Pub Date : 2007-03-03DOI: 10.1109/AERO.2007.353037
F. Bonneton, C. Jauffret
The framework of this paper is a passive sonar system, more precisely at the core of bearing estimation and bearings-only target motion analysis (BO-TMA). A cosine of relative bearing estimation and bearings v.s. time image is first obtained by a conventional frequency-domain beam-former [D.H Johnson et al, 1993]. Computing the first two moments of each line of this image, we evaluate the likelihood of the cosine of relative bearing of the target. Then, the cosine of relative bearing and its derivative are considered as the two components of a state vector of a linear dynamic system. This state vector is then estimated (or extracted) by a classical algorithm of the hidden Markov model (HMM) arsenal, whose parameters are adjusted according to the statistical assumptions. Unlike, we consider the presence of one sole target, but the beginning and the end of the line are unknown and must be estimated too. The extracted track is used as measurements set of the BO-TMA. Finally, the confrontation of the TMA results allow us to evaluate the performance of the triplet (beam-former, bearing extraction, BO-TMA).
{"title":"Bearing Line Tracking and Bearing-Only Target Motion Analysis","authors":"F. Bonneton, C. Jauffret","doi":"10.1109/AERO.2007.353037","DOIUrl":"https://doi.org/10.1109/AERO.2007.353037","url":null,"abstract":"The framework of this paper is a passive sonar system, more precisely at the core of bearing estimation and bearings-only target motion analysis (BO-TMA). A cosine of relative bearing estimation and bearings v.s. time image is first obtained by a conventional frequency-domain beam-former [D.H Johnson et al, 1993]. Computing the first two moments of each line of this image, we evaluate the likelihood of the cosine of relative bearing of the target. Then, the cosine of relative bearing and its derivative are considered as the two components of a state vector of a linear dynamic system. This state vector is then estimated (or extracted) by a classical algorithm of the hidden Markov model (HMM) arsenal, whose parameters are adjusted according to the statistical assumptions. Unlike, we consider the presence of one sole target, but the beginning and the end of the line are unknown and must be estimated too. The extracted track is used as measurements set of the BO-TMA. Finally, the confrontation of the TMA results allow us to evaluate the performance of the triplet (beam-former, bearing extraction, BO-TMA).","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"12 1","pages":"1-9"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"87342369","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.2007.352693
Christopher A. Brooks, K. Iagnemma
Autonomous mobility in rough terrain is key to enabling increased science data return from planetary rover missions. Current terrain sensing and path planning approaches can be used to avoid geometric hazards, such as rocks and steep slopes, but are unable to remotely identify and avoid non-geometric hazards, such as loose sand in which a rover may become entrenched. This paper proposes a self-supervised classification approach to learning the visual appearance of terrain classes which relies on vibration-based sensing of wheel-terrain interaction to identify these terrain classes. Experimental results from a four-wheeled rover in Mars analog terrain demonstrate the potential for this approach.
{"title":"Self-Supervised Classification for Planetary Rover Terrain Sensing","authors":"Christopher A. Brooks, K. Iagnemma","doi":"10.1109/AERO.2007.352693","DOIUrl":"https://doi.org/10.1109/AERO.2007.352693","url":null,"abstract":"Autonomous mobility in rough terrain is key to enabling increased science data return from planetary rover missions. Current terrain sensing and path planning approaches can be used to avoid geometric hazards, such as rocks and steep slopes, but are unable to remotely identify and avoid non-geometric hazards, such as loose sand in which a rover may become entrenched. This paper proposes a self-supervised classification approach to learning the visual appearance of terrain classes which relies on vibration-based sensing of wheel-terrain interaction to identify these terrain classes. Experimental results from a four-wheeled rover in Mars analog terrain demonstrate the potential for this approach.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"42 1","pages":"1-9"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"87710288","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.2007.352701
T. Roush, R. Hogan
Existing and planned space missions to planetary and satellite surfaces produce increasing volumes of spectral data. Understanding the scientific content in this large data volume is a daunting task. Various statistical approaches are available to assess such data sets. We apply an automated classification scheme based on Kohonen Self-Organizing maps (SOM) developed originally for the thermal infrared (TIR) and extended here to the visible and near-infrared (VNIR). Available data from spectral libraries are used to train and test the classification in the VNIR. The library spectra are labeled in a hierarchical scheme with class, sub-class, and mineral group names. After training, the test spectra are presented to the SOM output layer and assigned membership to the appropriate cluster. These assignments are then evaluated to assess the robustness, scientific meaning and accuracy of the derived SOM classes as they relate to the spectral labels. We investigate the influence of particle size on our results by training and classifying three particle size separates. We find the SOM results are robust based upon the number of clusters determined from ten independent training/testing efforts. We find the SOM results are most scientifically meaningful for the grossest differences between materials, although some individual groups retain high accuracy even when the overall accuracy of the SOM is low.
