The basic technology has been developed for high temperature (>1000°F) radiation resistant (>109 rad) space power switchgear under NASA's contract NAS 3-2546 with General Electric. The vacuum insulated switch has been selected to meet these requirements and the megawatt level high frequency (2000 cps) application. Refractory electrodes, tested at 1200°F in a radiant heated ceramic chamber, have cleared 2000 cps alternating currents of 4300 A at 2200 V. DC currents of 21 A have been chopped at 10.8 KV.
{"title":"Electrical Switchgear for Large Nuclear Space Power Systems","authors":"R. N. Edwards, E. A. Koutnik, E. F. Travis","doi":"10.1109/TA.1965.4319852","DOIUrl":"https://doi.org/10.1109/TA.1965.4319852","url":null,"abstract":"The basic technology has been developed for high temperature (>1000°F) radiation resistant (>109 rad) space power switchgear under NASA's contract NAS 3-2546 with General Electric. The vacuum insulated switch has been selected to meet these requirements and the megawatt level high frequency (2000 cps) application. Refractory electrodes, tested at 1200°F in a radiant heated ceramic chamber, have cleared 2000 cps alternating currents of 4300 A at 2200 V. DC currents of 21 A have been chopped at 10.8 KV.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":"34 1","pages":"552-559"},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"84290936","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 equilibrium temperature of a solar cell panel in space is a function of the ratio of solar absorptance to infrared emittance of the surface. This paper describes a method for reducing solar absorptance by constructing the solar cell so that it will be a reflector in the infrared part of the solar spectrum. Spectral transmittance, spectral reflectance, and spectral absorptance of silicon wafers and N/P and P/N solar cells are presented. A N/P cell equipped with a silver coating on the back surface and a 0.400 micron cutoff cover glass on the front was found to have solar absorptance of 0.66 which is 11 percent less than that of a standard N/P cell equipped with a similar cover glass.
{"title":"Infrared Reflecting Solar Cells","authors":"R. Tallent","doi":"10.1109/TA.1965.4319784","DOIUrl":"https://doi.org/10.1109/TA.1965.4319784","url":null,"abstract":"The equilibrium temperature of a solar cell panel in space is a function of the ratio of solar absorptance to infrared emittance of the surface. This paper describes a method for reducing solar absorptance by constructing the solar cell so that it will be a reflector in the infrared part of the solar spectrum. Spectral transmittance, spectral reflectance, and spectral absorptance of silicon wafers and N/P and P/N solar cells are presented. A N/P cell equipped with a silver coating on the back surface and a 0.400 micron cutoff cover glass on the front was found to have solar absorptance of 0.66 which is 11 percent less than that of a standard N/P cell equipped with a similar cover glass.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":"76 1","pages":"71-75"},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"88538148","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 illumination requirements for vision, both for acuity and a sustained effort, are briefly discussed. These requirements are related to the problem of driving a vehicle over the lunar surface during sunlight and during earthshine conditions. Both exterior lighting and interior lighting and their interrelation are discussed, as well as the problems introduced by viewing windows and interior wall finish. Various lighting arrangements are analyzed and recommendations made.
{"title":"Illumination for a Manned Lunar Surface Vehicle","authors":"Trevor A. Robinson","doi":"10.1109/TA.1965.4319817","DOIUrl":"https://doi.org/10.1109/TA.1965.4319817","url":null,"abstract":"The illumination requirements for vision, both for acuity and a sustained effort, are briefly discussed. These requirements are related to the problem of driving a vehicle over the lunar surface during sunlight and during earthshine conditions. Both exterior lighting and interior lighting and their interrelation are discussed, as well as the problems introduced by viewing windows and interior wall finish. Various lighting arrangements are analyzed and recommendations made.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":"25 1","pages":"304-309"},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"84863238","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}
Manned spacecraft designed for long lifetime in space impose a unique requirement for inflight maintenance for all vehicle systems. The key factors in implementing onboard maintenance are accessibility to equipment, rapid fault detection and isolation, and modularized equipment packaging using a supply of interchangeable components. This paper discusses the general configuration of the Manned Orbital Research Laboratory (MORL) studied under contract NAS 1-3612, NASA Langley Research Center and also presents in digest form some conceptual maintenance, design and installation approaches.
{"title":"Morl Configuration, Maintenance, and Installation Concepts","authors":"Harold S. Jencks, K. G. Englar","doi":"10.1109/TA.1965.4319820","DOIUrl":"https://doi.org/10.1109/TA.1965.4319820","url":null,"abstract":"Manned spacecraft designed for long lifetime in space impose a unique requirement for inflight maintenance for all vehicle systems. The key factors in implementing onboard maintenance are accessibility to equipment, rapid fault detection and isolation, and modularized equipment packaging using a supply of interchangeable components. This paper discusses the general configuration of the Manned Orbital Research Laboratory (MORL) studied under contract NAS 1-3612, NASA Langley Research Center and also presents in digest form some conceptual maintenance, design and installation approaches.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":"54 1","pages":"333-340"},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"85203152","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 perfect field safety record continues from these developments: 1) Determination of the threshold-energy (system safety) rating of several pyrotechnic devices via an advanced pulse technique. A 1 ampere, 1 watt power rating is incomplete and has no direct relationship to threshold energy levels. 2) Evolvement of an unconventional system circuit and logic design. 3) Continued field safety assessment using the Hughes stray energy monitor. It provides a simple, objective go, no-go indication of system safety.
