During cryogenic weigh system operation, hydrogen when combined with oxygen can create an unsafe condition. Therefore the concentration of the residual oxygen and hydrogen from leaks in the cryogenic weigh environmental bags must be known at all times during the cryogenic weigh. Hydrogen and oxygen detectors will provide the optimum method for maintaining safe conditions. Hydrogen properties and safe mixtures are reviewed. The method selected to analyze the oxygen content is discussed. The selection, development, and testing of a hydrogen detector system is examined.
{"title":"Saturn S-IV Cryogenic Weigh System Part IV: Safety","authors":"E. G. Corcoran","doi":"10.1109/TA.1965.4319798","DOIUrl":"https://doi.org/10.1109/TA.1965.4319798","url":null,"abstract":"During cryogenic weigh system operation, hydrogen when combined with oxygen can create an unsafe condition. Therefore the concentration of the residual oxygen and hydrogen from leaks in the cryogenic weigh environmental bags must be known at all times during the cryogenic weigh. Hydrogen and oxygen detectors will provide the optimum method for maintaining safe conditions. Hydrogen properties and safe mixtures are reviewed. The method selected to analyze the oxygen content is discussed. The selection, development, and testing of a hydrogen detector system is examined.","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":"89007919","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 secondary power system in which all secondary power was extracted from the engine by means of large, variable-voltage, variable-frequency generators was proposed for the Lockheed Phase I SST. The quantity of constant frequency power required in the Phase IIA airplane was not favorable to such a system. The selected system uses wing mounted accessory gear boxes, shaft driven from the engine. CSD/generators on the gear boxes generate the 240/416 volt, 400 cycle ac power which is utilized directly by the major loads.
{"title":"The Development of a Secondary Power System for a Commercial Supersonic Air Transport","authors":"M. Cronin, P. Frankel","doi":"10.1109/TA.1965.4319828","DOIUrl":"https://doi.org/10.1109/TA.1965.4319828","url":null,"abstract":"A secondary power system in which all secondary power was extracted from the engine by means of large, variable-voltage, variable-frequency generators was proposed for the Lockheed Phase I SST. The quantity of constant frequency power required in the Phase IIA airplane was not favorable to such a system. The selected system uses wing mounted accessory gear boxes, shaft driven from the engine. CSD/generators on the gear boxes generate the 240/416 volt, 400 cycle ac power which is utilized directly by the major 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":"78727810","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 long sought means whereby complete control can be simply exercised over the speed and torque of a 3-phase squirrel cage induction motor has recently been reduced to practice and is currently in operation in full scale hardware. By means of an all solid-state cycloconverter type frequency changer power is supplied to the motor at a controlled frequency and voltage such that the motor is operated at controlled slip in a closed feedback system. In this loop the torque (and therefore, speed) can be instantaneously controlled. A low power level signal which varies the motor slip frequency is the controlling variable. The application of this concept to aerospace drives is discussed with particular attention given to servo-controlled antenna drive systems.
{"title":"Precisely Controlled 3-Phase Squirrel Cage Induction Motor Drives for Aerospace Applications","authors":"L. J. Lawson","doi":"10.1109/TA.1965.4319788","DOIUrl":"https://doi.org/10.1109/TA.1965.4319788","url":null,"abstract":"The long sought means whereby complete control can be simply exercised over the speed and torque of a 3-phase squirrel cage induction motor has recently been reduced to practice and is currently in operation in full scale hardware. By means of an all solid-state cycloconverter type frequency changer power is supplied to the motor at a controlled frequency and voltage such that the motor is operated at controlled slip in a closed feedback system. In this loop the torque (and therefore, speed) can be instantaneously controlled. A low power level signal which varies the motor slip frequency is the controlling variable. The application of this concept to aerospace drives is discussed with particular attention given to servo-controlled antenna drive systems.","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":"73704766","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}
G. W. Ernsberger, H. R. Howell, F. Gourash, J. L. Klingenberger
Load division was accomplished by locking both static inverters in-phase and automatically controlling the magnitude of each inverter's internal voltage. Mathematical analysis shows (1) that the inverter internal impedance determines design of load division circuit, and (2) any reasonable load division accuracy can be obtained by using sufficient load division circuit gain. This paralleling method can be used with any number of static inverters and offers unique adaptability, reliability, and high power capability for aerospace applications.
