Pub Date : 1958-03-01DOI: 10.1109/TANE3.1958.4201573
Nathan A. Carhart
High-speed aircraft require the successful operation of large quantities of electronic equipment. The problem of providing a suitable environment for such equipment is of interest to both airplane and electronic designers. A proposal is offered by which cooling provisions may be standardized for airplanes of widely varying performance. Basic design parameters for the development of such a system are outlined, as are the economic factors involved.
{"title":"Problems Arising in High-Speed Aircraft Due to Cooling Requirements of Electronic Equipment","authors":"Nathan A. Carhart","doi":"10.1109/TANE3.1958.4201573","DOIUrl":"https://doi.org/10.1109/TANE3.1958.4201573","url":null,"abstract":"High-speed aircraft require the successful operation of large quantities of electronic equipment. The problem of providing a suitable environment for such equipment is of interest to both airplane and electronic designers. A proposal is offered by which cooling provisions may be standardized for airplanes of widely varying performance. Basic design parameters for the development of such a system are outlined, as are the economic factors involved.","PeriodicalId":332621,"journal":{"name":"IRE Transactions on Aeronautical and Navigational Electronics","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122760522","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 : 1958-03-01DOI: 10.1109/TANE3.1958.4201577
W. Robinson
Based on weight penality comparisons of ultimate heat sinks for electronic equipment cooling, the use of expendable evaporants and fuel is indicated for high supersonic flight. Centralized ram air should be the alternate coolant during subsonic flight. System integration is best accomplished with a recirculating liquid transfer system, which is relatively easy to control and which is characterized by small pumping power, line size, and heat gain from high temperature environments. Because of these features close temperature control of dispersed components and cooling of remote highpower units are best achieved by liquid coupling, regardless of the type of ultimate heat sink. Part temperature rises in high voltage equipment can be minimized by use of dielectric liquids. Although this permits some reduction in ultimnate coolant weight penalty, the reduction is usually not great enough to offset the equipment weight increases that are due to liquid filling. Vapor-filled or air-filled units with minimal liquid contents and liquid transport to part surfaces by capillary action or mechanical means are superior. Electronic assemblies that are to be series cooled in sealed liquid transfer systems should be designed for conduction, forced air convection, or radiation heat transfer from the parts, and high power units should have integral liquid cooled heat exchangers, placed in separate transfer system branches. Internal heat transfer in such units may be attained by conduction through flexible metal or rubber jackets and electrical insulators, by air convection in standard modules, and by liquid film cooling.
{"title":"Why and How Should High-Speed Aircraft Electronics Be Liquid Cooled?","authors":"W. Robinson","doi":"10.1109/TANE3.1958.4201577","DOIUrl":"https://doi.org/10.1109/TANE3.1958.4201577","url":null,"abstract":"Based on weight penality comparisons of ultimate heat sinks for electronic equipment cooling, the use of expendable evaporants and fuel is indicated for high supersonic flight. Centralized ram air should be the alternate coolant during subsonic flight. System integration is best accomplished with a recirculating liquid transfer system, which is relatively easy to control and which is characterized by small pumping power, line size, and heat gain from high temperature environments. Because of these features close temperature control of dispersed components and cooling of remote highpower units are best achieved by liquid coupling, regardless of the type of ultimate heat sink. Part temperature rises in high voltage equipment can be minimized by use of dielectric liquids. Although this permits some reduction in ultimnate coolant weight penalty, the reduction is usually not great enough to offset the equipment weight increases that are due to liquid filling. Vapor-filled or air-filled units with minimal liquid contents and liquid transport to part surfaces by capillary action or mechanical means are superior. Electronic assemblies that are to be series cooled in sealed liquid transfer systems should be designed for conduction, forced air convection, or radiation heat transfer from the parts, and high power units should have integral liquid cooled heat exchangers, placed in separate transfer system branches. Internal heat transfer in such units may be attained by conduction through flexible metal or rubber jackets and electrical insulators, by air convection in standard modules, and by liquid film cooling.","PeriodicalId":332621,"journal":{"name":"IRE Transactions on Aeronautical and Navigational Electronics","volume":"2083 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129842758","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 : 1958-03-01DOI: 10.1109/TANE3.1958.4201581
J. Wong
{"title":"Radiation Pattern Efficiencies of Some Suppressed HF Aircraft Antennas","authors":"J. Wong","doi":"10.1109/TANE3.1958.4201581","DOIUrl":"https://doi.org/10.1109/TANE3.1958.4201581","url":null,"abstract":"","PeriodicalId":332621,"journal":{"name":"IRE Transactions on Aeronautical and Navigational Electronics","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122745130","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 : 1958-03-01DOI: 10.1109/TANE3.1958.4201576
M. Mark
A solution to the problem of cooling certain types of high heat-dissipating airborne electronic equipment is the modification of the equipment chassis to incorporate a simple plate-fin heat exchanger, sometimes called a "cold plate." In this paper equations for cold plates are developed and the effect of variations in fin configuration on performance are discussed. Theoretical and experimental results based on tubes mounted on a cold plate are found to compare very favorably. The application of the cold-plate technique is illustrated for power transistors. This method of cooling is shown to be useful and efficient.
