Elenean, A. T. Hafez, A. Helmy, F. Eltohamy, A. Azouz
PolSAR (Polimetric Synthetic Aperture Radar) has been shown to be a powerful source of information. As a result of using up to four measurement channels at the same time, which increases the processing depth, it offers information about the geometrical and physical characteristics of objects. However, operating the PolSAR system to its full imaging potential requires significant computing power. In this study, a framework for fully polarimetric SAR image segmentation is proposed, in which the PolSAR signal is decomposed into four components that represent the eigenvectors of the autocovariance matrix corresponding to signals and clutter. The Unsupervised segmentation framework possesses two main processing levels. First level is the data preprocessing, including mean coherency matrix calculation, speckle reduction and polarimetric feature decomposition. Second level include the initial cluster Centers estimation, and edge-region based algorithm. This is achieved by using the combined H-Alpha and (averaged Intensity) lambda features derived from the target decomposition of the PolSAR data. Finally, k-Means clustering based on the Wishart distribution is used to optimize the iterative clustering by merging the clusters with the minimum Wishart distance. The proposed framework is applied on (Flevoland and San_Francisco Bay). The images are selected to react differently with different polarization. The performance evaluation based on qualitative (Visual) and quantitative assessments. Visual assessment provides an excellent information on clarity and delineation of different classes. It is applicable for applications need an accurate statistical information. Quantitative evaluations provide more accurate results for separating different classes in the images. The proposed algorithm is compared to the traditional Cloude-Pottier classification method. The results demonstrate that the proposed algorithm accuracy reaches (88.6 %) with error (0.114), advances over the traditional Cloude-Pottier method with accuracy (84.6 %) and error (0.154).
{"title":"Unsupervised Multi-level Segmentation Framework for PolSAR Data using H-Alpha features and the Combined Edge- Region based segmentation","authors":"M. A. Elenean, A. T. Hafez, A. Helmy, F. Eltohamy, A. Azouz","doi":"10.1109/AERO55745.2023.10115863","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115863","url":null,"abstract":"PolSAR (Polimetric Synthetic Aperture Radar) has been shown to be a powerful source of information. As a result of using up to four measurement channels at the same time, which increases the processing depth, it offers information about the geometrical and physical characteristics of objects. However, operating the PolSAR system to its full imaging potential requires significant computing power. In this study, a framework for fully polarimetric SAR image segmentation is proposed, in which the PolSAR signal is decomposed into four components that represent the eigenvectors of the autocovariance matrix corresponding to signals and clutter. The Unsupervised segmentation framework possesses two main processing levels. First level is the data preprocessing, including mean coherency matrix calculation, speckle reduction and polarimetric feature decomposition. Second level include the initial cluster Centers estimation, and edge-region based algorithm. This is achieved by using the combined H-Alpha and (averaged Intensity) lambda features derived from the target decomposition of the PolSAR data. Finally, k-Means clustering based on the Wishart distribution is used to optimize the iterative clustering by merging the clusters with the minimum Wishart distance. The proposed framework is applied on (Flevoland and San_Francisco Bay). The images are selected to react differently with different polarization. The performance evaluation based on qualitative (Visual) and quantitative assessments. Visual assessment provides an excellent information on clarity and delineation of different classes. It is applicable for applications need an accurate statistical information. Quantitative evaluations provide more accurate results for separating different classes in the images. The proposed algorithm is compared to the traditional Cloude-Pottier classification method. The results demonstrate that the proposed algorithm accuracy reaches (88.6 %) with error (0.114), advances over the traditional Cloude-Pottier method with accuracy (84.6 %) and error (0.154).","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"20 1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123538246","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115617
Kyoung Jae Kim, Taylor Schlotman, N. Newby, T. McGrath, Linh Q. Vu, Karina Marshall-Goebel, A. Abercromby, J. Somers
Inertial sensor-based task assessment while in a suited configuration can provide useful information for geology training programs and actual planetary Extravehicular Activities (EVAs). The purpose of this pilot study was to assess suited Lunar geology tasks from the postural perspective using inertial sensors and to gain a better understanding of the movements required during planetary EVAs and of the possible relationships with injury mechanisms. Professional geologist and non-geologist subjects participated in a suited geology task test, and preliminary analysis showed kinematic differences indicating a potential risk factor for lower back injury during future planetary EVAs.
