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":null,"pages":null},"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}
The effects of ferrite loading on the characteristics of the rectangular cavity slot antenna, the equiangular spiral antenna, and the log conical spiral antenna are studied. The object is size and weight reduction and this is accomplished at the expense of bandwidth and/or efficiency. The characteristics of the rectangular cavity slot antenna are analyzed and compared with experimental data. The operating frequency may be shifted by magnetic bias. Loading the spiral and log conical antennas lowers the low frequency limit by a factor of two or three. Data are presented on the temperature sensitivity of ferrite materials for aerospace antennas.
{"title":"Ferrite Loaded Antennas for Aerospace Applications","authors":"A. Adams, J. Lyon","doi":"10.1109/TA.1965.4319841","DOIUrl":"https://doi.org/10.1109/TA.1965.4319841","url":null,"abstract":"The effects of ferrite loading on the characteristics of the rectangular cavity slot antenna, the equiangular spiral antenna, and the log conical spiral antenna are studied. The object is size and weight reduction and this is accomplished at the expense of bandwidth and/or efficiency. The characteristics of the rectangular cavity slot antenna are analyzed and compared with experimental data. The operating frequency may be shifted by magnetic bias. Loading the spiral and log conical antennas lowers the low frequency limit by a factor of two or three. Data are presented on the temperature sensitivity of ferrite materials for aerospace antennas.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"78138347","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}
This paper describes the communications and data-handling subsystem (CDHS) for the Advanced Orbiting Solar Observatory (AOSO). The CDHS is presently being developed by Texas Instruments Incorporated for Republic Aviation. Goddard Space Flight Center is the responsible NASA agency. The paper includes a detailed functional description of the CDHS, a presentation of the packaging design, and a brief description of the engineering model constructed. Several pictures of the engineering model are included to aid in the description of the packaging.
{"title":"The Communication and Data-Handling Subsystem for the Advanced Orbiting Solar Observatory","authors":"J. Thompson, A. E. Mason","doi":"10.1109/TA.1965.4319822","DOIUrl":"https://doi.org/10.1109/TA.1965.4319822","url":null,"abstract":"This paper describes the communications and data-handling subsystem (CDHS) for the Advanced Orbiting Solar Observatory (AOSO). The CDHS is presently being developed by Texas Instruments Incorporated for Republic Aviation. Goddard Space Flight Center is the responsible NASA agency. The paper includes a detailed functional description of the CDHS, a presentation of the packaging design, and a brief description of the engineering model constructed. Several pictures of the engineering model are included to aid in the description of the packaging.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82210238","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 general design procedure is presented which allows a rapid graphical solution of the performance of the generator for a matched load condition. Furthermore, its performance is evaluated for solar concentrations of 1 to 2 times the solar constant, segmenting of the thermoelements with compatible Bi2Te3 cooling material, increase of the area of the radiator plate over that of the collector plate, and for a satellite probe to pass by Venus.
{"title":"Flat Plate Solar Thermoelectric Generator Design Analysis","authors":"R. Gibson, N. Fuschillo","doi":"10.1109/TA.1965.4319866","DOIUrl":"https://doi.org/10.1109/TA.1965.4319866","url":null,"abstract":"A general design procedure is presented which allows a rapid graphical solution of the performance of the generator for a matched load condition. Furthermore, its performance is evaluated for solar concentrations of 1 to 2 times the solar constant, segmenting of the thermoelements with compatible Bi2Te3 cooling material, increase of the area of the radiator plate over that of the collector plate, and for a satellite probe to pass by Venus.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"87232898","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}
Analysis and design of a cryostat which functions in space by radiative cooling alone are presented. Temperatures in the inner volume of the cryostat are predicted to reach cryogenic temperatures if the cryostat is placed in an earth orbit in the plane of the ecliptic. The advantages of the cryostat include (1) indefinitely long lifetime, (2) no cryogenic or heat pump plant as payload, and (3) the use of certain radio wave, millimeter wave, and infrared detectors. A parametric analysis of various cryostat configurations has been completed to allow solution of design parameters for various applications, earth orbital radii, and internal heat loads.
