Pub Date : 2007-03-03DOI: 10.1109/AERO.2007.352935
G. Mayhew
Order n de Bruijn sequences are the period 2n binary sequences from n-stage feedback shift registers. The de Bruijn sequences have good randomness and complexity properties. The number of de Bruijn sequences in a weight class of the order n generating functions is unknown for all but the smallest n. This paper posts the final results for weight class 47 and intermediate results for weight class 21 of the order 7 de Bruijn sequences.
{"title":"Third Update to the Order 7 de Bruijn Weight Class Distribution","authors":"G. Mayhew","doi":"10.1109/AERO.2007.352935","DOIUrl":"https://doi.org/10.1109/AERO.2007.352935","url":null,"abstract":"Order n de Bruijn sequences are the period 2n binary sequences from n-stage feedback shift registers. The de Bruijn sequences have good randomness and complexity properties. The number of de Bruijn sequences in a weight class of the order n generating functions is unknown for all but the smallest n. This paper posts the final results for weight class 47 and intermediate results for weight class 21 of the order 7 de Bruijn sequences.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"241 1","pages":"1-6"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"75780707","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 : 2007-03-03DOI: 10.1109/AERO.2007.352645
B. Bauer, W. M. Reid
New Horizons is a NASA sponsored mission to explore Pluto and its largest moon Charon. The New Horizons spacecraft, designed, built and operated by the Johns Hopkins University Applied Physics Laboratory (APL), was successfully launched in January 2006. New Horizon's closest encounter with Pluto will occur in the summer of 2015. Upon completion of its primary science objectives at the Pluto encounter, the spacecraft is expected to visit one or more Kuiper Belt objects in the outermost region of the solar system. This long duration mission requires high reliability and imposes some demanding fault management requirements upon the spacecraft. The spacecraft is highly redundant with onboard software that provides a rule based expert system for performing autonomous fault detection and recovery. Generally referred to as Autonomy, this software's design was largely driven by two factors, the concept of operations for the mission and the level of redundancy in the spacecraft hardware. This paper examines the unique mission requirements that drove the Autonomy design. It discusses how the Autonomy system supports all of the various phases of the mission and provides examples of how unique mission requirements of the New Horizons mission were implemented.
{"title":"Automating the Pluto Experience: An Examination of the New Horizons Autonomous Operations Subsystem","authors":"B. Bauer, W. M. Reid","doi":"10.1109/AERO.2007.352645","DOIUrl":"https://doi.org/10.1109/AERO.2007.352645","url":null,"abstract":"New Horizons is a NASA sponsored mission to explore Pluto and its largest moon Charon. The New Horizons spacecraft, designed, built and operated by the Johns Hopkins University Applied Physics Laboratory (APL), was successfully launched in January 2006. New Horizon's closest encounter with Pluto will occur in the summer of 2015. Upon completion of its primary science objectives at the Pluto encounter, the spacecraft is expected to visit one or more Kuiper Belt objects in the outermost region of the solar system. This long duration mission requires high reliability and imposes some demanding fault management requirements upon the spacecraft. The spacecraft is highly redundant with onboard software that provides a rule based expert system for performing autonomous fault detection and recovery. Generally referred to as Autonomy, this software's design was largely driven by two factors, the concept of operations for the mission and the level of redundancy in the spacecraft hardware. This paper examines the unique mission requirements that drove the Autonomy design. It discusses how the Autonomy system supports all of the various phases of the mission and provides examples of how unique mission requirements of the New Horizons mission were implemented.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"78 1","pages":"1-10"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"74496334","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 : 2007-03-03DOI: 10.1109/AERO.2007.352684
D. Helmick, A. Angelova, M. Livianu, L. Matthies
A navigation system for Mars rovers in very rough terrain has been designed, implemented, and tested on a research rover in Mars analog terrain. This navigation system consists of several technologies that are integrated to increase the capabilities compared to current rover navigation algorithms. These technologies include: goodness maps and terrain triage, terrain classification, remote slip prediction, path planning, high-fidelity traversability analysis (HFTA), and slip-compensated path following. The focus of this paper is not on the component technologies, but rather on the integration of these components. Results from the onboard integration of several of the key technologies described here are shown. Additionally, the results from independent demonstrations of several of these technologies are shown. Future work will include the demonstration of the entire integrated system.
