Pub Date : 1993-01-31DOI: 10.1109/AERO.1993.255320
J.J. Damran
The instrumentation and control system (ICS) of the Weapons Engineering Tritium Facility (WETF), a facility for processing tritium for various applications and experiments at the Los Alamos National Laboratory, is described. The ICS integrates all of the WETF process subsystems into a single cohesive unit. The hardware and software of the ICS provide a broad range of functions for the WETF operation, all of which must be performed under stringent safety requirements, and all of which must have a relatively high level of availability, efficiency of operations, and modifiability. The ICS features automatic computerized control for all of the WETF subsystems and permits computer manual control with appropriate software interlocks for process reliability and efficiency. It incorporates distributed intelligence to perform the data acquisition and process control functions and provides a centralized control room with color graphics monitors for the man-machine interface.<>
{"title":"Instrumentation and control system design for the Weapons Engineering Tritium Facility, Los Alamos National Laboratory","authors":"J.J. Damran","doi":"10.1109/AERO.1993.255320","DOIUrl":"https://doi.org/10.1109/AERO.1993.255320","url":null,"abstract":"The instrumentation and control system (ICS) of the Weapons Engineering Tritium Facility (WETF), a facility for processing tritium for various applications and experiments at the Los Alamos National Laboratory, is described. The ICS integrates all of the WETF process subsystems into a single cohesive unit. The hardware and software of the ICS provide a broad range of functions for the WETF operation, all of which must be performed under stringent safety requirements, and all of which must have a relatively high level of availability, efficiency of operations, and modifiability. The ICS features automatic computerized control for all of the WETF subsystems and permits computer manual control with appropriate software interlocks for process reliability and efficiency. It incorporates distributed intelligence to perform the data acquisition and process control functions and provides a centralized control room with color graphics monitors for the man-machine interface.<<ETX>>","PeriodicalId":136219,"journal":{"name":"1993 IEEE Aerospace Applications Conference Digest","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-01-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124433258","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 : 1993-01-31DOI: 10.1109/AERO.1993.255329
W. Gregorwich, R. Ward
A compact shipboard antenna array that provides full hemispherical electronic scan and tracking is described. Using surface acoustic wave (SAW) devices and microstrip variable power combiners (VPCs), the autonomous array can track and receive telemetry data from a submarine-launched Trident II missile just as well as a large mechanically scanned dish antenna. The tracking antenna consists of three-element microstrip patch antenna panels located every 60 degrees around the periphery of the antenna. There are two adjacent patch radiators for both azimuth and elevation angle-of-arrival direction-finding. The tracking information from the SAW is fed into a microprocessor which selects the optimum patch polarization and chooses which high-gain helix radiator to turn on to point to the missile. The energy is transferred from one helix to another by means of VPCs and switches via microprocessor commands. When the VPC has energy equal to that of two adjacent helices, there is a 3-dB increase in gain due to the two-element array factor.<>
{"title":"An autonomous antenna for aerospace applications","authors":"W. Gregorwich, R. Ward","doi":"10.1109/AERO.1993.255329","DOIUrl":"https://doi.org/10.1109/AERO.1993.255329","url":null,"abstract":"A compact shipboard antenna array that provides full hemispherical electronic scan and tracking is described. Using surface acoustic wave (SAW) devices and microstrip variable power combiners (VPCs), the autonomous array can track and receive telemetry data from a submarine-launched Trident II missile just as well as a large mechanically scanned dish antenna. The tracking antenna consists of three-element microstrip patch antenna panels located every 60 degrees around the periphery of the antenna. There are two adjacent patch radiators for both azimuth and elevation angle-of-arrival direction-finding. The tracking information from the SAW is fed into a microprocessor which selects the optimum patch polarization and chooses which high-gain helix radiator to turn on to point to the missile. The energy is transferred from one helix to another by means of VPCs and switches via microprocessor commands. When the VPC has energy equal to that of two adjacent helices, there is a 3-dB increase in gain due to the two-element array factor.<<ETX>>","PeriodicalId":136219,"journal":{"name":"1993 IEEE Aerospace Applications Conference Digest","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-01-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130443481","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 : 1993-01-31DOI: 10.1109/AERO.1993.255330
H. Malliot