{"title":"Automated Classification of Visible and Near-Infrared Spectra Using Self-Organizing Maps","authors":"T. Roush, R. Hogan","doi":"10.1109/AERO.2007.352701","DOIUrl":"https://doi.org/10.1109/AERO.2007.352701","url":null,"abstract":"Existing and planned space missions to planetary and satellite surfaces produce increasing volumes of spectral data. Understanding the scientific content in this large data volume is a daunting task. Various statistical approaches are available to assess such data sets. We apply an automated classification scheme based on Kohonen Self-Organizing maps (SOM) developed originally for the thermal infrared (TIR) and extended here to the visible and near-infrared (VNIR). Available data from spectral libraries are used to train and test the classification in the VNIR. The library spectra are labeled in a hierarchical scheme with class, sub-class, and mineral group names. After training, the test spectra are presented to the SOM output layer and assigned membership to the appropriate cluster. These assignments are then evaluated to assess the robustness, scientific meaning and accuracy of the derived SOM classes as they relate to the spectral labels. We investigate the influence of particle size on our results by training and classifying three particle size separates. We find the SOM results are robust based upon the number of clusters determined from ten independent training/testing efforts. We find the SOM results are most scientifically meaningful for the grossest differences between materials, although some individual groups retain high accuracy even when the overall accuracy of the SOM is low.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"57 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":"85987721","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.2007.352898
V. Maramreddy, O. Amadasun, V. Sarangan, J. Thomas
This paper proposes routing schemes to forward packets in deep space networks with lossy links. The proposed schemes build on the framework proposed by Clare et. al and are sensitive to the energy consumed and link error rates along a satellite link. In the presence of lossy links, it is a common practice in terrestrial networks to retransmit packets lost due to errors. However, it is not clear if such a strategy will be suitable for deep-space networks, since the long propagation delays associated with the satellite links could hinder the data transfer rate. Further, packet re-transmissions also increase the energy load on a satellite, thereby straining their limited energy reserves. This leads to the following question: "Is it worthy to retransmit packets lost due to errors in deep space networks to ensure 100% data reliability or is it sufficient to forward the packets along the path with maximum reliability without any re-transmissions?" In an attempt to answer the above question, we propose two routing schemes and compare their performance through simulations against a vanilla routing scheme in terms of energy consumption, reliability, and throughput.
