Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446841
S. Saha, B. Saha, A. Saxena, K. Goebel
Distributed prognostics architecture design is an enabling step for efficient implementation of health management systems. 12A major challenge encountered in such design is formulation of optimal distributed prognostics algorithms. In this paper, we present a distributed GPR based prognostics algorithm whose target platform is a wireless sensor network. In addition to challenges encountered in a distributed implementation, a wireless network poses constraints on communication patterns, thereby making the problem more challenging. The prognostics application that was used to demonstrate our new algorithms is battery prognostics. In order to present trade-offs within different prognostic approaches, we present comparison with the distributed implementation of a particle filter based prognostics for the same battery data.
{"title":"Distributed prognostic health management with gaussian process regression","authors":"S. Saha, B. Saha, A. Saxena, K. Goebel","doi":"10.1109/AERO.2010.5446841","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446841","url":null,"abstract":"Distributed prognostics architecture design is an enabling step for efficient implementation of health management systems. 12A major challenge encountered in such design is formulation of optimal distributed prognostics algorithms. In this paper, we present a distributed GPR based prognostics algorithm whose target platform is a wireless sensor network. In addition to challenges encountered in a distributed implementation, a wireless network poses constraints on communication patterns, thereby making the problem more challenging. The prognostics application that was used to demonstrate our new algorithms is battery prognostics. In order to present trade-offs within different prognostic approaches, we present comparison with the distributed implementation of a particle filter based prognostics for the same battery data.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123777084","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446669
M. Juliato, C. Gebotys
The growing demand for secure communications has lead to the utilization of cryptographic mechanisms on-board spacecrafts. However, that it not a trivial task due to sensitivity of cryptographic primitives to bit-flips, which are commonly caused by the radiation found in space. On-board processing has mitigated single event upsets (SEUs) by employing the traditional triple modular redundancy (TMR), but that technique incurs into huge area and energy penalties. This paper introduces an efficient approach to achieve fault tolerance in data origin authentication mechanisms based on the Keyed-Hash Message Authentication Code (HMAC). The proposed scheme achieves very high resistance against SEUs while reducing implementation area requirements and energy consumption compared to TMR. Results obtained through FPGA implementation show that HMAC-SHA512 utilizes 53% less area and consumes 25% less energy compared to the traditional TMR technique. Furthermore, the memory and registers of this hardware module are respectively 386 and 1140 times more resistant against SEUs than TMR. These results are crucial for substituting TMR with more efficient strategies therefore contributing to the achievement of higher levels of security in space systems.
{"title":"An efficient fault-tolerance technique for the Keyed-Hash Message Authentication Code","authors":"M. Juliato, C. Gebotys","doi":"10.1109/AERO.2010.5446669","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446669","url":null,"abstract":"The growing demand for secure communications has lead to the utilization of cryptographic mechanisms on-board spacecrafts. However, that it not a trivial task due to sensitivity of cryptographic primitives to bit-flips, which are commonly caused by the radiation found in space. On-board processing has mitigated single event upsets (SEUs) by employing the traditional triple modular redundancy (TMR), but that technique incurs into huge area and energy penalties. This paper introduces an efficient approach to achieve fault tolerance in data origin authentication mechanisms based on the Keyed-Hash Message Authentication Code (HMAC). The proposed scheme achieves very high resistance against SEUs while reducing implementation area requirements and energy consumption compared to TMR. Results obtained through FPGA implementation show that HMAC-SHA512 utilizes 53% less area and consumes 25% less energy compared to the traditional TMR technique. Furthermore, the memory and registers of this hardware module are respectively 386 and 1140 times more resistant against SEUs than TMR. These results are crucial for substituting TMR with more efficient strategies therefore contributing to the achievement of higher levels of security in space systems.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"125 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121494521","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446779
R. Drury, A. Tsourdos, A. Cooke
The optimality of a solution to a minimum-time aircraft trajectory generation problem depends on the closeness of the generated airspeed to the maximum airspeed that satisfies all path and boundary constraints. Airspeed is typically determined by nonlinear constrained optimization, hence the degree of the airspeed parameterization affects optimality and computational speed. An alternative approach, directly evaluating maximum feasible airspeed, is described and compared with the optimization approach. Results using Chebyshev polynomials show that, in isolation, parameterizations of degree 8–10 deliver a good trade-off between high degree for optimality and low degree for speed. However, directly evaluating airspeed is closer to optimality and not prone to convergence to a local solution. Accuracy of evaluation of the maxima of constrained variables is investigated using global Chebyshev, local quadratic, and local cubic, interpolation, and results show that quadratic interpolation in particular is computationally efficient, increasing speed while maintaining accuracy.
