Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446662
J. Rodgers, L. Rockett, J. Maimon, T. Storey, P. Nixon
BAE Systems has developed a 4Mb Non-Volatile Chalcogenide Random Access Memory (C-RAM) optimized for the radiation environments encountered in spacecraft applications. C-RAM is a phase change memory with a unique combination of features that collectively provide a high-density, low-power, non-volatile memory solution that is radiation hardened and meets rigorous reliability requirements. The device has completed QML-Q qualification testing and is now in full production. Flight qualified C-RAM will serve the critical need for rad hard nonvolatile RAM in strategic space and military applications. This paper describes the 4Mb C-RAM product and presents the results of C-RAM QML-Q qualification testing including detailed analyses of the test results in all the radiation environments. 1 2
{"title":"Characterization and qualification of radiation hardened nonvolatile phase change memory technology","authors":"J. Rodgers, L. Rockett, J. Maimon, T. Storey, P. Nixon","doi":"10.1109/AERO.2010.5446662","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446662","url":null,"abstract":"BAE Systems has developed a 4Mb Non-Volatile Chalcogenide Random Access Memory (C-RAM) optimized for the radiation environments encountered in spacecraft applications. C-RAM is a phase change memory with a unique combination of features that collectively provide a high-density, low-power, non-volatile memory solution that is radiation hardened and meets rigorous reliability requirements. The device has completed QML-Q qualification testing and is now in full production. Flight qualified C-RAM will serve the critical need for rad hard nonvolatile RAM in strategic space and military applications. This paper describes the 4Mb C-RAM product and presents the results of C-RAM QML-Q qualification testing including detailed analyses of the test results in all the radiation environments. 1 2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129435157","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.2010.5446974
W. Deininger, W. Purcell, P. Atcheson, G. Mills, S. Sandford, Robert P. Hanel, M. Mckelvey, Robert E. McMurray
The Astrobiology Space Infrared Explorer (ASPIRE) is a Probe-class mission concept developed as part of NASA's Astrophysics Strategic Mission Concept studies. 1 2 ASPIRE uses infrared spectroscopy to explore the identity, abundance, and distribution of molecules, particularly those of astrobiological importance throughout the Universe. ASPIRE's observational program is focused on investigating the evolution of ices and organics in all phases of the lifecycle of carbon in the universe, from stellar birth through stellar death while also addressing the role of silicates and gas-phase materials in interstellar organic chemistry. ASPIRE achieves these goals using a Spitzer-derived, cryogenically-cooled, 1-m-class telescope in an Earth drift-away heliocentric orbit, armed with a suite of infrared spectrometers operating in the 2.5–36 micron wavelength region supported by a Kepler-based spacecraft bus. This paper summarizes the results of the ASPIRE Origins Probe Mission Concept Study while focusing on its high heritage mission implementation.
{"title":"An implementation concept for the ASPIRE mission","authors":"W. Deininger, W. Purcell, P. Atcheson, G. Mills, S. Sandford, Robert P. Hanel, M. Mckelvey, Robert E. McMurray","doi":"10.1109/AERO.2010.5446974","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446974","url":null,"abstract":"The Astrobiology Space Infrared Explorer (ASPIRE) is a Probe-class mission concept developed as part of NASA's Astrophysics Strategic Mission Concept studies. 1 2 ASPIRE uses infrared spectroscopy to explore the identity, abundance, and distribution of molecules, particularly those of astrobiological importance throughout the Universe. ASPIRE's observational program is focused on investigating the evolution of ices and organics in all phases of the lifecycle of carbon in the universe, from stellar birth through stellar death while also addressing the role of silicates and gas-phase materials in interstellar organic chemistry. ASPIRE achieves these goals using a Spitzer-derived, cryogenically-cooled, 1-m-class telescope in an Earth drift-away heliocentric orbit, armed with a suite of infrared spectrometers operating in the 2.5–36 micron wavelength region supported by a Kepler-based spacecraft bus. This paper summarizes the results of the ASPIRE Origins Probe Mission Concept Study while focusing on its high heritage mission implementation.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129761454","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.2010.5446708
W. Johnson, S. Hook, P. Mouroulis, Daniel W. Wilson, S. Gunapala, C. Hill, V. Realmuto, J. Mumolo, B. Eng
We present field results showing excellent performance for a compact earth observing thermal infrared (EOTIR) hyperspectral grating spectrometer using a combination of a Quantum Well Infrared Photodetector (QWIP) and grating based Dyson spectrometer. 12The Dyson design allows for a very compact and optically fast system (F/1.6). Cooling requirements are minimized due to the single monolithic prism-like grating design. The configuration has the potential to be the optimal sciencegrade imaging spectroscopy solution for lighter-than-air (LTA) vehicles and unmanned aerial vehicles (UAV) due to its small form factor and relatively low power requirements. The QWIP allows for optimum spatial and spectral uniformity and provides adequate responsivity to allow for near 100mK noise equivalent temperature difference (NEDT) operation across the EOTIR passband. These tests are in preparation for the deployment of the Hypserspectral Thermal Infrared Spectrometer (HyTES) which is currently being funded under NASA's instrument incubator program (IIP). Test results show NEDT, linearity as well as applicable earth science emissivity target results (silicates, water) measured in direct sunlight. A calibration is also performed to derive direct water temperature using a well calibrated transfer radiometer operating simultaneously.
