DOCSLIB.ORG

Bibliography No. 39-3

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text

Load more

~ I t * Bibliography No. 39-3 S L, Kresser R, 1. Sippel OTS PRICE NATIONALAERONAUTICS AND SPACE ADMINISTRATION CONTRACTNo. NAS 7-100 Bibliography No. 39-3 Pw blications of the Jet Propulsion Luborutory July 1961 through June 1962 S. L. Kresser R. J. Sippel Irl E. Newlan, Manager Technical Information Section JET PROPULSION LABORATORY CALIFORNIA INSTITUTE OF TECHNOLOGY PASADENA.CALIFORNIA October 15, 1962 Copyright@ 1962 Jet Propulsion Laboratory California Institute of Technology JPL BIBLIOGRAPHY NO. 39-3 PREFACE JPL Bibliography No. 39-3 is a compilation of official reports of the Jet Propulsion Laboratory released July 1, 1961 through June 30, 1962. Current security classifications are indicated; titles and abstracts given herein are unclassified. Jet Propulsion Laboratory reports may be requested by the entry number or by the report number. When ordering classified reports, the government contract under which the report will be used should be indicated, and requests forwarded to JPL via the cognizant contracting officer for certification of security clearance and “need-to-know.” Copies of unclassified reports are available upon direct request to the Jet Propulsion Laboratory. The Bibliography has been divided as follows: Author Index. Comprising the main portion of the Bibliography, this section is composed of the following types of reports: Technical Reports, Technical Memorandums, and Technical Releases. Summary Publications. Quarterly Summary Reports, Bibliographies, Research and Space Programs Summaries and the Annual Ranger Report are included. Astronautics Information. This series of publications is composed of Abstracts, Open Literature Surveys, Literature Searches, and Translations. Numerical Index. The entry numbers for all reports in the Author Index, Summary Publications, and Astronautics Information sections are included in this index. Subject Index. All reports in the Author Index and Summary Publi- cations sections, as well as Literature Searches and Translations, are indexed. JPL BIBLIOGRAPHY NO. 39-3 CONTENTS Author Index ...................... 1 Summary Publications .................. 53 Astronautics Information .................57 Abstracts ..................... 57 Open Literature Surveys ................58 literature Searches ..................59 Translations .................... 60 Numerical Index ..................... 61 Subject Index ...................... 65 V JPL BIBLIOGRAPHY NO. 39-3 ACORD-APEL AUTHOR INDEX Acord, J. parable uranium carbide-fueled reactors. This assumes, however, that the solid fuel can achieve an average fuel A01 MARINER B CAPSULE PROPULSION STUDY burn-up of 30,OOO Mwd/t, a performance which remains Sehgal, R., Breashears, R., Acord J., Thompson, to be demonstrated for the 2000"Ff fuel-element surface R., Pounder, E., Comunbis, M. temperatures that should characterize such reactors. Technical Memorandum 33-86, June 1, 1962 (Unclassified) Alper, M. E. For abstract, see Entry S20. A04 WEIGHT VS. RELIABILITYA DESIGN CHOICE Alper, M. E. Adamski, D. F. Technical Report 32-1 10, August 18, 1961 (Unclassified) A02 THE LUNAR SEISMOGRAPH EXPERIMENT: RANGER 3, 4, 5 Several aspects of the problem of choosing a design Adamski, D. F. reliability for a subsystem whose weight varies in a de- terminable manner with design reliability are discussed. Technical Report 32-272, June 1, 1962 The choice of design reliability is shown to depend on (Unclassified) the other subsystems which make up the system and on A lunar seismograph experiment was carried aboard the type of program in which the system is used. A Rangers 3,4, and Sthehst spacecraft capable of land- design procedure and philosophy are proposed. ing operating instrument packages on the Moon's surface. The seismometer (seismic transducer) is described, along Ape!, W. C. with its environmental testing, its sterilization, and its integration in a lunar impact capsule. The data processing A05 INSTRUMENTATION REQUIREMENTS FOR THE system used is discussed, as well as the form in which ENGINEERING EVALUATION OF NUCLEAR- data will be presented to the seismologists. ELECTRIC SPACECRAFT Apel, W. C. Allen, L. S. Technical Report 32-160, October 25, 1961 (Unclassified) A03 A PARAMETRIC SURVEY OF CRITICALITY-LIMITED Spacecraft employing nuclear-electric propulsion are FAST REACTORS EMPLOYING URANIUM being proposed for missions to Venus and distances be- FLUORIDE FUELS yond. These spacecraft utilize a nuclear reactor to pro- Allen, 1. 