{"title":"Real-time trajectory generation: Improving the optimality and speed of an inverse dynamics method","authors":"R. Drury, A. Tsourdos, A. Cooke","doi":"10.1109/AERO.2010.5446779","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446779","url":null,"abstract":"The optimality of a solution to a minimum-time aircraft trajectory generation problem depends on the closeness of the generated airspeed to the maximum airspeed that satisfies all path and boundary constraints. Airspeed is typically determined by nonlinear constrained optimization, hence the degree of the airspeed parameterization affects optimality and computational speed. An alternative approach, directly evaluating maximum feasible airspeed, is described and compared with the optimization approach. Results using Chebyshev polynomials show that, in isolation, parameterizations of degree 8–10 deliver a good trade-off between high degree for optimality and low degree for speed. However, directly evaluating airspeed is closer to optimality and not prone to convergence to a local solution. Accuracy of evaluation of the maxima of constrained variables is investigated using global Chebyshev, local quadratic, and local cubic, interpolation, and results show that quadratic interpolation in particular is computationally efficient, increasing speed while maintaining accuracy.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"98 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121575703","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446979
B. Bortnik, J. P. Kirby, J. Lambert
In this paper we present the use of metallic waveguides as optical Raman probes for identification of various organic and inorganic compounds. In contrast to silica waveguides, metallic capillaries possess significant space savings and robust mechanical properties allowing the employment of such probes in hostile atmosphere and space environments. Furthermore, recent fabrication advances have produced metallic waveguides with low loss in the ultraviolet region, allowing the use of ultraviolet light as an excitation source in Raman spectroscopy, thereby decreasing background noise from sample and instrument fluorescence. Accordingly, we will present encouraging experimental results on the implementation of Raman spectroscopy using these metal capillaries and discuss their potential application to future space missions. This work is being developed as a NASA Planetary Instrument Definition and Development (PIDDP) task.
{"title":"Rugged compact metallized capillary Raman probe for material identification in hostile environments","authors":"B. Bortnik, J. P. Kirby, J. Lambert","doi":"10.1109/AERO.2010.5446979","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446979","url":null,"abstract":"In this paper we present the use of metallic waveguides as optical Raman probes for identification of various organic and inorganic compounds. In contrast to silica waveguides, metallic capillaries possess significant space savings and robust mechanical properties allowing the employment of such probes in hostile atmosphere and space environments. Furthermore, recent fabrication advances have produced metallic waveguides with low loss in the ultraviolet region, allowing the use of ultraviolet light as an excitation source in Raman spectroscopy, thereby decreasing background noise from sample and instrument fluorescence. Accordingly, we will present encouraging experimental results on the implementation of Raman spectroscopy using these metal capillaries and discuss their potential application to future space missions. This work is being developed as a NASA Planetary Instrument Definition and Development (PIDDP) task.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"130 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122658622","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446919
S. Sud, Edward B. Page
Cellular communications systems suffer from co-channel interference (CCI), due to signals from adjacent cells interfering with each other. Conventional demodulation techniques have relied on interference rejection to extract only the highest power signal. Recently, a joint reduced rank model-based demodulator (J-RRMBD) was presented that extracts two or more co-channel signals using continuous phase modulation (CPM) simultaneously. The technique is based upon a root selection algorithm using forward-backward linear prediction (FBLP), whereby multiple unequal powered signals are extracted by choosing the highest powered roots. Using synchronous continuous phase frequency shift keying (CPFSK) signals, the algorithm has been shown to provide up to 5 dB improvement over the conventional quadrature demodulator (QD) and single user model-based demodulator (MBD), which extracts only the highest powered user. In this paper, we apply the technique to received asynchronous Gaussian Minimum Shift Keying (GMSK) signals with unknown frequency offsets, encountered in terrestrial GSM networks. We compare performance to a joint Viterbi demodulator when two co-channel signals are present and show that the new technique provides an order of magnitude reduction in bit error rate (BER), and can more reliably demodulate signals with few samples as long as the carrier-to-interference ratio (CIR) ≥ 3 dB. When CIR ≪ 5 dB, a single user version of the algorithm provides performance improvement up to 7 dB over the Viterbi algorithm.