{"title":"Terrain Adaptive Navigation for Mars Rovers","authors":"D. Helmick, A. Angelova, M. Livianu, L. Matthies","doi":"10.1109/AERO.2007.352684","DOIUrl":"https://doi.org/10.1109/AERO.2007.352684","url":null,"abstract":"A navigation system for Mars rovers in very rough terrain has been designed, implemented, and tested on a research rover in Mars analog terrain. This navigation system consists of several technologies that are integrated to increase the capabilities compared to current rover navigation algorithms. These technologies include: goodness maps and terrain triage, terrain classification, remote slip prediction, path planning, high-fidelity traversability analysis (HFTA), and slip-compensated path following. The focus of this paper is not on the component technologies, but rather on the integration of these components. Results from the onboard integration of several of the key technologies described here are shown. Additionally, the results from independent demonstrations of several of these technologies are shown. Future work will include the demonstration of the entire integrated system.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"66 1","pages":"1-11"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"75396053","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 : 2007-03-03DOI: 10.1109/AERO.2007.352911
Y. Macheret, P. Koehn
Evaluating risk of aircraft failure is necessary for scheduling appropriate maintenance, avoiding aircraft losses and mission failures, maintaining a high level of readiness, and estimating aircraft fleet aging. This paper presents the results of calculating aircraft failure risk by estimating the probability of structural failure of F-18 wing attachment bulkheads. Laboratory fatigue-crack growth-test data (published in open literature) are utilized to describe the distribution of initial defects, which is then evolved as a function of applied loads and flight hours. The risk is calculated as a probability of failure (POF) during a single flight, and it is shown that the effect of uncertainty in the knowledge of applied flight loads on POF is significant. The reported results provide a framework for evaluating benefits of improving accuracy of load-monitoring data and POF.
{"title":"Effect of Improving Accuracy of Load Monitoring on Aircraft Probability of Failure","authors":"Y. Macheret, P. Koehn","doi":"10.1109/AERO.2007.352911","DOIUrl":"https://doi.org/10.1109/AERO.2007.352911","url":null,"abstract":"Evaluating risk of aircraft failure is necessary for scheduling appropriate maintenance, avoiding aircraft losses and mission failures, maintaining a high level of readiness, and estimating aircraft fleet aging. This paper presents the results of calculating aircraft failure risk by estimating the probability of structural failure of F-18 wing attachment bulkheads. Laboratory fatigue-crack growth-test data (published in open literature) are utilized to describe the distribution of initial defects, which is then evolved as a function of applied loads and flight hours. The risk is calculated as a probability of failure (POF) during a single flight, and it is shown that the effect of uncertainty in the knowledge of applied flight loads on POF is significant. The reported results provide a framework for evaluating benefits of improving accuracy of load-monitoring data and POF.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"25 1","pages":"1-7"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"78755174","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 : 2007-03-03DOI: 10.1109/AERO.2007.352700
Rebecca Castaño, T. Estlin, D. Gaines, C. Chouinard, B. Bornstein, Robert C. Anderson, Michael Burl, David Thompson, A. Castano, M. Judd
The Onboard Autonomous Science Investigation System (OASIS) was used in the first formal demonstration of closed loop opportunistic detection and reaction during a rover traverse on the FIDO rover at NASA's Jet Propulsion Laboratory. In addition to hardware demonstrations, the system has been demonstrated and exercised in simulation using the Rover Analysis, Modeling, and Simulation (ROAMS) planetary rover simulator, A. Jain et al (2003). We discuss several system enhancements including new planning and scheduling capabilities and image prioritization. We also describe the new end-of-traverse capability that includes taking a partial panorama of images, assessing these for targets of interest, and collecting narrow angle images of selected targets. Finally, we present several methods for estimating properties of rocks and provide a comparative assessment. Understanding the relationship of these methods is important to correctly interpret autonomous rock analyses performed during a traverse.
