Pub Date : 2001-03-10DOI: 10.1109/AERO.2001.931412
Sam Siewert
This paper summarizes results from both the hard real-time RACE optical navigation experiment and the soft real-time DATA-CHASER Shuttle demonstration project and presents an integrated architecture for both hard and soft real-time shared control. The results show significant performance advantages of the shared-control architecture and greatly simplified implementation using the derived framework. Lessons learned from both experiments and the implementation of this evolving architecture are presented along with plans for future work to make the framework a standardized kernel module available for VxWorks, Solaris, and Linux.
{"title":"Experiments with a real-time multi-pipeline architecture for shared control","authors":"Sam Siewert","doi":"10.1109/AERO.2001.931412","DOIUrl":"https://doi.org/10.1109/AERO.2001.931412","url":null,"abstract":"This paper summarizes results from both the hard real-time RACE optical navigation experiment and the soft real-time DATA-CHASER Shuttle demonstration project and presents an integrated architecture for both hard and soft real-time shared control. The results show significant performance advantages of the shared-control architecture and greatly simplified implementation using the derived framework. Lessons learned from both experiments and the implementation of this evolving architecture are presented along with plans for future work to make the framework a standardized kernel module available for VxWorks, Solaris, and Linux.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134207168","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 : 2001-03-10DOI: 10.1109/AERO.2001.931706
V. V. Kerzhanovich, J. L. Hall, A. Yavrouian
This paper proposes a precursor mission to the Venus Surface Sample return Mission (VSSR). The present scenario of the VSSR includes delivery by a balloon of the Venus Ascent Vehicle (VAV) from the surface to an altitude of approximately 60 km, where it can be launched without huge penalty for atmospheric losses. The mission includes a number of critical technologies that can be validated in this proposed precursor mission. The other objective of the proposed mission is to collect more accurate data on the Venus atmosphere that is essential for the VSSR mission design. The paper discusses the basic mission and system elements for the proposed precursor mission.
{"title":"Balloon precursor mission for Venus Surface Sample Return","authors":"V. V. Kerzhanovich, J. L. Hall, A. Yavrouian","doi":"10.1109/AERO.2001.931706","DOIUrl":"https://doi.org/10.1109/AERO.2001.931706","url":null,"abstract":"This paper proposes a precursor mission to the Venus Surface Sample return Mission (VSSR). The present scenario of the VSSR includes delivery by a balloon of the Venus Ascent Vehicle (VAV) from the surface to an altitude of approximately 60 km, where it can be launched without huge penalty for atmospheric losses. The mission includes a number of critical technologies that can be validated in this proposed precursor mission. The other objective of the proposed mission is to collect more accurate data on the Venus atmosphere that is essential for the VSSR mission design. The paper discusses the basic mission and system elements for the proposed precursor mission.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"70 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133905641","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 : 2001-03-10DOI: 10.1109/AERO.2001.931477
N. Pougatchev, W. Smith, F. Harrison, A. Larar, C. Rinsland, D. Jacob, I. Bey, B. Field, R. Yantosca, A. Huang, S. Nolf, S. Kireev
The Geostationary Imaging Fourier Transform Spectrometer (GIFTS) has been selected by the National Aeronautics and Space Administration (NASA) for its 2004 New Millennium Program mission. The GIFTS geophysical data products are derived from measurements of atmospheric thermal emission in 2 spectral bands: 685-1130 cm/sup -1/ and 1650-2250 cm/sup -1/, at high spectral resolution (up to 0.3 cm/sup -1/) on a 4-km spatial grid. Among key data products are vertically-resolved distributions of ozone and carbon monoxide. Vertical resolution attainable is in the range of 3- to 11-km, depending on a target gas and altitude. To evaluate the GIFTS capability for atmospheric chemistry studies, e.g., sources, sinks, transport and transformation of trace gas, simulations of the GIFTS observations have been performed. Real aircraft in situ profiles and results of the Harvard 3-D model were used as inputs for the simulations.
