Pub Date : 1990-02-04DOI: 10.1109/AERO.1990.109084
J. Smith
The preliminary design of the space-to-ground packet communications services that have been recommended for the Space Station Freedom Manned Base (SSFMB) is discussed. The packet communications services between the Space Station Freedom and the ground control centers are considered. The packet communications services described include path service for the unacknowledged and unconfirmed delivery of classical spacecraft telemetry, and internet service, which is to be used for the general computer-to-computer communications between the SSFMB and the ground control centers. The concepts of the virtual channel as it relates to delivery of the described packet services are introduced, and other data delivery services that will be provided by the Space Station Information System are briefly reviewed.<>
{"title":"Packet communications services for the Space Station Freedom","authors":"J. Smith","doi":"10.1109/AERO.1990.109084","DOIUrl":"https://doi.org/10.1109/AERO.1990.109084","url":null,"abstract":"The preliminary design of the space-to-ground packet communications services that have been recommended for the Space Station Freedom Manned Base (SSFMB) is discussed. The packet communications services between the Space Station Freedom and the ground control centers are considered. The packet communications services described include path service for the unacknowledged and unconfirmed delivery of classical spacecraft telemetry, and internet service, which is to be used for the general computer-to-computer communications between the SSFMB and the ground control centers. The concepts of the virtual channel as it relates to delivery of the described packet services are introduced, and other data delivery services that will be provided by the Space Station Information System are briefly reviewed.<<ETX>>","PeriodicalId":141316,"journal":{"name":"IEEE Conference on Aerospace Applications","volume":"37 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1990-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117224062","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 : 1990-02-04DOI: 10.1109/AERO.1990.109090
D. Tamanaha, P. Bourgeois
Rapid prototyping is examined from three points of view: management, rapid analysis, and design. A rapid prototyping approach is presented for end-user requirements of large, data-intensive, command and control (C/sup 2/); command, control, communications and intelligence (C/sup 3/I); and command and control information systems (CCIS). It is noted that participatory management, highly motivated personnel, thorough knowledge of the targeted system's operations, sound prototyping methodology, appropriate tools, and innovative techniques used by an integrated team allow for severe schedule constraints and provide the edge for fast implementation. Modified structured methods and further innovations allow a rapid prototype cycle. Experience gained and examples are cited to illustrate the ideas and methods used in successful C/sup 3/I and CCIS prototypes. The authors discuss the compressed usage of known methods and introduce an innovative design method for the rapid development of operational threads as an integrating design technique to quickly assemble knowledge of disparate design views and disciplines under severe prototyping schedule constraints.<>
{"title":"Rapid prototyping of large command, control, communications and intelligence C/sup 3/I systems","authors":"D. Tamanaha, P. Bourgeois","doi":"10.1109/AERO.1990.109090","DOIUrl":"https://doi.org/10.1109/AERO.1990.109090","url":null,"abstract":"Rapid prototyping is examined from three points of view: management, rapid analysis, and design. A rapid prototyping approach is presented for end-user requirements of large, data-intensive, command and control (C/sup 2/); command, control, communications and intelligence (C/sup 3/I); and command and control information systems (CCIS). It is noted that participatory management, highly motivated personnel, thorough knowledge of the targeted system's operations, sound prototyping methodology, appropriate tools, and innovative techniques used by an integrated team allow for severe schedule constraints and provide the edge for fast implementation. Modified structured methods and further innovations allow a rapid prototype cycle. Experience gained and examples are cited to illustrate the ideas and methods used in successful C/sup 3/I and CCIS prototypes. The authors discuss the compressed usage of known methods and introduce an innovative design method for the rapid development of operational threads as an integrating design technique to quickly assemble knowledge of disparate design views and disciplines under severe prototyping schedule constraints.<<ETX>>","PeriodicalId":141316,"journal":{"name":"IEEE Conference on Aerospace Applications","volume":"97 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1990-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122883124","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 : 1990-02-04DOI: 10.1109/AERO.1990.109075
C. Tsang
The basic operation principle of the TACAN navigation system on the Space Shuttle is described. An issue of interest to NASA engineers is the effect of the loss of the blanking pulse in the system. A simplified operation model of the shuttle TACAN receiver is presented. The effect is analyzed from the interference point of view in case of blanking pulse loss.<>
