In this paper the effects of the time harmonics on the output voltage are investigated. Instead of a complete analysis, the waveshape of the line current is considered as recorded on an oscilloscope when the alternator supplies an inverter. The minimum airgap induction occurs when the magnetomotive forces of the fifth and seventh time harmonic oppose the field excitation. The reduction in the amplitude of the fundamental of the airgap induction caused by the time harmonics was found to be of the order of fifteen to twenty percent for a typical cyclo-inverter load.
{"title":"Influence of Inverter Loads on the Airgap Flux of Aerospace Homopolar Alternators","authors":"E. Erdelyi","doi":"10.1109/TA.1965.4319774","DOIUrl":"https://doi.org/10.1109/TA.1965.4319774","url":null,"abstract":"In this paper the effects of the time harmonics on the output voltage are investigated. Instead of a complete analysis, the waveshape of the line current is considered as recorded on an oscilloscope when the alternator supplies an inverter. The minimum airgap induction occurs when the magnetomotive forces of the fifth and seventh time harmonic oppose the field excitation. The reduction in the amplitude of the fundamental of the airgap induction caused by the time harmonics was found to be of the order of fifteen to twenty percent for a typical cyclo-inverter load.","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":"84582525","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 design evolution of an amplifier for use in signal conditioning is presented. The advantages and limitations of several designs are discussed. The progressive development is described arriving finally at a most promising method which utilizes old circuitry but new concepts. Detailed characteristics that show unusual advances in power saving, weight, and volume, which are critical aspects in space application, are given.
{"title":"The Airborne DC Signal Conditioning Amplifier Yesterday, Today, and Tomorrow","authors":"G. E. Wenzel","doi":"10.1109/TA.1965.4319839","DOIUrl":"https://doi.org/10.1109/TA.1965.4319839","url":null,"abstract":"The design evolution of an amplifier for use in signal conditioning is presented. The advantages and limitations of several designs are discussed. The progressive development is described arriving finally at a most promising method which utilizes old circuitry but new concepts. Detailed characteristics that show unusual advances in power saving, weight, and volume, which are critical aspects in space application, are 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":"87632217","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}
Development of liquid and vapor screw seals to separate the bearing and rotor cavity in a potassium cooled and lubricated space electric power generator has been completed to the point where ground test application is possible. Individual tests were made in potassium simulating fluids to determine seal performance at laminar and turbulent conditions. Liquid seal performance was verified in 375°F potassium. Vapor seal performance concurred with analysis of a simplified flow model. Remaining problems associated with adaptation of these seals to an actual generator are discussed.
{"title":"Screw Type Shaft Seals for Potassium Lubricated Generators","authors":"A. E. King","doi":"10.1109/TA.1965.4319838","DOIUrl":"https://doi.org/10.1109/TA.1965.4319838","url":null,"abstract":"Development of liquid and vapor screw seals to separate the bearing and rotor cavity in a potassium cooled and lubricated space electric power generator has been completed to the point where ground test application is possible. Individual tests were made in potassium simulating fluids to determine seal performance at laminar and turbulent conditions. Liquid seal performance was verified in 375°F potassium. Vapor seal performance concurred with analysis of a simplified flow model. Remaining problems associated with adaptation of these seals to an actual generator 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":"84232628","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}
Two basic methods for mass determination are: (1) direct measurement, (2) volume and density determination. Both methods or variations have been used to determine space vehicle propellant mass with varying degrees of success. Stringent propellant loading accuracy requirements of ±0.5 percent for the Saturn S-IV Stage have led to the development of a Cryogenic Calibration Weigh System. The method employs accurate electronic force transducers and measuring systems as the standard and experimental weighings have verified achievement of better than the required accuracy.