{"title":"Imaging Geostationary Fourier Transform Spectrometer-revolutionary tool for tropospheric chemistry","authors":"N. Pougatchev, W. Smith, F. Harrison, A. Larar, C. Rinsland, D. Jacob, I. Bey, B. Field, R. Yantosca, A. Huang, S. Nolf, S. Kireev","doi":"10.1109/AERO.2001.931477","DOIUrl":"https://doi.org/10.1109/AERO.2001.931477","url":null,"abstract":"The Geostationary Imaging Fourier Transform Spectrometer (GIFTS) has been selected by the National Aeronautics and Space Administration (NASA) for its 2004 New Millennium Program mission. The GIFTS geophysical data products are derived from measurements of atmospheric thermal emission in 2 spectral bands: 685-1130 cm/sup -1/ and 1650-2250 cm/sup -1/, at high spectral resolution (up to 0.3 cm/sup -1/) on a 4-km spatial grid. Among key data products are vertically-resolved distributions of ozone and carbon monoxide. Vertical resolution attainable is in the range of 3- to 11-km, depending on a target gas and altitude. To evaluate the GIFTS capability for atmospheric chemistry studies, e.g., sources, sinks, transport and transformation of trace gas, simulations of the GIFTS observations have been performed. Real aircraft in situ profiles and results of the Harvard 3-D model were used as inputs for the simulations.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133952770","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 : 2001-03-10DOI: 10.1109/AERO.2001.931501
M. Spencer, J. Huddleston, B. Stiles
The SeaWinds wind scatterometer was first launched in June of 1999, and has contributed significantly to the study of global climate phenomena and to the fidelity of operational weather forecasting. A second SeaWinds instrument is planned to be launched aboard the Japanese ADEOS-II platform in late 2001, and operate until mid-decade. To extend the important Ku-Band scatterometer data base to the end of the decade and beyond, a follow-on system to the SeaWinds series of scatterometers is being developed. The goals for this system are to continue the core Ku-Band backscatter measurement, to further improve spacecraft accommodation constraints so as to be easily operated on a variety of platforms, and-where possible under existing cost constraints-improve wind retrieval performance. It is shown that a system, which meets these objectives, can be achieved by the addition of polarimetric measurement capability to the existing SeaWinds approach. Polarimetric scatterometry is demonstrated to improve wind measurement performance without impacting instrument complexity or cost, and has the long term potential to further ease spacecraft accommodation requirements.
{"title":"Advanced design concepts for a SeaWinds scatterometer follow-on mission","authors":"M. Spencer, J. Huddleston, B. Stiles","doi":"10.1109/AERO.2001.931501","DOIUrl":"https://doi.org/10.1109/AERO.2001.931501","url":null,"abstract":"The SeaWinds wind scatterometer was first launched in June of 1999, and has contributed significantly to the study of global climate phenomena and to the fidelity of operational weather forecasting. A second SeaWinds instrument is planned to be launched aboard the Japanese ADEOS-II platform in late 2001, and operate until mid-decade. To extend the important Ku-Band scatterometer data base to the end of the decade and beyond, a follow-on system to the SeaWinds series of scatterometers is being developed. The goals for this system are to continue the core Ku-Band backscatter measurement, to further improve spacecraft accommodation constraints so as to be easily operated on a variety of platforms, and-where possible under existing cost constraints-improve wind retrieval performance. It is shown that a system, which meets these objectives, can be achieved by the addition of polarimetric measurement capability to the existing SeaWinds approach. Polarimetric scatterometry is demonstrated to improve wind measurement performance without impacting instrument complexity or cost, and has the long term potential to further ease spacecraft accommodation requirements.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"61 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126575723","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 : 2001-03-10DOI: 10.1109/AERO.2001.931217
P. Gloyer, D. Goldstein
The past decade has seen efforts to lower costs by "doing more with less", instead of making innovative changes in the way missions are designed and implemented. Now, the industry is turning towards more intelligent approaches to mission design. AeroAstro has developed the Small Payload ORbit Transfer (SPORT/sup TM/) system to provide a flexible low-cost orbit transfer capability, enabling small payloads to use low-cost secondary launch opportunities and still reach their desired final orbits. This allows small payloads to effectively use a wider variety of launch opportunities, including numerous under-utilized geosynchronous transfer orbit (GTO) slots. Its use, in conjunction with growing opportunities for secondary launches, enables "better, cheaper, faster" missions through innovative mission design and lower cost access to space, not increased risk. SPORT uses a suite of innovative technologies that are packaged in a simple, reliable, modular system. SPORT achieves its orbit transfer capability through a combination of chemical propulsion and aerobraking technology. This paper discusses the SPORT design and its application to overall small satellite mission development.