5. vide thermal energy to a turboalternator which generates Technical Report 32-198, March 15, 1962 electric power for an ion motor and the other spacecraft (Unclassified) systems. Multigroup d3Tusion theory calculations are employed This report discusses the instrumentation and commu- to estimate the size and weight of a uranium fluoride- nications system needed to evaluate a nuclear-electric fueled reactor. Beryllium, beryllium oxide, and graphite spacecraft in flight, along with the problems expected. are investigated as possible reflector materials; diluents A representative spacecraft design is presented, which considered for the 93.5%-enriched fuel ,are the fluorides leads to a discussion of the instrumentation dedto of sodium, lithium, beryllium; and zirconium. All survey evaluate such a spacecraft. A basic communications sys- calculations utilize the onedimensional AIM-5 diffusion tem is considered for transmitting the spacecraft data to theory code and employ twelve energy groups. Earth. It is estimated that for spacecraft reactors in the The instrumentation and communications system, as 10-Mw ( th) class, the low fuel density of uranium fluoride well as all electronic systems on a nuclear-electric space- results in reactors which are somewhat larger than com- craft, will be operating in high-temperature and nuclear- 1 JPL BIBLIOGRAPHY NO. 39-3 BANK-BEALE radiation environments. The problems caused by these BO3 A SWEEP-FREQUENCY RADIOMETER FOR TER- environments are discussed, and possible solutions are RESTRIAL AND PLANETARY ATMOSPHERES offered. Barrett, A. H. Technical Memorandum 33-67, July 17, 1961 A06 TEST BED CONFIGURATIONS FOR THE FLIGHT (Unclassified) TESTING OF SNAP-8 POWERED ELECTRIC-PRO- The feasibility and desirability of using microwave PULSION SYSTEMS spectral lines of molecules to study the properties of Beale, R. J., Womack, J. R., Hirrel, P. J., Apel, W. C. planetary atmospheres will increase as the payload and Technical Report 32-190, November 24, 1961 power capabilities for deep-space exploration increase. (Unclassified) Some of the scientific justifications for developing special microwave equipment and the requirements and/or For abstract, see Entry B06. specifications of this equipment are presented. The fun- damental approaches to receiver development which must be explored are also discussed. Bank, H. BO1 APPLICATION OF THE SURVEYOR BUS AS A CEN- Batchelder, R. R. TAUR THIRD STAGE FOR ADVENT BO4 STIFFNESS MATRIX STRUCTURAL ANALYSIS Clarke, V. C., Jr., Eckman, P. K., Gordon, H. J., Batchelder, R. R., Wada, B. K. Bank, H., Blomeyer, 1. S. Technical Memorandum 33-75, February 12, 1962 Technical Memorandum 33-82, February 23, 1962 (Unclassified) (Confidential) Four computer programs are presented for stiffness For abstract, see Entry C12. matrix analysis of structural frameworks, each program representing a different type of framework. The programs will compute the static loads, eigenvectors, eigenvalues, Barrett, A. H. and dynamic stresses of the structure for various load- ings. The programs are coded in FORTRAN language, BO2 OBJECTIVES OF THE MARINER VENUS MICRO- and may be run at any IBM 704-7090 installation with a WAVE RADIOMETER EXPERIMENT system compatible with that at the Jet Propulsion Labor- Barrett, A. H., Copeland, J., Jones, D. E., atory. Since the programs are intended for use as a Lilley, A. E. design tool, particular attention has been given to sim- Technical Report 32-1 56, August 22, 1961 plicity and flexibility of input and output. Discussion of (Unclassified) the matrix equations and their application in analysis is supplemented by stiffness matrices and stresses for vari- At present there are several models involving the sur- ous member types; program input and output are given face, atmosphere (and ionosphere), and cloud conditions and illustrated by a sample problem. of the planet Venus which attempt to account for the observed high brightness temperature of 600" K in the Beale, R. J. microwave temperature region. None of these models can be definitely accepted or rejected on the basis of BO5 SYSTEMS ENGINEERING OF A NUCLEAR-ELECTRIC presently available data, and it is the goal of the micro- SPACECRAFT wave. radiometer experiment planned for the Mariner Beale, R. J. Venus mission to determine which of the proposed Technical Report 32-158, October 31, 1961 models most nearly approximates Venusian conditions. (Unclassified) The disk of the planet will be scanned at four wave- lengths (4,8, 13.5 and 19 mm) to measure the tempera- Studies have shown that nuclear-electric propulsion ture distribution across the planet. Measurement accu- systems will provide superior payload capability and racy is expected to be to within 2%. In addition to the unique advantages over chemical systems for high-energy study of gross thermal characteristics of surface and deep-space missions. atmosphere (or ionosphere), some information regard- Conceptual design studies of unmanned spacecraft ing the fine-scale thermal variations will be obtained. employing nuclear-electric propulsion systems
Recommended publications
  • Nasa Tm X-1864 *

