It is pointed out that significant work has recently been accomplished to develop and demonstrate GaAs RF integrated circuits for millimeter wave sensors. These chip components will affect the size, weight, power consumption, and cost of expendable sensors for tactical applications. This has also sparked renewed interest in collocated multimode sensors operating at both millimeter wave and infrared wavelengths. It is noted that the objective of the MMIC monolithic component development is to supplement, but not necessarily replace, all the hybrid circuitry in any given transceiver architecture. It can be predicted that the long-term implementation strategy for millimeter wave sensors will include a carefully controlled mix between MMIC and hybrid technologies with possibly some waveguide-based critical power components.<>
{"title":"Integrated circuit impact on millimeter wave sensors","authors":"C. Seashore","doi":"10.1109/NTC.1991.148047","DOIUrl":"https://doi.org/10.1109/NTC.1991.148047","url":null,"abstract":"It is pointed out that significant work has recently been accomplished to develop and demonstrate GaAs RF integrated circuits for millimeter wave sensors. These chip components will affect the size, weight, power consumption, and cost of expendable sensors for tactical applications. This has also sparked renewed interest in collocated multimode sensors operating at both millimeter wave and infrared wavelengths. It is noted that the objective of the MMIC monolithic component development is to supplement, but not necessarily replace, all the hybrid circuitry in any given transceiver architecture. It can be predicted that the long-term implementation strategy for millimeter wave sensors will include a carefully controlled mix between MMIC and hybrid technologies with possibly some waveguide-based critical power components.<<ETX>>","PeriodicalId":320008,"journal":{"name":"NTC '91 - National Telesystems Conference Proceedings","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1991-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117118553","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}
Summary form only given. The authors describe the Chromatics MX2500 monitor, a cost-effective large-screen cathode ray tube (CRT) display that will serve as the platform for applications that contain large amounts of data and require ultrahigh resolution. It is a display medium that will support the increasing demand for improved man/machine visual interface. The MX2500 monitor is designed to be compatible with signal levels and timing requirements of existing 2 K*2 K graphics controllers while adapting to the higher-performance formats of the chromatics graphics computer. A uniquely developed 27" precision in-line gun high-resolution shadow mask color display tube is used to present a 20" by 15" viewable display area. This CRT has a phosphor dot pitch of 0.29 mm, which offers a substantial increase in display performance over other large-screen monitors. A bonded anti-reflection coated panel is used to reduce front surface flare and enhance the ergonomic and safety aspects of the display monitor.<>
{"title":"A 2 K*2 K high resolution display and graphics workstation for air traffic control applications","authors":"P. Grimm, D. West","doi":"10.1109/NTC.1991.147987","DOIUrl":"https://doi.org/10.1109/NTC.1991.147987","url":null,"abstract":"Summary form only given. The authors describe the Chromatics MX2500 monitor, a cost-effective large-screen cathode ray tube (CRT) display that will serve as the platform for applications that contain large amounts of data and require ultrahigh resolution. It is a display medium that will support the increasing demand for improved man/machine visual interface. The MX2500 monitor is designed to be compatible with signal levels and timing requirements of existing 2 K*2 K graphics controllers while adapting to the higher-performance formats of the chromatics graphics computer. A uniquely developed 27\" precision in-line gun high-resolution shadow mask color display tube is used to present a 20\" by 15\" viewable display area. This CRT has a phosphor dot pitch of 0.29 mm, which offers a substantial increase in display performance over other large-screen monitors. A bonded anti-reflection coated panel is used to reduce front surface flare and enhance the ergonomic and safety aspects of the display monitor.<<ETX>>","PeriodicalId":320008,"journal":{"name":"NTC '91 - National Telesystems Conference Proceedings","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1991-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123582265","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}
Over the last ten years, Cross Systems has been developing real-time radar target and environment simulators according to end user requirements. The authors address, in general terms, some of the simulation modeling that has been implemented in these simulators with an emphasis on the varying degrees of model fidelity, especially relative to the end user's requirements. The general trend of increasing requirements in the area of simulation fidelity is also discussed.<>