{"title":"Small payload orbit transfer (SPORT/sup TM/) system: lowering launch cost without increased risk","authors":"P. Gloyer, D. Goldstein","doi":"10.1109/AERO.2001.931217","DOIUrl":"https://doi.org/10.1109/AERO.2001.931217","url":null,"abstract":"The past decade has seen efforts to lower costs by \"doing more with less\", instead of making innovative changes in the way missions are designed and implemented. Now, the industry is turning towards more intelligent approaches to mission design. AeroAstro has developed the Small Payload ORbit Transfer (SPORT/sup TM/) system to provide a flexible low-cost orbit transfer capability, enabling small payloads to use low-cost secondary launch opportunities and still reach their desired final orbits. This allows small payloads to effectively use a wider variety of launch opportunities, including numerous under-utilized geosynchronous transfer orbit (GTO) slots. Its use, in conjunction with growing opportunities for secondary launches, enables \"better, cheaper, faster\" missions through innovative mission design and lower cost access to space, not increased risk. SPORT uses a suite of innovative technologies that are packaged in a simple, reliable, modular system. SPORT achieves its orbit transfer capability through a combination of chemical propulsion and aerobraking technology. This paper discusses the SPORT design and its application to overall small satellite mission development.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"82 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133647055","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 : 2001-03-10DOI: 10.1109/AERO.2001.931258
Caputa, M. Stuchly
Design-development and performance evaluation of antennas on handheld telephones can be done experimentally or numerically. Numerical modeling approach or a combination of experiment and numerical modeling, offer many advantages compared with purely experimental approach, which has been often used till now. However, modeling poses many challenges and in order to be considered reliable has to be verified. In this work, modeling of an antenna consisting of two helices is verified by a comparison with measurements made in the laboratory of the handset manufacturer, and by use of two different computer codes. The numerical method used in this investigation is the finite difference time domain (FDTD). A comparison of the measured (in manufacturer's laboratory) electric and magnetic field in four planes at distances 1-4 cm from the antenna with the computed values shows agreement within 15% (which corresponds to the uncertainty in measurements). This agreement is for two operational positions of the antenna in free space. Performance of the handset antenna in the vicinity of the user's head is evaluated. Investigations include the input impedance, far-field radiation pattern and power deposited in the human tissue. The influences of the ear shape and various positions of the handset with respect to the user's head have been evaluated.
{"title":"Modeling a complex antenna on a handheld telephone close to human tissue","authors":"Caputa, M. Stuchly","doi":"10.1109/AERO.2001.931258","DOIUrl":"https://doi.org/10.1109/AERO.2001.931258","url":null,"abstract":"Design-development and performance evaluation of antennas on handheld telephones can be done experimentally or numerically. Numerical modeling approach or a combination of experiment and numerical modeling, offer many advantages compared with purely experimental approach, which has been often used till now. However, modeling poses many challenges and in order to be considered reliable has to be verified. In this work, modeling of an antenna consisting of two helices is verified by a comparison with measurements made in the laboratory of the handset manufacturer, and by use of two different computer codes. The numerical method used in this investigation is the finite difference time domain (FDTD). A comparison of the measured (in manufacturer's laboratory) electric and magnetic field in four planes at distances 1-4 cm from the antenna with the computed values shows agreement within 15% (which corresponds to the uncertainty in measurements). This agreement is for two operational positions of the antenna in free space. Performance of the handset antenna in the vicinity of the user's head is evaluated. Investigations include the input impedance, far-field radiation pattern and power deposited in the human tissue. The influences of the ear shape and various positions of the handset with respect to the user's head have been evaluated.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"45 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132096409","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 : 2001-03-10DOI: 10.1109/AERO.2001.931242
G. Rabideau, L. Reder, Steve Ankuo Chien, A. Booth
In this paper, we discuss Artificial Intelligence (AI) planning and scheduling technology and its application to interferometer configuration and control. Scientific demand and technical requirements necessitate streamlining and optimizing the operation of these instruments. However, it is difficult, often impossible, to achieve this streamlining manually. Moreover, harsh operating environments make manual operation impractical, further motivating the use of automation. We describe the use of the ASPEN automated planning system developed at JPL to demonstrate how planning can be used to perform many operation tasks with many benefits over manual operations. Automated planners can rapidly produce large command sequences. In addition, repairing altered plans is very fast and can be used to respond to unforeseen events.
