Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446898
C. Liebe, J. Burnham, R. Cook, B. Craig, T. Decker, D. Harp, B. Kecman, P. Meras, Michael Raffanti, C. Scholz, Christopher Smith, Jeff Waldman, James Wu
A metrology system designed and built for the NuSTAR mission is described. The NuSTAR mission is an orbiting X-ray telescope with a 10 meter focal length. The system consists of two laser pointers mounted rigidly together with a star tracker and the X-ray optics. The focused laser beams illuminates two metrology detectors mounted rigidly with the X-ray detectors. The detectors and optics/lasers are separated by a ∼10 meter deployable (and somewhat flexible) carbon fiber mast. Details about the implementation of the metrology system is discussed in this paper. 12
{"title":"Metrology system for measuring mast motions on the NuSTAR mission","authors":"C. Liebe, J. Burnham, R. Cook, B. Craig, T. Decker, D. Harp, B. Kecman, P. Meras, Michael Raffanti, C. Scholz, Christopher Smith, Jeff Waldman, James Wu","doi":"10.1109/AERO.2010.5446898","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446898","url":null,"abstract":"A metrology system designed and built for the NuSTAR mission is described. The NuSTAR mission is an orbiting X-ray telescope with a 10 meter focal length. The system consists of two laser pointers mounted rigidly together with a star tracker and the X-ray optics. The focused laser beams illuminates two metrology detectors mounted rigidly with the X-ray detectors. The detectors and optics/lasers are separated by a ∼10 meter deployable (and somewhat flexible) carbon fiber mast. Details about the implementation of the metrology system is discussed in this paper. 12","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"18 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":"123710438","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.2010.5446807
E. Pastor, Marc Solé, Juan López, P. Royo, C. Barrado
This work introduces a flexible and reusable architecture designed to facilitate the development of remote sensing applications. Based on it, we are developing a helicopter system, called Red-Eye, devoted to the detection, control and analysis of wild land forest fires in the Mediterranean area. The design of the proposed system is composed of five main components. Each component will work collaboratively to constitute a platform of high added value. The general architecture designed for wildfire monitoring is being tailored for two relevant objectives within the particular Mediterranean scenario: tactical day/night fire front evolution, and post-fire hot-spot detection.
{"title":"Helicopter-based wildfire monitoring system software architecture","authors":"E. Pastor, Marc Solé, Juan López, P. Royo, C. Barrado","doi":"10.1109/AERO.2010.5446807","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446807","url":null,"abstract":"This work introduces a flexible and reusable architecture designed to facilitate the development of remote sensing applications. Based on it, we are developing a helicopter system, called Red-Eye, devoted to the detection, control and analysis of wild land forest fires in the Mediterranean area. The design of the proposed system is composed of five main components. Each component will work collaboratively to constitute a platform of high added value. The general architecture designed for wildfire monitoring is being tailored for two relevant objectives within the particular Mediterranean scenario: tactical day/night fire front evolution, and post-fire hot-spot detection.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"28 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":"122056068","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.2010.5446833
M. Azam, S. Ghoshal, S. Dixit, M. Pecht
A major issue in system health forecasting emanates from the necessity of transforming instantaneous (fast time scale) health condition and/or performance related observations into slow time-scale estimates. Slow time-scale transformation refers to aggregation of information from observations within a time interval, and assigning a representative state or symbol to the whole interval. The sequence of such symbols can be used to track and forecast system performance/health condition in a reliable way. Symbolic time series analysis (STSA) that employs an entropy maximization approach towards observation partitioning and symbol assignment has been proven quite useful for this purpose. This paper presents an STSA based approach for forecasting performance/health conditions of complex electronic systems using outlier removal and information fusion based pre-processing, and non-linear dynamic Markov model-based post-processing schemes. The dynamic Markov model computes the probability of observing a word that is present in symbolic time series. The probability of transition from one state to another is estimated by traversing through the symbolic series transition probabilities. Thereby, a discrete state transition model is obtained that can serve as the estimator of a system's behavior (in terms of health or performance) over time. An advantage of Markov model is that it extends naturally to forecast the performance/health states and estimates the Remaining Useful Life (RUL). Under this work, a STSA-based forecasting scheme was developed and validated on a set of automotive GPS1,2.
