Capacitor sinusoidal alternating current characteristics were obtained as a function of temperature and frequency. Calorimeter measurements of capacitor heat loss rates were used to determine dissipation factors and to correct impedance bridge data. Application of dissipation factor data to the rms component values of the commutating capacitor complex waveforms yielded excellent agreement with commutating capacitor losses as measured by calorimeter.
{"title":"Investigation of Capacitors for Static Inverter Space Applications","authors":"J. F. Scoville","doi":"10.1109/TA.1965.4319802","DOIUrl":"https://doi.org/10.1109/TA.1965.4319802","url":null,"abstract":"Capacitor sinusoidal alternating current characteristics were obtained as a function of temperature and frequency. Calorimeter measurements of capacitor heat loss rates were used to determine dissipation factors and to correct impedance bridge data. Application of dissipation factor data to the rms component values of the commutating capacitor complex waveforms yielded excellent agreement with commutating capacitor losses as measured by calorimeter.","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":"90462537","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 limited, spacecraft transmission bandwidth has been used in the development of the Apollo Lunar Television system. Using 10 frames/sec and 320 non-interlaced scan lines, the system provides nearly commercial-quality TV pictures. A portable TV camera employing microcircuits is used onboard the spacecraft and on the lunar surface. Reiterative processing of the video signal is used in the scan conversion of the slow-scan TV signal to obtain a flicker-free commercially compatible picture at the home television receiver.
{"title":"The Apollo Lunar Television System","authors":"M. Engert","doi":"10.1109/TA.1965.4319824","DOIUrl":"https://doi.org/10.1109/TA.1965.4319824","url":null,"abstract":"A limited, spacecraft transmission bandwidth has been used in the development of the Apollo Lunar Television system. Using 10 frames/sec and 320 non-interlaced scan lines, the system provides nearly commercial-quality TV pictures. A portable TV camera employing microcircuits is used onboard the spacecraft and on the lunar surface. Reiterative processing of the video signal is used in the scan conversion of the slow-scan TV signal to obtain a flicker-free commercially compatible picture at the home television receiver.","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":"82012244","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 purpose of this paper is to reconcile the wide range of weights quoted for aerospace static inverters of the same VA rating. The inverters discussed are of conventional input and output: 15 to 500 vdc input and 400 cps sine wave output. Specification and application factors affecting inverter weight are tabulated. Graphical relationships are given for the effects of some factors for which relationships can be defined. Trends are indicated for the weight effect of factors for which graphical relationships are not given. The data presented should be useful to systems designers, in avoiding undue inverter weight, by proper specification and application of static inverters.
{"title":"Application Factors Affecting the Weight of Aerospace Static Inverters","authors":"L. Walker","doi":"10.1109/TA.1965.4319801","DOIUrl":"https://doi.org/10.1109/TA.1965.4319801","url":null,"abstract":"The purpose of this paper is to reconcile the wide range of weights quoted for aerospace static inverters of the same VA rating. The inverters discussed are of conventional input and output: 15 to 500 vdc input and 400 cps sine wave output. Specification and application factors affecting inverter weight are tabulated. Graphical relationships are given for the effects of some factors for which relationships can be defined. Trends are indicated for the weight effect of factors for which graphical relationships are not given. The data presented should be useful to systems designers, in avoiding undue inverter weight, by proper specification and application of static inverters.","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":"77703285","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 thin film thermocouple detector has been developed for use in the safety evaluation of electro explosive device wiring. The detector was fabricated using vacuum deposition techniques. Bismuth and tellurium were used as the thermoelectric materials. The resultant device has a thermoelectric power of 220 microvolts/°C and a response time of less than 17 milliseconds. Testing and calibration were accomplished using constant current pulse techniques.