在NASA喷气推进实验室的FIDO漫游车上，机载自主科学调查系统(OASIS)在漫游车上进行了闭环机会探测和反应的首次正式演示。除了硬件演示外，该系统还在漫游车分析、建模和仿真(ROAMS)行星漫游车模拟器(A. Jain et al .， 2003)中进行了演示和仿真。我们讨论了几个系统增强功能，包括新的计划和调度功能以及图像优先级。我们还描述了新的遍历结束功能，包括拍摄图像的部分全景，评估感兴趣的目标，以及收集选定目标的窄角度图像。最后，我们提出了几种估计岩石性质的方法，并进行了比较评估。了解这些方法之间的关系对于正确解释在遍历过程中进行的自主岩石分析非常重要。
{"title":"Onboard Autonomous Rover Science","authors":"Rebecca Castaño, T. Estlin, D. Gaines, C. Chouinard, B. Bornstein, Robert C. Anderson, Michael Burl, David Thompson, A. Castano, M. Judd","doi":"10.1109/AERO.2007.352700","DOIUrl":"https://doi.org/10.1109/AERO.2007.352700","url":null,"abstract":"The Onboard Autonomous Science Investigation System (OASIS) was used in the first formal demonstration of closed loop opportunistic detection and reaction during a rover traverse on the FIDO rover at NASA's Jet Propulsion Laboratory. In addition to hardware demonstrations, the system has been demonstrated and exercised in simulation using the Rover Analysis, Modeling, and Simulation (ROAMS) planetary rover simulator, A. Jain et al (2003). We discuss several system enhancements including new planning and scheduling capabilities and image prioritization. We also describe the new end-of-traverse capability that includes taking a partial panorama of images, assessing these for targets of interest, and collecting narrow angle images of selected targets. Finally, we present several methods for estimating properties of rocks and provide a comparative assessment. Understanding the relationship of these methods is important to correctly interpret autonomous rock analyses performed during a traverse.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"37 1","pages":"1-13"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"78033204","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 : 2007-03-03DOI: 10.1109/AERO.2007.352924
K. Alemany, E. Morse, R. Easter
In order to return humans to the Moon, the constellation program will be required to operate a complex network of humans and spacecraft in several locations. This requires an early look at how decision-making authority will be allocated and transferred between humans and computers, for each of the many decision steps required for the various mission phases. This paper presents an overview of such a control authority analysis, along with an example based upon a lunar outpost deployment scenario. The results illustrate how choosing an optimal control authority architecture can serve to significantly reduce overall mission risk, when applied early in the design process.
{"title":"Control Authority Network Analysis Applied to Lunar Outpost Deployment","authors":"K. Alemany, E. Morse, R. Easter","doi":"10.1109/AERO.2007.352924","DOIUrl":"https://doi.org/10.1109/AERO.2007.352924","url":null,"abstract":"In order to return humans to the Moon, the constellation program will be required to operate a complex network of humans and spacecraft in several locations. This requires an early look at how decision-making authority will be allocated and transferred between humans and computers, for each of the many decision steps required for the various mission phases. This paper presents an overview of such a control authority analysis, along with an example based upon a lunar outpost deployment scenario. The results illustrate how choosing an optimal control authority architecture can serve to significantly reduce overall mission risk, when applied early in the design process.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"13 1","pages":"1-13"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79240095","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 : 2007-03-03DOI: 10.1109/AERO.2007.353093
M. H. Toufighi, S. Sadati, F. Najafi
Mechatronic design deals with the integrated design of a mechanical system and its embedded control system. This definition implies that it is important, as far as possible, that the system be designed as a whole. This requires a system approach to the design problem. An important aspect of mechatronic systems is that the synergy realized by a clever combination of a mechanical system and its embedded control system leads to superior solutions and performances that could not be obtained by solutions in one domain. The bond graph methodology is a convenient and useful complimentary tool for obtaining both the behavioral and the diagnostic models. Moreover, the causal properties of the bond graph methodology can help to design fault detection and isolation (FDI) algorithms. In this paper, the bond graph modeling in the interest of actuator monitoring is given. Then the method to associate the bond graph description to the model, in order to complete the equipment description, is explained.
{"title":"Modeling and Analysis of a Mechatronic Actuator System by Using Bond Graph Methodology","authors":"M. H. Toufighi, S. Sadati, F. Najafi","doi":"10.1109/AERO.2007.353093","DOIUrl":"https://doi.org/10.1109/AERO.2007.353093","url":null,"abstract":"Mechatronic design deals with the integrated design of a mechanical system and its embedded control system. This definition implies that it is important, as far as possible, that the system be designed as a whole. This requires a system approach to the design problem. An important aspect of mechatronic systems is that the synergy realized by a clever combination of a mechanical system and its embedded control system leads to superior solutions and performances that could not be obtained by solutions in one domain. The bond graph methodology is a convenient and useful complimentary tool for obtaining both the behavioral and the diagnostic models. Moreover, the causal properties of the bond graph methodology can help to design fault detection and isolation (FDI) algorithms. In this paper, the bond graph modeling in the interest of actuator monitoring is given. Then the method to associate the bond graph description to the model, in order to complete the equipment description, is explained.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"74 1","pages":"1-8"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"81276618","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 : 2007-03-03DOI: 10.1109/AERO.2007.352775
G. Mungas, C. Sepulveda, Kenneth R. Johnson, Michael Pelletier, C. L. Baw, J. Boynton, M. Anderson
Lunar ISRU precursor prospecting missions are being considered in order to characterize the lunar surface environment and to determine volatile and mineral content as well as mechanical and thermal properties of the lunar regolith for purposes of designing future excavation and In-Situ Resource Utilization (ISRU) processing equipment. The Raman/CHAMP instrument (RCI) is being developed as part of an instrument/experiment suite development project known as Regolith and Environment Science and Oxygen and Lunar Volatile Extraction (RESOLVE) being developed and sponsored under the NASA ISRU Project. The RCI supports the lunar surface characterization measurements by providing crucial field macroscopic and microscopic images coupled with Raman spectroscopy. The RCI provides the ability to collect high resolution, hand lens to field microscopy images and spectroscopic measurements from a robotic arm with the ability to resolve, characterize, and chemically differentiate >90% of lunar Apollo fines. The entire measurement process is highly adaptive and does not necessarily require any type of active sampling. In this paper we provide an overview of the RCI. We discuss the optical design optimization and analysis process for this particular type of instrument. We discuss recent results of integration tests of the Mars Microbeam Raman Spectrometer (MMRS) with the MIDP CHAMP instrument, fluorescence analysis, and individual glass fluorescence tests. Finally, we conclude with a summary of anticipated instrument measurement performance based on Zemax optical modeling of an RCI engineering model that is currently in development.