{"title":"Field calibration of a broadband compact thermal infrared spectrometer for earth science","authors":"W. Johnson, S. Hook, P. Mouroulis, Daniel W. Wilson, S. Gunapala, C. Hill, V. Realmuto, J. Mumolo, B. Eng","doi":"10.1109/AERO.2010.5446708","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446708","url":null,"abstract":"We present field results showing excellent performance for a compact earth observing thermal infrared (EOTIR) hyperspectral grating spectrometer using a combination of a Quantum Well Infrared Photodetector (QWIP) and grating based Dyson spectrometer. 12The Dyson design allows for a very compact and optically fast system (F/1.6). Cooling requirements are minimized due to the single monolithic prism-like grating design. The configuration has the potential to be the optimal sciencegrade imaging spectroscopy solution for lighter-than-air (LTA) vehicles and unmanned aerial vehicles (UAV) due to its small form factor and relatively low power requirements. The QWIP allows for optimum spatial and spectral uniformity and provides adequate responsivity to allow for near 100mK noise equivalent temperature difference (NEDT) operation across the EOTIR passband. These tests are in preparation for the deployment of the Hypserspectral Thermal Infrared Spectrometer (HyTES) which is currently being funded under NASA's instrument incubator program (IIP). Test results show NEDT, linearity as well as applicable earth science emissivity target results (silicates, water) measured in direct sunlight. A calibration is also performed to derive direct water temperature using a well calibrated transfer radiometer operating simultaneously.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"93 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":"129868630","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.2010.5446683
D. Dunham, Scott E. August
When two objects separate there is typically a period of time after the separation when the two objects are unresolved by a radar. This is due to the radar range bin resolution, which will keep two returns as one measurement until there is a clear separation. At that point, a new track will start, but where exactly did the objects separate? The actual separation point may be of interest and finding that separation point is the topic of this paper.1 2 Using the PMHT algorithm allows measurements to be “shared” between tracks, and therefore, makes an excellent algorithm for when there are closely-spaced unresolved measurements. After a separation event, while the measurements are still unresolved, there will be only one measurement for the two objects. PMHT is quite comfortable with this situation when there are fewer measurements than there are objects because the PMHT has to know a priori how many objects there are. When a new track starts, the PMHT separation point estimation algorithm will be called. Then the PMHT algorithm can add in the unresolved measurements backwards in time to determine the likely separation point.
