The second-generation satellites of INMARSAT (International Maritime Satellite Organization) are in the final stage of integration and testing. The satellites will satisfy the needs originated by the rapid expansion of the system and will allow the introduction of new mobile communications services. The authors outline the essentials of the spacecraft design and the types of services that will be provided using the new satellites; in particular, they consider the characteristics of the communications transponder, its design and technology, the requirements and the design solutions, and the most significant communications parameters. Paralleled linearized traveling-wave amplifiers, L-band shaped global direct radiating array antennas, and surface-acoustic-wave channelization filters are being implemented in the system. Passive intermodulation product generation and multipaction are being recognized as design drivers.<>
{"title":"INMARSAT second generation satellites for mobile communications","authors":"E. Gambaruto, D. Banks, B. Krinsky","doi":"10.1109/AERO.1989.82422","DOIUrl":"https://doi.org/10.1109/AERO.1989.82422","url":null,"abstract":"The second-generation satellites of INMARSAT (International Maritime Satellite Organization) are in the final stage of integration and testing. The satellites will satisfy the needs originated by the rapid expansion of the system and will allow the introduction of new mobile communications services. The authors outline the essentials of the spacecraft design and the types of services that will be provided using the new satellites; in particular, they consider the characteristics of the communications transponder, its design and technology, the requirements and the design solutions, and the most significant communications parameters. Paralleled linearized traveling-wave amplifiers, L-band shaped global direct radiating array antennas, and surface-acoustic-wave channelization filters are being implemented in the system. Passive intermodulation product generation and multipaction are being recognized as design drivers.<<ETX>>","PeriodicalId":414116,"journal":{"name":"IEEE Aerospace Applications Conference","volume":"39 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1989-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114602253","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}
A database application called DFACS (database, forms and applications for cabling and systems) is described. The objective of DFACS is to improve the speed and accuracy of interconnection system information flow during the design and fabrication stages of a project, while simultaneously supporting both the horizontal (end-to-end wiring) and the vertical (wiring by connector) design stratagems used by the Jet Propulsion Laboratory (JPL) project engineering community. The DFACS architecture is centered around a centralized database and program methodology which emulates the manual design process hitherto used at JPL. DFACS has been tested and successfully applied to existing JPL hardware tasks with a resulting reduction in schedule time and costs.<>
{"title":"Centralized database for interconnection system design","authors":"J. W. Billitti","doi":"10.1109/AERO.1989.82412","DOIUrl":"https://doi.org/10.1109/AERO.1989.82412","url":null,"abstract":"A database application called DFACS (database, forms and applications for cabling and systems) is described. The objective of DFACS is to improve the speed and accuracy of interconnection system information flow during the design and fabrication stages of a project, while simultaneously supporting both the horizontal (end-to-end wiring) and the vertical (wiring by connector) design stratagems used by the Jet Propulsion Laboratory (JPL) project engineering community. The DFACS architecture is centered around a centralized database and program methodology which emulates the manual design process hitherto used at JPL. DFACS has been tested and successfully applied to existing JPL hardware tasks with a resulting reduction in schedule time and costs.<<ETX>>","PeriodicalId":414116,"journal":{"name":"IEEE Aerospace Applications Conference","volume":"45 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1989-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114849453","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}
The Air Force Space Technology Center (AFSTC) has been charged with the management of programs to reduce satellite costs through the appropriate use of microelectronics standardization. Ongoing AFSTC technology programs such as the Standard Spacecraft Memory Module (SSMM) and Generic VHSIC Spaceborne Computer (GVSC) have provided an insight into the value and application of microelectronics standardization. Based on these insights, an initiative has been started to coordinate microelectronics development around a standard satellite data bus. Efforts are underway to determine satellite data bus requirements and benefits. Development of a data bus standard is expected to reduce costs by eliminating program and contractor unique interfaces, allowing increased production runs and developing generic test equipment. Current standard data bus efforts are focusing on the satellite housekeeping functions. Based on housekeeping data traffic requirements that has been developed, several data bus candidates exist for the standard data bus.<>
