A packaging system usable for both oriented photovoltaic and flat plate thermoelectric solar arrays is presented which permits six circular disks to open out in an aerospace environment. For a base plate and disk radius of 50 cm, the system enables a maximum power of 435 watts to be delivered to a matched load by an oriented photovoltaic array of six disks plus base plate or 373 watts for 6 disks alone. The latter figure is to be compared with 150 watts (6 disks) for the oriented thermoelectric array. Several comparisons of the two systems in regard to weight, cost, and radiation resistance are discussed. Under certain circumstances, the thermoelectric array has potential cost and weight advantages on a per-watt basis in addition to radiation damage resistance advantages.
{"title":"Packaging System for Extendable Solar Photovoltaic or Thermoelectric Arrays","authors":"N. Fuschillo, R. Gibson, O. VanBlaricon","doi":"10.1109/TA.1965.4319785","DOIUrl":"https://doi.org/10.1109/TA.1965.4319785","url":null,"abstract":"A packaging system usable for both oriented photovoltaic and flat plate thermoelectric solar arrays is presented which permits six circular disks to open out in an aerospace environment. For a base plate and disk radius of 50 cm, the system enables a maximum power of 435 watts to be delivered to a matched load by an oriented photovoltaic array of six disks plus base plate or 373 watts for 6 disks alone. The latter figure is to be compared with 150 watts (6 disks) for the oriented thermoelectric array. Several comparisons of the two systems in regard to weight, cost, and radiation resistance are discussed. Under certain circumstances, the thermoelectric array has potential cost and weight advantages on a per-watt basis in addition to radiation damage resistance advantages.","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":"79665352","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 concerned with static inverters and dc link frequency converters. Its purpose is to describe some of the problem areas which should be considered in equipment design, equipment specification, and system design, with the goal of achieving optimum power system design. Five major areas are covered, as follows: (1) Input Overvoltage Transients Causes of transients and their effects on equipment design are discussed, and some means of reducing their effect are shown. Comments are made relative to methods of describing overvoltage transients for semiconductor circuits. (2) Overload and Short Circuit Capability The effect of overload requirements on design is shown, and typical data is given showing some of the trade-off involved. (3) Output Harmonic Requirements The source of harmonics is shown. Means of reduction by filtering and by harmonic cancellation is discussed and trade-off data is presented. (4) DC Source Requirements The need for a bilateral source of low ac impedance is shown. (5) AC Source Problems Rectifier distortion of the source is discussed, and the trade-offs involved in its reduction are shown.
{"title":"Interface Problems in the Use of Aerospace Static Power Conversion Equipment","authors":"S. Merritt","doi":"10.1109/TA.1965.4319833","DOIUrl":"https://doi.org/10.1109/TA.1965.4319833","url":null,"abstract":"This paper is concerned with static inverters and dc link frequency converters. Its purpose is to describe some of the problem areas which should be considered in equipment design, equipment specification, and system design, with the goal of achieving optimum power system design. Five major areas are covered, as follows: (1) Input Overvoltage Transients Causes of transients and their effects on equipment design are discussed, and some means of reducing their effect are shown. Comments are made relative to methods of describing overvoltage transients for semiconductor circuits. (2) Overload and Short Circuit Capability The effect of overload requirements on design is shown, and typical data is given showing some of the trade-off involved. (3) Output Harmonic Requirements The source of harmonics is shown. Means of reduction by filtering and by harmonic cancellation is discussed and trade-off data is presented. (4) DC Source Requirements The need for a bilateral source of low ac impedance is shown. (5) AC Source Problems Rectifier distortion of the source is discussed, and the trade-offs involved in its reduction are shown.","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":"75123653","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 feasibility of a variable-speed constant-frequency generating system for a supersonic transport airplane, having a service life equal to that of the airframe, is examined in the light of supersonic transport requirements and of the history and present development status of VSCF systems for subsonic airplanes The paper outlines work that should be done in order to increase the likelihood of achieving this goal.
{"title":"A Variable-Speed Constant-Frequency Generating System for a Supersonic Transport","authors":"K. M. Chirgwin","doi":"10.1109/TA.1965.4319827","DOIUrl":"https://doi.org/10.1109/TA.1965.4319827","url":null,"abstract":"The feasibility of a variable-speed constant-frequency generating system for a supersonic transport airplane, having a service life equal to that of the airframe, is examined in the light of supersonic transport requirements and of the history and present development status of VSCF systems for subsonic airplanes The paper outlines work that should be done in order to increase the likelihood of achieving this goal.","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":"75209995","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 treats some of the theoretical and practical aspects of problems encountered in the development of bonds to thermoelectric materials for a flat plate solar thermoelectric generator. The specific problems encountered in the design and development of a lightweight generator capable of producing 3 watts/ft2 in a variety of earth orbital attitudes are presented and approaches to their solutions are outlined. Design considerations led to the selection of a Bi2Te3-based thermoelectric material and a barrier multilayer-type bond. Performance data are presented on various kinds of bonds to Bi2Te3 alloys; at present, it appears that barrier-type bond performance is critically dependent on the perfection of the barrier layer.