{"title":"Routing In Deep-Space Satellite Networks With Lossy Links","authors":"V. Maramreddy, O. Amadasun, V. Sarangan, J. Thomas","doi":"10.1109/AERO.2007.352898","DOIUrl":"https://doi.org/10.1109/AERO.2007.352898","url":null,"abstract":"This paper proposes routing schemes to forward packets in deep space networks with lossy links. The proposed schemes build on the framework proposed by Clare et. al and are sensitive to the energy consumed and link error rates along a satellite link. In the presence of lossy links, it is a common practice in terrestrial networks to retransmit packets lost due to errors. However, it is not clear if such a strategy will be suitable for deep-space networks, since the long propagation delays associated with the satellite links could hinder the data transfer rate. Further, packet re-transmissions also increase the energy load on a satellite, thereby straining their limited energy reserves. This leads to the following question: \"Is it worthy to retransmit packets lost due to errors in deep space networks to ensure 100% data reliability or is it sufficient to forward the packets along the path with maximum reliability without any re-transmissions?\" In an attempt to answer the above question, we propose two routing schemes and compare their performance through simulations against a vanilla routing scheme in terms of energy consumption, reliability, and throughput.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"16 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":"85993725","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.2007.352856
G. Hopkins, J. Ratner, A. Traille, V. Tripp
Array antennas offer a wide range of opportunities in the variation of their directivity patterns through amplitude and phase control. Peak sidelobe levels may be reduced via amplitude control or weighting across the array aperture. Several authors have made significant contributions in detailing processes for synthesizing these aperture amplitude distributions for the purpose of sidelobe level control. One of the basic trade-offs when implementing amplitude weighting functions is that a trade between low sidelobe levels and a loss in main beam directivity always results. Some of the commercially available pattern calculation programs that can implement sidelobe level control do not provide calculations of the aperture efficiencies given different amplitude weightings. Calculation of the aperture efficiency can be somewhat confusing, particularly with regards to the difference between tapering via attenuation versus redistribution. The purpose of this paper is to define these terms, to provide a review of the proper normalization technique that is important in obtaining accurate aperture efficiency estimation. Descriptions of the amplitude tapers and their utility will be presented. A design example will be presented which will compare theoretical efficiencies with those obtained via finite element method simulation.
{"title":"Aperture Efficiency of Amplitude Weighting Distributions for Array Antennas","authors":"G. Hopkins, J. Ratner, A. Traille, V. Tripp","doi":"10.1109/AERO.2007.352856","DOIUrl":"https://doi.org/10.1109/AERO.2007.352856","url":null,"abstract":"Array antennas offer a wide range of opportunities in the variation of their directivity patterns through amplitude and phase control. Peak sidelobe levels may be reduced via amplitude control or weighting across the array aperture. Several authors have made significant contributions in detailing processes for synthesizing these aperture amplitude distributions for the purpose of sidelobe level control. One of the basic trade-offs when implementing amplitude weighting functions is that a trade between low sidelobe levels and a loss in main beam directivity always results. Some of the commercially available pattern calculation programs that can implement sidelobe level control do not provide calculations of the aperture efficiencies given different amplitude weightings. Calculation of the aperture efficiency can be somewhat confusing, particularly with regards to the difference between tapering via attenuation versus redistribution. The purpose of this paper is to define these terms, to provide a review of the proper normalization technique that is important in obtaining accurate aperture efficiency estimation. Descriptions of the amplitude tapers and their utility will be presented. A design example will be presented which will compare theoretical efficiencies with those obtained via finite element method simulation.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"48 1","pages":"1-9"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90940595","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.2007.352686
K. Nickels, M. Bajracharya, A. Trebi-Ollennu, R. Liebersbach
This paper describes the design, validation, and integration of a tool to locate a portion of the instrument deployment device (IDD) on the Mars exploration rover (MER) vehicles on Mars in imagery from the front hazard avoidance cameras, and to track the differences between the predicted and detected position of the manipulator over time. The analysis of kinematic-vision residuals, or the difference between where a manipulator is expected to appear in onboard imagery and where it actually appears in the imagery, yields insight into several aspects of an operational robotic system. The fidelity of the IDD and camera models is evaluated. Systematic changes in the performance over time can give insight to rover degradation or other changes. Finally, new models can be proposed and evaluated on the basis of trended data over time.