    Nasa Tm X-1864 *

    NASA TECHNICAL. • £HP2fKit NASA TM X-1864 * ... MEMORANDUM oo fe *' > ;ff f- •* '• . ;.*• f PROPULSION • FOR *MANN1D E30PLORATION-k '* *Of THE SOEAE " • » £ Moedkel • - " *' ' ' y Lem$ Research Center Cleveland, Qbt® NATIONAL AERONAUTICS AND SFACE ADMINISTRATION • WASHINGTON, D. €, * AUCUST 1969 NASA TM X-1864 PROPULSION SYSTEMS FOR MANNED EXPLORATION OF THE SOLAR SYSTEM By W. E. Moeckel Lewis Research Center Cleveland, Ohio NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sale by the Clearinghouse for Federal Scientific and. Technical Information Springfield, Virginia 22151 - CFSTI price $3.00 ABSTRACT What propulsion systems are in sight for fast interplanetary travel? Only a few show promise of reducing trip times to values comparable to those of 16th century terrestrial expeditions. The first portion of this report relates planetary round-trip times to the performance parameters of two types of propulsion systems: type I is specific-impulse limited (with high thrust), and type n is specific-mass limited (with low thrust). The second part of the report discusses advanced propulsion concepts of both types and evaluates their limitations. The discussion includes nuclear-fission . rockets (solid, liquid, and gaseous core), nuclear-pulse propulsion, nuclear-electric rockets, and thermonuclear-fusion rockets. Particular attention is given to the last of these, because it is less familiar than the others. A general conclusion is that the more advanced systems, if they prove feasible, will reduce trip time to the near planets by factors of 3 to 5, and will make several outer planets accessible to manned exploration. PROPULSION SYSTEMS FOR MANNED EXPLORATION OF THE SOLAR SYSTEM* byW. E. Moeckel Lewis Research Center SUMMARY What propulsion systems are in sight for fast interplanetary travel? Only a few show promise of reducing trip times to values comparable to those of 16th century terrestrial expeditions.
  • Transport of Dangerous Goods