{"title":"Kinematic separation point estimation using PMHT","authors":"D. Dunham, Scott E. August","doi":"10.1109/AERO.2010.5446683","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446683","url":null,"abstract":"When two objects separate there is typically a period of time after the separation when the two objects are unresolved by a radar. This is due to the radar range bin resolution, which will keep two returns as one measurement until there is a clear separation. At that point, a new track will start, but where exactly did the objects separate? The actual separation point may be of interest and finding that separation point is the topic of this paper.1 2 Using the PMHT algorithm allows measurements to be “shared” between tracks, and therefore, makes an excellent algorithm for when there are closely-spaced unresolved measurements. After a separation event, while the measurements are still unresolved, there will be only one measurement for the two objects. PMHT is quite comfortable with this situation when there are fewer measurements than there are objects because the PMHT has to know a priori how many objects there are. When a new track starts, the PMHT separation point estimation algorithm will be called. Then the PMHT algorithm can add in the unresolved measurements backwards in time to determine the likely separation point.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128430682","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.2010.5446758
M. Wilde, U. Walter
The major part of the recent research efforts in the field of robotic on-orbit servicing (OOS) has been spent on pursuing autonomous systems, such as Orbital Express or ETS-VII. TU Munich's Institute of Astronautics (LRT) considers the degree of flexibility required of an OOS system to be only achievable by keeping human operators in the loop, by means of telepresence. However, the absence of important sensory input, such as acoustic and tactile information and peripheral vision, the lack of reference points for discerning orientations, distances and velocities, and the unfamiliar behavior and motion of objects in space reduce the situational awareness of the human operator. In order to provide the human operator with additional visual input and to enable him/her to take up vantage points which would not be available by means of platform-fixed or manipulator-fixed sensors, the utility of a dedicated robotic camera arm is investigated which will be used by the human operator for judging relative attitude and position of chaser and target vehicle and for viewing the remote work site from otherwise unattainable angles and over obstacles. The stereo video stream delivered by this so-called “Third Eye” will be superimposed with head-up display type graphics in order to provide the operator with attitude and position cues. These enable him/her to integrate the additional visual information into his mental model of the surroundings. Operator performance and maneuver safety is also supported by the projection of laser grids onto the surfaces of the target satellite, thereby facilitating attitude and position determination during station keeping.1 2
{"title":"A robotic camera arm for increased situational awareness in telepresent on-orbit servicing","authors":"M. Wilde, U. Walter","doi":"10.1109/AERO.2010.5446758","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446758","url":null,"abstract":"The major part of the recent research efforts in the field of robotic on-orbit servicing (OOS) has been spent on pursuing autonomous systems, such as Orbital Express or ETS-VII. TU Munich's Institute of Astronautics (LRT) considers the degree of flexibility required of an OOS system to be only achievable by keeping human operators in the loop, by means of telepresence. However, the absence of important sensory input, such as acoustic and tactile information and peripheral vision, the lack of reference points for discerning orientations, distances and velocities, and the unfamiliar behavior and motion of objects in space reduce the situational awareness of the human operator. In order to provide the human operator with additional visual input and to enable him/her to take up vantage points which would not be available by means of platform-fixed or manipulator-fixed sensors, the utility of a dedicated robotic camera arm is investigated which will be used by the human operator for judging relative attitude and position of chaser and target vehicle and for viewing the remote work site from otherwise unattainable angles and over obstacles. The stereo video stream delivered by this so-called “Third Eye” will be superimposed with head-up display type graphics in order to provide the operator with attitude and position cues. These enable him/her to integrate the additional visual information into his mental model of the surroundings. Operator performance and maneuver safety is also supported by the projection of laser grids onto the surfaces of the target satellite, thereby facilitating attitude and position determination during station keeping.1 2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"41 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":"129675119","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.2010.5446792
E. D. de Visser, Melanie LeGoullon, D. Horvath, G. Weltman, A. Freedy, P. Durlach, R. Parasuraman
This paper describes the design and initial positive evaluation of a prototype adaptive automation system to create an enhanced command and control (C2) infrastructure for more effective operation of unmanned vehicles.1,2 Our main project objective is to apply recent advances in cognitive engineering and display automation to create Technology for Enhanced Command and Control of Small Robotic Assets (TECRA). The initial goal is an enhanced C2 system for small unmanned aircraft vehicles (SUAVs). Our approach is to use adaptive display technology to improve shared situation awareness between the SUAV Commander and the SUAV Operator, to provide new channels of Commander-Operator communication, and to reduce Commander workload.
{"title":"TECRA: C2 application of adaptive automation theory","authors":"E. D. de Visser, Melanie LeGoullon, D. Horvath, G. Weltman, A. Freedy, P. Durlach, R. Parasuraman","doi":"10.1109/AERO.2010.5446792","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446792","url":null,"abstract":"This paper describes the design and initial positive evaluation of a prototype adaptive automation system to create an enhanced command and control (C2) infrastructure for more effective operation of unmanned vehicles.1,2 Our main project objective is to apply recent advances in cognitive engineering and display automation to create Technology for Enhanced Command and Control of Small Robotic Assets (TECRA). The initial goal is an enhanced C2 system for small unmanned aircraft vehicles (SUAVs). Our approach is to use adaptive display technology to improve shared situation awareness between the SUAV Commander and the SUAV Operator, to provide new channels of Commander-Operator communication, and to reduce Commander workload.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"14 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":"127435120","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.2010.5446895
B. Bluethmann, E. Herrera, Aaron Hulse, J. Figuered, L. Junkin, M. Markee, R. Ambrose
This paper describes the design and control of the first generation active suspension for NASA's Chariot rover and Lunar Electric Rover (LER). Within the paper is a general overview of the needs and benefits of active suspensions for crew mobility systems on the lunar surface. In the spectrum of active suspensions, the Chariot system falls into the category of a series active or low bandwidth suspension. The passive suspension elements absorb the high frequency content of driving over rugged terrain and the active element sets the height of the suspension allowing the vehicle to conform to the terrain. This suspension system is capable of raising and lowering the vehicle, adjusting roll and pitch attitude for docking operations, leveling the chassis against gravity, and balancing the force across the six wheels during low speed operations. In addition to the existing system, initial results of an incremental design upgrade are discussed and future considerations for suspension systems for the lunar surface are described.
