The need for microelectronics in aerospace systems arises from demands for increased reliability and payload. Much existing equipment can be converted to microelectronics without extensive redesign, without sacrificing reliability, and without increasing circuit fabrication costs. This paper discusses the problems and techniques involved in converting a specific VHF subsystem, and the practicality of achieving this at competitive costs under an accelerated schedule.
{"title":"The Microelectronics Fabrication of VHF Systems","authors":"M. Shannon, D. L. Cannon","doi":"10.1109/TA.1965.4319826","DOIUrl":"https://doi.org/10.1109/TA.1965.4319826","url":null,"abstract":"The need for microelectronics in aerospace systems arises from demands for increased reliability and payload. Much existing equipment can be converted to microelectronics without extensive redesign, without sacrificing reliability, and without increasing circuit fabrication costs. This paper discusses the problems and techniques involved in converting a specific VHF subsystem, and the practicality of achieving this at competitive costs under an accelerated schedule.","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":"90389540","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}
W. E. Hammond, T. Wilson, I. M. H. Babaa, Y. Yu, E. Moore
Efficiencies of over 90 percent have been obtained in this high-frequency non-dissipatively regulated d-c to d-c converter over a wide variation of temperature, load, and input supply voltages. Synchronization and phase-locking of two identical complementary converters are used to minimize many of the ripple and filtering problems which have been disadvantages of previous converters using similar techniques for voltage conversion and regulation. Operation of the converter is described in detail with emphasis being placed on the energy-storage and energy-transfer functions of the reactive elements and on the synchronization of the two converters.
{"title":"A D-C to D-C Converter Using Two Synchronized Complementary Converters","authors":"W. E. Hammond, T. Wilson, I. M. H. Babaa, Y. Yu, E. Moore","doi":"10.1109/TA.1965.4319803","DOIUrl":"https://doi.org/10.1109/TA.1965.4319803","url":null,"abstract":"Efficiencies of over 90 percent have been obtained in this high-frequency non-dissipatively regulated d-c to d-c converter over a wide variation of temperature, load, and input supply voltages. Synchronization and phase-locking of two identical complementary converters are used to minimize many of the ripple and filtering problems which have been disadvantages of previous converters using similar techniques for voltage conversion and regulation. Operation of the converter is described in detail with emphasis being placed on the energy-storage and energy-transfer functions of the reactive elements and on the synchronization of the two converters.","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":"89148496","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 new technique is presented for measuring thermal radiation. The technique was conceived to aid in the evaluation of the base heating experienced by rocket vehicles due to radiation from the exhaust plumes. The instrumentation, chosen for its ruggedness combined with high sensitivity, is derived from thin-film resistance thermometry as originally developed for short-duration test devices such as hypersonic impulse wind tunnels. A heat meter based on thin-film resistance thermometry functions on the basis of the sudden application of a heat pulse. In the present application, for which the incident heat flux is steady, the heat pulsing is accomplished by actuating a shutter interposed between the sensing element and the incident radiation. Sample gages have been built and subjected to preliminary testing. Attention has been given to the problem of compensating the data for departures from ideal operating conditions such as the finite opening time of the shutter, and also the possible two-dimensional pattern of heat flow into the substrate material of the sensor. In addition, a special method for recalibrating the thin-film sensor is presented and illustrated with experimental results.
{"title":"A New Technique for Measuring Thermal Radiation","authors":"J. W. Reece, G. Theoclitus","doi":"10.1109/TA.1965.4319806","DOIUrl":"https://doi.org/10.1109/TA.1965.4319806","url":null,"abstract":"A new technique is presented for measuring thermal radiation. The technique was conceived to aid in the evaluation of the base heating experienced by rocket vehicles due to radiation from the exhaust plumes. The instrumentation, chosen for its ruggedness combined with high sensitivity, is derived from thin-film resistance thermometry as originally developed for short-duration test devices such as hypersonic impulse wind tunnels. A heat meter based on thin-film resistance thermometry functions on the basis of the sudden application of a heat pulse. In the present application, for which the incident heat flux is steady, the heat pulsing is accomplished by actuating a shutter interposed between the sensing element and the incident radiation. Sample gages have been built and subjected to preliminary testing. Attention has been given to the problem of compensating the data for departures from ideal operating conditions such as the finite opening time of the shutter, and also the possible two-dimensional pattern of heat flow into the substrate material of the sensor. In addition, a special method for recalibrating the thin-film sensor is presented and illustrated with experimental results.","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":"88402275","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 means of rapid, maintenance free activation has been developed for aqueous primary batteries which must operate at extremely low temperatures by employing chemical heat and a heat exchanger device. Units of various sizes have been made to activate in less than one second and provide normal operation throughout a -650 to 160°F temperature range. A description of the heating device is given together with typical performance results for batteries which have various electrical characteristics.