{"title":"Performance of the joint reduced rank model-based demodulator for asynchronous co-channel GMSK signals","authors":"S. Sud, Edward B. Page","doi":"10.1109/AERO.2010.5446919","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446919","url":null,"abstract":"Cellular communications systems suffer from co-channel interference (CCI), due to signals from adjacent cells interfering with each other. Conventional demodulation techniques have relied on interference rejection to extract only the highest power signal. Recently, a joint reduced rank model-based demodulator (J-RRMBD) was presented that extracts two or more co-channel signals using continuous phase modulation (CPM) simultaneously. The technique is based upon a root selection algorithm using forward-backward linear prediction (FBLP), whereby multiple unequal powered signals are extracted by choosing the highest powered roots. Using synchronous continuous phase frequency shift keying (CPFSK) signals, the algorithm has been shown to provide up to 5 dB improvement over the conventional quadrature demodulator (QD) and single user model-based demodulator (MBD), which extracts only the highest powered user. In this paper, we apply the technique to received asynchronous Gaussian Minimum Shift Keying (GMSK) signals with unknown frequency offsets, encountered in terrestrial GSM networks. We compare performance to a joint Viterbi demodulator when two co-channel signals are present and show that the new technique provides an order of magnitude reduction in bit error rate (BER), and can more reliably demodulate signals with few samples as long as the carrier-to-interference ratio (CIR) ≥ 3 dB. When CIR ≪ 5 dB, a single user version of the algorithm provides performance improvement up to 7 dB over the Viterbi algorithm.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"47 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131369127","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446768
David J. Anderson, J. Dankanich, M. Munk, E. Pencil, L. Liou
Since its inception in 2001, the objective of the In-Space12 Propulsion Technology (ISPT) project has been developing and delivering in-space propulsion technologies that enable or enhance NASA robotic science missions. These in-space propulsion technologies are applicable, and potentially enabling for future NASA flagship and sample return missions currently under consideration, as well as having broad applicability to future Discovery and New Frontiers mission solicitations. This paper provides status of the technology development, applicability, and availability of in-space propulsion technologies that recently completed, or will be completing within the next year, their technology development and are ready for infusion into missions. The paper also describes the ISPT project's future focus on propulsion for sample return missions.
{"title":"The NASA In-Space Propulsion Technology project's current products and future directions","authors":"David J. Anderson, J. Dankanich, M. Munk, E. Pencil, L. Liou","doi":"10.1109/AERO.2010.5446768","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446768","url":null,"abstract":"Since its inception in 2001, the objective of the In-Space12 Propulsion Technology (ISPT) project has been developing and delivering in-space propulsion technologies that enable or enhance NASA robotic science missions. These in-space propulsion technologies are applicable, and potentially enabling for future NASA flagship and sample return missions currently under consideration, as well as having broad applicability to future Discovery and New Frontiers mission solicitations. This paper provides status of the technology development, applicability, and availability of in-space propulsion technologies that recently completed, or will be completing within the next year, their technology development and are ready for infusion into missions. The paper also describes the ISPT project's future focus on propulsion for sample return missions.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"106 1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116522107","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 Soft X-Ray Telescope (SXT) modules are the fundamental focusing assemblies on NASA's next major X-ray telescope mission, the International X-Ray Observatory (IXO). {su12]The preliminary design and analysis of these assemblies has been completed, addressing the major engineering challenges and leading to an understanding of the factors effecting module performance. Each of the 60 modules in the Flight Mirror Assembly (FMA) supports 200–300 densely packed 0.4 mm thick glass mirror segments in order to meet the unprecedented effective area required to achieve the scientific objectives of the mission. Detailed Finite Element Analysis (FEA), materials testing, and environmental testing have been completed to ensure the modules can be successfully launched. Resulting stress margins are positive based on detailed FEA, a large factor of safety, and a design strength determined by robust characterization of the glass properties. FEA correlates well with the results of the successful modal, vibration, and acoustic environmental tests. Deformation of the module due to on-orbit thermal conditions is also a major design driver. A preliminary thermal control system has been designed and the sensitivity of module optical performance to various thermal loads has been determined using optomechanical analysis methods developed for this unique assembly. This design and analysis furthers the goal of building a module that demonstrates the ability to meet IXO requirements, which is the current focus of IXO FMA technology development team.