{"title":"Operation principle and loss of blanking pulse of the navigation system on Space Shuttle","authors":"C. Tsang","doi":"10.1109/AERO.1990.109075","DOIUrl":"https://doi.org/10.1109/AERO.1990.109075","url":null,"abstract":"The basic operation principle of the TACAN navigation system on the Space Shuttle is described. An issue of interest to NASA engineers is the effect of the loss of the blanking pulse in the system. A simplified operation model of the shuttle TACAN receiver is presented. The effect is analyzed from the interference point of view in case of blanking pulse loss.<<ETX>>","PeriodicalId":141316,"journal":{"name":"IEEE Conference on Aerospace Applications","volume":"39 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1990-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123304637","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 : 1990-02-04DOI: 10.1109/AERO.1990.109074
G.H. Schennum, L. Ersoy
A multifunction antenna subsystem consisting of communications and telemetry/command antennas for the INTELSAT VII communications satellite is described. The antenna subsystem design is dictated by a requirement to provide multiple communications links between the Earth and the spacecraft and by a need to track, command, and monitor the spacecraft during all phases of its flight. The eight different types of antennas on the spacecraft are described in detail. The subsystem performance has been analytically verified by computer modeling. The basic hardware design has been completed, and fabrication and testing of the engineering model hardware are in progress.<>
{"title":"Antenna subsystem for the INTELSAT VII spacecraft","authors":"G.H. Schennum, L. Ersoy","doi":"10.1109/AERO.1990.109074","DOIUrl":"https://doi.org/10.1109/AERO.1990.109074","url":null,"abstract":"A multifunction antenna subsystem consisting of communications and telemetry/command antennas for the INTELSAT VII communications satellite is described. The antenna subsystem design is dictated by a requirement to provide multiple communications links between the Earth and the spacecraft and by a need to track, command, and monitor the spacecraft during all phases of its flight. The eight different types of antennas on the spacecraft are described in detail. The subsystem performance has been analytically verified by computer modeling. The basic hardware design has been completed, and fabrication and testing of the engineering model hardware are in progress.<<ETX>>","PeriodicalId":141316,"journal":{"name":"IEEE Conference on Aerospace Applications","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1990-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127901039","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 : 1990-02-04DOI: 10.1109/AERO.1990.109072
W. Gregorwich
The design and development of a K-band polarization selective reflector (PRS) system are discussed. Waveguide simulator measurements showed close agreement with parallel wire theory. The radiation pattern measurements of PSR demonstrated almost complete reflection in one polarization with excellent cross-polarization isolation. An offset reflector configuration was chosen for the investigation because it is a compact versatile design for spacecraft applications. Transmissivity tests demonstrated that there is no significant change in the principal polarization patterns of the solid reflector with the PSR placed in front of the solid. The cross-polarization level is lower with the PSR in place. The measurements also demonstrated that the waveguide simulator is an essential tool in the design of grid reflectors. The excellent correlation between measured and calculated performance of reflected energy from parallel wires indicates that an experiment is not necessary to determine the electric field (E-field) parallel to the wires. However, for transmission through the grid, the inexpensive waveguide simulator is indispensable for predicting transmission at various angles for an E-field perpendicular to the grid.<>
{"title":"Polarization selective reflectors for spacecraft applications","authors":"W. Gregorwich","doi":"10.1109/AERO.1990.109072","DOIUrl":"https://doi.org/10.1109/AERO.1990.109072","url":null,"abstract":"The design and development of a K-band polarization selective reflector (PRS) system are discussed. Waveguide simulator measurements showed close agreement with parallel wire theory. The radiation pattern measurements of PSR demonstrated almost complete reflection in one polarization with excellent cross-polarization isolation. An offset reflector configuration was chosen for the investigation because it is a compact versatile design for spacecraft applications. Transmissivity tests demonstrated that there is no significant change in the principal polarization patterns of the solid reflector with the PSR placed in front of the solid. The cross-polarization level is lower with the PSR in place. The measurements also demonstrated that the waveguide simulator is an essential tool in the design of grid reflectors. The excellent correlation between measured and calculated performance of reflected energy from parallel wires indicates that an experiment is not necessary to determine the electric field (E-field) parallel to the wires. However, for transmission through the grid, the inexpensive waveguide simulator is indispensable for predicting transmission at various angles for an E-field perpendicular to the grid.<<ETX>>","PeriodicalId":141316,"journal":{"name":"IEEE Conference on Aerospace Applications","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1990-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117057138","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 : 1990-02-04DOI: 10.1109/AERO.1990.109070