    Transport of Dangerous Goods

    ST/SG/AC.10/1/Rev.16 (Vol.I) Recommendations on the TRANSPORT OF DANGEROUS GOODS Model Regulations Volume I Sixteenth revised edition UNITED NATIONS New York and Geneva, 2009 NOTE The designations employed and the presentation of the material in this publication do not imply the expression of any opinion whatsoever on the part of the Secretariat of the United Nations concerning the legal status of any country, territory, city or area, or of its authorities, or concerning the delimitation of its frontiers or boundaries. ST/SG/AC.10/1/Rev.16 (Vol.I) Copyright © United Nations, 2009 All rights reserved. No part of this publication may, for sales purposes, be reproduced, stored in a retrieval system or transmitted in any form or by any means, electronic, electrostatic, magnetic tape, mechanical, photocopying or otherwise, without prior permission in writing from the United Nations. UNITED NATIONS Sales No. E.09.VIII.2 ISBN 978-92-1-139136-7 (complete set of two volumes) ISSN 1014-5753 Volumes I and II not to be sold separately FOREWORD The Recommendations on the Transport of Dangerous Goods are addressed to governments and to the international organizations concerned with safety in the transport of dangerous goods. The first version, prepared by the United Nations Economic and Social Council's Committee of Experts on the Transport of Dangerous Goods, was published in 1956 (ST/ECA/43-E/CN.2/170). In response to developments in technology and the changing needs of users, they have been regularly amended and updated at succeeding sessions of the Committee of Experts pursuant to Resolution 645 G (XXIII) of 26 April 1957 of the Economic and Social Council and subsequent resolutions.
  • Pulsed Fusion Space Propulsion: Computational Ideal Magneto-Hydro Dynamics of a Magnetic Flux Compression Reaction Chamber

    Pulsed Fusion Space Propulsion: Computational Ideal Magneto-Hydro Dynamics of a Magnetic Flux Compression Reaction Chamber

    Pulsed Fusion Space Propulsion: Computational Ideal Magneto-Hydro Dynamics of a Magnetic Flux Compression Reaction Chamber G. Romanelli Master of Science Thesis Space Systems Engineering PULSED FUSION SPACE PROPULSION: COMPUTATIONAL IDEAL MAGNETO-HYDRO DYNAMICS OFA MAGNETIC FLUX COMPRESSION REACTION CHAMBER by Gherardo ROMANELLI to obtain the degree of Master of Science at the Delft University of Technology, to be defended publicly on Friday February 26, 2016 at 10:00 AM. Student number: 4299876 Thesis committee: Dr. A. Cervone, TU Delft, supervisor Prof. Dr. E. K. A. Gill, TU Delft Dr. Ir. E. Mooij, TU Delft Prof. A. Mignone, Politecnico di Torino An electronic version of this thesis is available at http://repository.tudelft.nl/. To boldly go where no one has gone before. James T. Kirk ACKNOWLEDGEMENTS First of all I would like to thank my supervisor Dr. A. Cervone who has always sup- ported me despite my “quite exotic” interests. He left me completely autonomous in shaping my thesis project, and still, was always there every time I needed help. Then, I would of course like to thank Prof. A. Mignone who decided to give his contribute to this seemingly crazy project of mine. His advice arrived just in time to give an happy ending to this story. Il ringraziamento più grande, però, va di certo alla mia famiglia. Alla mia mamma e a mio babbo, perché hanno sempre avuto fiducia in me e non hanno mai chiesto ragioni o spiegazioni alle mie scelte. Ai miei nonni, perché se di punto in bianco, un giorno di novembre ho deciso di intraprendere questa lunga strada verso l’Olanda, l’ho potuto fare anche per merito loro.
  • Propulsion Options for the Global Precipitation Measurement Core Satellite