The conceptual design and a spaceborne, high-resolution, wide-swath synthetic aperture radar (SAR) and radar altimeter that can be implemented in L, C or X-band or in a combination of bands is described. The design uses active planar array antennas to form multiple independent beams that cover swaths of up to 700 km. A dual C/X-band array can be used. From an altitude of 800 km, up to five beams provide contiguous SAR coverage tracks. A sixth beam, directed at nadir, is used for radar altimetry. Any combination of SAR beams can be selected and they can be scanned in elevation and azimuth to optimize image geometry and resolution. All beams transmit, simultaneously, 66.2- mu s pulses at a pulse repetition frequency (PRF) of 1365 Hz. The multiple-look cross-track-resolved distance ranges from 6.5 m to 7.8 m, and the azimuth-resolved distance ranges from 6 to 11 m over a 491 km swath made up to four tracks. The altimeter beam transmits linear frequency modulated pulses with a bandwidth of 320 MHz and can obtain an altitude precision of 4.2 cm.<>
{"title":"Wide swath SAR and radar altimeter","authors":"H. Malliot","doi":"10.1109/AERO.1993.255330","DOIUrl":"https://doi.org/10.1109/AERO.1993.255330","url":null,"abstract":"The conceptual design and a spaceborne, high-resolution, wide-swath synthetic aperture radar (SAR) and radar altimeter that can be implemented in L, C or X-band or in a combination of bands is described. The design uses active planar array antennas to form multiple independent beams that cover swaths of up to 700 km. A dual C/X-band array can be used. From an altitude of 800 km, up to five beams provide contiguous SAR coverage tracks. A sixth beam, directed at nadir, is used for radar altimetry. Any combination of SAR beams can be selected and they can be scanned in elevation and azimuth to optimize image geometry and resolution. All beams transmit, simultaneously, 66.2- mu s pulses at a pulse repetition frequency (PRF) of 1365 Hz. The multiple-look cross-track-resolved distance ranges from 6.5 m to 7.8 m, and the azimuth-resolved distance ranges from 6 to 11 m over a 491 km swath made up to four tracks. The altimeter beam transmits linear frequency modulated pulses with a bandwidth of 320 MHz and can obtain an altitude precision of 4.2 cm.<<ETX>>","PeriodicalId":136219,"journal":{"name":"1993 IEEE Aerospace Applications Conference Digest","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-01-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133170083","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 : 1993-01-31DOI: 10.1109/AERO.1993.255337
C. Tsang
The simulation performance of simultaneous tracking and data-relay satellite system (TDRSS) support of Space Station and Space Shuttle communication is discussed. Eight Ku- and S-band forward and return links are considered. The models and parameters of the systems are described in detail in an accompanying paper (see ibid., p.1-9).<>
{"title":"Simulation performance of simultaneous TDRSS support of Space Station and Space Shuttle","authors":"C. Tsang","doi":"10.1109/AERO.1993.255337","DOIUrl":"https://doi.org/10.1109/AERO.1993.255337","url":null,"abstract":"The simulation performance of simultaneous tracking and data-relay satellite system (TDRSS) support of Space Station and Space Shuttle communication is discussed. Eight Ku- and S-band forward and return links are considered. The models and parameters of the systems are described in detail in an accompanying paper (see ibid., p.1-9).<<ETX>>","PeriodicalId":136219,"journal":{"name":"1993 IEEE Aerospace Applications Conference Digest","volume":"2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-01-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125457053","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 : 1993-01-31DOI: 10.1109/AERO.1993.255321
C. Grimes, D. M. Grimes
The concepts and materials for reducing electromagnetic interference (EMI) are reviewed. Configurations that are and are not susceptible to EMI are discussed. EMI-reducing materials (absorbers) that are dielectric or magnetic, uniform or nonuniform, chiral or nonchiral, and natural or synthetic are discussed. Absorber design depends on the frequency range, the quantity of shielding required, and the physical characteristics of the devices being shielded.<>
{"title":"A brief discussion of EMI shielding materials","authors":"C. Grimes, D. M. Grimes","doi":"10.1109/AERO.1993.255321","DOIUrl":"https://doi.org/10.1109/AERO.1993.255321","url":null,"abstract":"The concepts and materials for reducing electromagnetic interference (EMI) are reviewed. Configurations that are and are not susceptible to EMI are discussed. EMI-reducing materials (absorbers) that are dielectric or magnetic, uniform or nonuniform, chiral or nonchiral, and natural or synthetic are discussed. Absorber design depends on the frequency range, the quantity of shielding required, and the physical characteristics of the devices being shielded.<<ETX>>","PeriodicalId":136219,"journal":{"name":"1993 IEEE Aerospace Applications Conference Digest","volume":"144 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-01-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132577197","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 : 1993-01-31DOI: 10.1109/AERO.1993.255324
M. Maier