{"title":"Design and analysis of the International X-Ray Observatory mirror modules","authors":"R. Mcclelland, T. Carnahan","doi":"10.1117/12.857535","DOIUrl":"https://doi.org/10.1117/12.857535","url":null,"abstract":"The Soft X-Ray Telescope (SXT) modules are the fundamental focusing assemblies on NASA's next major X-ray telescope mission, the International X-Ray Observatory (IXO). {su12]The preliminary design and analysis of these assemblies has been completed, addressing the major engineering challenges and leading to an understanding of the factors effecting module performance. Each of the 60 modules in the Flight Mirror Assembly (FMA) supports 200–300 densely packed 0.4 mm thick glass mirror segments in order to meet the unprecedented effective area required to achieve the scientific objectives of the mission. Detailed Finite Element Analysis (FEA), materials testing, and environmental testing have been completed to ensure the modules can be successfully launched. Resulting stress margins are positive based on detailed FEA, a large factor of safety, and a design strength determined by robust characterization of the glass properties. FEA correlates well with the results of the successful modal, vibration, and acoustic environmental tests. Deformation of the module due to on-orbit thermal conditions is also a major design driver. A preliminary thermal control system has been designed and the sensitivity of module optical performance to various thermal loads has been determined using optomechanical analysis methods developed for this unique assembly. This design and analysis furthers the goal of building a module that demonstrates the ability to meet IXO requirements, which is the current focus of IXO FMA technology development team.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"104 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128021923","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446745
Jane Hansen, P. Graven
Over the past 7 years, the term “responsive space” has come into common use, yet the definition, the implementation approach, and the key mission applications are still in flux. Most will agree that responsive implies being able to respond in the near-term to changing world events and to meet the near-term needs of the warfighter. However, the definition of near-term, especially when applied to spacecraft, is not generally agreed to. Responsive spacecraft can be created in days, as described by AFRL with their 6-day spacecraft that makes extensive use of plug-and-play (PnP) technologies, or in weeks to months, as required by ORS Tier II, through rapid integration of readily available components and subsystems. In general, for a spacecraft to be available responsively, some elements of the vehicle must be “built-to-inventory”, such that the spacecraft can be constructed from off-the-shelf components and rapidly integrated into a launch ready spacecraft. Again, there are differing opinions as to the granularity of the built-to-inventory components: 1) complete, ready-to-fly spacecraft, 2) spacecraft busses and payloads held separately in inventory, 3) functional subsystem elements combined to create functional services, then stocked on shelves and snapped together to create a complete spacecraft, or 4) lower-level components being rapidly assembled with the aid of a configuration wizard that determines the parts that are needed to create a spacecraft that will meet specific mission requirements. In any of these scenarios, there are a few technologies, that when used together, will enhance the success of responsive space. These technologies include the use of PnP interfaces, machine parsable interface control documentation (ICDs), and the creation of self-configuring and/or re-configuring networks. This paper will address the approach explored by Microcosm, with partner HRP Systems, to have Guidance, Navigation, and Control (GN&C) components available in a hierarchical fashion, as a turn-key subsystem or services, or as the lowest level, individual components, to respond to the near-term needs of the warfighter. 1 2
{"title":"A hierarchy of Guidance, Navigation, and Control elements for responsive space missions","authors":"Jane Hansen, P. Graven","doi":"10.1109/AERO.2010.5446745","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446745","url":null,"abstract":"Over the past 7 years, the term “responsive space” has come into common use, yet the definition, the implementation approach, and the key mission applications are still in flux. Most will agree that responsive implies being able to respond in the near-term to changing world events and to meet the near-term needs of the warfighter. However, the definition of near-term, especially when applied to spacecraft, is not generally agreed to. Responsive spacecraft can be created in days, as described by AFRL with their 6-day spacecraft that makes extensive use of plug-and-play (PnP) technologies, or in weeks to months, as required by ORS Tier II, through rapid integration of readily available components and subsystems. In general, for a spacecraft to be available responsively, some elements of the vehicle must be “built-to-inventory”, such that the spacecraft can be constructed from off-the-shelf components and rapidly integrated into a launch ready spacecraft. Again, there are differing opinions as to the granularity of the built-to-inventory components: 1) complete, ready-to-fly spacecraft, 2) spacecraft busses and payloads held separately in inventory, 3) functional subsystem elements combined to create functional services, then stocked on shelves and snapped together to create a complete spacecraft, or 4) lower-level components being rapidly assembled with the aid of a configuration wizard that determines the parts that are needed to create a spacecraft that will meet specific mission requirements. In any of these scenarios, there are a few technologies, that when used together, will enhance the success of responsive space. These technologies include the use of PnP interfaces, machine parsable interface control documentation (ICDs), and the creation of self-configuring and/or re-configuring networks. This paper will address the approach explored by Microcosm, with partner HRP Systems, to have Guidance, Navigation, and Control (GN&C) components available in a hierarchical fashion, as a turn-key subsystem or services, or as the lowest level, individual components, to respond to the near-term needs of the warfighter. 1 2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125547091","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446677