{"title":"An Aerospace Dilemma: The Incompatibility of Electromagnetics and Necessary Pyrotechnic Devices","authors":"A. F. Milano, R. Colin","doi":"10.1109/TA.1965.4319845","DOIUrl":"https://doi.org/10.1109/TA.1965.4319845","url":null,"abstract":"A perfect field safety record continues from these developments: 1) Determination of the threshold-energy (system safety) rating of several pyrotechnic devices via an advanced pulse technique. A 1 ampere, 1 watt power rating is incomplete and has no direct relationship to threshold energy levels. 2) Evolvement of an unconventional system circuit and logic design. 3) Continued field safety assessment using the Hughes stray energy monitor. It provides a simple, objective go, no-go indication of system safety.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":"18 1","pages":"514-522"},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90342132","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}
Continuing refinement of the cycloconverter design art has produced an all solid-state power converter which exhibits high efficiency, small size, light weight and high reliability. The controlability of the modern cycloconverter makes it particularly suitable for such applications as precise AC electric drive systems and light weight variable speed, constant frequency power generating systems. Due to the assumptions of infinite load inductance and infinite frequency ratio, the use of classical grid-controlled rectifier theory in the analysis of practical cycloconverters is not sufficiently accurate. According to classical theory, only ripple components of distortion appear in the cycloconverter output. This paper deals with the origin and nature of sub-ripple distortion components in the output.
{"title":"Sub-Ripple Distortion Components in Practical Gycloconverters","authors":"C. Amato","doi":"10.1109/TA.1965.4319789","DOIUrl":"https://doi.org/10.1109/TA.1965.4319789","url":null,"abstract":"Continuing refinement of the cycloconverter design art has produced an all solid-state power converter which exhibits high efficiency, small size, light weight and high reliability. The controlability of the modern cycloconverter makes it particularly suitable for such applications as precise AC electric drive systems and light weight variable speed, constant frequency power generating systems. Due to the assumptions of infinite load inductance and infinite frequency ratio, the use of classical grid-controlled rectifier theory in the analysis of practical cycloconverters is not sufficiently accurate. According to classical theory, only ripple components of distortion appear in the cycloconverter output. This paper deals with the origin and nature of sub-ripple distortion components in the output.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":"PP 1","pages":"98-106"},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"84353884","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}
During the normal progress of design, fabrication, and integration of communications subsystems for spacecraft and for ground installations, every effort is made to assure that the equipment meets certain specifications relating to performance, environment, reliability, and interface capability. These specifications are based on the best available definition of requirements and interface characteristics of complementing subsystems. Frequently, in the field of manned spaceflight, the spacecraft subsystems, the launch vehicle subsystems, and the ground systems must be designed and constructed concurrently. This means that the operating and interface characteristics of one subsystem are not available for use by the engineers in the design of the other subsystems. Close technical liaison among the various engineering groups is essential in the accomplishment of overall systems' integrity. Component and subsystem testing has been developed to a high degree, but the results of these are necessarily limited. They cannot validate the overall systems' performance and compatibility. It is considered mandatory that the interfacing subsystems be mated to form a complete system in a controlled test environment as early as practicable in any program, especially in one involving communications systems as new and as complex as those for Apollo. This must be accomplished at such a phase in the program that corrective engineering details can be fed back to the cognizant design, fabrication, or integration groups involved in time for necessary modifications prior to the beginning of the flight phase.
{"title":"Compatibility and Performance Testing of Communications Systems","authors":"H. C. Kyle","doi":"10.1109/TA.1965.4319794","DOIUrl":"https://doi.org/10.1109/TA.1965.4319794","url":null,"abstract":"During the normal progress of design, fabrication, and integration of communications subsystems for spacecraft and for ground installations, every effort is made to assure that the equipment meets certain specifications relating to performance, environment, reliability, and interface capability. These specifications are based on the best available definition of requirements and interface characteristics of complementing subsystems. Frequently, in the field of manned spaceflight, the spacecraft subsystems, the launch vehicle subsystems, and the ground systems must be designed and constructed concurrently. This means that the operating and interface characteristics of one subsystem are not available for use by the engineers in the design of the other subsystems. Close technical liaison among the various engineering groups is essential in the accomplishment of overall systems' integrity. Component and subsystem testing has been developed to a high degree, but the results of these are necessarily limited. They cannot validate the overall systems' performance and compatibility. It is considered mandatory that the interfacing subsystems be mated to form a complete system in a controlled test environment as early as practicable in any program, especially in one involving communications systems as new and as complex as those for Apollo. This must be accomplished at such a phase in the program that corrective engineering details can be fed back to the cognizant design, fabrication, or integration groups involved in time for necessary modifications prior to the beginning of the flight phase.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":"70 1","pages":"139-143"},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"81540293","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}
To determine the harmful effects of micrometeoroids and measure their occurrence in space, a unique detector-analyzer system has been developed for NASA Manned Spacecraft Center. The system consists of a modified ballistic pendulum for momentum measurement and appropriate arrangement of capacitive foils for velocity determination. A prototype instrument has been successfully tested in the dynamic range extending from 1 to 45 dynesec.