{"title":"A Thin Film Micro Thermocouple R.F. Energy Detector for Electro Explosive Device Wiring","authors":"O. Mulkey","doi":"10.1109/TA.1965.4319864","DOIUrl":"https://doi.org/10.1109/TA.1965.4319864","url":null,"abstract":"A thin film thermocouple detector has been developed for use in the safety evaluation of electro explosive device wiring. The detector was fabricated using vacuum deposition techniques. Bismuth and tellurium were used as the thermoelectric materials. The resultant device has a thermoelectric power of 220 microvolts/°C and a response time of less than 17 milliseconds. Testing and calibration were accomplished using constant current pulse techniques.","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":"77812873","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 passive mass transfer thermodynamic device employing the latent heat of vaporization of an enclosed liquid is described as a method of precise thermal control for single, low-mass, high-energy electronic components. This device has particular application for electronic components having high power density which are incorporated in spacecraft electronic systems relying otherwise on radiant exchange with the environment as a means of space-environmental thermal control. Specific areas of interest growing out of the design requirements for such a mass transfer device are 1) liquid ullage control under zero-g conditions, precluding loss of liquid due to blow-out, and 2) favorable exploitation of liquid adsorption and surface phenomena in maintaining a continuous heat-sinking effect. The latter effect is demonstrated by data obtained in operating appropriately instrumented thermal control test articles under one-g conditions in vacuum and non-vacuum environments. Satisfactory heat-sinking is demonstrated over a range of energy inputs. Application of the system methodology and capabilities to the problem of space-environmental thermal control is evaluated and summarized.
{"title":"A Simple Evaporative System for Space-Environmental Thermal Control of Electronic Components","authors":"R. F. O'Neill","doi":"10.1109/TA.1965.4319816","DOIUrl":"https://doi.org/10.1109/TA.1965.4319816","url":null,"abstract":"A passive mass transfer thermodynamic device employing the latent heat of vaporization of an enclosed liquid is described as a method of precise thermal control for single, low-mass, high-energy electronic components. This device has particular application for electronic components having high power density which are incorporated in spacecraft electronic systems relying otherwise on radiant exchange with the environment as a means of space-environmental thermal control. Specific areas of interest growing out of the design requirements for such a mass transfer device are 1) liquid ullage control under zero-g conditions, precluding loss of liquid due to blow-out, and 2) favorable exploitation of liquid adsorption and surface phenomena in maintaining a continuous heat-sinking effect. The latter effect is demonstrated by data obtained in operating appropriately instrumented thermal control test articles under one-g conditions in vacuum and non-vacuum environments. Satisfactory heat-sinking is demonstrated over a range of energy inputs. Application of the system methodology and capabilities to the problem of space-environmental thermal control is evaluated and summarized.","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":"89825751","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 is an approach to materials selection and design considerations of rotating machines subjected to difficult environmental conditions.
本文探讨了在恶劣环境条件下旋转机械的材料选择和设计考虑。
{"title":"Rotating Machines for Extreme Environments","authors":"D. Irani, C. S. Smith","doi":"10.1109/TA.1965.4319860","DOIUrl":"https://doi.org/10.1109/TA.1965.4319860","url":null,"abstract":"This paper is an approach to materials selection and design considerations of rotating machines subjected to difficult environmental conditions.","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":"80849231","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 deals with several selected aspects of signal distribution in automatic checkout systems. These are: 1. The use of relay matrices as control elements 2. The inclusion of self-checking capabilities 3. Problems of systems integration These aspects are not unique to automatic checkout systems. However, due to the nature of automatic checkout systems as presently being designed around digital circuitry, they find either fuller or different applications than in other types of systems. Also, while they are on the surface somewhat disconnected in nature, they tend to interrelate during the implementation of an automatic checkout system.