{"title":"Parallel Operation of Aerospace Static Inverters","authors":"G. W. Ernsberger, H. R. Howell, F. Gourash, J. L. Klingenberger","doi":"10.1109/TA.1965.4319800","DOIUrl":"https://doi.org/10.1109/TA.1965.4319800","url":null,"abstract":"Load division was accomplished by locking both static inverters in-phase and automatically controlling the magnitude of each inverter's internal voltage. Mathematical analysis shows (1) that the inverter internal impedance determines design of load division circuit, and (2) any reasonable load division accuracy can be obtained by using sufficient load division circuit gain. This paralleling method can be used with any number of static inverters and offers unique adaptability, reliability, and high power capability for aerospace 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":"74032369","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 analyzes the rotating rectifier type aircraft generator system so that a digital computer study of system transient response may be made. A detailed analysis of the generator is made using Park's equations. This analysis results in a mathematical model which is quite easily handled by a digital computer. A single time constant transfer function is used for the exciter-rectifier which has proved sufficiently accurate. The generator analysis could be extended to the exciter and rectifier equations derived in Reference 3 used to obtain better accuracy if sufficient exciter-rectifier data is available. The regulator transfer function is a ratio of polynomials with limits and constants furnished by the designer. The purpose of this paper is to present the detailed generator analysis and briefly discuss the methods of representing other system elements and the computer program used for problem solution.
{"title":"Dynamic System Analysis for Electrical Power Systems","authors":"D. Clark","doi":"10.1109/TA.1965.4319790","DOIUrl":"https://doi.org/10.1109/TA.1965.4319790","url":null,"abstract":"This paper analyzes the rotating rectifier type aircraft generator system so that a digital computer study of system transient response may be made. A detailed analysis of the generator is made using Park's equations. This analysis results in a mathematical model which is quite easily handled by a digital computer. A single time constant transfer function is used for the exciter-rectifier which has proved sufficiently accurate. The generator analysis could be extended to the exciter and rectifier equations derived in Reference 3 used to obtain better accuracy if sufficient exciter-rectifier data is available. The regulator transfer function is a ratio of polynomials with limits and constants furnished by the designer. The purpose of this paper is to present the detailed generator analysis and briefly discuss the methods of representing other system elements and the computer program used for problem solution.","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":"80263463","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}
Statistical methods of analysis are used to obtain important physical properties of random signals. A description is given of the system which was designed for use in the Propulsion Wind Tunnel, Arnold Engineering Development Center, to provide the necessary signal conditioning and the analog-to-digital conversion at a rate high enough to prevent mixing of the spectral densities. The overall system transfer function is discussed, and the system limitations are defined.
{"title":"A Digital System for the Acquisition and Analysis of Random Data","authors":"W. Comer","doi":"10.1109/TA.1965.4319779","DOIUrl":"https://doi.org/10.1109/TA.1965.4319779","url":null,"abstract":"Statistical methods of analysis are used to obtain important physical properties of random signals. A description is given of the system which was designed for use in the Propulsion Wind Tunnel, Arnold Engineering Development Center, to provide the necessary signal conditioning and the analog-to-digital conversion at a rate high enough to prevent mixing of the spectral densities. The overall system transfer function is discussed, and the system limitations are defined.","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":"73464294","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 dynamic equations for a rigid asymmetrical spinning space station with an internal movable mass are presented in the appendix. The body rates induced by certain mass movements are shown to be elliptic functions for the uncontrolled space station. This assumes the mass movement is simulated by impulsive product of inertia changes. A linear analysis is presented for the controlled space station using a gyroscopic controller. The controller provides nutation damping and limited precession control.