{"title":"Standard satellite data bus initiative","authors":"T. Spinney, H. Yousef","doi":"10.1109/AERO.1989.82414","DOIUrl":"https://doi.org/10.1109/AERO.1989.82414","url":null,"abstract":"The Air Force Space Technology Center (AFSTC) has been charged with the management of programs to reduce satellite costs through the appropriate use of microelectronics standardization. Ongoing AFSTC technology programs such as the Standard Spacecraft Memory Module (SSMM) and Generic VHSIC Spaceborne Computer (GVSC) have provided an insight into the value and application of microelectronics standardization. Based on these insights, an initiative has been started to coordinate microelectronics development around a standard satellite data bus. Efforts are underway to determine satellite data bus requirements and benefits. Development of a data bus standard is expected to reduce costs by eliminating program and contractor unique interfaces, allowing increased production runs and developing generic test equipment. Current standard data bus efforts are focusing on the satellite housekeeping functions. Based on housekeeping data traffic requirements that has been developed, several data bus candidates exist for the standard data bus.<<ETX>>","PeriodicalId":414116,"journal":{"name":"IEEE Aerospace Applications Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1989-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129261025","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}
Large-area surveillance can be achieved by the use of a beam-forming antenna consisting of two crossed linear arrays. Such an antenna has the advantage that it can be steered electronically and its beam synthesized so that it will have a resolution fully equivalent to that of a filled antenna of equal diameter. It would also be a much lighter antenna, probably no more than 10% to 15% the weight of a filled aperture. The beam-forming function would require the use of high-speed, integrated circuitry. Coverage issues are addressed, and implementation is discussed.<>
{"title":"A cross-array radiometer for spacecraft applications","authors":"W. Gregorwich, D. Dickinson","doi":"10.1109/AERO.1989.82409","DOIUrl":"https://doi.org/10.1109/AERO.1989.82409","url":null,"abstract":"Large-area surveillance can be achieved by the use of a beam-forming antenna consisting of two crossed linear arrays. Such an antenna has the advantage that it can be steered electronically and its beam synthesized so that it will have a resolution fully equivalent to that of a filled antenna of equal diameter. It would also be a much lighter antenna, probably no more than 10% to 15% the weight of a filled aperture. The beam-forming function would require the use of high-speed, integrated circuitry. Coverage issues are addressed, and implementation is discussed.<<ETX>>","PeriodicalId":414116,"journal":{"name":"IEEE Aerospace Applications Conference","volume":"35 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1989-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115166330","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}
The authors discuss deficiencies of CASE (computer-aided software engineering) for aerospace applications, namely little support for large system development, integrated life-cycle development, and system engineering (including functional allocation to hardware and software as well as system specification traceability). They first review components of 'ideal' as well as actual CASE environments and present key selection criteria for such an environment. Presently no CASE product supports all facets of aerospace applications; an interim solution is to combine separate CASE tools for selected areas and/or customize existing CASE products to meet customer or company specified requirements. The authors present an example of customizing a commercial CASE tool to create hardware block diagrams, specification traceability, and specialized reports. The example application involved the customization of Excelerator, a CASE product from Index Technology, so as to incorporate hardware allocation in system engineering requirement analysis.<>
{"title":"The application of CASE in large aerospace projects","authors":"D. Tamanaha, W. C. Wenjen, B. Patel","doi":"10.1109/AERO.1989.82428","DOIUrl":"https://doi.org/10.1109/AERO.1989.82428","url":null,"abstract":"The authors discuss deficiencies of CASE (computer-aided software engineering) for aerospace applications, namely little support for large system development, integrated life-cycle development, and system engineering (including functional allocation to hardware and software as well as system specification traceability). They first review components of 'ideal' as well as actual CASE environments and present key selection criteria for such an environment. Presently no CASE product supports all facets of aerospace applications; an interim solution is to combine separate CASE tools for selected areas and/or customize existing CASE products to meet customer or company specified requirements. The authors present an example of customizing a commercial CASE tool to create hardware block diagrams, specification traceability, and specialized reports. The example application involved the customization of Excelerator, a CASE product from Index Technology, so as to incorporate hardware allocation in system engineering requirement analysis.<<ETX>>","PeriodicalId":414116,"journal":{"name":"IEEE Aerospace Applications Conference","volume":"16 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1989-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128562001","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}