{"title":"Raman/CHAMP Instrument for Lunar In-situ Resource Prospecting I - Imager Design","authors":"G. Mungas, C. Sepulveda, Kenneth R. Johnson, Michael Pelletier, C. L. Baw, J. Boynton, M. Anderson","doi":"10.1109/AERO.2007.352775","DOIUrl":"https://doi.org/10.1109/AERO.2007.352775","url":null,"abstract":"Lunar ISRU precursor prospecting missions are being considered in order to characterize the lunar surface environment and to determine volatile and mineral content as well as mechanical and thermal properties of the lunar regolith for purposes of designing future excavation and In-Situ Resource Utilization (ISRU) processing equipment. The Raman/CHAMP instrument (RCI) is being developed as part of an instrument/experiment suite development project known as Regolith and Environment Science and Oxygen and Lunar Volatile Extraction (RESOLVE) being developed and sponsored under the NASA ISRU Project. The RCI supports the lunar surface characterization measurements by providing crucial field macroscopic and microscopic images coupled with Raman spectroscopy. The RCI provides the ability to collect high resolution, hand lens to field microscopy images and spectroscopic measurements from a robotic arm with the ability to resolve, characterize, and chemically differentiate >90% of lunar Apollo fines. The entire measurement process is highly adaptive and does not necessarily require any type of active sampling. In this paper we provide an overview of the RCI. We discuss the optical design optimization and analysis process for this particular type of instrument. We discuss recent results of integration tests of the Mars Microbeam Raman Spectrometer (MMRS) with the MIDP CHAMP instrument, fluorescence analysis, and individual glass fluorescence tests. Finally, we conclude with a summary of anticipated instrument measurement performance based on Zemax optical modeling of an RCI engineering model that is currently in development.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"46 1","pages":"1-8"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"80850391","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 : 2007-03-03DOI: 10.1109/AERO.2007.352834
J.H. MacConnell
This paper summarizes the results of the Integrated Systems Health Management Design Study, performed by Consensus Technology, LLC for the Wright Brothers Institute, Inc., under contract with The Air Force Research Labs (CPO 9012). To define the overall scope and key research areas of a possible cross technical directorate effort in Integrated Systems Health Management (ISHM), a team of health management experts from the Air Force, industry and academia was assembled to explore the design related benefits of ISHM. This team defined a set of scenarios made possible by the ideal ISHM system. These scenarios and the technologies associated with them were evaluated for their system impact, design impact, innovativeness and timeliness. The scenarios were grouped into four benefit categories and the technology needs associated with the scenarios defined. The result is a prioritized set of technology development needs linked to specific benefits and scenarios. The benefits of the ideal ISHM system were quantified from a cost and capability perspective based on the specific scenarios and data provided by the participants. The collected benefits provide a compelling rationale for pursuing the development of fully integrated ISHM design capability and the technology development defined in the study. Finally, the study developed a proposal for specific next steps, connecting the individual technology development needs with an overarching program direction and set of midterm demonstrations to support that development.
