Pub Date : 2023-03-04DOI: 10.1109/AERO55745.2023.10115825
Emma Young, Ge Yang, Travis L. Wagner, Flora Ridenhour, C. Lawler, Nagin Cox
Since landing in Jezero Crater on Mars on February 18, 2021, the Mars 2020 mission's Perseverance rover has been performing daily operations on the Martian surface and has been collecting samples that may one day be returned to Earth. The majority of science and engineering data from the Perseverance rover is returned through the Mars orbiters operated by the National Aeronautics and Space Administration (NASA) and the European Space Agency (ESA) that make up the Mars Relay Network: Mars Reconnaissance Orbiter (MRO), Mars Odyssey (ODY), Mars Atmosphere and Volatile Evolution (MAVEN), and Trace Gas Orbiter (TGO). Prior to the rover's landing, the Mars 2020 team joined the Mars Relay Network to begin planning relay through the coordinated, multi-mission process that is the cornerstone of relay planning. The Perseverance rover has now been on the Martian surface for more than 600 Martian solar days (“sols”) with several UHF relay sessions planned and executed per sol. The Mars 2020 relay planning team has established and improved upon the recurring process and tool suite to enable both data return and forward link of rover uplink products, and continues to coordinate and negotiate relay asset usages and constraints with the Mars Science Laboratory and Insight relay planning teams. Among many accomplishments, the relay planning team has supported checkouts and commissioning of Low-Density Parity-Check (LDPC) relay link configurations, the mission's first solar conjunction period, and several rover flight software transitions. The Mars 2020 team has also been performing a checkout and commissioning campaign for the use of bitstream, or “unreliable”, relay sessions. Nominal use of bitstream relay is a new operational capability intended for the Perseverance rover that will allow specific science or engineering activities to run in parallel with the relay session, rather than pausing all other activities during relay, enabling additional and more timely data return. Pending the completion of the checkout and commissioning campaign, the operations team plans to approve and begin regular scheduling and use of bitstream UHF relay sessions beginning in 2023. This paper describes the Mars 2020 relay planning processes and tool architecture, key accomplishments (including progress for the bitstream checkout and commissioning campaign), and lessons learned and ongoing challenges during the first 600 sols of the Mars 2020 surface mission.
{"title":"Relay Planning in the Perseverance Rover's First 600 Solar Days on Mars","authors":"Emma Young, Ge Yang, Travis L. Wagner, Flora Ridenhour, C. Lawler, Nagin Cox","doi":"10.1109/AERO55745.2023.10115825","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115825","url":null,"abstract":"Since landing in Jezero Crater on Mars on February 18, 2021, the Mars 2020 mission's Perseverance rover has been performing daily operations on the Martian surface and has been collecting samples that may one day be returned to Earth. The majority of science and engineering data from the Perseverance rover is returned through the Mars orbiters operated by the National Aeronautics and Space Administration (NASA) and the European Space Agency (ESA) that make up the Mars Relay Network: Mars Reconnaissance Orbiter (MRO), Mars Odyssey (ODY), Mars Atmosphere and Volatile Evolution (MAVEN), and Trace Gas Orbiter (TGO). Prior to the rover's landing, the Mars 2020 team joined the Mars Relay Network to begin planning relay through the coordinated, multi-mission process that is the cornerstone of relay planning. The Perseverance rover has now been on the Martian surface for more than 600 Martian solar days (“sols”) with several UHF relay sessions planned and executed per sol. The Mars 2020 relay planning team has established and improved upon the recurring process and tool suite to enable both data return and forward link of rover uplink products, and continues to coordinate and negotiate relay asset usages and constraints with the Mars Science Laboratory and Insight relay planning teams. Among many accomplishments, the relay planning team has supported checkouts and commissioning of Low-Density Parity-Check (LDPC) relay link configurations, the mission's first solar conjunction period, and several rover flight software transitions. The Mars 2020 team has also been performing a checkout and commissioning campaign for the use of bitstream, or “unreliable”, relay sessions. Nominal use of bitstream relay is a new operational capability intended for the Perseverance rover that will allow specific science or engineering activities to run in parallel with the relay session, rather than pausing all other activities during relay, enabling additional and more timely data return. Pending the completion of the checkout and commissioning campaign, the operations team plans to approve and begin regular scheduling and use of bitstream UHF relay sessions beginning in 2023. This paper describes the Mars 2020 relay planning processes and tool architecture, key accomplishments (including progress for the bitstream checkout and commissioning campaign), and lessons learned and ongoing challenges during the first 600 sols of the Mars 2020 surface mission.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"82 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":"124401762","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/AERO55745.2023.10115919