{"title":"Fidelity aspects of radar target and environment simulation","authors":"B. Leighty, M.D. Perkins","doi":"10.1109/NTC.1991.148026","DOIUrl":"https://doi.org/10.1109/NTC.1991.148026","url":null,"abstract":"Over the last ten years, Cross Systems has been developing real-time radar target and environment simulators according to end user requirements. The authors address, in general terms, some of the simulation modeling that has been implemented in these simulators with an emphasis on the varying degrees of model fidelity, especially relative to the end user's requirements. The general trend of increasing requirements in the area of simulation fidelity is also discussed.<<ETX>>","PeriodicalId":320008,"journal":{"name":"NTC '91 - National Telesystems Conference Proceedings","volume":"34 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1991-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115062621","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 flight support system/servicing aid tool (FSS/SAT) consists of two systems: the FSS, a cradle used with the Shuttle to berth, position, and power satellites, and the SAT, a telerobot to be attached to the FSS. The author identifies the design goals of the FSS/SAT and discusses the major features of the SAT. Particular attention is given to the main components of the protoflight system, a motorized Mini-Master, integrated into the Shuttle's aft flight deck, and an electric slave, integrated into the FSS and installed in the Shuttle's cargo bay.<>
{"title":"Design goals and system description of the flight support system/servicing aid tool","authors":"M. Jaster","doi":"10.1109/NTC.1991.148054","DOIUrl":"https://doi.org/10.1109/NTC.1991.148054","url":null,"abstract":"The flight support system/servicing aid tool (FSS/SAT) consists of two systems: the FSS, a cradle used with the Shuttle to berth, position, and power satellites, and the SAT, a telerobot to be attached to the FSS. The author identifies the design goals of the FSS/SAT and discusses the major features of the SAT. Particular attention is given to the main components of the protoflight system, a motorized Mini-Master, integrated into the Shuttle's aft flight deck, and an electric slave, integrated into the FSS and installed in the Shuttle's cargo bay.<<ETX>>","PeriodicalId":320008,"journal":{"name":"NTC '91 - National Telesystems Conference Proceedings","volume":"46 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1991-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124653609","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}
Using H-Infinity/ mu control analysis and synthesis methods, a first-order controller is derived for aircraft flight through moderate to severe windshear. It satisfies robust performance as well as robust stability requirements for a constructed linearized uncertain system containing two repeated scalar uncertainties due to changes in dynamic pressure and angle of attack. Results of applying the derived mu controllers are given for the severe windshear models in W.J. Grantham (1990) and Y. Zhao and A.E. Bryson, Jr. (1990). The input to the controller is the tracking error between a commanded windshear-free nominal airspeed value and the actual windshear-free airspeed during flight through windshear. Controlling this error leads to robust performance against moderate to severe windshear. The results illustrate the significance of keeping the windshear-free airspeed near its nominal windshear-free value. Decreasing it before controlling the aircraft against windshear leads to unnecessary loss in altitude as flight progresses through windshear.<>
{"title":"Mu control of aircraft in windshear","authors":"H. Stalford","doi":"10.1109/NTC.1991.147981","DOIUrl":"https://doi.org/10.1109/NTC.1991.147981","url":null,"abstract":"Using H-Infinity/ mu control analysis and synthesis methods, a first-order controller is derived for aircraft flight through moderate to severe windshear. It satisfies robust performance as well as robust stability requirements for a constructed linearized uncertain system containing two repeated scalar uncertainties due to changes in dynamic pressure and angle of attack. Results of applying the derived mu controllers are given for the severe windshear models in W.J. Grantham (1990) and Y. Zhao and A.E. Bryson, Jr. (1990). The input to the controller is the tracking error between a commanded windshear-free nominal airspeed value and the actual windshear-free airspeed during flight through windshear. Controlling this error leads to robust performance against moderate to severe windshear. The results illustrate the significance of keeping the windshear-free airspeed near its nominal windshear-free value. Decreasing it before controlling the aircraft against windshear leads to unnecessary loss in altitude as flight progresses through windshear.