{"title":"Saturn S-IV Cryogenic Weigh System Part II: Weigh Operations","authors":"G. Matsumoto","doi":"10.1109/TA.1965.4319796","DOIUrl":"https://doi.org/10.1109/TA.1965.4319796","url":null,"abstract":"Two basic methods for mass determination are: (1) direct measurement, (2) volume and density determination. Both methods or variations have been used to determine space vehicle propellant mass with varying degrees of success. Stringent propellant loading accuracy requirements of ±0.5 percent for the Saturn S-IV Stage have led to the development of a Cryogenic Calibration Weigh System. The method employs accurate electronic force transducers and measuring systems as the standard and experimental weighings have verified achievement of better than the required accuracy.","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":"79315367","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}
Error-free radio command control of manned and unmanned spacecraft used in the manned spacecraft program is mandatory for mission success. This paper outlines the history, philosophies, and methods used in the development of the Digital Command Network implemented for this purpose. This network is designed to the concepts of error detection, versatility, and reliability. This paper will explain the basic concepts of design, the configuration of ground command sites involved, and the overall network which evolved to satisfy the command requirements of manned spaceflight control.
{"title":"Digital Command - A Network for Manned Spaceflight","authors":"V. M. Dauphin","doi":"10.1109/TA.1965.4319793","DOIUrl":"https://doi.org/10.1109/TA.1965.4319793","url":null,"abstract":"Error-free radio command control of manned and unmanned spacecraft used in the manned spacecraft program is mandatory for mission success. This paper outlines the history, philosophies, and methods used in the development of the Digital Command Network implemented for this purpose. This network is designed to the concepts of error detection, versatility, and reliability. This paper will explain the basic concepts of design, the configuration of ground command sites involved, and the overall network which evolved to satisfy the command requirements of manned spaceflight control.","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":"79532582","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 100 AH hermetically sealed nickel-cadmium cell has been developed. The problem of heat dissipation, which adversely affects cycle life, has been solved by preventing overcharge. This was accomplished using the recently developed Adhydrode concept. Other advantages of the Adhydrodes are rapid recharge, high recharge efficiency, and operation at low internal pressures. Some characteristics of the Adhydrode signal are given.
{"title":"Large Size Sealed Nickel-Cadmium Cells","authors":"H. Seiger","doi":"10.1109/TA.1965.4319848","DOIUrl":"https://doi.org/10.1109/TA.1965.4319848","url":null,"abstract":"A 100 AH hermetically sealed nickel-cadmium cell has been developed. The problem of heat dissipation, which adversely affects cycle life, has been solved by preventing overcharge. This was accomplished using the recently developed Adhydrode concept. Other advantages of the Adhydrodes are rapid recharge, high recharge efficiency, and operation at low internal pressures. Some characteristics of the Adhydrode signal are 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":"80710854","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 automatic technique, utilizing a large high speed computer for the analysis of records obtained from accelerometers, pressure guages and gyros installed in the re-entry vehicles of the Black Knight rocket, is described. It is shown that this enables a suitable arrangement of only three accelerometers to yield trajectory data, angular motion and the aerodynamic characteristics of the re-entry body. Examples of the analysis of accelerometer and rate gyro data are given and the lines of further development and some applications are indicated.
{"title":"Techniques of Measurement and Automatic Analysis of Dynamic Motion with Application to Some Re-Entry Experiments","authors":"A. Waterfall","doi":"10.1109/TA.1965.4319805","DOIUrl":"https://doi.org/10.1109/TA.1965.4319805","url":null,"abstract":"An automatic technique, utilizing a large high speed computer for the analysis of records obtained from accelerometers, pressure guages and gyros installed in the re-entry vehicles of the Black Knight rocket, is described. It is shown that this enables a suitable arrangement of only three accelerometers to yield trajectory data, angular motion and the aerodynamic characteristics of the re-entry body. Examples of the analysis of accelerometer and rate gyro data are given and the lines of further development and some applications are indicated.","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":"79667760","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}
In order to achieve maximum vehicle efficiency, it is essential that the vehicle propellants be loaded to desired values and that these propellants approach simultaneous depletion at the end of powered flight. To accomplish precise loading and assure minimum residuals, a highly accurate and repeatable, vehicle located, propellant management (PM) or propellant utilization (PU) system must be used. As the ability to load propellants to predetermined values depends directly on the ability of the system to accurately sense the propellant masses, it is essential that the system be calibrated with respect to propellant mass under conditions resembling those to be experienced during final loading and powered flight. The use of a cryogenic weigh system will reduce the unknown factors in capacitance sensor element shaping, tank geometry, and propellant properties to a degree which will permit the determination of propellant masses to within 0.25%. This paper describes the basic purpose for acryogenic weigh system in connection with the calibration of the Saturn Propellant Utilization System used on the S-IV stage.
