The increased blast area associated with the 120-inch solid rocket motors used on the Titan IIIC required locating the launch control center three and one half miles from the nearest launch complex. To transmit data over this distance, a data transmission system (DTS) with a transmission capability in excess of five miles was developed. The Titan IIIC DTS uses discrete, digital, and analog signals to monitor and control checkout and launch operations.
{"title":"Titan IIIC Ground Checkout Data Transmission System","authors":"James P. Janis","doi":"10.1109/TA.1965.4319831","DOIUrl":"https://doi.org/10.1109/TA.1965.4319831","url":null,"abstract":"The increased blast area associated with the 120-inch solid rocket motors used on the Titan IIIC required locating the launch control center three and one half miles from the nearest launch complex. To transmit data over this distance, a data transmission system (DTS) with a transmission capability in excess of five miles was developed. The Titan IIIC DTS uses discrete, digital, and analog signals to monitor and control checkout and launch operations.","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":"80813542","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 covers work on established reliability for power relays by the National Association of Relay Manufacturers and an Air Force appointed committee working cooperatively with SAE Subcommittee A-2R. A practical means of specifying established reliability for power relays using MIL-R-6106 as a basic specification is proposed. Life cycles from qualification, acceptance and requalification tests are combined to establish a reliability of 1% per 10,000 cycles. The authors also cover principles and procedures for the design and manufacture of established reliability power relays.
{"title":"Specification and Design of Established Reliability Power Relays","authors":"JohnA . Quaal, James E. Davies","doi":"10.1109/TA.1965.4319857","DOIUrl":"https://doi.org/10.1109/TA.1965.4319857","url":null,"abstract":"This paper covers work on established reliability for power relays by the National Association of Relay Manufacturers and an Air Force appointed committee working cooperatively with SAE Subcommittee A-2R. A practical means of specifying established reliability for power relays using MIL-R-6106 as a basic specification is proposed. Life cycles from qualification, acceptance and requalification tests are combined to establish a reliability of 1% per 10,000 cycles. The authors also cover principles and procedures for the design and manufacture of established reliability power relays.","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":"81177855","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 results of a study of secondary power generating systems for a twelve-man logistic spacecraft are presented for orbital space flights of 24 hours and launch dates during the post 1968 time period. Power systems are evaluated on the basis of performance, weight, radiator area and availability. The secondary power systems considered were fuel cells, batteries, Stirling engines, internal combustion engines and turbines. The power generating systems are evaluated for a nominal 1-1/2 kwe continuous load during orbital space flight to establish the various system trends. The peak power requirement for aerodynamic control was established at 14 kwe during entry.
{"title":"Secondary Power Generating System for a Manned Logistic Spacecraft","authors":"C. Shinbrot","doi":"10.1109/TA.1965.4319854","DOIUrl":"https://doi.org/10.1109/TA.1965.4319854","url":null,"abstract":"The results of a study of secondary power generating systems for a twelve-man logistic spacecraft are presented for orbital space flights of 24 hours and launch dates during the post 1968 time period. Power systems are evaluated on the basis of performance, weight, radiator area and availability. The secondary power systems considered were fuel cells, batteries, Stirling engines, internal combustion engines and turbines. The power generating systems are evaluated for a nominal 1-1/2 kwe continuous load during orbital space flight to establish the various system trends. The peak power requirement for aerodynamic control was established at 14 kwe during entry.","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":"89189430","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 tutorial paper develops equations and techniques useful for designing narrow deviation phase modulated signals containing information-bearing subcarriers and a binary ranging code. Sufficient information is presented to allow a reader, who has access to a digital computer, to design these types of signals. A sample signal design is presented for clarification.
{"title":"Synthesis Techniques for a Class of Phase-Modulated Signals","authors":"J. Painter","doi":"10.1109/TA.1965.4319811","DOIUrl":"https://doi.org/10.1109/TA.1965.4319811","url":null,"abstract":"This tutorial paper develops equations and techniques useful for designing narrow deviation phase modulated signals containing information-bearing subcarriers and a binary ranging code. Sufficient information is presented to allow a reader, who has access to a digital computer, to design these types of signals. A sample signal design is presented for clarification.","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":"84890404","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}
Product reliability, costs, and schedules have been improved on some programs by the use of digital computers to process and print wiring and equipment lists. This paper describes a project completed this year for the U.S. Navy Bureau of Weapons by North American Aviation, Inc, Los Angeles Division which (1) extended the listings produced, (2), added the automatic production of pictorial wiring diagrams, and (3) prepared a proposed Military Standard - "Automatic Processing of Wiring Data and Diagrams." Evaluation is made of computer data processing and future growth potential is presented.