M. Plonski
One component of the Automated Remote Tracking Station (ARTS) Program is the ability to acquire a satellite transmission automatically. Under abnormal conditions, where the ephemeris is not precisely known, it is necessary to ensure that the antenna is positioned on the main beam prior to engaging monopulse tracking to complete the acquisition. The ARTS program uses an automated main beam acquisition procedure that is based on auxiliary-aperture amplitude comparison (AAAC) for initial main beam detection, followed by centroiding for main beam convergence. A method for determining a robust decision boundary for use in AAAC is presented. Compared to other methods, this boundary allows for greater tolerance of errors at a lower cost to the input dynamic range. Several improved alternatives to centroiding for main beam convergence are also presented. These techniques are not restricted to satellites and can be used to acquire the transmission from any transmitter.<>
{"title":"Spatial acquisition of satellite transmissions in the presence of ephemeris errors","authors":"M. Plonski","doi":"10.1109/AERO.1990.109070","DOIUrl":"https://doi.org/10.1109/AERO.1990.109070","url":null,"abstract":"One component of the Automated Remote Tracking Station (ARTS) Program is the ability to acquire a satellite transmission automatically. Under abnormal conditions, where the ephemeris is not precisely known, it is necessary to ensure that the antenna is positioned on the main beam prior to engaging monopulse tracking to complete the acquisition. The ARTS program uses an automated main beam acquisition procedure that is based on auxiliary-aperture amplitude comparison (AAAC) for initial main beam detection, followed by centroiding for main beam convergence. A method for determining a robust decision boundary for use in AAAC is presented. Compared to other methods, this boundary allows for greater tolerance of errors at a lower cost to the input dynamic range. Several improved alternatives to centroiding for main beam convergence are also presented. These techniques are not restricted to satellites and can be used to acquire the transmission from any transmitter.<<ETX>>","PeriodicalId":141316,"journal":{"name":"IEEE Conference on Aerospace Applications","volume":"84 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1990-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124142367","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 : 1990-02-04DOI: 10.1109/AERO.1990.109077
D. Dickinson, W. Straka
The possibility of using long (multi-kilometer) tethers in orbit, particularly for passive radar surveillance, is examined. Such devices could use the echo derived from common UHF and VHF sources (primarily commercial radio and television stations) for target range and Doppler estimation. Such systems could provide high gain (50-60 dB) and high spatial resolution at low frequencies. Configurations, stability, and other problems associated with satellite tethers are discussed.<>
{"title":"Tethered satellite antenna arrays for passive radar systems","authors":"D. Dickinson, W. Straka","doi":"10.1109/AERO.1990.109077","DOIUrl":"https://doi.org/10.1109/AERO.1990.109077","url":null,"abstract":"The possibility of using long (multi-kilometer) tethers in orbit, particularly for passive radar surveillance, is examined. Such devices could use the echo derived from common UHF and VHF sources (primarily commercial radio and television stations) for target range and Doppler estimation. Such systems could provide high gain (50-60 dB) and high spatial resolution at low frequencies. Configurations, stability, and other problems associated with satellite tethers are discussed.<<ETX>>","PeriodicalId":141316,"journal":{"name":"IEEE Conference on Aerospace Applications","volume":"70 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1990-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129494339","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 : 1990-02-04DOI: 10.1109/AERO.1990.109087
B. Patel
The application of a relational DBMS (database management system) to the development, generation, and operation of NATO's Northern European Command (NEC) Command, Control, Information System (CCIS) is discussed. The DBMS (Britton Lee's back-end processor IDM 500) is used both as a component of the deliverable application system and as a support tool for offline development work. An overview of the system data engineering methodology used in the project is presented together with the lessons learned in designing such a large complex data-intensive system. The DBMS, in supporting the application database, handles formatted text, graphics and message data. The data model for this database supports sixteen military operational disciplines (air operations, intelligence, weather, etc.).<>
{"title":"Application of a DBMS in a large command, control, and information system","authors":"B. Patel","doi":"10.1109/AERO.1990.109087","DOIUrl":"https://doi.org/10.1109/AERO.1990.109087","url":null,"abstract":"The application of a relational DBMS (database management system) to the development, generation, and operation of NATO's Northern European Command (NEC) Command, Control, Information System (CCIS) is discussed. The DBMS (Britton Lee's back-end processor IDM 500) is used both as a component of the deliverable application system and as a support tool for offline development work. An overview of the system data engineering methodology used in the project is presented together with the lessons learned in designing such a large complex data-intensive system. The DBMS, in supporting the application database, handles formatted text, graphics and message data. The data model for this database supports sixteen military operational disciplines (air operations, intelligence, weather, etc.).<<ETX>>","PeriodicalId":141316,"journal":{"name":"IEEE Conference on Aerospace Applications","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1990-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126047849","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 : 1990-02-04DOI: 10.1109/AERO.1990.109068