{"title":"Automated planning for interferometer configuration and control","authors":"G. Rabideau, L. Reder, Steve Ankuo Chien, A. Booth","doi":"10.1109/AERO.2001.931242","DOIUrl":"https://doi.org/10.1109/AERO.2001.931242","url":null,"abstract":"In this paper, we discuss Artificial Intelligence (AI) planning and scheduling technology and its application to interferometer configuration and control. Scientific demand and technical requirements necessitate streamlining and optimizing the operation of these instruments. However, it is difficult, often impossible, to achieve this streamlining manually. Moreover, harsh operating environments make manual operation impractical, further motivating the use of automation. We describe the use of the ASPEN automated planning system developed at JPL to demonstrate how planning can be used to perform many operation tasks with many benefits over manual operations. Automated planners can rapidly produce large command sequences. In addition, repairing altered plans is very fast and can be used to respond to unforeseen events.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"86 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132688230","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 : 2001-03-10DOI: 10.1109/AERO.2001.931402
B. Nickerson, R. Lally
Oceana Sensor Technologies (OST) is working with the Joint Strike Fighter (JSF), DARPA, and the Office of Naval Research (ONR) under a cooperative agreement to develop a new class of networkable, smart sensors for prognostics and health management (PHM) aboard JSF, other aircraft, and industrial applications. We call these devices Intelligent Component Health Monitors or ICHM/sup TM/. The ICHM has been prototyped in relatively large form factors built for normal industrial environments. The effort described herein has several objectives targeted to deliver a class of devices ready to be incorporated into the JSF design. Specifically we will: 1) environmentally harden the ICHM/sup TM/ design; 2) incorporate additional self-calibration/test functions; 3) integrate and demonstrate transducer technologies of Stewart Hughes Limited (SHL) with the Intelligent Component Health Monitor (ICHMTM); 4) integrate an ICHM-based engine sensor network; and 5) conduct testing in realistic engine and aircraft environments. This paper describe this development effort.
{"title":"Development of a smart wireless networkable sensor for aircraft engine health management","authors":"B. Nickerson, R. Lally","doi":"10.1109/AERO.2001.931402","DOIUrl":"https://doi.org/10.1109/AERO.2001.931402","url":null,"abstract":"Oceana Sensor Technologies (OST) is working with the Joint Strike Fighter (JSF), DARPA, and the Office of Naval Research (ONR) under a cooperative agreement to develop a new class of networkable, smart sensors for prognostics and health management (PHM) aboard JSF, other aircraft, and industrial applications. We call these devices Intelligent Component Health Monitors or ICHM/sup TM/. The ICHM has been prototyped in relatively large form factors built for normal industrial environments. The effort described herein has several objectives targeted to deliver a class of devices ready to be incorporated into the JSF design. Specifically we will: 1) environmentally harden the ICHM/sup TM/ design; 2) incorporate additional self-calibration/test functions; 3) integrate and demonstrate transducer technologies of Stewart Hughes Limited (SHL) with the Intelligent Component Health Monitor (ICHMTM); 4) integrate an ICHM-based engine sensor network; and 5) conduct testing in realistic engine and aircraft environments. This paper describe this development effort.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"60 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131289465","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 : 2001-03-10DOI: 10.1109/AERO.2001.931360
H. Gehue, Warren Hewerdine
With the removal of the dithering effects of Selective Availability (SA), use of Differential GPS (DGPS) corrections can now be applied for extended periods of time allowing enhanced performance for low power configurations of a Si RF based GPS receiver. The software selectable low power settings, implemented by Si RF, employ three states; track, navigate and trickle. During track and trickle states there is no UART communication making reception of DGPS correction unavailable. During the NAV state (when the navigation calculation is performed), corrections may be received. Previously, SA induced error shortened the viable extrapolation time to less than 30 seconds; else significant navigation error would build up between measurements. Additionally, the need to return to a full power state every 30 seconds significantly increased the overall average power dissipation over standard TricklePower/sup TM/ operation. Now that SA (the dominate error source of the DGPS correction) has been removed, the time limit that a DGPS correction can be applied has been extended from 30 seconds to several minutes without significant degradation in navigation performance. This opens up opportunity for low power GPS receiver operation to make use of the DGPS correction to improve navigation without severely impacting the average power requirements. Si RF's implementations of low power operation, leverages off its unique architecture that allows 100 ms signal reacquisition allowing a pseudorange measurement to as little 200 ms. The chipset is then shut down for 800 ms, significantly reducing the power consumption, while still maintaining 1 Hz navigation updates.