{"title":"Kinematic-Vision Residuals Analysis","authors":"K. Nickels, M. Bajracharya, A. Trebi-Ollennu, R. Liebersbach","doi":"10.1109/AERO.2007.352686","DOIUrl":"https://doi.org/10.1109/AERO.2007.352686","url":null,"abstract":"This paper describes the design, validation, and integration of a tool to locate a portion of the instrument deployment device (IDD) on the Mars exploration rover (MER) vehicles on Mars in imagery from the front hazard avoidance cameras, and to track the differences between the predicted and detected position of the manipulator over time. The analysis of kinematic-vision residuals, or the difference between where a manipulator is expected to appear in onboard imagery and where it actually appears in the imagery, yields insight into several aspects of an operational robotic system. The fidelity of the IDD and camera models is evaluated. Systematic changes in the performance over time can give insight to rover degradation or other changes. Finally, new models can be proposed and evaluated on the basis of trended data over time.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"38 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":"74175123","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.2007.353084
S. Kizhner, U.D. Patel, Meg Vootukuru
Sensor Web-based adaptation and sharing of space flight mission resources, including those of the Space-Ground and Control-User communication segments, could greatly benefit from utilization of heritage Internet Protocols and devices applied for Spaceflight (SpacelP). This had been successfully demonstrated by a few recent spaceflight experiments. However, while terrestrial applications of Internet protocols are well developed and understood (mostly due to billions of dollars in investments by the military and industry), the spaceflight application of Internet protocols is still in its infancy. Progress in the developments of SpacelP-enabled instrument components will largely determine the SpacelP utilization of those investments and acceptance in years to come. Likewise SpacelP, the development of commercial real-time and instrument co-located computational resources, data compression and storage, can be enabled on-board a spacecraft instrument and, in turn, support a powerful application to Sensor Web-based design of a spaceflight instrument. These are presently only co-located with the spacecraft Command and Data Handling System (C&DH). Sensor Web-enabled re-configuration and adaptation of structures for hardware resources and information systems on instrument level will commence application of Field Programmable Gate Arrays (FPGA) and other aerospace programmable logic devices for what this technology was intended. These are a few obvious potential benefits of Sensor Web technologies for spaceflight applications on instrument level. However, they are still waiting to be explored. This is because there is a need for a new approach to spaceflight instrumentation in order to make these mature sensor web technologies applicable for spaceflight. In this paper we present an approach in developing related and enabling spaceflight instrument-level technologies based on the new concept of a representative Instrument Sensor Web (ISW). This concept widens the scope of heritage sensor webs and facilitates the application of sensor web technologies to complex representative instruments onboard future spacecrafts.
{"title":"On Representative Spaceflight Instrument and Associated Instrument Sensor Web Framework","authors":"S. Kizhner, U.D. Patel, Meg Vootukuru","doi":"10.1109/AERO.2007.353084","DOIUrl":"https://doi.org/10.1109/AERO.2007.353084","url":null,"abstract":"Sensor Web-based adaptation and sharing of space flight mission resources, including those of the Space-Ground and Control-User communication segments, could greatly benefit from utilization of heritage Internet Protocols and devices applied for Spaceflight (SpacelP). This had been successfully demonstrated by a few recent spaceflight experiments. However, while terrestrial applications of Internet protocols are well developed and understood (mostly due to billions of dollars in investments by the military and industry), the spaceflight application of Internet protocols is still in its infancy. Progress in the developments of SpacelP-enabled instrument components will largely determine the SpacelP utilization of those investments and acceptance in years to come. Likewise SpacelP, the development of commercial real-time and instrument