{"title":"Saturn S-IV Cryogenic Weigh System Part I: Propellant Utilization","authors":"R. Nichols, E. A. Hendee","doi":"10.1109/TA.1965.4319795","DOIUrl":"https://doi.org/10.1109/TA.1965.4319795","url":null,"abstract":"In order to achieve maximum vehicle efficiency, it is essential that the vehicle propellants be loaded to desired values and that these propellants approach simultaneous depletion at the end of powered flight. To accomplish precise loading and assure minimum residuals, a highly accurate and repeatable, vehicle located, propellant management (PM) or propellant utilization (PU) system must be used. As the ability to load propellants to predetermined values depends directly on the ability of the system to accurately sense the propellant masses, it is essential that the system be calibrated with respect to propellant mass under conditions resembling those to be experienced during final loading and powered flight. The use of a cryogenic weigh system will reduce the unknown factors in capacitance sensor element shaping, tank geometry, and propellant properties to a degree which will permit the determination of propellant masses to within 0.25%. This paper describes the basic purpose for acryogenic weigh system in connection with the calibration of the Saturn Propellant Utilization System used on the S-IV stage.","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":"79696858","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 pulse reflection test method permits a more comprehensive electrical check of an EBW ordnance device than can be obtained by the ac and dc continuity check methods currently in use throughout the industry. Pulse reflection testing is a specialized application of time domain reflectometry. Laboratory tests performed on a triple-scale EBW Test Model showed that waveforms produced by imposing various test conditions are definite and repeatable, and that these waveforms can be interpreted so as to determine whether an EBW device is electrically operable or defective.
{"title":"Electro-Explosive Device Pulse Reflection Checkout Technique","authors":"J. R. Petrick","doi":"10.1109/TA.1965.4319862","DOIUrl":"https://doi.org/10.1109/TA.1965.4319862","url":null,"abstract":"The pulse reflection test method permits a more comprehensive electrical check of an EBW ordnance device than can be obtained by the ac and dc continuity check methods currently in use throughout the industry. Pulse reflection testing is a specialized application of time domain reflectometry. Laboratory tests performed on a triple-scale EBW Test Model showed that waveforms produced by imposing various test conditions are definite and repeatable, and that these waveforms can be interpreted so as to determine whether an EBW device is electrically operable or defective.","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":"81337956","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 sensor has been developed to measure electrostatic fields between a few tenths of a volt/cm and many thousands of volts/cm. The sensor replaces the rotating chopper in traditional electric field meters with a vibrating sensing disk. Since there are no frictional moving parts, the sensor is ideally suited for the space environment and long lifetime applications. The instrument weighs less than 2.0 pounds; the volume is less than 20 cubic inches. Input power is less than 2.0 watts. Output is two 0 to 5 volt telemetry signals indicating magnitude, sign, and decade multiplier of the electrostatic field.
{"title":"A New Electrostatic Field Measuring Instrument","authors":"J. Palmer","doi":"10.1109/TA.1965.4319846","DOIUrl":"https://doi.org/10.1109/TA.1965.4319846","url":null,"abstract":"A sensor has been developed to measure electrostatic fields between a few tenths of a volt/cm and many thousands of volts/cm. The sensor replaces the rotating chopper in traditional electric field meters with a vibrating sensing disk. Since there are no frictional moving parts, the sensor is ideally suited for the space environment and long lifetime applications. The instrument weighs less than 2.0 pounds; the volume is less than 20 cubic inches. Input power is less than 2.0 watts. Output is two 0 to 5 volt telemetry signals indicating magnitude, sign, and decade multiplier of the electrostatic field.","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":"74461365","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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