{"title":"Dynamic Response of an Asymmetrical Spinning Space Station","authors":"J. L. Fowler","doi":"10.1109/TA.1965.4319812","DOIUrl":"https://doi.org/10.1109/TA.1965.4319812","url":null,"abstract":"The dynamic equations for a rigid asymmetrical spinning space station with an internal movable mass are presented in the appendix. The body rates induced by certain mass movements are shown to be elliptic functions for the uncontrolled space station. This assumes the mass movement is simulated by impulsive product of inertia changes. A linear analysis is presented for the controlled space station using a gyroscopic controller. The controller provides nutation damping and limited precession 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":"73358074","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}
Aircraft generating systems are sometimes used in applications in which a large part, if not all, of the system load is pulsating--a load requiring repetitive pulses of current. One example of this type of load is a rectifier system feeding a resonant L-C charging circuit which is periodically charged and discharged. This type of load presents unique problems in the design of the generating system. This paper discusses the general behavior of a generating system with this type of pulsating-load and analyzes voltage and current wave shapes, equivalent generator load, effect of the load on voltage modulation and on voltage regulator design, and other factors. Test data for a model system is included.
{"title":"Behavior of Aircraft Generating Systems with Pulsating Loads","authors":"H. W. Gayek, Lawrence R. Peaslee","doi":"10.1109/TA.1965.4319858","DOIUrl":"https://doi.org/10.1109/TA.1965.4319858","url":null,"abstract":"Aircraft generating systems are sometimes used in applications in which a large part, if not all, of the system load is pulsating--a load requiring repetitive pulses of current. One example of this type of load is a rectifier system feeding a resonant L-C charging circuit which is periodically charged and discharged. This type of load presents unique problems in the design of the generating system. This paper discusses the general behavior of a generating system with this type of pulsating-load and analyzes voltage and current wave shapes, equivalent generator load, effect of the load on voltage modulation and on voltage regulator design, and other factors. Test data for a model system is included.","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":"83980222","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}
Fuel cells hold a great deal of promise as power sources for space systems; however, much remains to be learned about the performance of available fuel-cell systems during extended operation (over 2 weeks). This paper describes a test program being conducted to determine the operating characteristics and life of a 1.5 kw Allis Chalmers fuel cell. Although the tests have not been completed, the test setup, procedure, and preliminary results are discussed.
{"title":"Performance and Life Testing of a 1.5 KW Allis Chalmers Fuel Cell","authors":"G. Turner, A. N. Himle","doi":"10.1109/TA.1965.4319851","DOIUrl":"https://doi.org/10.1109/TA.1965.4319851","url":null,"abstract":"Fuel cells hold a great deal of promise as power sources for space systems; however, much remains to be learned about the performance of available fuel-cell systems during extended operation (over 2 weeks). This paper describes a test program being conducted to determine the operating characteristics and life of a 1.5 kw Allis Chalmers fuel cell. Although the tests have not been completed, the test setup, procedure, and preliminary results 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":"78568637","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 an accurate and rapid non-contact surface analyzer for defining a three-dimensional solar concentrator surface contour using a digital computer. The data, representing the surface contour, can be recorded on computer tape and used for a number of final results. In addition to concentrator surface analysis, the analyzer is designed to have the capability for defining surfaces on numerous materials ranging in size from small machined parts to large airplane or missile skin contour.
{"title":"Solar Concentrator Surface Contour","authors":"Bruce E. Keller","doi":"10.1109/TA.1965.4319782","DOIUrl":"https://doi.org/10.1109/TA.1965.4319782","url":null,"abstract":"This paper describes an accurate and rapid non-contact surface analyzer for defining a three-dimensional solar concentrator surface contour using a digital computer. The data, representing the surface contour, can be recorded on computer tape and used for a number of final results. In addition to concentrator surface analysis, the analyzer is designed to have the capability for defining surfaces on numerous materials ranging in size from small machined parts to large airplane or missile skin contour.","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":"80279226","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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