{"title":"Cold Plate Design for Airborne Electronic Equipment","authors":"M. Mark","doi":"10.1109/TANE3.1958.4201576","DOIUrl":"https://doi.org/10.1109/TANE3.1958.4201576","url":null,"abstract":"A solution to the problem of cooling certain types of high heat-dissipating airborne electronic equipment is the modification of the equipment chassis to incorporate a simple plate-fin heat exchanger, sometimes called a \"cold plate.\" In this paper equations for cold plates are developed and the effect of variations in fin configuration on performance are discussed. Theoretical and experimental results based on tubes mounted on a cold plate are found to compare very favorably. The application of the cold-plate technique is illustrated for power transistors. This method of cooling is shown to be useful and efficient.","PeriodicalId":332621,"journal":{"name":"IRE Transactions on Aeronautical and Navigational Electronics","volume":"50 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133898798","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 : 1958-03-01DOI: 10.1109/TANE3.1958.4201578
M. Mark, M. Stephenson, C. Goltsos
In airborne electronic packages, for either thermal or electrical reasons cooling air often is not ducted directly over the components but is passed through a heat exchanger. Consequently, the thermal path between the heat exchanger and the components must be of low impedance to result in efficient heat transfer. The high heat transfer coefficients obtainable as a liquid boils and condenses permit an effective reduction of the temperature drop between the electronic components and the heat exchanger. In this paper the development and design of an evaporative system utilizing gravity return flow is discussed, and the test results of such a system are compared with those obtained utilizing a conventional metallic conductive paths technique. Where heat dissipation or cooling air inlet temperature is high, the evaporative-gravity (ev-grav) system is shown to be the most effective.
{"title":"An Evaporative-Gravity Technique for Airborne Equipment Cooling","authors":"M. Mark, M. Stephenson, C. Goltsos","doi":"10.1109/TANE3.1958.4201578","DOIUrl":"https://doi.org/10.1109/TANE3.1958.4201578","url":null,"abstract":"In airborne electronic packages, for either thermal or electrical reasons cooling air often is not ducted directly over the components but is passed through a heat exchanger. Consequently, the thermal path between the heat exchanger and the components must be of low impedance to result in efficient heat transfer. The high heat transfer coefficients obtainable as a liquid boils and condenses permit an effective reduction of the temperature drop between the electronic components and the heat exchanger. In this paper the development and design of an evaporative system utilizing gravity return flow is discussed, and the test results of such a system are compared with those obtained utilizing a conventional metallic conductive paths technique. Where heat dissipation or cooling air inlet temperature is high, the evaporative-gravity (ev-grav) system is shown to be the most effective.","PeriodicalId":332621,"journal":{"name":"IRE Transactions on Aeronautical and Navigational Electronics","volume":"29 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127069057","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 : 1958-03-01DOI: 10.1109/TANE3.1958.4201572
J. Kaye, H. Y. Choi
A brief introduction and review is presented of the problems of protecting and cooling airborne electronic equipment in present and future high-speed devices. The thermal characteristics associated with high-speed flight of manned and unmanned vehicles are related to the thermal problems of irreversible electrical and magnetic components which possess upper bounds of temperature for reliable operation. Various types of cooling devices, fluid flow processes, and techniques are presented and discussed, and the trends of future development are reviewed briefly.