S. Rahmani, B. Smith
A system concept to improve the state of practice in space-based payload support and provide data processing, command and telemetry, and friendly crew interface for Shuttle experiments is introduced. It is also designed to serve as a mission support system on the ground. A prototype of the system was developed in the laboratory and demonstrated in real time. It includes custom-made units such as the flight computer (MIL-STD-1750A), flat panel display, programmable decommutator, and command formatter. The system can also be used as a ground control and monitor station. The system software was modified to handle up to four payloads concurrently while maintaining isolation among them. The prototype system was demonstrated in multiple payload applications, including the orbital refueling system flown on the Shuttle. It was demonstrated that the effectiveness of the Shuttle system for handling and supporting payloads can be improved by streamlining the payload integration process by decoupling it from the Shuttle core avionics system, using advanced technologies for effective use by the Shuttle crew, and reducing and/or eliminating the need to develop payload-unique avionics.<>
{"title":"A command and data system for concurrent handling of multiple payloads","authors":"S. Rahmani, B. Smith","doi":"10.1109/AERO.1990.109068","DOIUrl":"https://doi.org/10.1109/AERO.1990.109068","url":null,"abstract":"A system concept to improve the state of practice in space-based payload support and provide data processing, command and telemetry, and friendly crew interface for Shuttle experiments is introduced. It is also designed to serve as a mission support system on the ground. A prototype of the system was developed in the laboratory and demonstrated in real time. It includes custom-made units such as the flight computer (MIL-STD-1750A), flat panel display, programmable decommutator, and command formatter. The system can also be used as a ground control and monitor station. The system software was modified to handle up to four payloads concurrently while maintaining isolation among them. The prototype system was demonstrated in multiple payload applications, including the orbital refueling system flown on the Shuttle. It was demonstrated that the effectiveness of the Shuttle system for handling and supporting payloads can be improved by streamlining the payload integration process by decoupling it from the Shuttle core avionics system, using advanced technologies for effective use by the Shuttle crew, and reducing and/or eliminating the need to develop payload-unique avionics.<<ETX>>","PeriodicalId":141316,"journal":{"name":"IEEE Conference on Aerospace Applications","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1990-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133273616","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 : 1990-02-04DOI: 10.1109/AERO.1990.109076
A. Maksymowicz
It is pointed out that the detection of a limited number of key words in voice communications, combined with nonlinguistic cues and situation knowledge, holds out the promise for automatic extraction of the general content or gist of the transmitted messages. A systems-level description of an end-to-end automatic gisting system for screening voice communications is presented. The emphasis is on identifying information which can usefully supplement the detected key words in the gisting process. Principal subsystems are identified, and their functions are discussed in the context of an overall system architecture. The example of automatic determination of aircraft takeoffs and landings at an airport, based on monitoring conversations between pilots and air traffic controllers, is used for illustrative purposes.<>
{"title":"Automated gisting systems for voice communications","authors":"A. Maksymowicz","doi":"10.1109/AERO.1990.109076","DOIUrl":"https://doi.org/10.1109/AERO.1990.109076","url":null,"abstract":"It is pointed out that the detection of a limited number of key words in voice communications, combined with nonlinguistic cues and situation knowledge, holds out the promise for automatic extraction of the general content or gist of the transmitted messages. A systems-level description of an end-to-end automatic gisting system for screening voice communications is presented. The emphasis is on identifying information which can usefully supplement the detected key words in the gisting process. Principal subsystems are identified, and their functions are discussed in the context of an overall system architecture. The example of automatic determination of aircraft takeoffs and landings at an airport, based on monitoring conversations between pilots and air traffic controllers, is used for illustrative purposes.<<ETX>>","PeriodicalId":141316,"journal":{"name":"IEEE Conference on Aerospace Applications","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1990-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127934296","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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