{"title":"Development of an Inertial Sensor-Based Methodology for Spacesuited Lunar Geology Task Assessments","authors":"Kyoung Jae Kim, Taylor Schlotman, N. Newby, T. McGrath, Linh Q. Vu, Karina Marshall-Goebel, A. Abercromby, J. Somers","doi":"10.1109/AERO55745.2023.10115617","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115617","url":null,"abstract":"Inertial sensor-based task assessment while in a suited configuration can provide useful information for geology training programs and actual planetary Extravehicular Activities (EVAs). The purpose of this pilot study was to assess suited Lunar geology tasks from the postural perspective using inertial sensors and to gain a better understanding of the movements required during planetary EVAs and of the possible relationships with injury mechanisms. Professional geologist and non-geologist subjects participated in a suited geology task test, and preliminary analysis showed kinematic differences indicating a potential risk factor for lower back injury during future planetary EVAs.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123553151","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115691
Ethan Abele, S. Altunc, O. Kegege, Kaitlyn L. Ryder, Behnam Azimi, M. Campola, Kevin J. Lynaugh, Gianfranco Barnaba, P. Lopresti, S. Ekin, J. O’Hara
Free space optical (FSO) communication links increase data rate, reduce size and power, and increase security. These criteria are particularly important in space communication. Increasing mission complexity and crowding of lower frequency bands is driving the need for optical communications. This makes FSO communication technology extremely attractive, and there is significant ongoing work towards the development of FSO transceivers, ground stations, and relays. Notable projects include the Laser Communications Relay Demonstrator (LCRD), Integrated LCRD Low-Earth Orbit User Modem and Amplifier Terminal (ILLUMA-T), and CubeSat Laser Infrared Crosslink (CLICK) CubeSats. These technologies will eventually operate in unison with existing Radio Frequency (RF) systems, but there is little experimental investigation of such hybrid networks. This paper presents some experimental underpinnings of switching strategies for hybrid RF/FSO systems in various attenuation conditions. A 170 m optical path was constructed in an enclosed test chamber where atmospheric conditions can be tightly controlled. The performance of a 1550 nm infrared FSO link was evaluated in this chamber under varying conditions of turbulence and jitter. The system will eventually be used to investigate switching criteria between the FSO and RF channels. Optimizing the use of RF/FSO communication links will allow data rate, size, power, and security improvements. Therefore, this research will help to mature the network architecture and improve the performance of communication networks to be used for LEO, GEO, Lagrange, Lunar missions and beyond.
{"title":"Channel Measurements for Switching Strategies in Hybrid RF/Optical Communications","authors":"Ethan Abele, S. Altunc, O. Kegege, Kaitlyn L. Ryder, Behnam Azimi, M. Campola, Kevin J. Lynaugh, Gianfranco Barnaba, P. Lopresti, S. Ekin, J. O’Hara","doi":"10.1109/AERO55745.2023.10115691","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115691","url":null,"abstract":"Free space optical (FSO) communication links increase data rate, reduce size and power, and increase security. These criteria are particularly important in space communication. Increasing mission complexity and crowding of lower frequency bands is driving the need for optical communications. This makes FSO communication technology extremely attractive, and there is significant ongoing work towards the development of FSO transceivers, ground stations, and relays. Notable projects include the Laser Communications Relay Demonstrator (LCRD), Integrated LCRD Low-Earth Orbit User Modem and Amplifier Terminal (ILLUMA-T), and CubeSat Laser Infrared Crosslink (CLICK) CubeSats. These technologies will eventually operate in unison with existing Radio Frequency (RF) systems, but there is little experimental investigation of such hybrid networks. This paper presents some experimental underpinnings of switching strategies for hybrid RF/FSO systems in various attenuation conditions. A 170 m optical path was constructed in an enclosed test chamber where atmospheric conditions can be tightly controlled. The performance of a 1550 nm infrared FSO link was evaluated in this chamber under varying conditions of turbulence and jitter. The system will eventually be used to investigate switching criteria between the FSO and RF channels. Optimizing the use of RF/FSO communication links will allow data rate, size, power, and security improvements. Therefore, this research will help to mature the network architecture and improve the performance of communication networks to be used for LEO, GEO, Lagrange, Lunar missions and beyond.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117197345","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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