{"title":"Thermoelectric Bond Development for the Flat Plate Solar Thermoelectric Generator","authors":"J. Black, F. K. Eggleston, N. Fuschillo","doi":"10.1109/TA.1965.4319868","DOIUrl":"https://doi.org/10.1109/TA.1965.4319868","url":null,"abstract":"This paper treats some of the theoretical and practical aspects of problems encountered in the development of bonds to thermoelectric materials for a flat plate solar thermoelectric generator. The specific problems encountered in the design and development of a lightweight generator capable of producing 3 watts/ft2 in a variety of earth orbital attitudes are presented and approaches to their solutions are outlined. Design considerations led to the selection of a Bi2Te3-based thermoelectric material and a barrier multilayer-type bond. Performance data are presented on various kinds of bonds to Bi2Te3 alloys; at present, it appears that barrier-type bond performance is critically dependent on the perfection of the barrier layer.","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":"79735051","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 a limited simulation of airborne or space system equipment assembled in the laboratory, on which interference tests were performed concurrently with an analysis of the compatibility using a general-purpose digital computer. Conclusions are presented concerning the needs for input data for a computer analysis of system electromagnetic compatibility, the adaptability of specification test data to these needs, and additional test data which could supply useful information for a computer analysis.
{"title":"Experimental Computer Analysis of Cable Coupling for Intra-System Electromagnetic Compatibility","authors":"J. Maynard, H. L. Rehkopf, B. Carlson","doi":"10.1109/TA.1965.4319844","DOIUrl":"https://doi.org/10.1109/TA.1965.4319844","url":null,"abstract":"This paper describes a limited simulation of airborne or space system equipment assembled in the laboratory, on which interference tests were performed concurrently with an analysis of the compatibility using a general-purpose digital computer. Conclusions are presented concerning the needs for input data for a computer analysis of system electromagnetic compatibility, the adaptability of specification test data to these needs, and additional test data which could supply useful information for a computer analysis.","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":"78841127","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 designers of the Apollo G&N system adopted a conservative but flexible design philosophy. In this paper the development of the guidance computer is described which typifies the application of the design approach throughout the development of the system. The computers have demonstrated a mean-time-between-failure (MTBF) of four to five times that predicted. The success of the design approach has thus been shown by the observed reliability of the system.
{"title":"Apollo Guidance and Navigation Electronics","authors":"Charles D. Brady","doi":"10.1109/TA.1965.4319823","DOIUrl":"https://doi.org/10.1109/TA.1965.4319823","url":null,"abstract":"The designers of the Apollo G&N system adopted a conservative but flexible design philosophy. In this paper the development of the guidance computer is described which typifies the application of the design approach throughout the development of the system. The computers have demonstrated a mean-time-between-failure (MTBF) of four to five times that predicted. The success of the design approach has thus been shown by the observed reliability of the 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":"89575756","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}
Twenty-two gage and 12-gage power conductors were developed using rhodium power wires, magnesium oxide insulation, platinum sheathing, and alumina end-seals. The conductor systems maintained their electrical integrity through a variety of environmental tests, including vibration, mechanical shock, acceleration, humidity, vacuum, and nuclear radiation. The wires were operated successfully at 2000°F. Rated current was determined and assigned as 10 amperes for 22-gage and 60 amperes for 12-gage conductors. The conductors passed the final cyclic test of carrying rated current at room temperature for 2 hours, at high vacuum for 25 hours, and at a reduced pressure at 2000°F for 3 hours.