{"title":"Use of DGPS corrections with low power GPS receivers in a post SA environment","authors":"H. Gehue, Warren Hewerdine","doi":"10.1109/AERO.2001.931360","DOIUrl":"https://doi.org/10.1109/AERO.2001.931360","url":null,"abstract":"With the removal of the dithering effects of Selective Availability (SA), use of Differential GPS (DGPS) corrections can now be applied for extended periods of time allowing enhanced performance for low power configurations of a Si RF based GPS receiver. The software selectable low power settings, implemented by Si RF, employ three states; track, navigate and trickle. During track and trickle states there is no UART communication making reception of DGPS correction unavailable. During the NAV state (when the navigation calculation is performed), corrections may be received. Previously, SA induced error shortened the viable extrapolation time to less than 30 seconds; else significant navigation error would build up between measurements. Additionally, the need to return to a full power state every 30 seconds significantly increased the overall average power dissipation over standard TricklePower/sup TM/ operation. Now that SA (the dominate error source of the DGPS correction) has been removed, the time limit that a DGPS correction can be applied has been extended from 30 seconds to several minutes without significant degradation in navigation performance. This opens up opportunity for low power GPS receiver operation to make use of the DGPS correction to improve navigation without severely impacting the average power requirements. Si RF's implementations of low power operation, leverages off its unique architecture that allows 100 ms signal reacquisition allowing a pseudorange measurement to as little 200 ms. The chipset is then shut down for 800 ms, significantly reducing the power consumption, while still maintaining 1 Hz navigation updates.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"36 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115779017","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 : 2001-03-10DOI: 10.1109/AERO.2001.931169
F. Roush, A.H. Kalma, I. Kasai, G. Venzor, D. A. Estrada, J. E. Jensen, J. Robinson
The AFRL has pursued high temperature IR FPAs for three years. A 10 K increase has been obtained to date by thinning the HgCdTe base-layer. A contract has recently been let to DRS Infrared Technologies to further increase operating temperature by 15 K utilizing their gold doped High Density Vertically Integrated Photodiode (HDVIP/sup TM/) technology. The increased operating temperatures of these devices will reduce power, weight, and cost, as well as extend the lifetime of space surveillance satellites, satisfying a critical 21st century device technology need.
{"title":"High operating temperature FPAs for lighter, lower power satellite surveillance in the infrared","authors":"F. Roush, A.H. Kalma, I. Kasai, G. Venzor, D. A. Estrada, J. E. Jensen, J. Robinson","doi":"10.1109/AERO.2001.931169","DOIUrl":"https://doi.org/10.1109/AERO.2001.931169","url":null,"abstract":"The AFRL has pursued high temperature IR FPAs for three years. A 10 K increase has been obtained to date by thinning the HgCdTe base-layer. A contract has recently been let to DRS Infrared Technologies to further increase operating temperature by 15 K utilizing their gold doped High Density Vertically Integrated Photodiode (HDVIP/sup TM/) technology. The increased operating temperatures of these devices will reduce power, weight, and cost, as well as extend the lifetime of space surveillance satellites, satisfying a critical 21st century device technology need.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"63 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114766996","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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