co-located computational resources, data compression and storage, can be enabled on-board a spacecraft instrument and, in turn, support a powerful application to Sensor Web-based design of a spaceflight instrument. These are presently only co-located with the spacecraft Command and Data Handling System (C&DH). Sensor Web-enabled re-configuration and adaptation of structures for hardware resources and information systems on instrument level will commence application of Field Programmable Gate Arrays (FPGA) and other aerospace programmable logic devices for what this technology was intended. These are a few obvious potential benefits of Sensor Web technologies for spaceflight applications on instrument level. However, they are still waiting to be explored. This is because there is a need for a new approach to spaceflight instrumentation in order to make these mature sensor web technologies applicable for spaceflight. In this paper we present an approach in developing related and enabling spaceflight instrument-level technologies based on the new concept of a representative Instrument Sensor Web (ISW). This concept widens the scope of heritage sensor webs and facilitates the application of sensor web technologies to complex representative instruments onboard future spacecrafts.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"16 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":"75091619","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.2007.353097
G. Rakow, P. McGuirk, C. Kimmery, Paul Jaffe
The ability to rapidly deploy inexpensive satellites to meet tactical goals has become an important goal for military space systems. In fact, Operationally Responsive Space (ORS) has been in the spotlight at the highest levels. The Office of the Secretary of Defense (OSD) has identified that the critical next step is developing the bus standards and modular interfaces. Historically, satellite components have been constructed based on bus standards and standardized interfaces. However, this has not been done to a degree, which would allow the rapid deployment of a satellite. Advancements in plug-and-play (PnP) technologies for terrestrial applications can serve as a baseline model for a PnP approach for satellite applications. Since SpaceWire (SpW) has become a de facto standard for satellite high-speed (>200Mbp) on-board communications, it has become important for SpW to adapt to this plug and play (PnP) environment. Because SpW is simply a bulk transport protocol and lacks built-in PnP 9.3 SpaceWire Router features, several changes are required to facilitate PnP with SpW. The first is for Host(s) to figure out what the network looks like, i.e., how pieces of the network, routers and nodes, are connected together; network mapping, and to receive notice of changes to the network. The second is for the components connected to the network to be understood so that they can communicate. The first element, network topology mapping & change of status indication, is being defined (topic of this paper). The second element describing how components are to communicate has been defined by ARFL with the electronic data sheets known as XTEDS. The first element, network mapping, is recent activities performed by Air Force Research Lab (ARFL), Naval Research Lab (NRL), NASA and US industry (Honeywell Clearwater, FL, and others). This work has resulted in the development of a protocol that will perform the lower evel functions of network mapping and Change Of Status (COS) indication required by Plug n Play over SpaceWire. This work will be presented to the SpaceWire working group for standardization under European Cooperation for Space Standardization (ECSS) and to obtain a permanent Protocol ID (G. Rakow et al., 2006).The portion of the Plug n Play protocol that will be described in this paper is how the Host(s) of a SpaceWire network map the network and detect additions and deletions of devices on a SpaceWire network.
快速部署廉价卫星以满足战术目标的能力已成为军事空间系统的重要目标。事实上，操作响应空间(operational Responsive Space, ORS)已经成为最高层关注的焦点。国防部长办公室(OSD)已经确定，关键的下一步是开发总线标准和模块化接口。从历史上看，卫星组件是基于总线标准和标准化接口构建的。然而，这还没有达到可以快速部署卫星的程度。地面应用的即插即用(PnP)技术的进步可以作为卫星应用的PnP方法的基线模型。由于SpaceWire (SpW)已经成为卫星高速(>200Mbp)机载通信的事实上的标准，因此SpW适应这种即插即用(PnP)环境变得非常重要。由于SpW只是一个批量传输协议，缺乏内置的PnP 9.3 SpaceWire路由器功能，因此需要进行一些更改以促进SpW的PnP。首先，主机(s)要弄清楚网络是什么样子的，即，网络的各个部分，路由器和节点是如何连接在一起的;网络映射，并接收网络变更通知。第二个是要理解连接到网络的组件，以便它们能够通信。定义了第一个要素——网络拓扑映射和状态指示的变化(本文的主题)。描述组件如何通信的第二个元素由ARFL用称为XTEDS的电子数据表定义。第一个要素，网络映射，是最近由空军研究实验室(ARFL)、海军研究实验室(NRL)、NASA和美国工业界(Honeywell Clearwater, FL等)执行的活动。这项工作导致了一种协议的开发，该协议将执行SpaceWire上即插即用所需的网络映射和状态变化(COS)指示的低级功能。这项工作将提交给欧洲空间标准化合作(ECSS)下的SpaceWire标准化工作组，并获得永久协议ID (G. Rakow et al.， 2006)。即插即用协议将在本文中描述的部分是SpaceWire网络的主机如何映射网络并检测SpaceWire网络上设备的添加和删除。