Quality function deployment, (QFD), an approach to synthesizing several elements of system modeling and design into single unit, is presented. Behavioral, physical, and performance modeling are usually considered as separate aspects of system design without explicit linkages. Structured methodologies have developed linkages between behavioral and physical models before, but have not considered the integration of performance models. QFD integrates performance models with traditional structured models. In this method, performance requirements such as cost, weight, and detection range are partitioned into matrices. Partitioning is done by developing a performance model, preferably quantitative, for each requirement. The parameters of the model become the engineering objectives in a QFD analysis and the models are embedded in a spreadsheet version of the traditional QFD matrices. The performance model and its parameters are used to derive part of the functional model by recognizing that a given performance model implies some structure to the functionality of the system.<>
{"title":"Performance analysis, quality function deployment and structured methods","authors":"M. Maier","doi":"10.1109/AERO.1993.255324","DOIUrl":"https://doi.org/10.1109/AERO.1993.255324","url":null,"abstract":"Quality function deployment, (QFD), an approach to synthesizing several elements of system modeling and design into single unit, is presented. Behavioral, physical, and performance modeling are usually considered as separate aspects of system design without explicit linkages. Structured methodologies have developed linkages between behavioral and physical models before, but have not considered the integration of performance models. QFD integrates performance models with traditional structured models. In this method, performance requirements such as cost, weight, and detection range are partitioned into matrices. Partitioning is done by developing a performance model, preferably quantitative, for each requirement. The parameters of the model become the engineering objectives in a QFD analysis and the models are embedded in a spreadsheet version of the traditional QFD matrices. The performance model and its parameters are used to derive part of the functional model by recognizing that a given performance model implies some structure to the functionality of the system.<<ETX>>","PeriodicalId":136219,"journal":{"name":"1993 IEEE Aerospace Applications Conference Digest","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-01-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132851141","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 : 1993-01-31DOI: 10.1109/AERO.1993.255326
N. A. Nelson, J.M. Lenehan
The elements of a space system, presented in a conversational form meant for a broad audience, are reviewed. The rationale of why space is useful for certain missions and each of the elements of a space system are described. The elements are the orbits and constellations, launch vehicles, and the design and construction of the spacecraft. The launch systems discussion emphasizes the enormous amount of energy required to put an object into orbit, a fact critical to understanding why weight is such an important parameter for spacecraft design. The chronology and spatial characteristics of launches into various orbits are covered. Worldwide launch sites are shown along with the reasons why their locations are chosen. A significant portion of the discussion covers spacecraft design. Beginning with the payload, which is the subsystem that performs the mission, each spacecraft subsystem is described. The final subsystem described is telemetry, tracking, and control, followed by a discussion of ground stations.<>
{"title":"Space systems overview","authors":"N. A. Nelson, J.M. Lenehan","doi":"10.1109/AERO.1993.255326","DOIUrl":"https://doi.org/10.1109/AERO.1993.255326","url":null,"abstract":"The elements of a space system, presented in a conversational form meant for a broad audience, are reviewed. The rationale of why space is useful for certain missions and each of the elements of a space system are described. The elements are the orbits and constellations, launch vehicles, and the design and construction of the spacecraft. The launch systems discussion emphasizes the enormous amount of energy required to put an object into orbit, a fact critical to understanding why weight is such an important parameter for spacecraft design. The chronology and spatial characteristics of launches into various orbits are covered. Worldwide launch sites are shown along with the reasons why their locations are chosen. A significant portion of the discussion covers spacecraft design. Beginning with the payload, which is the subsystem that performs the mission, each spacecraft subsystem is described. The final subsystem described is telemetry, tracking, and control, followed by a discussion of ground stations.<<ETX>>","PeriodicalId":136219,"journal":{"name":"1993 IEEE Aerospace Applications Conference Digest","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-01-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130379145","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 : 1993-01-31DOI: 10.1109/AERO.1993.255325
R. Higgins, J. Tront
The HERCULES (hand held, earth oriented, real-time, cooperative, user friendly, location, targeting, and environmental system) attitude processor (HAP), a microprocessor-based gyro attitude data processing system used in the geolocation process, is described. The HAP software and hardware structures are discussed. A worst-case analysis of the design shows that there are no design flaws. The HERCULES HAP and attitude reference unit (ARU) are able to track the Earth rate to within 0.005 degrees per hour in some cases, and always within 0.05 degrees per hour. ARU alignment methods have been verified. Typical alignment errors are less than 0.03 degrees.<>