{"title":"Chemically Heated Batteries","authors":"Joseph J. Holechek","doi":"10.1109/TA.1965.4319849","DOIUrl":"https://doi.org/10.1109/TA.1965.4319849","url":null,"abstract":"A means of rapid, maintenance free activation has been developed for aqueous primary batteries which must operate at extremely low temperatures by employing chemical heat and a heat exchanger device. Units of various sizes have been made to activate in less than one second and provide normal operation throughout a -650 to 160°F temperature range. A description of the heating device is given together with typical performance results for batteries which have various electrical characteristics.","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":"88767524","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 practical thermomechanical configurational design was developed for flat plate thermoelectric generator unit couples (approximately 1 inch by 1 inch) and panels (approximately 3 inches by 3 inches). An account of the techniques used in fabricating these solar energy conversion devices is given. Resulting unit couples provide 3 watts/ft2 with a weight factor of 30 watts/lb for the couple and 15 watts/lb for the panel form. Steady-state and thermal cycle life tests indicate an output degradation of less than 10% in 2000 cycles. These results offer promise of lower cost space power systems with special adaptability to missions not suited to photovoltaic cells. The fabrication of 3-by 3-inch panels of nine unit cells giving 15 watts/lb is described.
{"title":"Fabrication of Flat Plate Solar Thermoelectric Generator Panels for Near-Earth Orbits","authors":"F. K. Eggleston, N. Fuschillo","doi":"10.1109/TA.1965.4319867","DOIUrl":"https://doi.org/10.1109/TA.1965.4319867","url":null,"abstract":"A practical thermomechanical configurational design was developed for flat plate thermoelectric generator unit couples (approximately 1 inch by 1 inch) and panels (approximately 3 inches by 3 inches). An account of the techniques used in fabricating these solar energy conversion devices is given. Resulting unit couples provide 3 watts/ft2 with a weight factor of 30 watts/lb for the couple and 15 watts/lb for the panel form. Steady-state and thermal cycle life tests indicate an output degradation of less than 10% in 2000 cycles. These results offer promise of lower cost space power systems with special adaptability to missions not suited to photovoltaic cells. The fabrication of 3-by 3-inch panels of nine unit cells giving 15 watts/lb is described.","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":"85960776","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}
1) The ionized wakes of hypervelocity pellets are investigated by the resonant cavity method (TM010, 250 Mcs). The input admittance of the cavity is measured with a four-probe admittancemeter, providing a XY - trace together with a SMITH chart on an oscilloscope CRT. Two methods are suggested to make the measurement time - resolved. From the two measured parameters (real and imaginary part of the admittance), the plasma parameters (total number N of electrons within the cavity and electron collision frequency ν) are deduced, owing to an energy perturbation theory, which is described. Discussions are included about accuracy, calibration methods and limitations. 2) The same apparatus is used to probe shock - ionized air in a coaxial shock-tube. The propagation of 250 Mcs waves is studied by this way.
{"title":"Sondage Des Plasmas Par Des Mesures D'Impedance","authors":"M. Laug, P. Clavelin","doi":"10.1109/TA.1965.4319755","DOIUrl":"https://doi.org/10.1109/TA.1965.4319755","url":null,"abstract":"1) The ionized wakes of hypervelocity pellets are investigated by the resonant cavity method (TM010, 250 Mcs). The input admittance of the cavity is measured with a four-probe admittancemeter, providing a XY - trace together with a SMITH chart on an oscilloscope CRT. Two methods are suggested to make the measurement time - resolved. From the two measured parameters (real and imaginary part of the admittance), the plasma parameters (total number N of electrons within the cavity and electron collision frequency ν) are deduced, owing to an energy perturbation theory, which is described. Discussions are included about accuracy, calibration methods and limitations. 2) The same apparatus is used to probe shock - ionized air in a coaxial shock-tube. The propagation of 250 Mcs waves is studied by this way.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"74451732","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}
Several unique conditions are imposed upon measurements made in ONERA hotshot wind tunnels: the duration of flow; the environmental conditions; the circumstances under which the tunnels are used. Flow durations between 40 and 100 milliseconds are produced, and this imposes demands upon transducer performance. Instantaneous power consumed by the tunnels is of the order of 200 megavolt-amperes, and this places the transducers and portions of the readout system in an electrical environment wherein elaborate shielding precautions are required. The contract arrangement under which the tunnels are operated necessitates their use in testing for an optimum number of runs within a half-day of operation, and this necessitates the use of highly automated readout apparatus. This paper describes the solutions to these and other hotshot instrumentation problems. Methods of measurement and readout of pressure, forces, and rates of heat transfer are discussed, and systems for calibration are presented. Many elements of the calibration and readout processes have been made largely automatic. Errors contained among data representing the measurement of forces are sufficiently small as to be considered negligible in the face of minor uncertainties in readout constants. Measurement of pressures is conducted to an overall accuracy (including calibration and readout) of 2.5%. Heat transfer calibrations of 5-10% accuracy are imposed, and overall accuracy of heat transfer data ranges between 15 and 20 percent.