Lukas Meyer, Mallikarjuna Vayugundla, Patrick Kenny, Michal Smíšek, J. Biele, A. Maturilli, M. Müller, W. Stürzl, M. J. Schuster, T. Bodenmüller, A. Wedler, Rudolph Triebel
The MMX rover will explore the surface of Phobos, Mars' bigger moon. It will use its stereo cameras for perceiving the environment, enabling the use of vision based autonomous navigation algorithms. The German Aerospace Center (DLR) is currently developing the corresponding autonomous navigation experiment that will allow the rover to efficiently explore the surface of Phobos, despite limited communication with Earth and long turn-around times for operations. This paper discusses our testing strategy regarding the autonomous navigation solution. We present our general testing strategy for the software considering a development approach with agile aspects. We detail, how we ensure successful integration with the rover system despite having limited access to the flight hardware. We furthermore discuss, what environmental conditions on Phobos pose a potential risk for the navigation algorithms and how we test for these accordingly. Our testing is mostly data set-based and we describe our approaches for recording navigation data that is representative both for the rover system and also for the Phobos environment. Finally, we make the corresponding data set publicly available and provide an overview on its content.
{"title":"Testing for the MMX Rover Autonomous Navigation Experiment on Phobos","authors":"Lukas Meyer, Mallikarjuna Vayugundla, Patrick Kenny, Michal Smíšek, J. Biele, A. Maturilli, M. Müller, W. Stürzl, M. J. Schuster, T. Bodenmüller, A. Wedler, Rudolph Triebel","doi":"10.1109/AERO55745.2023.10115919","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115919","url":null,"abstract":"The MMX rover will explore the surface of Phobos, Mars' bigger moon. It will use its stereo cameras for perceiving the environment, enabling the use of vision based autonomous navigation algorithms. The German Aerospace Center (DLR) is currently developing the corresponding autonomous navigation experiment that will allow the rover to efficiently explore the surface of Phobos, despite limited communication with Earth and long turn-around times for operations. This paper discusses our testing strategy regarding the autonomous navigation solution. We present our general testing strategy for the software considering a development approach with agile aspects. We detail, how we ensure successful integration with the rover system despite having limited access to the flight hardware. We furthermore discuss, what environmental conditions on Phobos pose a potential risk for the navigation algorithms and how we test for these accordingly. Our testing is mostly data set-based and we describe our approaches for recording navigation data that is representative both for the rover system and also for the Phobos environment. Finally, we make the corresponding data set publicly available and provide an overview on its content.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"15 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":"125055479","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/AERO55745.2023.10115806
T. Tikka, J. Makynen, M. Shimoni
Over the past few decades, Earth observation technology has provided highly useful information for global climate change research, particularly in providing biological, physical, and chemical parameters on a global scale. Nevertheless, the low revisit rate and spectral resolution, as well as the expensive operational capacities of current spaceborne missions, make it difficult to gain rapid and accurate insights into degrading ecosystems or dissect faltering food security or carbon sinks. The Hyperfield constellation that will be launched in 2023 consists of 100 CubeSats with hyperspectral imagers operating in the visible-to-near-infrared (VIS-NIR, 450–1100 nm) and Visible-to-shortwave infrared (VIS-SWIR, 450–2500 nm) ranges and provides two to three times daily images from any location on Earth. The hyperspectral is based on a Piezo-actuated Fabry-Perot interferometer (PFPI) and a tailored camera with innovative modes of acquisition. A novel artificial intelligence (AI) processing platform will be used to provide stakeholders with high-quality, affordable data, analytical services and forecasts on a daily basis, enabling them to make informed decisions that lead to a more sustainable environment, carbon sequestration, food security, and a reduction in climate change impacts. This paper presents the first and second generations of the Hyperfield satellites. It reviews their innovative platform and detector technology, the optical modes, planned mission operations, processing architecture and services.