R. Barton, T. F. Kennedy, Robert M. Williams, P. Fink, P. Ngo, R. Ingle
We consider the problem of simultaneous detection, identification, location estimation, and remote sensing for multiple objects in an environment. In particular, we describe the design and performance of a system capable of simultaneously detecting the presence of multiple objects, identifying each object, and acquiring both a low-resolution estimate of location and a high-resolution estimate of temperature for each object based on wireless interrogation of passive surface acoustic wave (SAW) radio-frequency identification (RFID) sensor tags affixed to each object. The system is being studied for application on the lunar surface as well as for terrestrial remote sensing applications such as pre-launch monitoring and testing of spacecraft on the launch pad and monitoring of test facilities. The system utilizes a digitally beam-formed planar receiving antenna array to extend range and provide direction-of-arrival information coupled with an approximate maximum-likelihood signal processing algorithm to provide near-optimal estimation of both range and temperature. We examine the theoretical performance characteristics of the system and compare the theoretical results with results obtained from controlled laboratory experiments.1,2
{"title":"Detection, identification, location, and remote sensing using SAW RFID sensor tags","authors":"R. Barton, T. F. Kennedy, Robert M. Williams, P. Fink, P. Ngo, R. Ingle","doi":"10.1109/AERO.2010.5446677","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446677","url":null,"abstract":"We consider the problem of simultaneous detection, identification, location estimation, and remote sensing for multiple objects in an environment. In particular, we describe the design and performance of a system capable of simultaneously detecting the presence of multiple objects, identifying each object, and acquiring both a low-resolution estimate of location and a high-resolution estimate of temperature for each object based on wireless interrogation of passive surface acoustic wave (SAW) radio-frequency identification (RFID) sensor tags affixed to each object. The system is being studied for application on the lunar surface as well as for terrestrial remote sensing applications such as pre-launch monitoring and testing of spacecraft on the launch pad and monitoring of test facilities. The system utilizes a digitally beam-formed planar receiving antenna array to extend range and provide direction-of-arrival information coupled with an approximate maximum-likelihood signal processing algorithm to provide near-optimal estimation of both range and temperature. We examine the theoretical performance characteristics of the system and compare the theoretical results with results obtained from controlled laboratory experiments.1,2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"75 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134311164","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446827
J. Reimann, G. Kacprzynski
This paper outlines an Adaptive Kernel-based Bayesian Inference regression/classification technique that can be applied to a broad range of problems due to the scalable nature of the approach. 12 In addition, the framework is built such that little manual adjustment of the classifier is needed when applying it to new problems thereby ensuring that the classifier can be readily applied to problems without time consuming customization. To test the performance of the framework it was applied to two very different classification problems; namely, a bearing health classification problem and a sonar image classification problem. The performance of the approach is very promising; however, further tests must be performed on larger data collections to truly gauge the overall scalability and performance.
{"title":"An Adaptive Kernel-based Bayesian Inference technique for failure classification","authors":"J. Reimann, G. Kacprzynski","doi":"10.1109/AERO.2010.5446827","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446827","url":null,"abstract":"This paper outlines an Adaptive Kernel-based Bayesian Inference regression/classification technique that can be applied to a broad range of problems due to the scalable nature of the approach. 12 In addition, the framework is built such that little manual adjustment of the classifier is needed when applying it to new problems thereby ensuring that the classifier can be readily applied to problems without time consuming customization. To test the performance of the framework it was applied to two very different classification problems; namely, a bearing health classification problem and a sonar image classification problem. The performance of the approach is very promising; however, further tests must be performed on larger data collections to truly gauge the overall scalability and performance.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131492838","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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