The authors describe an autonomous embedded expert system for satellite-based electronic control systems using multiple sensors. The autonomous expert control system methodology was developed with emphasis on expert system verification. It was demonstrated with a multisensor satellite thermal control subsystem responsible for real-time health and status monitoring, subsystem commanding, and decision assistance. A propositional logic rule base was used to create a rule structure that can be verified and easily transferred into a hardware implementation. The 400 propositional logic rule demonstration of the thermal control subsystem showed the feasibility and testability of the compact expert system approach for autonomous embedded applications.<>
{"title":"A verifiable, autonomous satellite control system","authors":"E. Andert, C. Frasher","doi":"10.1109/AERO.1989.82420","DOIUrl":"https://doi.org/10.1109/AERO.1989.82420","url":null,"abstract":"The authors describe an autonomous embedded expert system for satellite-based electronic control systems using multiple sensors. The autonomous expert control system methodology was developed with emphasis on expert system verification. It was demonstrated with a multisensor satellite thermal control subsystem responsible for real-time health and status monitoring, subsystem commanding, and decision assistance. A propositional logic rule base was used to create a rule structure that can be verified and easily transferred into a hardware implementation. The 400 propositional logic rule demonstration of the thermal control subsystem showed the feasibility and testability of the compact expert system approach for autonomous embedded applications.<<ETX>>","PeriodicalId":414116,"journal":{"name":"IEEE Aerospace Applications Conference","volume":"53 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1989-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126319241","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}
The author describes the work performed in replacing four microwave telemetry data communications systems with one single analog fiber-optics system at Edwards Air Force Base. The fiber-optic system used was initially designed for use in a television video system. Therefore, the author was faced with the problem of determining a method of aligning the fiber-optic system to meet the required needs of the transmission system. The objectives were met by utilizing several well-known methods of AM and FM measurement techniques not yet described in the implementation of fiber-optic communications systems. After alignment, the system transmitted the already developed basebands as well as the original microwave equipment.<>
{"title":"Upgrading microwave telemetry data communications with an analog lightwave system","authors":"H. D. Reynolds","doi":"10.1109/AERO.1989.82415","DOIUrl":"https://doi.org/10.1109/AERO.1989.82415","url":null,"abstract":"The author describes the work performed in replacing four microwave telemetry data communications systems with one single analog fiber-optics system at Edwards Air Force Base. The fiber-optic system used was initially designed for use in a television video system. Therefore, the author was faced with the problem of determining a method of aligning the fiber-optic system to meet the required needs of the transmission system. The objectives were met by utilizing several well-known methods of AM and FM measurement techniques not yet described in the implementation of fiber-optic communications systems. After alignment, the system transmitted the already developed basebands as well as the original microwave equipment.<<ETX>>","PeriodicalId":414116,"journal":{"name":"IEEE Aerospace Applications Conference","volume":"45 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1989-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131601860","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}
S. H. Wood, J.C. Marr, T.T. Nguyen, D. J. Padgett, J.C. Tran, T. Griswold, D.C. Lebowitz
The authors describe an extensive investigation into pattern-sensitive soft errors (read disturb errors) in the TCC244 CMOS static RAM chip. The TCC244, also known as the SA2838, is a radiation-hard, single-event-upset (SEU)-resistant 4 by 256 memory chip. This device is being used by NASA's Jet Propulsion Laboratory in the Galileo and Magellan spacecraft, which will have encounters with Jupiter and Venus, respectively. Two aspects of the part's design are shown to result in the occurrence of read disturb errors: the transparence of the signal path from the address pins to the array of cells, and the large resistance in the Vdd and Vss lines of the cells in the center of the array. Probe measurements taken during a read disturb failure illustrate how address skews and the data pattern in the chip combine to produce a bit flip. A capacitive charge pump formed by the individual cell capacitances and the resistance in the supply lines pumps down both the internal cell voltage and the local supply voltage until a bit flip occurs.<>