{"title":"Hyperfield - Hyperspectral small satellites for improving life on Earth","authors":"T. Tikka, J. Makynen, M. Shimoni","doi":"10.1109/AERO55745.2023.10115806","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115806","url":null,"abstract":"Over the past few decades, Earth observation technology has provided highly useful information for global climate change research, particularly in providing biological, physical, and chemical parameters on a global scale. Nevertheless, the low revisit rate and spectral resolution, as well as the expensive operational capacities of current spaceborne missions, make it difficult to gain rapid and accurate insights into degrading ecosystems or dissect faltering food security or carbon sinks. The Hyperfield constellation that will be launched in 2023 consists of 100 CubeSats with hyperspectral imagers operating in the visible-to-near-infrared (VIS-NIR, 450–1100 nm) and Visible-to-shortwave infrared (VIS-SWIR, 450–2500 nm) ranges and provides two to three times daily images from any location on Earth. The hyperspectral is based on a Piezo-actuated Fabry-Perot interferometer (PFPI) and a tailored camera with innovative modes of acquisition. A novel artificial intelligence (AI) processing platform will be used to provide stakeholders with high-quality, affordable data, analytical services and forecasts on a daily basis, enabling them to make informed decisions that lead to a more sustainable environment, carbon sequestration, food security, and a reduction in climate change impacts. This paper presents the first and second generations of the Hyperfield satellites. It reviews their innovative platform and detector technology, the optical modes, planned mission operations, processing architecture and services.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"28 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":"126031294","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/AERO55745.2023.10115801
Jonis Kiesbye, Kush Grover, Jan Křetínský
Developing the Fault Detection, Isolation & Recovery (FDIR) policy often happens late in the design phase of a spacecraft and might reveal significant gaps in the redundancy concept. We propose a process for continuously analyzing and improving the architecture of a spacecraft throughout the design phase to ensure successful fault isolation and recovery. The systems engineer provides a graph of the system's architecture containing the functional modes, the hardware components, and their dependency on each other as an input and gets back a weakness report listing the gaps in the redundancy concept. Overlaying the sub-graphs for every fault scenario allows us to reason about the feasibility of fault isolation and recovery. The graph is automatically converted to a Markov Decision Process for use with a model checker to generate a control policy for the FDIR process. The model is optimized by pruning inefficient branches with Monte Carlo Tree Search. We export this policy as a decision tree that ensures explainability, fast execution, and low memory requirements during runtime. We also generate C-code for fault isolation and reconfiguration that can be integrated in the FDIR software. The tool was used on system architectures created in the Modular ADCS project which is part of ESA's GSTP program. In this context, it helped to yield an effective redundancy concept with minimum overhead and dramatically reduce the programming effort for FDIR routines. Since we use model checking for the analysis, the designer gains formal verification of the robustness towards faults.