{"title":"General Aspects of Cooling Airborne Electronic Equipment","authors":"J. Kaye, H. Y. Choi","doi":"10.1109/TANE3.1958.4201572","DOIUrl":"https://doi.org/10.1109/TANE3.1958.4201572","url":null,"abstract":"A brief introduction and review is presented of the problems of protecting and cooling airborne electronic equipment in present and future high-speed devices. The thermal characteristics associated with high-speed flight of manned and unmanned vehicles are related to the thermal problems of irreversible electrical and magnetic components which possess upper bounds of temperature for reliable operation. Various types of cooling devices, fluid flow processes, and techniques are presented and discussed, and the trends of future development are reviewed briefly.","PeriodicalId":332621,"journal":{"name":"IRE Transactions on Aeronautical and Navigational Electronics","volume":"96 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115930011","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 : 1958-03-01DOI: 10.1109/TANE3.1958.4201575
T. Jordan
A brief explanation of the principles of forced-air direct-contact cooling is given, and it is shown that the heat density of the electronic part being cooled determines essentially the range of applicability of this method. The discussion then progresses to cooling problems arising when this concept is applied to airborne electronic equipment. Several techniques are presented for obtaining high heat transfer coefficients and good air distribution with small pressure drops. The use of laminar flow in all of these techniques is shown to be effective, and examples are given of practical applications, such as the use of tube shields and special solenoid designs. Applications of thermal insulation to forced-air direct-contact cooling in aircraft are also treated, and the shortcomings, as well as the advantages of forced-air direct-contact cooling, are pointed out.
{"title":"Forced-Air Direct-Contact Cooling of Airborne Electronic Equipment","authors":"T. Jordan","doi":"10.1109/TANE3.1958.4201575","DOIUrl":"https://doi.org/10.1109/TANE3.1958.4201575","url":null,"abstract":"A brief explanation of the principles of forced-air direct-contact cooling is given, and it is shown that the heat density of the electronic part being cooled determines essentially the range of applicability of this method. The discussion then progresses to cooling problems arising when this concept is applied to airborne electronic equipment. Several techniques are presented for obtaining high heat transfer coefficients and good air distribution with small pressure drops. The use of laminar flow in all of these techniques is shown to be effective, and examples are given of practical applications, such as the use of tube shields and special solenoid designs. Applications of thermal insulation to forced-air direct-contact cooling in aircraft are also treated, and the shortcomings, as well as the advantages of forced-air direct-contact cooling, are pointed out.","PeriodicalId":332621,"journal":{"name":"IRE Transactions on Aeronautical and Navigational Electronics","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128749539","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 : 1958-03-01DOI: 10.1109/TANE3.1958.4201580
T. Ellison
Limited heat dissipation from the necessarily compact electronic equipment installations of airline aircraft has been a problem to commercial air carriers for many years. To deal with this problem, United Air Lines, in August, 1955, began equipping fleet aircraft with a forced air electronic equipment cooling system, with the following objectives: 1) improvement of electronic equipment reliability, 2) reduction of crew discomfort caused by electronic-equipment generated heat in the flight deck area, and 3) evacuation of any smoke from the flight deck area which might arise from electronic equipment failure. Observation of electronic equipment maintenance records during the subsequent transition period from convection to forced air equipment cooling shows characteristic failure rate trends which indicate the dependence of equipment reliability on operating temperature. These patterns occur independently in fleet records for the Convair 340, and DC-6 and DC-6B fleets, in time phase with the progress of conversion to forced air cooling in the fleet. These records, in conjunction with other comparative testing of forced cooled and convective cooled equipment installations indicate that forced air cooling provides an effective answer to airline equipment heat problems.