{"title":"Signal Distribution in Automatic Checkout Systems","authors":"George F. Meister","doi":"10.1109/TA.1965.4319834","DOIUrl":"https://doi.org/10.1109/TA.1965.4319834","url":null,"abstract":"This paper deals with several selected aspects of signal distribution in automatic checkout systems. These are: 1. The use of relay matrices as control elements 2. The inclusion of self-checking capabilities 3. Problems of systems integration These aspects are not unique to automatic checkout systems. However, due to the nature of automatic checkout systems as presently being designed around digital circuitry, they find either fuller or different applications than in other types of systems. Also, while they are on the surface somewhat disconnected in nature, they tend to interrelate during the implementation of an automatic checkout system.","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":"76102509","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}
Since a prime objective of static power converter design is to minimize weight, optimizing magnetic components is particularly important. This paper derives the fundamental relationship between magnetic device weight and the basic design parameters. These include volt-ampere rating and frequency, characteristics of core and conductor materials, and ratios defining physical dimensions. Also, an expression for estimating heat rejection is obtained; thus, the practicality of a given design can easily be determined.
{"title":"Analytical Optimization of Magnetics for Static Power Conversion","authors":"P. Corey","doi":"10.1109/TA.1965.4319787","DOIUrl":"https://doi.org/10.1109/TA.1965.4319787","url":null,"abstract":"Since a prime objective of static power converter design is to minimize weight, optimizing magnetic components is particularly important. This paper derives the fundamental relationship between magnetic device weight and the basic design parameters. These include volt-ampere rating and frequency, characteristics of core and conductor materials, and ratios defining physical dimensions. Also, an expression for estimating heat rejection is obtained; thus, the practicality of a given design can easily be determined.","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":"84715876","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 development of a special servo computer for wind tunnel applications to provide analog computations and indications of Mach number and dynamic pressure. Division of up to six aerodynamic variables by the dynamic pressure can also be performed. The computer uses simplified techniques as compared to usual analog computer practices which are allowable because of the special application. Multiple ranges of Mach number and dynamic pressure are used to obtain improved accuracy. The system can be used, with minor modifications, by most wind tunnel facilities. The basic techniques could also be used for an accurate air data computer for aircraft applications.
{"title":"A Mach Number and Dynamic Pressure Computer for Analog Reduction of Wind Tunnel Data","authors":"J. Cooksey, E. C. Vogt","doi":"10.1109/TA.1965.4319780","DOIUrl":"https://doi.org/10.1109/TA.1965.4319780","url":null,"abstract":"This paper describes the development of a special servo computer for wind tunnel applications to provide analog computations and indications of Mach number and dynamic pressure. Division of up to six aerodynamic variables by the dynamic pressure can also be performed. The computer uses simplified techniques as compared to usual analog computer practices which are allowable because of the special application. Multiple ranges of Mach number and dynamic pressure are used to obtain improved accuracy. The system can be used, with minor modifications, by most wind tunnel facilities. The basic techniques could also be used for an accurate air data computer for aircraft applications.","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":"87263742","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}
Testing in sunlight is an essential step in verifying the quality of large solar-cell panels, and in predicting space performance. Solar testing is usually done at high elevations to minimize absorption of sunlight by the atmosphere. A problem in such solar testing is the orientation of large panels toward the sun continuously, especially when wind gusts can occur. This paper describes a portable electric-motor driven equatorial mount for testing large solar panels. The equatorial mount is anchored by means of an automobile or truck. Design criteria such as geometrical relationships, structural loads, and gearbox details are provided. The pointing accuracy obtained is given.
{"title":"A Portable Equatorial Mount for Solar-Testing Large Solar Panels","authors":"G. E. Schmeer, H. Oman","doi":"10.1109/TA.1965.4319783","DOIUrl":"https://doi.org/10.1109/TA.1965.4319783","url":null,"abstract":"Testing in sunlight is an essential step in verifying the quality of large solar-cell panels, and in predicting space performance. Solar testing is usually done at high elevations to minimize absorption of sunlight by the atmosphere. A problem in such solar testing is the orientation of large panels toward the sun continuously, especially when wind gusts can occur. This paper describes a portable electric-motor driven equatorial mount for testing large solar panels. The equatorial mount is anchored by means of an automobile or truck. Design criteria such as geometrical relationships, structural loads, and gearbox details are provided. The pointing accuracy obtained is given.","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":"86704592","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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