{"title":"Model Checking for Proving and Improving Fault Tolerance of Satellites","authors":"Jonis Kiesbye, Kush Grover, Jan Křetínský","doi":"10.1109/AERO55745.2023.10115801","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115801","url":null,"abstract":"Developing the Fault Detection, Isolation & Recovery (FDIR) policy often happens late in the design phase of a spacecraft and might reveal significant gaps in the redundancy concept. We propose a process for continuously analyzing and improving the architecture of a spacecraft throughout the design phase to ensure successful fault isolation and recovery. The systems engineer provides a graph of the system's architecture containing the functional modes, the hardware components, and their dependency on each other as an input and gets back a weakness report listing the gaps in the redundancy concept. Overlaying the sub-graphs for every fault scenario allows us to reason about the feasibility of fault isolation and recovery. The graph is automatically converted to a Markov Decision Process for use with a model checker to generate a control policy for the FDIR process. The model is optimized by pruning inefficient branches with Monte Carlo Tree Search. We export this policy as a decision tree that ensures explainability, fast execution, and low memory requirements during runtime. We also generate C-code for fault isolation and reconfiguration that can be integrated in the FDIR software. The tool was used on system architectures created in the Modular ADCS project which is part of ESA's GSTP program. In this context, it helped to yield an effective redundancy concept with minimum overhead and dramatically reduce the programming effort for FDIR routines. Since we use model checking for the analysis, the designer gains formal verification of the robustness towards faults.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"29 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":"126738601","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/AERO55745.2023.10115716
Florian Strasser, Martin Favin–Lévêque, Till Assmann, F. Schummer
The operation of any spacecraft requires a constant trade-off between available resources onboard the spacecraft such as power, the correct thermal operating range, downlink capacity, and payload stakeholder interests. On a commercial spacecraft, cost-efficient operations pose an additional requirement with significant influence on the success of the mission. On hosted payload missions, the interface and contractual constraints between the spacecraft operator and payload operator add to the challenges. Economic success calls for automated scheduling of operations and must consider all of the above constraints. This paper presents the algorithm-based optimization of the operational schedule for the wildfire detection satellite mission FOREST-1, the concept of which can be transferred to the operation of any Low-Earth-Orbit Earth observation satellite. The state of the art of generally applicable algorithms is presented and a comparison for the adaptability to the underlying problem statement is made. Compared algorithms include sequential, forward-chronological, linear search, and evolutionary algorithms. For this application, the simplex algorithm was chosen due to its capabilities regarding depleting one pivotal resource to maximize a mathematically defined gain to the mission. The implementation of this algorithm, which now is used to build the schedules of FOREST-1 regularly is presented. It is compared against the manual scheduling approach used during the commissioning phase in terms of controllability, flex-ibility, transparency, and efficiency. When used for scheduling weekly operations, the automatic scheduler achieves a reliable resource allocation of at least 98%, with an average cloud coverage of 2.5% and the highest value at 13% compared to around 80% utilization, 16.5% and up to 79% respectively. The benchmarks for the manual scheduling approach required 90 minutes on average while one execution of the automated scheduler required around 20 minutes. The manually generated schedules consist of 96% of requested sequences and only three out of 73 targets where chosen from areas of interest whereas the scheduler allocated 81.25% to areas of interest and 18.75% to requests.
{"title":"Algorithmic Resource Allocation for Spacecraft Operations","authors":"Florian Strasser, Martin Favin–Lévêque, Till Assmann, F. Schummer","doi":"10.1109/AERO55745.2023.10115716","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115716","url":null,"abstract":"The operation of any spacecraft requires a constant trade-off between available resources onboard the spacecraft such as power, the correct thermal operating range, downlink capacity, and payload stakeholder interests. On a commercial spacecraft, cost-efficient operations pose an additional requirement with significant influence on the success of the mission. On hosted payload missions, the interface and contractual constraints between the spacecraft operator and payload operator add to the challenges. Economic success calls for automated scheduling of operations and must consider all of the above constraints. This paper presents the algorithm-based optimization of the operational schedule for the wildfire detection satellite mission FOREST-1, the concept of which can be transferred to the operation of any Low-Earth-Orbit Earth observation satellite. The state of the art of generally applicable algorithms is presented and a comparison for the adaptability to the underlying problem statement is made. Compared algorithms include sequential, forward-chronological, linear search, and evolutionary algorithms. For this application, the simplex algorithm was chosen due to its capabilities regarding depleting one pivotal resource to maximize a mathematically defined gain to the mission. The implementation of this algorithm, which now is used to build the schedules of FOREST-1 regularly is presented. It is compared against the manual scheduling approach used during the commissioning phase in terms of controllability, flex-ibility, transparency, and efficiency. When used for scheduling weekly operations, the automatic scheduler achieves a reliable resource allocation of at least 98%, with an average cloud coverage of 2.5% and the highest value at 13% compared to around 80% utilization, 16.5% and up to 79% respectively. The benchmarks for the manual scheduling approach required 90 minutes on average while one execution of the automated scheduler required around 20 minutes. The manually generated schedules consist of 96% of requested sequences and only three out of 73 targets where chosen from areas of interest whereas the scheduler allocated 81.25% to areas of interest and 18.75% to requests.