{"title":"Radio Rack Cooling in Present Commercial Aircraft","authors":"T. Ellison","doi":"10.1109/TANE3.1958.4201580","DOIUrl":"https://doi.org/10.1109/TANE3.1958.4201580","url":null,"abstract":"Limited heat dissipation from the necessarily compact electronic equipment installations of airline aircraft has been a problem to commercial air carriers for many years. To deal with this problem, United Air Lines, in August, 1955, began equipping fleet aircraft with a forced air electronic equipment cooling system, with the following objectives: 1) improvement of electronic equipment reliability, 2) reduction of crew discomfort caused by electronic-equipment generated heat in the flight deck area, and 3) evacuation of any smoke from the flight deck area which might arise from electronic equipment failure. Observation of electronic equipment maintenance records during the subsequent transition period from convection to forced air equipment cooling shows characteristic failure rate trends which indicate the dependence of equipment reliability on operating temperature. These patterns occur independently in fleet records for the Convair 340, and DC-6 and DC-6B fleets, in time phase with the progress of conversion to forced air cooling in the fleet. These records, in conjunction with other comparative testing of forced cooled and convective cooled equipment installations indicate that forced air cooling provides an effective answer to airline equipment heat problems.","PeriodicalId":332621,"journal":{"name":"IRE Transactions on Aeronautical and Navigational Electronics","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130997116","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 : 1957-12-01DOI: 10.1109/TANE3.1957.4201551
F. B. Berger
The nature of Doppler velocity measurement is reviewed briefly. This is followed by a discussion of the basic requirements for obtaining a usable signal for practical systems, which include achieving requisite coherence, fulfilling certain signal-to-noise criteria, and maintaining known functional relationships between measured Doppler frequencies and aircraft velocity. Then, those factors peculiar to over-water operation of Doppler systems are discussed. Techniques suitable for the design of systems that fulfill the various existing theoretical and practical requirements are considered. The various interrelated design considerations are grouped into five main categories: 1) choice of the number of beams to employ, 2) antenna stabilization, 3) type of antenna, 4) transmission-reception techniques, and 5) Doppler frequency measurement techniques. A summary of design considerations and the choices made in the cases of systems now declassified are contained in Tables I and III-VI.
{"title":"The Design of Airborne Doppler Velocity Measuring Systems","authors":"F. B. Berger","doi":"10.1109/TANE3.1957.4201551","DOIUrl":"https://doi.org/10.1109/TANE3.1957.4201551","url":null,"abstract":"The nature of Doppler velocity measurement is reviewed briefly. This is followed by a discussion of the basic requirements for obtaining a usable signal for practical systems, which include achieving requisite coherence, fulfilling certain signal-to-noise criteria, and maintaining known functional relationships between measured Doppler frequencies and aircraft velocity. Then, those factors peculiar to over-water operation of Doppler systems are discussed. Techniques suitable for the design of systems that fulfill the various existing theoretical and practical requirements are considered. The various interrelated design considerations are grouped into five main categories: 1) choice of the number of beams to employ, 2) antenna stabilization, 3) type of antenna, 4) transmission-reception techniques, and 5) Doppler frequency measurement techniques. A summary of design considerations and the choices made in the cases of systems now declassified are contained in Tables I and III-VI.","PeriodicalId":332621,"journal":{"name":"IRE Transactions on Aeronautical and Navigational Electronics","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1957-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114220243","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 : 1957-12-01DOI: 10.1109/TANE3.1957.4201558
L. Wadel
{"title":"Characteristic Navigational Period on Other Planets","authors":"L. Wadel","doi":"10.1109/TANE3.1957.4201558","DOIUrl":"https://doi.org/10.1109/TANE3.1957.4201558","url":null,"abstract":"","PeriodicalId":332621,"journal":{"name":"IRE Transactions on Aeronautical and Navigational Electronics","volume":"34 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1957-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133396481","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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