{"title":"Space Wire Plug `n' Play","authors":"G. Rakow, P. McGuirk, C. Kimmery, Paul Jaffe","doi":"10.1109/AERO.2007.353097","DOIUrl":"https://doi.org/10.1109/AERO.2007.353097","url":null,"abstract":"The ability to rapidly deploy inexpensive satellites to meet tactical goals has become an important goal for military space systems. In fact, Operationally Responsive Space (ORS) has been in the spotlight at the highest levels. The Office of the Secretary of Defense (OSD) has identified that the critical next step is developing the bus standards and modular interfaces. Historically, satellite components have been constructed based on bus standards and standardized interfaces. However, this has not been done to a degree, which would allow the rapid deployment of a satellite. Advancements in plug-and-play (PnP) technologies for terrestrial applications can serve as a baseline model for a PnP approach for satellite applications. Since SpaceWire (SpW) has become a de facto standard for satellite high-speed (>200Mbp) on-board communications, it has become important for SpW to adapt to this plug and play (PnP) environment. Because SpW is simply a bulk transport protocol and lacks built-in PnP 9.3 SpaceWire Router features, several changes are required to facilitate PnP with SpW. The first is for Host(s) to figure out what the network looks like, i.e., how pieces of the network, routers and nodes, are connected together; network mapping, and to receive notice of changes to the network. The second is for the components connected to the network to be understood so that they can communicate. The first element, network topology mapping & change of status indication, is being defined (topic of this paper). The second element describing how components are to communicate has been defined by ARFL with the electronic data sheets known as XTEDS. The first element, network mapping, is recent activities performed by Air Force Research Lab (ARFL), Naval Research Lab (NRL), NASA and US industry (Honeywell Clearwater, FL, and others). This work has resulted in the development of a protocol that will perform the lower evel functions of network mapping and Change Of Status (COS) indication required by Plug n Play over SpaceWire. This work will be presented to the SpaceWire working group for standardization under European Cooperation for Space Standardization (ECSS) and to obtain a permanent Protocol ID (G. Rakow et al., 2006).The portion of the Plug n Play protocol that will be described in this paper is how the Host(s) of a SpaceWire network map the network and detect additions and deletions of devices on a SpaceWire network.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"34 1 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":"77461382","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.2007.352894
S. Shambayati
32-GHz Ka-band was first considered for deep-space use in 1976. In 1979, 1 GHz of spectrum at 32-GHz Ka-band was allocated for deep space use. Since then NASA's Jet Propulsion Laboratory (JPL) has been developing technologies and architectures necessary to support Ka-band planetary missions. This paper is a survey of JPL's effort. This survey includes a summary of early paper studies done in the 1980's and 1990's, development of the 34-m beam waveguide (BWG) antennas at the deep space network (DSN), and Ka-band experiments on Mars Observer, Mars Global Surveyor, Deep Space 1, Cassini and Mars reconnaissance orbiter spacecraft. The focus of this paper is on the technological and architectural challenges that 32-GHz Ka-band operations have presented throughout this long history. These include challenges presented by the weather and tighter pointing requirements for the spacecraft as well as the need to use multiple data rates during a pass.
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Pub Date : 2007-03-03DOI: 10.1109/AERO.2007.352906
J. Line, A. Iyer
Electronic prognostics is a growing field important to both military and commercial applications. When implemented, this capability will greatly enhance the maintenance management of platforms. Electronic prognostics require extensive use of physics of failure models to predict the remaining useful life of complex electronic failure modes.
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