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"300 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":"115247805","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/AERO55745.2023.10115967
Robin Forsling, F. Gustafsson, Zoran Sjanic, Gustaf Hendeby
This paper considers fusion of dimension-reduced estimates in a decentralized sensor network. The benefits of a decentralized sensor network include modularity, robustness and flexibility. Moreover, since preprocessed data is exchanged between the agents it allows for reduced communication. Nevertheless, in certain applications the communication load is required to be reduced even further. One way to decrease the communication load is to exchange dimension-reduced estimates instead of full estimates. Previous work on this topic assumes global availability of covariance matrices, an assumption which is not realistic in decentralized applications. Hence, in this paper we consider the problem of deriving dimension-reduced estimates using only local information. The proposed solution is based on an estimate of the information common to the network. This common information estimate is computed locally at each agent by fusion of all information that is either received or transmitted by that agent. It is shown how the common information estimate is utilized for fusion of dimension-reduced estimates using two well-known fusion methods: the Kalman fuser which is optimal under the assumption of uncorrelated estimates, and covariance intersection. One main theoretical result is that the common information estimate allows for a decorrelation procedure such that uncorrelated estimates can be maintained. This property is crucial to be able to use the Kalman fuser without double counting of information. A numerical comparison suggests that the performance degradation of using the common information estimate, compared to having local access to the actual covariance matrices computed by other agents, is relatively small.
{"title":"Decentralized Data Fusion of Dimension-Reduced Estimates Using Local Information Only","authors":"Robin Forsling, F. Gustafsson, Zoran Sjanic, Gustaf Hendeby","doi":"10.1109/AERO55745.2023.10115967","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115967","url":null,"abstract":"This paper considers fusion of dimension-reduced estimates in a decentralized sensor network. The benefits of a decentralized sensor network include modularity, robustness and flexibility. Moreover, since preprocessed data is exchanged between the agents it allows for reduced communication. Nevertheless, in certain applications the communication load is required to be reduced even further. One way to decrease the communication load is to exchange dimension-reduced estimates instead of full estimates. Previous work on this topic assumes global availability of covariance matrices, an assumption which is not realistic in decentralized applications. Hence, in this paper we consider the problem of deriving dimension-reduced estimates using only local information. The proposed solution is based on an estimate of the information common to the network. This common information estimate is computed locally at each agent by fusion of all information that is either received or transmitted by that agent. It is shown how the common information estimate is utilized for fusion of dimension-reduced estimates using two well-known fusion methods: the Kalman fuser which is optimal under the assumption of uncorrelated estimates, and covariance intersection. One main theoretical result is that the common information estimate allows for a decorrelation procedure such that uncorrelated estimates can be maintained. This property is crucial to be able to use the Kalman fuser without double counting of information. A numerical comparison suggests that the performance degradation of using the common information estimate, compared to having local access to the actual covariance matrices computed by other agents, is relatively small.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"70 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":"115539170","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/AERO55745.2023.10115952
Shashvat Prakash, Katarina Vuckovic, S. Amin
Prognostic analytic models have become a viable way to reduce operational interruptions when sufficient timely data is available and the resultant model is a good predictor. This paper describes a set of evaluation metrics which can characterize model performance as a degradation estimate and as a decision enabler. The model accuracy over time is assessed against a correlation with the remaining useful life. This yields both a prediction accuracy and confidence interval. The decision can be based on the level of confidence around the prediction, which is based on both how far into the future the event is predicted and how well the current health and its deterioration is estimated. With an effective means of evaluating prognostic models, better benchmarks can be established to communicate model effectiveness and appropriately schedule routine service.
