1 Price, E. W., "Charge Geometry and Ballistic Parameters for Solid Propellant Rocket Motor s / ' J E T PROPULSION, vol. 24, Jan.-Feb. 1954, p. 16. 2 Vogel, J. M., "A Quasi-Morphological Approach to the Geometry of Charges for Solid Propellant Rockets: The Family Tree of Charge Designs," J E T PROPULSION, vol. 26, Feb. 1956, p. 102. 3 Epstein, L. I., "The Design of Cylindrical Propellant Grains," JET PROPULSION, vol. 26, Sept. 1956, p. 757. 4, 5 These graphs, though unclassified, appear in classified reports. Copies may be obtained from the author. 6 Wimpress, R. N., "Internal Ballistics of Solid-Fuel Rockets ," McGraw-Hill, New York, 1950. 7 "Rocket Fundamentals ," OSRD 3992.
1 Price, E. W.，“固体推进剂火箭发动机装药几何和弹道参数”[J] . E. T . PROPULSION, vol. 24, 1 - 2。1954，第16页。2 Vogel, J. M.，“固体推进剂火箭装药几何的准形态学方法:装药设计的家族树”，《电子推进》，第26卷，1956年2月，第102页。3 Epstein, L. I.，“圆柱形推进剂颗粒的设计”，《喷气推进》，第26卷，1956年9月，第757页。这些图表虽然不是机密的，但出现在机密报告中。可向作者索取副本。6 Wimpress, R. N.，“固体燃料火箭的内部弹道”，纽约麦格劳-希尔，1950年。7“火箭基础”，OSRD 3992。
{"title":"Design, Fabrication and Testing of the Vanguard Satellite","authors":"R. Baumann","doi":"10.2514/8.7286","DOIUrl":"https://doi.org/10.2514/8.7286","url":null,"abstract":"1 Price, E. W., \"Charge Geometry and Ballistic Parameters for Solid Propellant Rocket Motor s / ' J E T PROPULSION, vol. 24, Jan.-Feb. 1954, p. 16. 2 Vogel, J. M., \"A Quasi-Morphological Approach to the Geometry of Charges for Solid Propellant Rockets: The Family Tree of Charge Designs,\" J E T PROPULSION, vol. 26, Feb. 1956, p. 102. 3 Epstein, L. I., \"The Design of Cylindrical Propellant Grains,\" JET PROPULSION, vol. 26, Sept. 1956, p. 757. 4, 5 These graphs, though unclassified, appear in classified reports. Copies may be obtained from the author. 6 Wimpress, R. N., \"Internal Ballistics of Solid-Fuel Rockets ,\" McGraw-Hill, New York, 1950. 7 \"Rocket Fundamentals ,\" OSRD 3992.","PeriodicalId":304231,"journal":{"name":"Journal of Jet Propulsion","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129271558","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}
Equations were developed relating solid propellant grain geometry to the important ballistic parameters of crosssectional loading density, sliver or tail-off fraction, progressivity ratio, initial surface and web. The equations were then solved by means of high speed computers and the results graphed in a readily usable form. If the loading fraction, sliver, progressivity ratio and web are given, grain designs which meet or most nearly meet given requirements can be found from the graphs. The graphs are useful in determining the effect of slight variations in design parameters. Illustrations of the use of the graphs are given for the internal-burning star and the internal-burning wagon wheel configurations. Calculations have also been made on a modified form of the wagon wheel which permits one, two or three levels of thrust during burning.