{"title":"A Proposed Military Standard \"Automatically Processed Wiring Data and Diagrams\"","authors":"F. Glenn Fielding","doi":"10.1109/TA.1965.4319856","DOIUrl":"https://doi.org/10.1109/TA.1965.4319856","url":null,"abstract":"Product reliability, costs, and schedules have been improved on some programs by the use of digital computers to process and print wiring and equipment lists. This paper describes a project completed this year for the U.S. Navy Bureau of Weapons by North American Aviation, Inc, Los Angeles Division which (1) extended the listings produced, (2), added the automatic production of pictorial wiring diagrams, and (3) prepared a proposed Military Standard - \"Automatic Processing of Wiring Data and Diagrams.\" Evaluation is made of computer data processing and future growth potential is presented.","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":"83591942","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 the first part of the optimization process, the width and depth of the rotor tooth are incrementally varied for two airgap radial lengths and two field excitations. In the second part the tooth shape that would yield a sinusoidal voltage is investigated. The numerical results are represented by curves for the no-load radial flux density in a 95 KVA, 120/208 v 3,400 cps alternator. The results show that the fundamental airgap flux density depends on the length of the airgap and on the rotor tooth width. It depends only slightly on the rotor tooth depth and excitation. A more sinusoidal output voltage can be obtained by flaring the tips of the rotor tooth and widening the rotor tooth.
{"title":"Optimization of Rotor Tooth Shape of Aerospace Homopolar Alternators","authors":"R. E. Hopkins, E. Erdelyi","doi":"10.1109/TA.1965.4319775","DOIUrl":"https://doi.org/10.1109/TA.1965.4319775","url":null,"abstract":"In the first part of the optimization process, the width and depth of the rotor tooth are incrementally varied for two airgap radial lengths and two field excitations. In the second part the tooth shape that would yield a sinusoidal voltage is investigated. The numerical results are represented by curves for the no-load radial flux density in a 95 KVA, 120/208 v 3,400 cps alternator. The results show that the fundamental airgap flux density depends on the length of the airgap and on the rotor tooth width. It depends only slightly on the rotor tooth depth and excitation. A more sinusoidal output voltage can be obtained by flaring the tips of the rotor tooth and widening the rotor tooth.","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":"80609109","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 study was designed to determine whether specific control/display association stereotypes exist in the population when controls and their corresponding displays are arranged sequentially on a two dimensional surface. The null hypothesis was tested under three control/display configuration conditions by means of a paper and pencil test administered to 70 male college students. Results showed that a reliable correspondence between the location of the display stimulus and the control response exists in orthogonal, rectangular and alternate arrangements of controls and displays.
{"title":"Control/Display Association Stereotypes in Grouped Panel Arrangements","authors":"Michael V. Fiore","doi":"10.1109/TA.1965.4319818","DOIUrl":"https://doi.org/10.1109/TA.1965.4319818","url":null,"abstract":"This study was designed to determine whether specific control/display association stereotypes exist in the population when controls and their corresponding displays are arranged sequentially on a two dimensional surface. The null hypothesis was tested under three control/display configuration conditions by means of a paper and pencil test administered to 70 male college students. Results showed that a reliable correspondence between the location of the display stimulus and the control response exists in orthogonal, rectangular and alternate arrangements of controls and displays.","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":"84208399","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 an advanced thermal-insulation and structural-support concept developed at Battelle Memorial Institute. A unique, high-temperature, lightweight, metallic structure of relatively high strength is described, which is particularly suited for aerospace applications in which environmental extremes render conventional insulations inadequate. The parameters of the device, a multiple web and foil structure, are explained in detail and related to strength and insulation criteria. The relations developed are sufficiently general to allow custom designing of these two property requirements.
{"title":"A New Thermal-Insulation and Support Concept for Extreme Environments","authors":"J. Ketchman, R. J. Burian","doi":"10.1109/TA.1965.4319859","DOIUrl":"https://doi.org/10.1109/TA.1965.4319859","url":null,"abstract":"This paper presents an advanced thermal-insulation and structural-support concept developed at Battelle Memorial Institute. A unique, high-temperature, lightweight, metallic structure of relatively high strength is described, which is particularly suited for aerospace applications in which environmental extremes render conventional insulations inadequate. The parameters of the device, a multiple web and foil structure, are explained in detail and related to strength and insulation criteria. The relations developed are sufficiently general to allow custom designing of these two property requirements.","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":"77319565","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 equilibrium temperature of a solar cell panel in space is a function of the ratio of solar absorptance to infrared emittance of the surface. This paper describes a method for reducing solar absorptance by constructing the solar cell so that it will be a reflector in the infrared part of the solar spectrum. Spectral transmittance, spectral reflectance, and spectral absorptance of silicon wafers and N/P and P/N solar cells are presented. A N/P cell equipped with a silver coating on the back surface and a 0.400 micron cutoff cover glass on the front was found to have solar absorptance of 0.66 which is 11 percent less than that of a standard N/P cell equipped with a similar cover glass.