{"title":"2000°F Power Conductors for Aerospace Applications","authors":"K. Zwilsky, N. Fuschillo, H. Hahn, M. Gimpl","doi":"10.1109/TA.1965.4319814","DOIUrl":"https://doi.org/10.1109/TA.1965.4319814","url":null,"abstract":"Twenty-two gage and 12-gage power conductors were developed using rhodium power wires, magnesium oxide insulation, platinum sheathing, and alumina end-seals. The conductor systems maintained their electrical integrity through a variety of environmental tests, including vibration, mechanical shock, acceleration, humidity, vacuum, and nuclear radiation. The wires were operated successfully at 2000°F. Rated current was determined and assigned as 10 amperes for 22-gage and 60 amperes for 12-gage conductors. The conductors passed the final cyclic test of carrying rated current at room temperature for 2 hours, at high vacuum for 25 hours, and at a reduced pressure at 2000°F for 3 hours.","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":"82042052","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 presents the electrical system used to drive the chilldown motor pumps on the S-IVB space vehicle. This system consists of a 56 volt battery supplying power to the two three-phase solid state inverters which in turn drive two cryogenic motor pumps. Included in this paper is a short description of the overall chilldown system requirements. The advantages of the a-c system over the d-c system are discussed with emphasis on weight and reliability. Two functionally identical 1.5kva inverters were designed. One inverter uses germanium transistors in the output stage while the other uses silicon transistors. Both inverters were designed to have a quasi-square wave output. The inverter circuitry is described and the advantages of each is discussed including a comparison of weight, size, operating temperature, efficiency and voltage rating.
{"title":"Chilldown Electrical System for S-IVB Space Vehicle","authors":"John H. Lanaman, R. J. Morrow, D. Tesdall","doi":"10.1109/TA.1965.4319799","DOIUrl":"https://doi.org/10.1109/TA.1965.4319799","url":null,"abstract":"This paper presents the electrical system used to drive the chilldown motor pumps on the S-IVB space vehicle. This system consists of a 56 volt battery supplying power to the two three-phase solid state inverters which in turn drive two cryogenic motor pumps. Included in this paper is a short description of the overall chilldown system requirements. The advantages of the a-c system over the d-c system are discussed with emphasis on weight and reliability. Two functionally identical 1.5kva inverters were designed. One inverter uses germanium transistors in the output stage while the other uses silicon transistors. Both inverters were designed to have a quasi-square wave output. The inverter circuitry is described and the advantages of each is discussed including a comparison of weight, size, operating temperature, efficiency and voltage rating.","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":"86199063","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}
Low-voltage converter-regulators provide the key to the utilization of new energy conversion power sources in future space applications. It is now possible to use transistor-converters to boost the low voltage level of thermionic, fuel cell, thermoelectric, and electro-chemical sources to a higher more useable regulated voltage. Improved low-voltage converter-regulators have efficiencies between 70 and 90%. This approach will allow the space power system designer to achieve higher reliability with single-cell sources coupled to low-voltage converter-regulators.
{"title":"Reliable Energy Conversion Power Systems for Space Flight","authors":"J. Lingle","doi":"10.1109/TA.1965.4319850","DOIUrl":"https://doi.org/10.1109/TA.1965.4319850","url":null,"abstract":"Low-voltage converter-regulators provide the key to the utilization of new energy conversion power sources in future space applications. It is now possible to use transistor-converters to boost the low voltage level of thermionic, fuel cell, thermoelectric, and electro-chemical sources to a higher more useable regulated voltage. Improved low-voltage converter-regulators have efficiencies between 70 and 90%. This approach will allow the space power system designer to achieve higher reliability with single-cell sources coupled to low-voltage converter-regulators.","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":"77289413","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 provide stage pre-launch thermal environment and to prevent frost formation on the exterior tank surfaces, it was necessary to provide a heated, gaseous nitrogen atmosphere around the stage during cryogenic calibration. Frost formation is undersirable since it would add to the stage tare weight by an unknown amount. Nitrogen conforming to military dryness and cleanliness specifications was chosen for use in contact with the stage skin because of its low moisture content, its inertness with hydrogen or oxygen, its availability, and cost. This paper presents the design concepts of the S-IV and S-IVB stage systems, an appraisal of the S-IV design, and the design changes in the S-IV system as a result of the S-IV experience.
{"title":"Saturn S-IVB Cryogenic Weigh System Part III: Environmental Control","authors":"E. C. Ross","doi":"10.1109/TA.1965.4319797","DOIUrl":"https://doi.org/10.1109/TA.1965.4319797","url":null,"abstract":"In order to provide stage pre-launch thermal environment and to prevent frost formation on the exterior tank surfaces, it was necessary to provide a heated, gaseous nitrogen atmosphere around the stage during cryogenic calibration. Frost formation is undersirable since it would add to the stage tare weight by an unknown amount. Nitrogen conforming to military dryness and cleanliness specifications was chosen for use in contact with the stage skin because of its low moisture content, its inertness with hydrogen or oxygen, its availability, and cost. This paper presents the design concepts of the S-IV and S-IVB stage systems, an appraisal of the S-IV design, and the design changes in the S-IV system as a result of the S-IV experience.","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":"81305956","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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