{"title":"A Practical Mathematical Approach to Grain Design","authors":"M. Stone","doi":"10.2514/8.7285","DOIUrl":"https://doi.org/10.2514/8.7285","url":null,"abstract":"Equations were developed relating solid propellant grain geometry to the important ballistic parameters of crosssectional loading density, sliver or tail-off fraction, progressivity ratio, initial surface and web. The equations were then solved by means of high speed computers and the results graphed in a readily usable form. If the loading fraction, sliver, progressivity ratio and web are given, grain designs which meet or most nearly meet given requirements can be found from the graphs. The graphs are useful in determining the effect of slight variations in design parameters. Illustrations of the use of the graphs are given for the internal-burning star and the internal-burning wagon wheel configurations. Calculations have also been made on a modified form of the wagon wheel which permits one, two or three levels of thrust during burning.","PeriodicalId":304231,"journal":{"name":"Journal of Jet Propulsion","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125845833","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 instrument for the measurement of flame temperatures from 1500 to 2700 deg C by the sodium-line reversal method is described in which the eye and hand of a trained operator are replaced by a closed-loop electromechanical system. The advantages are in continuous recording of varying flame temperatures, increased accuracy, and measurement on flames that would be dangerous to an observer. (auth)
{"title":"A RECORDING SODIUM-LINE REVERSAL PYROMETER","authors":"W. M. Brobeck, R. E. Clemensen, W. E. Voreck","doi":"10.2514/8.7287","DOIUrl":"https://doi.org/10.2514/8.7287","url":null,"abstract":"An instrument for the measurement of flame temperatures from 1500 to 2700 deg C by the sodium-line reversal method is described in which the eye and hand of a trained operator are replaced by a closed-loop electromechanical system. The advantages are in continuous recording of varying flame temperatures, increased accuracy, and measurement on flames that would be dangerous to an observer. (auth)","PeriodicalId":304231,"journal":{"name":"Journal of Jet Propulsion","volume":"223 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133309839","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}
{"title":"Influence of Pressure on the Combustion of Liquid Spheres","authors":"G. Agoston","doi":"10.2514/8.7266","DOIUrl":"https://doi.org/10.2514/8.7266","url":null,"abstract":"","PeriodicalId":304231,"journal":{"name":"Journal of Jet Propulsion","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128975255","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}
{"title":"Escape From a Circular Orbit Using Tangential Thrust","authors":"D. J. Benney","doi":"10.2514/8.7261","DOIUrl":"https://doi.org/10.2514/8.7261","url":null,"abstract":"","PeriodicalId":304231,"journal":{"name":"Journal of Jet Propulsion","volume":"41 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122670275","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}
{"title":"Heat Transfer in Laminar Pipe Flow With Uniform Coolant Injection","authors":"S. W. Yuan, A. Finkelstein","doi":"10.2514/8.7264","DOIUrl":"https://doi.org/10.2514/8.7264","url":null,"abstract":"","PeriodicalId":304231,"journal":{"name":"Journal of Jet Propulsion","volume":"38 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125926804","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}
Examinat ion of Figs. 3(a) and 3(b) reveals, as is to be expected, t ha t the choice of area ratio has little effect on missile performance when the nozzle weight is a very small port ion of the burnout weight. The importance of correct choice of area ratio increases as the nozzle weight becomes more significant. Nozzle weights, in conventional practice, seldom become large enough in relation to the rest of the inert weight to invalidate the approximation made in Equa t ion [7]. The gains in velocity increment realized by correct choice of area ratio are usually only a few per cent, which m a y be impor tan t in some applications. In other cases, nozzle design m a y still be dictated by structural , cooling, etc., requirements. 2490