{"title":"Prognostic Model Evaluation Metrics","authors":"Shashvat Prakash, Katarina Vuckovic, S. Amin","doi":"10.1109/AERO55745.2023.10115952","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115952","url":null,"abstract":"Prognostic analytic models have become a viable way to reduce operational interruptions when sufficient timely data is available and the resultant model is a good predictor. This paper describes a set of evaluation metrics which can characterize model performance as a degradation estimate and as a decision enabler. The model accuracy over time is assessed against a correlation with the remaining useful life. This yields both a prediction accuracy and confidence interval. The decision can be based on the level of confidence around the prediction, which is based on both how far into the future the event is predicted and how well the current health and its deterioration is estimated. With an effective means of evaluating prognostic models, better benchmarks can be established to communicate model effectiveness and appropriately schedule routine service.","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":"122481065","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/AERO55745.2023.10115973
J. Arribas, M.A. Gómez, C. Fernández-Prades, David Laso Martín, Julio María García-Tuñón, Tamara García Rioja
It is well known that the presence of unintentional or intentional Radio Frequency Interference (RFI) signals in the Global Navigation Satellite Systems (GNSS) frequency bands can cause severe positioning performance degradation and even a complete service unavailability. Moreover, with the development of Software Defined Radio (SDR) GNSS signal generators and the popularization of low-cost SDR front-ends, the spoofing of the GNSS civil service turns out to be a real threat for GNSS receivers. Complementary to time and frequency-domain mit-igation techniques, antenna-array based receivers can benefit from spatial domain processing. An antenna array receiver can also discriminate between legitimate GNSS signals from these being broadcasted by the spoofer. In this work, we present an evolution of a receiver-independent GNSS smart antenna architecture for a real-time, automatic and autonomous, simultaneous anti-jamming and anti-spoofing spatial filtering for GNSS bands. The novel spoofer detection and mitigation algorithm is able to detect the spoofer and protect the receiver even in a scenario where the spoofer is transmitted in combination with a strong jammer to force the receiver to lose the legitimate GNSS signal lock. A prototype is also presented, implemented using Commercial Off The Shelf (COTS) components. The proposed smart antenna can be connected to any conventional single-antenna GNSS receiver. The paper includes both the theory of operation, the implementation details and its performance analysis in an extended measurement campaign.
{"title":"A Receiver-Independent GNSS Smart Antenna for Simultaneous Jamming and Spoofing Protection","authors":"J. Arribas, M.A. Gómez, C. Fernández-Prades, David Laso Martín, Julio María García-Tuñón, Tamara García Rioja","doi":"10.1109/AERO55745.2023.10115973","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115973","url":null,"abstract":"It is well known that the presence of unintentional or intentional Radio Frequency Interference (RFI) signals in the Global Navigation Satellite Systems (GNSS) frequency bands can cause severe positioning performance degradation and even a complete service unavailability. Moreover, with the development of Software Defined Radio (SDR) GNSS signal generators and the popularization of low-cost SDR front-ends, the spoofing of the GNSS civil service turns out to be a real threat for GNSS receivers. Complementary to time and frequency-domain mit-igation techniques, antenna-array based receivers can benefit from spatial domain processing. An antenna array receiver can also discriminate between legitimate GNSS signals from these being broadcasted by the spoofer. In this work, we present an evolution of a receiver-independent GNSS smart antenna architecture for a real-time, automatic and autonomous, simultaneous anti-jamming and anti-spoofing spatial filtering for GNSS bands. The novel spoofer detection and mitigation algorithm is able to detect the spoofer and protect the receiver even in a scenario where the spoofer is transmitted in combination with a strong jammer to force the receiver to lose the legitimate GNSS signal lock. A prototype is also presented, implemented using Commercial Off The Shelf (COTS) components. The proposed smart antenna can be connected to any conventional single-antenna GNSS receiver. The paper includes both the theory of operation, the implementation details and its performance analysis in an extended measurement campaign.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"18 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":"114168896","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/AERO55745.2023.10115711
D. Dunham, T. Ogle
A hotly debated topic that has been around for decades-probably as long as the Kalman Filter-is what advantage is there to fusing measurements as opposed to fusing tracks at the system level. Many systems use the measurements and have been designed to do so. On the other hand, some systems only utilize tracks from sensors and have had excellent success in this manner. One line of thinking is that it depends on the target that is being tracked. If the target is expected to maneuver in a significant manner then it may be better to use measurements in order to reduce overall lag in the system. Conversely if the target is not expected to maneuver significantly then tracks from each sensor may be a better alternative to allow for bias estimation and removal. The motivation for this paper is not to provide the definitive answer to this topic, but rather the purpose of this paper is to explore and document many of benefits of each approach. It will begin with a basic three-sensor scenario where both measurement and track fusion are performed with the same update rates.