{"title":"Read disturb errors in a CMOS static RAM chip","authors":"S. H. Wood, J.C. Marr, T.T. Nguyen, D. J. Padgett, J.C. Tran, T. Griswold, D.C. Lebowitz","doi":"10.1109/AERO.1989.82424","DOIUrl":"https://doi.org/10.1109/AERO.1989.82424","url":null,"abstract":"The authors describe an extensive investigation into pattern-sensitive soft errors (read disturb errors) in the TCC244 CMOS static RAM chip. The TCC244, also known as the SA2838, is a radiation-hard, single-event-upset (SEU)-resistant 4 by 256 memory chip. This device is being used by NASA's Jet Propulsion Laboratory in the Galileo and Magellan spacecraft, which will have encounters with Jupiter and Venus, respectively. Two aspects of the part's design are shown to result in the occurrence of read disturb errors: the transparence of the signal path from the address pins to the array of cells, and the large resistance in the Vdd and Vss lines of the cells in the center of the array. Probe measurements taken during a read disturb failure illustrate how address skews and the data pattern in the chip combine to produce a bit flip. A capacitive charge pump formed by the individual cell capacitances and the resistance in the supply lines pumps down both the internal cell voltage and the local supply voltage until a bit flip occurs.<<ETX>>","PeriodicalId":414116,"journal":{"name":"IEEE Aerospace Applications Conference","volume":"134 Supplement_1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1989-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125377069","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}
Commercial and research-oriented database design tools for the design of data-intensive systems are surveyed. An overview of a generic database design methodology is first given, followed by a set of criteria for selecting an appropriate design tool for the user's environment. Issues dealing with integrating computer-aided software engineering (CASE) tools with database (DB) design tools and the support environment (e.g. configuration control of data dictionary and schemas, database population and testing) are discussed.<>
{"title":"Automated tools for database design and criteria for their selection for aerospace applications","authors":"B. Patel","doi":"10.1109/AERO.1989.82421","DOIUrl":"https://doi.org/10.1109/AERO.1989.82421","url":null,"abstract":"Commercial and research-oriented database design tools for the design of data-intensive systems are surveyed. An overview of a generic database design methodology is first given, followed by a set of criteria for selecting an appropriate design tool for the user's environment. Issues dealing with integrating computer-aided software engineering (CASE) tools with database (DB) design tools and the support environment (e.g. configuration control of data dictionary and schemas, database population and testing) are discussed.<<ETX>>","PeriodicalId":414116,"journal":{"name":"IEEE Aerospace Applications Conference","volume":"134 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1989-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116045368","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}
The authors present a least-squares covariance analysis approach for determining geolocation accuracy using long-baseline interferometry (LBI) measurements from airborne platforms. The equations derived determine the accuracy of the emitter location by extraction of the position error ellipse from the covariance matrix. The model is applicable, however, to both ground-fixed and moving emitters. Emitter position and velocity vector accuracy are evaluated using three aircraft configurations. The sources of error modeled include random and bias measurement error. The results confirm that the covariance approach enables quantitative assessment of the key factors in the engineering synthesis of requirements for aircraft deployment, signal measurement, and geolocation accuracy.<>
{"title":"Passive location accuracy via a general covariance error model","authors":"R. Day, D.R. Oxe","doi":"10.1109/AERO.1989.82423","DOIUrl":"https://doi.org/10.1109/AERO.1989.82423","url":null,"abstract":"The authors present a least-squares covariance analysis approach for determining geolocation accuracy using long-baseline interferometry (LBI) measurements from airborne platforms. The equations derived determine the accuracy of the emitter location by extraction of the position error ellipse from the covariance matrix. The model is applicable, however, to both ground-fixed and moving emitters. Emitter position and velocity vector accuracy are evaluated using three aircraft configurations. The sources of error modeled include random and bias measurement error. The results confirm that the covariance approach enables quantitative assessment of the key factors in the engineering synthesis of requirements for aircraft deployment, signal measurement, and geolocation accuracy.<<ETX>>","PeriodicalId":414116,"journal":{"name":"IEEE Aerospace Applications Conference","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1989-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124075864","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}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：