{"title":"An Analysis of Fuel-Oxidant Mixing in Screaming Combustors","authors":"W. Mickelsen","doi":"10.2514/8.7263","DOIUrl":"https://doi.org/10.2514/8.7263","url":null,"abstract":"Examinat ion of Figs. 3(a) and 3(b) reveals, as is to be expected, t ha t the choice of area ratio has little effect on missile performance when the nozzle weight is a very small port ion of the burnout weight. The importance of correct choice of area ratio increases as the nozzle weight becomes more significant. Nozzle weights, in conventional practice, seldom become large enough in relation to the rest of the inert weight to invalidate the approximation made in Equa t ion [7]. The gains in velocity increment realized by correct choice of area ratio are usually only a few per cent, which m a y be impor tan t in some applications. In other cases, nozzle design m a y still be dictated by structural , cooling, etc., requirements. 2490","PeriodicalId":304231,"journal":{"name":"Journal of Jet Propulsion","volume":"54 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131068672","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}
{"title":"Some Effects of Oxidizer Concentration and Particle Size on Resonance Burning of Composite Solid Propellants","authors":"L. Green","doi":"10.2514/8.7259","DOIUrl":"https://doi.org/10.2514/8.7259","url":null,"abstract":"","PeriodicalId":304231,"journal":{"name":"Journal of Jet Propulsion","volume":"258 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114941262","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 author studied engineering _ science at Harvard University ^ t f t f f lH^ where he received an A.B. in 1946 J ^ B I ^ ^ J L and a Ph.D. in 1949. His thesis flB V | was on an experimental measureI p l l llfcll ment of vibrational relaxation ISfl l ^iTW times in gases. In 1950 he joined ^ ' * 8 U H Wr the shock wave laboratory of the ^ n H E ' ^^i^mi^tJt Physics Department at Princeton ^SK^SJ^L I I L Z ^ ^ 1 ^ University where he continued his l l l l ^ j l H H k ^ research on physical problems in ' l l L ^ ^ • I H H B L gas dynamics. In 1951 he was ^ B « . / | ^ ^ H | | | H u appointed assistant professor of physics; later, associate professor. The subjects on which he has worked extensively include transonic flow, thermal boundary layers, shock structure, chemical kinetics, diffraction of blast waves, and supersonic flow. As one of the editors of the Journal of Fluid Mechanics, he has an intimate and up-to-date knowledge of the problem on which he writes. Dr. Griffith is currently manager of the Flight Sciences Division in the Missile Systems Division of Lockheed Aircraft Corp.
作者在哈佛大学学习工程科学，1946年获得学士学位，1949年获得博士学位。他的论文flB V |是关于气体中振动弛豫ISfl ^iTW次的实验测量。1950年，他加入了普林斯顿大学物理系的冲击波实验室，在那里他继续他的L L L L L L L气体动力学的物理问题的研究。1951年，他被评为“B”。/ | ^ ^ H | | H被任命为物理学助理教授;后来，成为副教授。他广泛研究的课题包括跨音速流动、热边界层、激波结构、化学动力学、冲击波衍射和超音速流动。作为《流体力学杂志》的编辑之一，他对他所写的问题有着深入的、最新的了解。Griffith博士目前是洛克希德飞机公司导弹系统部飞行科学部的经理。
{"title":"Recent Advances in Real Gas Effects in Hypersonic Flow","authors":"W. Griffith","doi":"10.2514/8.7258","DOIUrl":"https://doi.org/10.2514/8.7258","url":null,"abstract":"The author studied engineering _ science at Harvard University ^ t f t f f lH^ where he received an A.B. in 1946 J ^ B I ^ ^ J L and a Ph.D. in 1949. His thesis flB V | was on an experimental measureI p l l llfcll ment of vibrational relaxation ISfl l ^iTW times in gases. In 1950 he joined ^ ' * 8 U H Wr the shock wave laboratory of the ^ n H E ' ^^i^mi^tJt Physics Department at Princeton ^SK^SJ^L I I L Z ^ ^ 1 ^ University where he continued his l l l l ^ j l H H k ^ research on physical problems in ' l l L ^ ^ • I H H B L gas dynamics. In 1951 he was ^ B « . / | ^ ^ H | | | H u appointed assistant professor of physics; later, associate professor. The subjects on which he has worked extensively include transonic flow, thermal boundary layers, shock structure, chemical kinetics, diffraction of blast waves, and supersonic flow. As one of the editors of the Journal of Fluid Mechanics, he has an intimate and up-to-date knowledge of the problem on which he writes. Dr. Griffith is currently manager of the Flight Sciences Division in the Missile Systems Division of Lockheed Aircraft Corp.","PeriodicalId":304231,"journal":{"name":"Journal of Jet Propulsion","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1958-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124967195","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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