{"title":"Symbolic time series analysis based health condition forecasting in complex electronic systems","authors":"M. Azam, S. Ghoshal, S. Dixit, M. Pecht","doi":"10.1109/AERO.2010.5446833","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446833","url":null,"abstract":"A major issue in system health forecasting emanates from the necessity of transforming instantaneous (fast time scale) health condition and/or performance related observations into slow time-scale estimates. Slow time-scale transformation refers to aggregation of information from observations within a time interval, and assigning a representative state or symbol to the whole interval. The sequence of such symbols can be used to track and forecast system performance/health condition in a reliable way. Symbolic time series analysis (STSA) that employs an entropy maximization approach towards observation partitioning and symbol assignment has been proven quite useful for this purpose. This paper presents an STSA based approach for forecasting performance/health conditions of complex electronic systems using outlier removal and information fusion based pre-processing, and non-linear dynamic Markov model-based post-processing schemes. The dynamic Markov model computes the probability of observing a word that is present in symbolic time series. The probability of transition from one state to another is estimated by traversing through the symbolic series transition probabilities. Thereby, a discrete state transition model is obtained that can serve as the estimator of a system's behavior (in terms of health or performance) over time. An advantage of Markov model is that it extends naturally to forecast the performance/health states and estimates the Remaining Useful Life (RUL). Under this work, a STSA-based forecasting scheme was developed and validated on a set of automotive GPS1,2.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"31 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114060005","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.2010.5446760
J. Ziemer, T. Randolph, G. Franklin, V. Hruby, D. Spence, N. Demmons, T. Roy, E. Ehrbar, J. Zwahlen, Roy Martin, W. Connolly
Two flight-qualified clusters of four Colloid Micro-Newton Thruster (CMNT) systems have been delivered to the Jet Propulsion Laboratory (JPL) and subsequently delivered to ESA for spacecraft integration. The clusters will provide precise spacecraft control for the drag-free technology demonstration mission, Space Technology 7 (ST7). The ST7 mission is sponsored by the NASA New Millennium Program and will demonstrate precision formation flying technologies for future missions such as the Laser Interferometer Space Antenna (LISA) mission. The ST7 disturbance reduction system (DRS) is a payload on the ESA LISA Pathfinder spacecraft along with the European gravitational reference sensor (GRS) as part of the ESA LISA Technology Package (LTP). To achieve the nanometer-level precision spacecraft control requirements, each of eight thruster systems is required to provide thrust between 5 and 30 µN with resolution ≤0.1 µN and thrust noise ≤0.1 µN/vHz. Developed by Busek Co. Inc., with support from JPL in design and testing, the CMNT has been developed over the last six years into a flight-ready and flight-qualified microthruster system, the first of its kind. Recent flight-unit qualification tests have included vibration and thermal vacuum environmental testing, as well as performance verification and acceptance tests. All tests have been completed successfully prior to delivery to JPL. Delivery of the first flight unit occurred in February of 2008 with the second unit following in May of 2008. Since arrival at JPL, the units have successfully passed through mass distribution, magnetic, and EMI/EMC measurements and tests as part of the integration and test (I&T) activities including the integrated avionics unit (IAU). Flight software sequences have been tested and validated with the full flight DRS instrument successfully to the extent possible in ground testing, including full functional and 72 hour autonomous operations tests. In the summer of 2009 the cluster assemblies were delivered to ESA along with the IAU for integration into the LISA Pathfinder spacecraft. Spacecraft-level testing will include magnetics, acoustic, and thermal vacuum environmental testing with a planned launch and flight demonstration in April 2012. 1 2