{"title":"HERCULES attitude processor: gyro data processing system for real-time geolocation of images captured by astronauts","authors":"R. Higgins, J. Tront","doi":"10.1109/AERO.1993.255325","DOIUrl":"https://doi.org/10.1109/AERO.1993.255325","url":null,"abstract":"The HERCULES (hand held, earth oriented, real-time, cooperative, user friendly, location, targeting, and environmental system) attitude processor (HAP), a microprocessor-based gyro attitude data processing system used in the geolocation process, is described. The HAP software and hardware structures are discussed. A worst-case analysis of the design shows that there are no design flaws. The HERCULES HAP and attitude reference unit (ARU) are able to track the Earth rate to within 0.005 degrees per hour in some cases, and always within 0.05 degrees per hour. ARU alignment methods have been verified. Typical alignment errors are less than 0.03 degrees.<<ETX>>","PeriodicalId":136219,"journal":{"name":"1993 IEEE Aerospace Applications Conference Digest","volume":"15 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-01-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122505052","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 : 1993-01-31DOI: 10.1109/AERO.1993.255333
W. Jemison, P. Herczfeld
A novel acoustooptic beamsteering control system for monolithic-microwave-integrated-circuit (MMIC)-based phased array antennas that uses parallel optical signal processing is presented. The approach is compatible with existing MMIC digital phase shifter and gain controller designs and offers several advantages over conventional beamsteering control systems. An overview of the system architecture, comparison to other beamsteering control alternatives, discussion of several key design issues, and experimental results validating the approach are given.<>
{"title":"An acousto-optically controlled phased array beamsteering system","authors":"W. Jemison, P. Herczfeld","doi":"10.1109/AERO.1993.255333","DOIUrl":"https://doi.org/10.1109/AERO.1993.255333","url":null,"abstract":"A novel acoustooptic beamsteering control system for monolithic-microwave-integrated-circuit (MMIC)-based phased array antennas that uses parallel optical signal processing is presented. The approach is compatible with existing MMIC digital phase shifter and gain controller designs and offers several advantages over conventional beamsteering control systems. An overview of the system architecture, comparison to other beamsteering control alternatives, discussion of several key design issues, and experimental results validating the approach are given.<<ETX>>","PeriodicalId":136219,"journal":{"name":"1993 IEEE Aerospace Applications Conference Digest","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-01-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124831169","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 : 1993-01-31DOI: 10.1109/AERO.1993.255331
A. Harold, ot, L. Missiles
The conceptual design of a cross beam interferometer radiometer (CBIR) for sea surface temperature sensing at 5.0 GHz is described. In a 833-km orbit, the radiometer provides 0.48 K sensitivity with a spatial resolution less than 25 km in a 1561-km swath. The radiometer consists of a pair of rectangular phased arrays in a T configuration. Each array forms ten colinear beams that project ten pairs of crossed elliptical footprints on the sea surface. The footprints from the horizontal array have minor axes that range from 14.6 km to 22.9 km and are oriented in the cross-track direction. The footprints from the vertical array have minor axes that range from 18.6 km to 25.0 km and are oriented in the along-track direction. The Mills periodic 0-180 degrees switching radio telescope technique is used to sense the variations in sea surface radio-thermal brightness temperature in the coincidence areas where the beams overlap. The CBIR concept, system design approach, antenna design and beamforming technique are described.<>
{"title":"A cross beam interferometer radiometer for high resolution microwave sensing","authors":"A. Harold, ot, L. Missiles","doi":"10.1109/AERO.1993.255331","DOIUrl":"https://doi.org/10.1109/AERO.1993.255331","url":null,"abstract":"The conceptual design of a cross beam interferometer radiometer (CBIR) for sea surface temperature sensing at 5.0 GHz is described. In a 833-km orbit, the radiometer provides 0.48 K sensitivity with a spatial resolution less than 25 km in a 1561-km swath. The radiometer consists of a pair of rectangular phased arrays in a T configuration. Each array forms ten colinear beams that project ten pairs of crossed elliptical footprints on the sea surface. The footprints from the horizontal array have minor axes that range from 14.6 km to 22.9 km and are oriented in the cross-track direction. The footprints from the vertical array have minor axes that range from 18.6 km to 25.0 km and are oriented in the along-track direction. The Mills periodic 0-180 degrees switching radio telescope technique is used to sense the variations in sea surface radio-thermal brightness temperature in the coincidence areas where the beams overlap. The CBIR concept, system design approach, antenna design and beamforming technique are described.<<ETX>>","PeriodicalId":136219,"journal":{"name":"1993 IEEE Aerospace Applications Conference Digest","volume":"39 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-01-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126670008","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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