{"title":"A Direct Reading Micrometeoroid Detector-Analyzer","authors":"L. Snyder","doi":"10.1109/TA.1965.4319810","DOIUrl":"https://doi.org/10.1109/TA.1965.4319810","url":null,"abstract":"To determine the harmful effects of micrometeoroids and measure their occurrence in space, a unique detector-analyzer system has been developed for NASA Manned Spacecraft Center. The system consists of a modified ballistic pendulum for momentum measurement and appropriate arrangement of capacitive foils for velocity determination. A prototype instrument has been successfully tested in the dynamic range extending from 1 to 45 dynesec.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":"17 1","pages":"258-263"},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"88021097","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 experimental program to select and develop the journal bearing configuration for use in a 24,000 rpm liquid potassium cooled space electric power generator is described. A preliminary study identified the pivoted-pad bearing as most nearly meeting the requirements of the proposed application. Initial tests, using water as the lubricant, revealed the formation of an unusual wear pattern on the pad corners at high speeds (8000-24,000 rpm). The problem was solved with the development of a method of relieving the pad edges to introduce and maintain the lubricant film. Thereafter, extended tests at speeds up to 26,000 rpm proved the bearing could be operated under the proposed conditions. The bearing configuration was then operated successfully to 12,000 rpm in potassium.
{"title":"Development of Pivoted-Pad Journal Bearings for Potassium Lubricated Space Electric Power Generators","authors":"F. Dobler","doi":"10.1109/TA.1965.4319835","DOIUrl":"https://doi.org/10.1109/TA.1965.4319835","url":null,"abstract":"An experimental program to select and develop the journal bearing configuration for use in a 24,000 rpm liquid potassium cooled space electric power generator is described. A preliminary study identified the pivoted-pad bearing as most nearly meeting the requirements of the proposed application. Initial tests, using water as the lubricant, revealed the formation of an unusual wear pattern on the pad corners at high speeds (8000-24,000 rpm). The problem was solved with the development of a method of relieving the pad edges to introduce and maintain the lubricant film. Thereafter, extended tests at speeds up to 26,000 rpm proved the bearing could be operated under the proposed conditions. The bearing configuration was then operated successfully to 12,000 rpm in potassium.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":"122 1","pages":"451-458"},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"78448564","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}
When an extra-vehicular suited astronaut steps onto the hostile environment of the lunar surface, he is essentially operating in his own personal spacecraft - the extra-vehicular suit system. The primary function of this system is of course, life support, but at least secondary in importance is the communications link with the lunar spacecraft and earth. Another function supplied by the system is suit telemetry to safeguard the astronaut's well being, as observed by monitors on earth. This includes the transmission of physiological data as well as suit environmental and performance data. The latter includes such things as suit pressure and the amount of oxygen remaining in the suit system. This paper describes the two functions of voice communications and suit telemetry. It includes functional requirements of the communication system which encompass range, relay links, and redundant modes. Design considerations are also briefly covered including past development work leading to the present prototype system. The paper also describes some of the hardware implementation problems including suit antenna considerations.
{"title":"Lunar Surface Suit Telemetry and Voice Communications","authors":"D. Hickman","doi":"10.1109/TA.1965.4319840","DOIUrl":"https://doi.org/10.1109/TA.1965.4319840","url":null,"abstract":"When an extra-vehicular suited astronaut steps onto the hostile environment of the lunar surface, he is essentially operating in his own personal spacecraft - the extra-vehicular suit system. The primary function of this system is of course, life support, but at least secondary in importance is the communications link with the lunar spacecraft and earth. Another function supplied by the system is suit telemetry to safeguard the astronaut's well being, as observed by monitors on earth. This includes the transmission of physiological data as well as suit environmental and performance data. The latter includes such things as suit pressure and the amount of oxygen remaining in the suit system. This paper describes the two functions of voice communications and suit telemetry. It includes functional requirements of the communication system which encompass range, relay links, and redundant modes. Design considerations are also briefly covered including past development work leading to the present prototype system. The paper also describes some of the hardware implementation problems including suit antenna considerations.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":"18 1","pages":"484-488"},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"85644922","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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