{"title":"An active suspension system for lunar crew mobility","authors":"B. Bluethmann, E. Herrera, Aaron Hulse, J. Figuered, L. Junkin, M. Markee, R. Ambrose","doi":"10.1109/AERO.2010.5446895","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446895","url":null,"abstract":"This paper describes the design and control of the first generation active suspension for NASA's Chariot rover and Lunar Electric Rover (LER). Within the paper is a general overview of the needs and benefits of active suspensions for crew mobility systems on the lunar surface. In the spectrum of active suspensions, the Chariot system falls into the category of a series active or low bandwidth suspension. The passive suspension elements absorb the high frequency content of driving over rugged terrain and the active element sets the height of the suspension allowing the vehicle to conform to the terrain. This suspension system is capable of raising and lowering the vehicle, adjusting roll and pitch attitude for docking operations, leveling the chassis against gravity, and balancing the force across the six wheels during low speed operations. In addition to the existing system, initial results of an incremental design upgrade are discussed and future considerations for suspension systems for the lunar surface are described.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"17 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":"127526336","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.2010.5447018
C. Duncan, M. S. Dennis, A. Kalman, Kevin Anand Stein, Yonas Tesfaye, Bryan I-Ming Lin, E. Truong-Cao, C. Foster
The Communications, Tracking, and Radar Division at NASA's Jet Propulsion Laboratory (JPL) and the Space and Systems Development Lab (SSDL) at Stanford University are collaborating to fly a nanosat-class mission for costs usually associated with small technology development tasks, a few $100K. The mission hosts a JPL-developed Low Mass Radio Science Transponder (LMRST) on a university-class CubeSat bus as a satellite that occupies a total volume of two liters plus deployable antennas. In low earth orbit, the LMRST payload will provide a far-field source for calibration of Deep Space Network X-Band equipment in the form of an integer turnaround X-Band transponder with support for ranging modulation. The CubeSat bus provided by SSDL supplies power, structural support, and command and telemetry while on orbit. CubeSat development and operations are conducted as a student project.
{"title":"LMRST-Sat: A small, high value-to-cost mission","authors":"C. Duncan, M. S. Dennis, A. Kalman, Kevin Anand Stein, Yonas Tesfaye, Bryan I-Ming Lin, E. Truong-Cao, C. Foster","doi":"10.1109/AERO.2010.5447018","DOIUrl":"https://doi.org/10.1109/AERO.2010.5447018","url":null,"abstract":"The Communications, Tracking, and Radar Division at NASA's Jet Propulsion Laboratory (JPL) and the Space and Systems Development Lab (SSDL) at Stanford University are collaborating to fly a nanosat-class mission for costs usually associated with small technology development tasks, a few $100K. The mission hosts a JPL-developed Low Mass Radio Science Transponder (LMRST) on a university-class CubeSat bus as a satellite that occupies a total volume of two liters plus deployable antennas. In low earth orbit, the LMRST payload will provide a far-field source for calibration of Deep Space Network X-Band equipment in the form of an integer turnaround X-Band transponder with support for ranging modulation. The CubeSat bus provided by SSDL supplies power, structural support, and command and telemetry while on orbit. CubeSat development and operations are conducted as a student project.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"14 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":"128930813","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.2010.5446853
J. Ludwig, J. Mohammed, Jim Ong
DARPA's Bootstrapped Learning (BL) program is aimed at advancing the state of the art in instructable computing. Two objectives of this program are developing a general electronic student that makes use of machine learning algorithms to learn from the kind of focused instruction typically provided by a human teacher and creating a repository of automated curricula that can be taught to the student. This paper focuses on the second objective, describing a curriculum developed for the BL program to both instruct and test the student that places the electronic student (eStudent) in the role of an International Space Station (ISS) flight controller. The eStudent is taught how to detect and diagnose single-fault problems within the thermal control system of the ISS. During each lesson, the eStudent interacts with an ISS simulator to review alerts and access telemetry values. To obtain greater visibility into its diagnostic reasoning, the eStudent is trained to create an external representation of its reasoning about the current problem - a diagnostic rationale. This includes describing potential problems, hypothesizing possible events and states, positing possible causal explanations as rationale assertions, seeking evidence for or against these assertions, projecting possible risks, and using possible risks to focus attention when developing a rationale. In addition to describing the curriculum developed as part of the first year of the BL program, we also describe some of the future directions we will investigate as part of the second year. 1,2