{"title":"Organisation Et Depouillement Automatique Des Mesures Dans Les Deux Soufflerier a Arc De L'Onera","authors":"M. Delattre","doi":"10.1109/TA.1965.4319752","DOIUrl":"https://doi.org/10.1109/TA.1965.4319752","url":null,"abstract":"Several unique conditions are imposed upon measurements made in ONERA hotshot wind tunnels: the duration of flow; the environmental conditions; the circumstances under which the tunnels are used. Flow durations between 40 and 100 milliseconds are produced, and this imposes demands upon transducer performance. Instantaneous power consumed by the tunnels is of the order of 200 megavolt-amperes, and this places the transducers and portions of the readout system in an electrical environment wherein elaborate shielding precautions are required. The contract arrangement under which the tunnels are operated necessitates their use in testing for an optimum number of runs within a half-day of operation, and this necessitates the use of highly automated readout apparatus. This paper describes the solutions to these and other hotshot instrumentation problems. Methods of measurement and readout of pressure, forces, and rates of heat transfer are discussed, and systems for calibration are presented. Many elements of the calibration and readout processes have been made largely automatic. Errors contained among data representing the measurement of forces are sufficiently small as to be considered negligible in the face of minor uncertainties in readout constants. Measurement of pressures is conducted to an overall accuracy (including calibration and readout) of 2.5%. Heat transfer calibrations of 5-10% accuracy are imposed, and overall accuracy of heat transfer data ranges between 15 and 20 percent.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90094372","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 successful development of a reliable electrical interconnection system for space vehicles is a difficult and challenging assignment, requiring ingenuity and engineering know-how. The design team approach, involving all factors of interconnection design, draws upon the combined experience and knowledge of those intimately aware of the requirements of their specific activity. This approach to interconnection design has already proven itself through a number of successful space missions. Tomorrow's space transportation will require further concentrated efforts in this field.
{"title":"Design of Electric Interconnecting Cables and Connectors for Space Power Systems","authors":"R. Franks","doi":"10.1109/TA.1965.4319753","DOIUrl":"https://doi.org/10.1109/TA.1965.4319753","url":null,"abstract":"The successful development of a reliable electrical interconnection system for space vehicles is a difficult and challenging assignment, requiring ingenuity and engineering know-how. The design team approach, involving all factors of interconnection design, draws upon the combined experience and knowledge of those intimately aware of the requirements of their specific activity. This approach to interconnection design has already proven itself through a number of successful space missions. Tomorrow's space transportation will require further concentrated efforts in this field.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79173584","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}
{"title":"Cameras Pour Photographie Des Projectiles En Vol Hypersonique","authors":"M. Pâques, M. Lecomte","doi":"10.1109/TA.1965.4319756","DOIUrl":"https://doi.org/10.1109/TA.1965.4319756","url":null,"abstract":"","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"74344307","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 resonant properties of a spherical cavity are described as a means of gauging liquid propellants in a zero-gravity field. The configuration of a liquid propellant in a partially filled spherical cavity have been shown to be such that a spherical vapor bubble exists in the center of the cavity. Spherical wave functions are developed and the boundary conditions applied to give an analytical expression for the cavity resonant frequency as a function of volumetric propellant loading. An aluminum scale-model, two inches in diameter, spherical cavity was constructed and loaded with varying dielectric shells to verify the mathematical predictions. Close agreement, within several percent, was obtained for three different dielectric constants, 2.5, 5, and 10.
{"title":"Zero-G Propellant Gauging Utilizing Radio Frequency Techniques in a Spherical Resonator","authors":"R. Garriott, G. Burns","doi":"10.1109/TA.1965.4319754","DOIUrl":"https://doi.org/10.1109/TA.1965.4319754","url":null,"abstract":"The resonant properties of a spherical cavity are described as a means of gauging liquid propellants in a zero-gravity field. The configuration of a liquid propellant in a partially filled spherical cavity have been shown to be such that a spherical vapor bubble exists in the center of the cavity. Spherical wave functions are developed and the boundary conditions applied to give an analytical expression for the cavity resonant frequency as a function of volumetric propellant loading. An aluminum scale-model, two inches in diameter, spherical cavity was constructed and loaded with varying dielectric shells to verify the mathematical predictions. Close agreement, within several percent, was obtained for three different dielectric constants, 2.5, 5, and 10.","PeriodicalId":13050,"journal":{"name":"IEEE Transactions on Aerospace","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1965-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77717196","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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