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Pub Date : 2023-03-04DOI: 10.1109/AERO55745.2023.10116024
Tristan K. Schuler, Michael Debbins, Maxwell Cobar, J. Thangavelautham, D. Sofge
Vented Solar High Altitude Balloons (SHAB-Vs) utilize a lightweight balloon envelope with ideal thermal properties for absorbing direct solar radiation and heating the envelope and internal ambient air through conduction and convection. These balloons therefore do not require a lifting gas to generate lift, and are a simple, inexpensive, passive form of high altitude balloon flight. Until recently, SHABs have not had venting capabilities and been strictly free floating for high altitude science missions. In this work we present vent technology development and flight experiments for vented solar high altitude balloons (SHAB-Vs), Early vent experiments proved that changing altitude with a mechanically vented SHAB was possible. These early flights were on timed missions with precisely timed vent openings; after venting the balloon descended to a new altitude and settled at the new equilibrium. On more recent flights we introduced altitude control to guide the balloons to specific altitudes. During these flights we demonstrated precise altitude control down to 16 km with ± 75 m altitude oscillations and changed the horizontal trajectory of the SHAB-Vs several times by entering different wind flows. The ability to change the altitude of the SHABs can lead to more sophisticated maneuvers in the future such as station-keeping or waypoint trajectory following by leveraging opposing winds at various layers of the atmosphere.
{"title":"Altitude Control with Vented Solar High Altitude Balloons (SHAB-Vs)","authors":"Tristan K. Schuler, Michael Debbins, Maxwell Cobar, J. Thangavelautham, D. Sofge","doi":"10.1109/AERO55745.2023.10116024","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10116024","url":null,"abstract":"Vented Solar High Altitude Balloons (SHAB-Vs) utilize a lightweight balloon envelope with ideal thermal properties for absorbing direct solar radiation and heating the envelope and internal ambient air through conduction and convection. These balloons therefore do not require a lifting gas to generate lift, and are a simple, inexpensive, passive form of high altitude balloon flight. Until recently, SHABs have not had venting capabilities and been strictly free floating for high altitude science missions. In this work we present vent technology development and flight experiments for vented solar high altitude balloons (SHAB-Vs), Early vent experiments proved that changing altitude with a mechanically vented SHAB was possible. These early flights were on timed missions with precisely timed vent openings; after venting the balloon descended to a new altitude and settled at the new equilibrium. On more recent flights we introduced altitude control to guide the balloons to specific altitudes. During these flights we demonstrated precise altitude control down to 16 km with ± 75 m altitude oscillations and changed the horizontal trajectory of the SHAB-Vs several times by entering different wind flows. The ability to change the altitude of the SHABs can lead to more sophisticated maneuvers in the future such as station-keeping or waypoint trajectory following by leveraging opposing winds at various layers of the atmosphere.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"64 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":"116676681","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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