<<ETX>>","PeriodicalId":320008,"journal":{"name":"NTC '91 - National Telesystems Conference Proceedings","volume":"26 2","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1991-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132532155","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 technique has been developed that allows imaging of ships at high resolution with low pulse repetition frequencies (PRFs) using stepped frequency radar systems. The two parameters of PRF and resolution are typically conflicting, allowing either high resolution at high PRFs or low resolution at low PRFs. This technique is called target striping because it measures the target in sections or stripes. This technique is most useful when imaging targets at great distances. At great distances, the PRF has to be very low so that only one pulse is in the air at a time. At low PRFs the target moves too much during bursts to support high resolution imaging. Using multiple range gates (multiple timed samples of the return pulse) with short pulse widths provides a mechanism to measure sections of the target that can later be pieced together during data processing. The author describes the technique used to measure and process data in target striping mode. Examples of actual data are provided.<>
{"title":"Radar cross section measurements using target striping","authors":"R.M. Pokrass","doi":"10.1109/NTC.1991.148012","DOIUrl":"https://doi.org/10.1109/NTC.1991.148012","url":null,"abstract":"A technique has been developed that allows imaging of ships at high resolution with low pulse repetition frequencies (PRFs) using stepped frequency radar systems. The two parameters of PRF and resolution are typically conflicting, allowing either high resolution at high PRFs or low resolution at low PRFs. This technique is called target striping because it measures the target in sections or stripes. This technique is most useful when imaging targets at great distances. At great distances, the PRF has to be very low so that only one pulse is in the air at a time. At low PRFs the target moves too much during bursts to support high resolution imaging. Using multiple range gates (multiple timed samples of the return pulse) with short pulse widths provides a mechanism to measure sections of the target that can later be pieced together during data processing. The author describes the technique used to measure and process data in target striping mode. Examples of actual data are provided.<<ETX>>","PeriodicalId":320008,"journal":{"name":"NTC '91 - National Telesystems Conference Proceedings","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1991-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130112468","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 discusses some of the significant differences between gated CW (continuous wave) and pulse instrumentation radars for making RCS (radar cross section) and imaging measurements. General similarities and differences are discussed under the heading of fundamental operating characteristics. Specific performances of the two types of systems are discussed, including system sensitivity, gate performance, clutter rejection, and measurement times. Other considerations such as Doppler and interpulse modulation are also discussed.<>
{"title":"Some differences between gated CW and pulse radars in RCS and imaging measurements","authors":"R. H. Bryan","doi":"10.1109/NTC.1991.148008","DOIUrl":"https://doi.org/10.1109/NTC.1991.148008","url":null,"abstract":"The author discusses some of the significant differences between gated CW (continuous wave) and pulse instrumentation radars for making RCS (radar cross section) and imaging measurements. General similarities and differences are discussed under the heading of fundamental operating characteristics. Specific performances of the two types of systems are discussed, including system sensitivity, gate performance, clutter rejection, and measurement times. Other considerations such as Doppler and interpulse modulation are also discussed.<<ETX>>","PeriodicalId":320008,"journal":{"name":"NTC '91 - National Telesystems Conference Proceedings","volume":"44 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1991-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134265467","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}
An approach that uses linear quadratic output feedback techniques is given for designing digital control systems of specified structure for shaping the closed-loop step response. This approach results in digital controllers that take advantage of the wealth of experience in aircraft controls design. The correct initial conditions for determining the output-feedback gains are not uniformly distributed as is traditionally assumed, but are shown to be explicitly given in terms of the step command magnitude. Arbitrary systems are treated, not only those with integrators in the forward paths, by adding a term to the performance index that weights the steady-state error. Necessary conditions are derived that may be used in a gradient-based routine to determine the optimal digital control gains. The approach does not rely on redesign of a continuous control system using techniques like the bilinear transformation, but uses direct discrete-time design.<>