{"title":"Colloid Micro-Newton Thrusters for the space technology 7 mission","authors":"J. Ziemer, T. Randolph, G. Franklin, V. Hruby, D. Spence, N. Demmons, T. Roy, E. Ehrbar, J. Zwahlen, Roy Martin, W. Connolly","doi":"10.1109/AERO.2010.5446760","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446760","url":null,"abstract":"Two flight-qualified clusters of four Colloid Micro-Newton Thruster (CMNT) systems have been delivered to the Jet Propulsion Laboratory (JPL) and subsequently delivered to ESA for spacecraft integration. The clusters will provide precise spacecraft control for the drag-free technology demonstration mission, Space Technology 7 (ST7). The ST7 mission is sponsored by the NASA New Millennium Program and will demonstrate precision formation flying technologies for future missions such as the Laser Interferometer Space Antenna (LISA) mission. The ST7 disturbance reduction system (DRS) is a payload on the ESA LISA Pathfinder spacecraft along with the European gravitational reference sensor (GRS) as part of the ESA LISA Technology Package (LTP). To achieve the nanometer-level precision spacecraft control requirements, each of eight thruster systems is required to provide thrust between 5 and 30 µN with resolution ≤0.1 µN and thrust noise ≤0.1 µN/vHz. Developed by Busek Co. Inc., with support from JPL in design and testing, the CMNT has been developed over the last six years into a flight-ready and flight-qualified microthruster system, the first of its kind. Recent flight-unit qualification tests have included vibration and thermal vacuum environmental testing, as well as performance verification and acceptance tests. All tests have been completed successfully prior to delivery to JPL. Delivery of the first flight unit occurred in February of 2008 with the second unit following in May of 2008. Since arrival at JPL, the units have successfully passed through mass distribution, magnetic, and EMI/EMC measurements and tests as part of the integration and test (I&T) activities including the integrated avionics unit (IAU). Flight software sequences have been tested and validated with the full flight DRS instrument successfully to the extent possible in ground testing, including full functional and 72 hour autonomous operations tests. In the summer of 2009 the cluster assemblies were delivered to ESA along with the IAU for integration into the LISA Pathfinder spacecraft. Spacecraft-level testing will include magnetics, acoustic, and thermal vacuum environmental testing with a planned launch and flight demonstration in April 2012. 1 2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"406 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":"122858597","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.2010.5447035
Daniel L. Brown, B. Beal, J. Haas
Space solar power generation systems have a significant impact on Electric Propulsion (EP) technology development.1,2,3 Recent advances in solar cell, deployment, and concentrator hardware have led to significant reductions in component mass, thereby decreasing power generation system specific mass. Combined with maneuvering requirements for Air Force and DoD missions of interest, propulsive requirements emerge that provide direction for technology investments. Projections for near- to mid-term propulsion capabilities are presented indicating the need for thrusters capable of processing larger amounts of power (100 – 200 kW), operating at relatively moderate specific impulse (2000 – 6000 seconds) and high efficiency (≫ 60%), and having low propulsion system mass (≪ 1 kg/kW). Two technology areas are identified and discussed in the context of the above thruster constraints. Concentric channel Hall thrusters are an extension of a mature technology, offering operation over expanded power levels and lower propulsion system specific mass at state-of-the-art (SOTA) efficiencies. Field Reverse Configuration (FRC) thrusters are a specific type of pulsed inductive accelerator that have the potential to operate up to MW power levels, at propulsion system specific masses even lower than concentric channel Hall thrusters, and on a wider range of propellants. However, FRCs are currently less mature than the Hall thruster variants. Comparisons of candidate technologies are evaluated with VASIMR, a well publicized high power EP device currently under development.