{"title":"Radiation Cooled Cryostat for Infrared Detectors","authors":"N. Fuschillo, C. Schultz, R. Gibson","doi":"10.1109/TA.1965.4319786","DOIUrl":"https://doi.org/10.1109/TA.1965.4319786","url":null,"abstract":"Analysis and design of a cryostat which functions in space by radiative cooling alone are presented. Temperatures in the inner volume of the cryostat are predicted to reach cryogenic temperatures if the cryostat is placed in an earth orbit in the plane of the ecliptic. The advantages of the cryostat include (1) indefinitely long lifetime, (2) no cryogenic or heat pump plant as payload, and (3) the use of certain radio wave, millimeter wave, and infrared detectors. A parametric analysis of various cryostat configurations has been completed to allow solution of design parameters for various applications, earth orbital radii, and internal heat loads.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77270335","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 configuration and design features of a potassium cooled 50 kw model (LMCD-II) generator are described, including the stator bore seal, bearing and shaft seal configuration, and cooling path arrangement. The unique fabrication techniques discussed include precision machining of the rotor, joining of components by electron beam welding, and assembly of the ceramic-glass insulation system. Results of tests both in conventional fluids and liquid potassium are compared with calculated performance. The problems encountered and the areas requiring further development are presented. Finally, the requirements anticipated for the integration of a generator with the power conversion portion of the SNAP-50/SPUR system are discussed.
{"title":"Development Status of the LMCD-II Potassium Cooled Inductor Generator","authors":"F. Dobler, P. Scheffler","doi":"10.1109/TA.1965.4319836","DOIUrl":"https://doi.org/10.1109/TA.1965.4319836","url":null,"abstract":"The configuration and design features of a potassium cooled 50 kw model (LMCD-II) generator are described, including the stator bore seal, bearing and shaft seal configuration, and cooling path arrangement. The unique fabrication techniques discussed include precision machining of the rotor, joining of components by electron beam welding, and assembly of the ceramic-glass insulation system. Results of tests both in conventional fluids and liquid potassium are compared with calculated performance. The problems encountered and the areas requiring further development are presented. Finally, the requirements anticipated for the integration of a generator with the power conversion portion of the SNAP-50/SPUR system are discussed.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79635734","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 design approach to a high-temperature pressure transducer system for use in closed cycle liquid metal facilities utilizes the displacement of a diaphragm member by the liquid metal pressure. The displacement is then monitored by a suitable transduction device whose output indicates the pressure. A main problem area involves the pertinent characteristics of the transducer. This paper presents the analyses of two transduction system approaches based on (1) thermionic and (2) variable impedance phenomena.
{"title":"Analysis of Two High-Temperature Liquid Metal Pressure Measuring Systems","authors":"A. J. Cassano","doi":"10.1109/TA.1965.4319837","DOIUrl":"https://doi.org/10.1109/TA.1965.4319837","url":null,"abstract":"A design approach to a high-temperature pressure transducer system for use in closed cycle liquid metal facilities utilizes the displacement of a diaphragm member by the liquid metal pressure. The displacement is then monitored by a suitable transduction device whose output indicates the pressure. A main problem area involves the pertinent characteristics of the transducer. This paper presents the analyses of two transduction system approaches based on (1) thermionic and (2) variable impedance phenomena.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"78401038","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 heat transfer analysis has been made of a typical ordnance header to derive the relationship between the various parameters which determine thermo-dissipative characteristics of the device. Because of the complex geometries and the large number of parameters involved, the solution to this general problem has long been regarded as too complex for direct solution. It has been shown that an equation may be greatly simplified and the number of parameters reduced to eight important ones so that the problem can be programmed for solution by a computer. The program yields temperature distributions as a function of both space and time and for time periods appropriate to the all-fire and the no-fire test conditions, i.e., milliseconds or five minutes. The solutions of the equation have been checked by over 400 firings with various header geometries, materials, and firing currents and found to be quite accurate. The solutions allow one to design ordnance hardware to have a wide range of all-fire characteristics for any designated no-fire characteristic. They also make it possible to predict the changes in ordnance design necessary to increase the no-fire characteristic from present one watt levels to 2, 5, or 10 watt no-fire levels.