{"title":"Digital aircraft flight controls design using output feedback","authors":"F. Lewis, B. Stevens, G. Al-Sunni","doi":"10.1109/NTC.1991.147980","DOIUrl":"https://doi.org/10.1109/NTC.1991.147980","url":null,"abstract":"An approach that uses linear quadratic output feedback techniques is given for designing digital control systems of specified structure for shaping the closed-loop step response. This approach results in digital controllers that take advantage of the wealth of experience in aircraft controls design. The correct initial conditions for determining the output-feedback gains are not uniformly distributed as is traditionally assumed, but are shown to be explicitly given in terms of the step command magnitude. Arbitrary systems are treated, not only those with integrators in the forward paths, by adding a term to the performance index that weights the steady-state error. Necessary conditions are derived that may be used in a gradient-based routine to determine the optimal digital control gains. The approach does not rely on redesign of a continuous control system using techniques like the bilinear transformation, but uses direct discrete-time design.<<ETX>>","PeriodicalId":320008,"journal":{"name":"NTC '91 - National Telesystems Conference Proceedings","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1991-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131067555","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 development test flight (DTF-1) is the first of two Space Shuttle flights to test operations of the Flight Telerobotic Servicer (FTS) in space and to demonstrate its capabilities in performing tasks for Space Station Freedom. The DTF-1 system is scheduled to be flown in early 1993 as an attached payload on the Shuttle. The authors discuss the design of the DTF-1 system, the tests to be performed, and the data to be gathered.<>
{"title":"Flight Telerobotic Servicer: the development test flight","authors":"J. Andary, P. Spidaliere","doi":"10.1109/NTC.1991.148050","DOIUrl":"https://doi.org/10.1109/NTC.1991.148050","url":null,"abstract":"The development test flight (DTF-1) is the first of two Space Shuttle flights to test operations of the Flight Telerobotic Servicer (FTS) in space and to demonstrate its capabilities in performing tasks for Space Station Freedom. The DTF-1 system is scheduled to be flown in early 1993 as an attached payload on the Shuttle. The authors discuss the design of the DTF-1 system, the tests to be performed, and the data to be gathered.<<ETX>>","PeriodicalId":320008,"journal":{"name":"NTC '91 - National Telesystems Conference Proceedings","volume":"39 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1991-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114789461","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}
It is pointed out that a cockpit revolution is in the making. Many of the promised, but little delivered technologies of the 1970s and 1980s will finally come of age in the 1990s just in time to complement the data explosion coming from sensor and processing advances. Technologies such as helmet systems, large flat panel displays, speech recognition, color graphics, decision aiding, and stereopsis are simultaneously reaching technology maturities that promise big payoffs for the third-generation cockpit and beyond. The author examines tactical cockpit problems and the technologies needed to solve them and recommends three generations of solutions. He discusses what the third-generation cockpit might look like and how it might integrate many of the above-mentioned technologies.<>
{"title":"Tactical cockpits-the coming revolution","authors":"E. Adam","doi":"10.1109/NTC.1991.147985","DOIUrl":"https://doi.org/10.1109/NTC.1991.147985","url":null,"abstract":"It is pointed out that a cockpit revolution is in the making. Many of the promised, but little delivered technologies of the 1970s and 1980s will finally come of age in the 1990s just in time to complement the data explosion coming from sensor and processing advances. Technologies such as helmet systems, large flat panel displays, speech recognition, color graphics, decision aiding, and stereopsis are simultaneously reaching technology maturities that promise big payoffs for the third-generation cockpit and beyond. The author examines tactical cockpit problems and the technologies needed to solve them and recommends three generations of solutions. He discusses what the third-generation cockpit might look like and how it might integrate many of the above-mentioned technologies.<<ETX>>","PeriodicalId":320008,"journal":{"name":"NTC '91 - National Telesystems Conference Proceedings","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1991-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122088662","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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