{"title":"Air Force Research Laboratory high power electric propulsion technology development","authors":"Daniel L. Brown, B. Beal, J. Haas","doi":"10.1109/AERO.2010.5447035","DOIUrl":"https://doi.org/10.1109/AERO.2010.5447035","url":null,"abstract":"Space solar power generation systems have a significant impact on Electric Propulsion (EP) technology development.1,2,3 Recent advances in solar cell, deployment, and concentrator hardware have led to significant reductions in component mass, thereby decreasing power generation system specific mass. Combined with maneuvering requirements for Air Force and DoD missions of interest, propulsive requirements emerge that provide direction for technology investments. Projections for near- to mid-term propulsion capabilities are presented indicating the need for thrusters capable of processing larger amounts of power (100 – 200 kW), operating at relatively moderate specific impulse (2000 – 6000 seconds) and high efficiency (≫ 60%), and having low propulsion system mass (≪ 1 kg/kW). Two technology areas are identified and discussed in the context of the above thruster constraints. Concentric channel Hall thrusters are an extension of a mature technology, offering operation over expanded power levels and lower propulsion system specific mass at state-of-the-art (SOTA) efficiencies. Field Reverse Configuration (FRC) thrusters are a specific type of pulsed inductive accelerator that have the potential to operate up to MW power levels, at propulsion system specific masses even lower than concentric channel Hall thrusters, and on a wider range of propellants. However, FRCs are currently less mature than the Hall thruster variants. Comparisons of candidate technologies are evaluated with VASIMR, a well publicized high power EP device currently under development.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"60 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":"125561774","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.2010.5446752
C. Calle, C. Buhler, M. Hogue, M. R. Johansen, N.J. Van Suetendael, A. Chen, S. O. Case, S. Snyder, J. S. Clements, J. Moebus, J. Miller, N. D. Cox, S. Irwin
Dust buildup on thermal radiating surfaces can reduce the efficiencies at which thermal energy can be radiated away during lunar exploration missions.1−2 To mitigate this problem, prototype Electrodynamic Dust Shields (EDS) capable of removing accumulated dust and of preventing dust accumulation have been constructed and tested. The EDS, an active dust mitigation technology for lunar exploration systems, has been under development in our laboratory at the Kennedy Space Center for the last several years. The EDS uses electrostatic and dielectrophoretic forces to remove dust from opaque, transparent, rigid, and flexible surfaces. The EDS consists of an array of electrodes on a substrate that are coated with a material possessing a high dielectric constant. The EDS has been tested with JSC-1A lunar dust simulant and with Apollo 16 samples at high vacuum pressures of the order of 10−6 kPa. In this paper, we report on the development of two types of prototype dust shields for thermal radiators. For the first prototype, the EDS electrode grid was vapor-deposited on a polyimide-coated aluminum coupon. AZ-93, a space-rated thermal paint was applied as the top coating for the thermal radiator. For the second prototype, silver electrode grids were sputtered onto fluorethylene polypropylene (FEP) films that were back coated with an aluminum layer. These prototypes were tested with JSC-1A lunar dust stimulant at 10−6 kPa.
{"title":"Development of a dust mitigation technology for thermal radiators for lunar exploration","authors":"C. Calle, C. Buhler, M. Hogue, M. R. Johansen, N.J. Van Suetendael, A. Chen, S. O. Case, S. Snyder, J. S. Clements, J. Moebus, J. Miller, N. D. Cox, S. Irwin","doi":"10.1109/AERO.2010.5446752","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446752","url":null,"abstract":"Dust buildup on thermal radiating surfaces can reduce the efficiencies at which thermal energy can be radiated away during lunar exploration missions.1−2 To mitigate this problem, prototype Electrodynamic Dust Shields (EDS) capable of removing accumulated dust and of preventing dust accumulation have been constructed and tested. The EDS, an active dust mitigation technology for lunar exploration systems, has been under development in our laboratory at the Kennedy Space Center for the last several years. The EDS uses electrostatic and dielectrophoretic forces to remove dust from opaque, transparent, rigid, and flexible surfaces. The EDS consists of an array of electrodes on a substrate that are coated with a material possessing a high dielectric constant. The EDS has been tested with JSC-1A lunar dust simulant and with Apollo 16 samples at high vacuum pressures of the order of 10−6 kPa. In this paper, we report on the development of two types of prototype dust shields for thermal radiators. For the first prototype, the EDS electrode grid was vapor-deposited on a polyimide-coated aluminum coupon. AZ-93, a space-rated thermal paint was applied as the top coating for the thermal radiator. For the second prototype, silver electrode grids were sputtered onto fluorethylene polypropylene (FEP) films that were back coated with an aluminum layer. These prototypes were tested with JSC-1A lunar dust stimulant at 10−6 kPa.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"40 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":"129854215","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}
Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446682
F. Reali, G. Palmerini, A. Farina, A. Graziano, S. Giompapa, B. Parisi
Radar tracking of a projectile flying in the Earth's atmosphere is a very complex issue to cope with, due to the need of (suboptimal) nonlinear filtering techniques. Almost all cases found in literature assume that the target trajectory is observable from the firing point to the impact point on the ground, namely the trajectory observation gets under way from the first available measurement. The radar track initiation time is actually a stochastic quantity that has to be treated by means of a statistical procedure. In this paper a preliminary analysis of the effect of a more realistic filter initialization is proposed12.