{"title":"Theoretical Approach to 1 Amp/1 Watt, No-Fire Ordnance Designs","authors":"D. E. Davenport","doi":"10.1109/TA.1965.4319863","DOIUrl":"https://doi.org/10.1109/TA.1965.4319863","url":null,"abstract":"A heat transfer analysis has been made of a typical ordnance header to derive the relationship between the various parameters which determine thermo-dissipative characteristics of the device. Because of the complex geometries and the large number of parameters involved, the solution to this general problem has long been regarded as too complex for direct solution. It has been shown that an equation may be greatly simplified and the number of parameters reduced to eight important ones so that the problem can be programmed for solution by a computer. The program yields temperature distributions as a function of both space and time and for time periods appropriate to the all-fire and the no-fire test conditions, i.e., milliseconds or five minutes. The solutions of the equation have been checked by over 400 firings with various header geometries, materials, and firing currents and found to be quite accurate. The solutions allow one to design ordnance hardware to have a wide range of all-fire characteristics for any designated no-fire characteristic. They also make it possible to predict the changes in ordnance design necessary to increase the no-fire characteristic from present one watt levels to 2, 5, or 10 watt no-fire levels.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"78618112","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 partial differential equation for the vector-potential of heteropolar machines is established taking into account the non-linearities of the materials and the current distributions. The non-linear equation, similar to Poisson's equation, is transformed into a partial difference equation. The magnetic induction is found at discrete points in the cross section of the machine. A new relaxation procedure, accelerated greatly by the use of a new physical method of adjusting the vector potential between two successive iterations, is used. The method is shown for an aerospace synchronous generator. Calculated and test results of the no-load characteristic agree quite well. Pole tip saturation is fully considered.
{"title":"Non-Linear Theory of Heteropolar Electrical Machines","authors":"S. Ahamed, E. Erdelyi, R. E. Hopkins","doi":"10.1109/TA.1965.4319778","DOIUrl":"https://doi.org/10.1109/TA.1965.4319778","url":null,"abstract":"The partial differential equation for the vector-potential of heteropolar machines is established taking into account the non-linearities of the materials and the current distributions. The non-linear equation, similar to Poisson's equation, is transformed into a partial difference equation. The magnetic induction is found at discrete points in the cross section of the machine. A new relaxation procedure, accelerated greatly by the use of a new physical method of adjusting the vector potential between two successive iterations, is used. The method is shown for an aerospace synchronous generator. Calculated and test results of the no-load characteristic agree quite well. Pole tip saturation is fully considered.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77946712","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}
This paper propounds the philosophy behind the design of a sensing and data collection system for the handling of low-potential physiological signals used in the determination of astronaut well-being. The experience gained from Project Mercury manned flights and numerous studies performed by the NASA, industry, and university groups has contributed to the establishment of the design criteria. The actual hardware for support of the Gemini manned missions has been designed, built, and flight qualified.
{"title":"Monitoring and Recording of Physiological Data of the Manned Space Flight Program","authors":"T. Holt, R. Lamonte","doi":"10.1109/TA.1965.4319821","DOIUrl":"https://doi.org/10.1109/TA.1965.4319821","url":null,"abstract":"This paper propounds the philosophy behind the design of a sensing and data collection system for the handling of low-potential physiological signals used in the determination of astronaut well-being. The experience gained from Project Mercury manned flights and numerous studies performed by the NASA, industry, and university groups has contributed to the establishment of the design criteria. The actual hardware for support of the Gemini manned missions has been designed, built, and flight qualified.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90329517","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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