本文总结了集成系统健康管理设计研究的结果，该研究由Consensus Technology, LLC为Wright Brothers Institute, Inc.执行，并与空军研究实验室(CPO 9012)签订了合同。为了确定综合系统健康管理(ISHM)的总体范围和关键研究领域，来自空军、工业界和学术界的健康管理专家组成了一个团队，以探索ISHM设计相关的好处。该团队定义了一组由理想的ISHM系统实现的场景。对这些场景及其相关技术的系统影响、设计影响、创新性和及时性进行了评估。这些场景被分为四个利益类别，并定义了与这些场景相关的技术需求。其结果是一组与特定利益和场景相关的优先技术开发需求。基于参与者提供的具体场景和数据，从成本和能力的角度对理想的ISHM系统的收益进行了量化。所收集的利益为追求完全集成的ISHM设计能力的发展和研究中定义的技术发展提供了令人信服的理由。最后，该研究为具体的后续步骤提出了建议，将个人技术开发需求与总体计划方向和一组中期演示联系起来，以支持该开发。
{"title":"ISHM & Design: A review of the benefits of the ideal ISHM system","authors":"J.H. MacConnell","doi":"10.1109/AERO.2007.352834","DOIUrl":"https://doi.org/10.1109/AERO.2007.352834","url":null,"abstract":"This paper summarizes the results of the Integrated Systems Health Management Design Study, performed by Consensus Technology, LLC for the Wright Brothers Institute, Inc., under contract with The Air Force Research Labs (CPO 9012). To define the overall scope and key research areas of a possible cross technical directorate effort in Integrated Systems Health Management (ISHM), a team of health management experts from the Air Force, industry and academia was assembled to explore the design related benefits of ISHM. This team defined a set of scenarios made possible by the ideal ISHM system. These scenarios and the technologies associated with them were evaluated for their system impact, design impact, innovativeness and timeliness. The scenarios were grouped into four benefit categories and the technology needs associated with the scenarios defined. The result is a prioritized set of technology development needs linked to specific benefits and scenarios. The benefits of the ideal ISHM system were quantified from a cost and capability perspective based on the specific scenarios and data provided by the participants. The collected benefits provide a compelling rationale for pursuing the development of fully integrated ISHM design capability and the technology development defined in the study. Finally, the study developed a proposal for specific next steps, connecting the individual technology development needs with an overarching program direction and set of midterm demonstrations to support that development.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"19 1","pages":"1-18"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"80944754","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 : 2007-03-03DOI: 10.1109/AERO.2007.352793
J. Moscola, Young-Hee Cho, J. Lockwood
We have implemented a new network information processing system using reconfigurable hardware that scans volumes of data in real-time. One of the key functions of the system is to extract semantic information. Before we can determine the meaning of text, we must identify its language. In a previous project, we have implemented an N-gram based language identifier that can process up to 1 Gbps throughput. However, a large percentage of computer network traffic, such as email and Web data, consists of markup information such as tags and protocol specific options. This additional data interferes with the language identification process causing decreased accuracy. Thus, we developed a hardware architecture for configurable application level processing. Our Application Level Processing System (ALPS) is a custom processor that is automatically generated using syntactic structure of the content. The resulting circuit is mapped on to a reconfigurable device to efficiently extract only the relevant data for the language identifier. To illustrate the effectiveness of the architecture, we have implemented a system that can process electronic mail. Our experiments show that ALPS can improve the accuracy of the hardware language identifier by up to a factor of 200 as compared to a system that does not decode the application-level protocol data.
{"title":"Hardware-Accelerated Parser for Extraction of Metadata in Semantic Network Content","authors":"J. Moscola, Young-Hee Cho, J. Lockwood","doi":"10.1109/AERO.2007.352793","DOIUrl":"https://doi.org/10.1109/AERO.2007.352793","url":null,"abstract":"We have implemented a new network information processing system using reconfigurable hardware that scans volumes of data in real-time. One of the key functions of the system is to extract semantic information. Before we can determine the meaning of text, we must identify its language. In a previous project, we have implemented an N-gram based language identifier that can process up to 1 Gbps throughput. However, a large percentage of computer network traffic, such as email and Web data, consists of markup information such as tags and protocol specific options. This additional data interferes with the language identification process causing decreased accuracy. Thus, we developed a hardware architecture for configurable application level processing. Our Application Level Processing System (ALPS) is a custom processor that is automatically generated using syntactic structure of the content. The resulting circuit is mapped on to a reconfigurable device to efficiently extract only the relevant data for the language identifier. To illustrate the effectiveness of the architecture, we have implemented a system that can process electronic mail. Our experiments show that ALPS can improve the accuracy of the hardware language identifier by up to a factor of 200 as compared to a system that does not decode the application-level protocol data.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"151 1","pages":"1-8"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79541767","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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