{"title":"Initialization of ballistic targets tracking filters with detection probability lower than unity","authors":"F. Reali, G. Palmerini, A. Farina, A. Graziano, S. Giompapa, B. Parisi","doi":"10.1109/AERO.2010.5446682","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446682","url":null,"abstract":"Radar tracking of a projectile flying in the Earth's atmosphere is a very complex issue to cope with, due to the need of (suboptimal) nonlinear filtering techniques. Almost all cases found in literature assume that the target trajectory is observable from the firing point to the impact point on the ground, namely the trajectory observation gets under way from the first available measurement. The radar track initiation time is actually a stochastic quantity that has to be treated by means of a statistical procedure. In this paper a preliminary analysis of the effect of a more realistic filter initialization is proposed12.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"43 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":"115960503","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.2010.5446775
J. Ludwig, R. Richards
The US Navy's PMA-205, in conjunction with the training and simulation industry, has developed and deployed OMIA: a flexible, multi-platform, Web-based crew trainer for the Navy's new MH-60S and MH-60R helicopters. 12OMIA is currently in use by HSC-2, HSC-3 and HSM-41 and is available to all crewmembers throughout the Navy. To maximize access to the trainer and to make deployment easier, OMIA is written in Java, and deployed both as a portable application and as a web application. A portable application does not require any special user rights to install; a web application is run over the internet from a browser. OMIA includes a simulation of the MH-60S/R Common Cockpit, including a FLIR capability that includes using an actual hardware FLIR hand-control unit when attached through USB. OMIA has been designed and implemented to be flexible to changing Navy needs, a design aspect which proved itself again in 2009 when OMIA's FLIR was converted for use in the fixed wing EP-3E aircraft. OMIA illustrates solutions to three critical issues in developing low-cost training software for aircraft: quickly responding to the ever-changing demands, re-use of interface components across multiple aircraft, and providing training that can be accessed where and when it is needed.
{"title":"MH60S/R helicopter multi-platform & Web-based crew trainer with FLIR","authors":"J. Ludwig, R. Richards","doi":"10.1109/AERO.2010.5446775","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446775","url":null,"abstract":"The US Navy's PMA-205, in conjunction with the training and simulation industry, has developed and deployed OMIA: a flexible, multi-platform, Web-based crew trainer for the Navy's new MH-60S and MH-60R helicopters. 12OMIA is currently in use by HSC-2, HSC-3 and HSM-41 and is available to all crewmembers throughout the Navy. To maximize access to the trainer and to make deployment easier, OMIA is written in Java, and deployed both as a portable application and as a web application. A portable application does not require any special user rights to install; a web application is run over the internet from a browser. OMIA includes a simulation of the MH-60S/R Common Cockpit, including a FLIR capability that includes using an actual hardware FLIR hand-control unit when attached through USB. OMIA has been designed and implemented to be flexible to changing Navy needs, a design aspect which proved itself again in 2009 when OMIA's FLIR was converted for use in the fixed wing EP-3E aircraft. OMIA illustrates solutions to three critical issues in developing low-cost training software for aircraft: quickly responding to the ever-changing demands, re-use of interface components across multiple aircraft, and providing training that can be accessed where and when it is needed.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"29 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":"116177311","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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