{"title":"Developing an International Space Station curriculum for the Bootstrapped Learning program","authors":"J. Ludwig, J. Mohammed, Jim Ong","doi":"10.1109/AERO.2010.5446853","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446853","url":null,"abstract":"DARPA's Bootstrapped Learning (BL) program is aimed at advancing the state of the art in instructable computing. Two objectives of this program are developing a general electronic student that makes use of machine learning algorithms to learn from the kind of focused instruction typically provided by a human teacher and creating a repository of automated curricula that can be taught to the student. This paper focuses on the second objective, describing a curriculum developed for the BL program to both instruct and test the student that places the electronic student (eStudent) in the role of an International Space Station (ISS) flight controller. The eStudent is taught how to detect and diagnose single-fault problems within the thermal control system of the ISS. During each lesson, the eStudent interacts with an ISS simulator to review alerts and access telemetry values. To obtain greater visibility into its diagnostic reasoning, the eStudent is trained to create an external representation of its reasoning about the current problem - a diagnostic rationale. This includes describing potential problems, hypothesizing possible events and states, positing possible causal explanations as rationale assertions, seeking evidence for or against these assertions, projecting possible risks, and using possible risks to focus attention when developing a rationale. In addition to describing the curriculum developed as part of the first year of the BL program, we also describe some of the future directions we will investigate as part of the second year. 1,2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129010194","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.2010.5446786
Zhang Xiao-ying
In the present study, an unstructured finite volume method for radiative transfer in 3-D enclosure with inhomegeneous participating medium is developed. That method is applicable for complex geometry enclosure. The computational domain is divided into many tetrahedral volume cells, which is easily applied into structured or unstructured. A general discretization equation based on step scheme for spatial differencing and azimuthal discretization in angular domain was derived. In order to validated the developed unstructured finite volume method, three test cases were chosen, including a cubic enclosure with absorbing-emitting medium, an equilateral triangular enclosure with absorbing-emitting medium, a 3D L-shaped enclosure with absorbing-emitting/scattering medium. All the solutions based on the present method have a good agreement with available other solutions. Then, one case with more complex geometry, a hollow cubic enclosure with absorbing-emitting and isotropic scattering medium, was investigated. The effects of scattering albedo on wall radiative flux, incident radiation and radiative flux divergence were analyzed. It was found that the developed model is reliable and accurate and suitable for radiative transfer in complex 3-D enclosure with inhomegeneous absorbing-emitting and scattering medium.12
{"title":"Radiative transfer in 3-D enclosure with inhomogeneous participating medium with unstructured FVM","authors":"Zhang Xiao-ying","doi":"10.1109/AERO.2010.5446786","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446786","url":null,"abstract":"In the present study, an unstructured finite volume method for radiative transfer in 3-D enclosure with inhomegeneous participating medium is developed. That method is applicable for complex geometry enclosure. The computational domain is divided into many tetrahedral volume cells, which is easily applied into structured or unstructured. A general discretization equation based on step scheme for spatial differencing and azimuthal discretization in angular domain was derived. In order to validated the developed unstructured finite volume method, three test cases were chosen, including a cubic enclosure with absorbing-emitting medium, an equilateral triangular enclosure with absorbing-emitting medium, a 3D L-shaped enclosure with absorbing-emitting/scattering medium. All the solutions based on the present method have a good agreement with available other solutions. Then, one case with more complex geometry, a hollow cubic enclosure with absorbing-emitting and isotropic scattering medium, was investigated. The effects of scattering albedo on wall radiative flux, incident radiation and radiative flux divergence were analyzed. It was found that the developed model is reliable and accurate and suitable for radiative transfer in complex 3-D enclosure with inhomegeneous absorbing-emitting and scattering medium.12","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"77 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":"126966244","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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