{"title":"Infrared Reflecting Solar Cells","authors":"R. Tallent","doi":"10.1109/TA.1965.4319784","DOIUrl":"https://doi.org/10.1109/TA.1965.4319784","url":null,"abstract":"The equilibrium temperature of a solar cell panel in space is a function of the ratio of solar absorptance to infrared emittance of the surface. This paper describes a method for reducing solar absorptance by constructing the solar cell so that it will be a reflector in the infrared part of the solar spectrum. Spectral transmittance, spectral reflectance, and spectral absorptance of silicon wafers and N/P and P/N solar cells are presented. A N/P cell equipped with a silver coating on the back surface and a 0.400 micron cutoff cover glass on the front was found to have solar absorptance of 0.66 which is 11 percent less than that of a standard N/P cell equipped with a similar cover glass.","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":"88538148","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 reports on an investigation of techniques concerned with development of efficient and lightweight power conversion units for use with space power systems currently being developed. Results of the investigation provide an insight into the best system approach for supplying high frequency power. The effort was accomplished as part of Contract AF33(657)-11049 for the Research and Technology Division of Air Force Systems Command with Captain Harold L. Briggs as the Project Officer. Specifically, the conversion units analyzed are for supplying high-frequency (50 to 800KC), high-voltage power to accelerate plasma in an electric propulsion engine. Various conversion and power generation techniques are reviewed. Conceptual designs are established for conversion of 60 KW and 300 KW of power from a basic nuclear turbine system. A high frequency alternator is compared with a low frequency alternator using a frequency converter. A number of high frequency alternators are compared. Also, three frequency converter approaches are evaluated and compared; namely, a motor-generator unit, a transistor unit and a vacuum tube unit. The alternate system approaches are compared. Significant design data was derived for a high-speed, solid-rotor type of generator for generating a c power with frequencies up to 200 KC. Parametric data is included to show component sizes, weights and losses for converter units and high-frequency generator concepts. Problem areas for each conversion and generation technique are outlined.
本文报告了一项有关开发用于目前正在开发的空间动力系统的高效和轻便的功率转换单元的技术的调查。研究结果为提供高频电源的最佳系统方法提供了见解。这项工作是空军系统司令部研究与技术部AF33(657)-11049合同的一部分，由Harold L. Briggs上尉担任项目官员。具体来说，所分析的转换单元用于提供高频(50至800KC)高压功率，以加速电力推进发动机中的等离子体。介绍了各种转换和发电技术。从一个基本的核涡轮系统转换60千瓦和300千瓦的功率，建立了概念设计。使用变频器将高频交流发电机与低频交流发电机进行比较。对几种高频交流发电机进行了比较。同时，对三种变频方法进行了评价和比较;即，一个电机发电机单元，一个晶体管单元和一个真空管单元。对不同的系统方法进行了比较。为产生频率高达200kc的c功率的高速、固体转子型发电机导出了重要的设计数据。参数数据包括转换器单元和高频发电机概念的组件尺寸、重量和损耗。概述了每种转换和生成技术的问题区域。
{"title":"Investigation of High-Frequency Power Conversion and Generator Techniques","authors":"J. Pierro, J. Phillips","doi":"10.1109/TA.1965.4319830","DOIUrl":"https://doi.org/10.1109/TA.1965.4319830","url":null,"abstract":"This paper reports on an investigation of techniques concerned with development of efficient and lightweight power conversion units for use with space power systems currently being developed. Results of the investigation provide an insight into the best system approach for supplying high frequency power. The effort was accomplished as part of Contract AF33(657)-11049 for the Research and Technology Division of Air Force Systems Command with Captain Harold L. Briggs as the Project Officer. Specifically, the conversion units analyzed are for supplying high-frequency (50 to 800KC), high-voltage power to accelerate plasma in an electric propulsion engine. Various conversion and power generation techniques are reviewed. Conceptual designs are established for conversion of 60 KW and 300 KW of power from a basic nuclear turbine system. A high frequency alternator is compared with a low frequency alternator using a frequency converter. A number of high frequency alternators are compared. Also, three frequency converter approaches are evaluated and compared; namely, a motor-generator unit, a transistor unit and a vacuum tube unit. The alternate system approaches are compared. Significant design data was derived for a high-speed, solid-rotor type of generator for generating a c power with frequencies up to 200 KC. Parametric data is included to show component sizes, weights and losses for converter units and high-frequency generator concepts. Problem areas for each conversion and generation technique are outlined.","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":"83832209","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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