    Propulsion Options for the Global Precipitation Measurement Core Satellite

    PROPULSION OPTIONS FOR THE GLOBAL PRECIPITATION MEASUREMENT CORE SATELLITE Eric H. Cardiff*, Gary T. Davist, and David C. FoltaS NASA Goddard Space Flight Center Greenbelt, MD 2077 1 Abstract This study was conducted to evaluate several propulsion system options for the Global Precipitation Measurement (GPM) core satellite. Orbital simulations showed clear benefits for the scientific data to be obtained at a constant orbital altitude rather than with a decayheboost approach. An orbital analysis estimated the drag force on the satellite will be 1 to 12 mN during the five-year mission. Four electric propulsion systems were identified that are able to compensate for these drag forces and maintain a circular orbit. The four systems were the UK-lO/TS and the NASA 8 cm ion engines, and the ESA RMT and RITlO EVO radio-frequency ion engines. The mass, cost, and power requirements were examined for these four systems. The systems were also evaluated for the transfer time from the initial orbit of 400 x 650 km altitude orbit to a circular 400 km orbit. The transfer times were excessive, and as a consequence a “dual” system concept (with a hydrazine monopropellant system for the orbit transfer and electric propulsion for drag compensation) was examined. Clear mass benefits were obtained with the “dual” system, but cost remains an issue because of the larger power system required for the electric propulsion system. An electrodynamic tether was also evaluated in this trade study. Introduction The propulsion system is required to perform two The Global Precipitation Measurement (GPM) primary functions. The first is to transfer the mission will be launched in late 2008 to measure satellite from the launch insertion orbit to the final the amount and type of precipitation around the circular orbit.
  • Monopropellant System

    Monopropellant System

    ~™ mil ii ii nun mi iiiii iiiii (19) J European Patent Office Office europeen des brevets (11) EP 0 950 648 A1 (12) EUROPEAN PATENT APPLICATION (43) Date of publication:ation: (51) Int. CI.6: C06D 5/08 20.10.1999 Bulletin 1999/42 (21) Application number: 98201190.0 (22) Date of filing: 15.04.1998 (84) Designated Contracting States: (72) Inventors: AT BE CH CY DE DK ES Fl FR GB GR IE IT LI LU • van den Berg, Ronald Peter MC NL PT SE 2291 KJ Wateringen (NL) Designated Extension States: • Mul, Johannes Maria AL LT LV MK RO SI 2013 AE Haarlem (NL) • Elands, Petrus Johannes Maria (71) Applicant: 2804 LK Gouda (NL) NEDERLANDSE ORGANISATIE VOOR TOEGEPAST-NATUURWETENSCHAPPELIJK (74) Representative: ONDERZOEK Smulders, Theodorus A.H.J., Ir. et al TNO Vereenigde Octrooibureaux 2628 VK Delft (NL) Nieuwe Parklaan 97 2587 BN 's-Gravenhage (NL) (54) Monopropellant system (57) The invention is directed to a monopropellant composition for propulsion and/or gas generation, com- prising a solution of hydrazinium nitroformate (HNF) and/or ammonium dinitramide (ADN) in water and/or an alkanol. < CO CO o LO o Q_ LU Printed by Xerox (UK) Business Services 2.16.7/3.6 EP 0 950 648 A1 Description [0001] The present invention is in the area of monopropellant composition systems, for instance for spacecraft pro- pulsion, in emergency systems for jet fighters or in emergency gasgeneration systems for submarines. 5 [0002] Spacecraft propulsion is defined as that needed for the orientation (attitude control) and positioning (orbit con- trol including de-orbiting) of spacecraft after delivery into the required orbit by the launch vehicle.
  • 1 the Merits of Cold Gas Micropropulsion in State-Of

    1 the Merits of Cold Gas Micropropulsion in State-Of

    IAC-02-S.2.07 THE MERITS OF COLD GAS MICROPROPULSION IN STATE-OF-THE-ART SPACE MISSIONS Hugo Nguyen, Johan Köhler and Lars Stenmark The Ångström Space Technology Centre, Uppsala University, Box 534, SE-751 21 Uppsala, Sweden. [email protected] Fax: +46 18 471 3572 Abstract: Cold gas micropropulsion is a sound 1. INTRODUCTION choice for space missions that require extreme For Attitude and Orbit Control System (AOCS) stabilisation, pointing precision or contamination- requirements on extreme stabilisation, pointing free operation. The use of forces in the micronewton precision, contamination-free operation is the range for spacecraft operations has been identified as most important for many missions. Examples a mission-critical item in several demanding space include DARWIN, LISA, SIM, NGST, and those systems currently under development. which have optical or other equipments pointing Cold gas micropropulsion systems share merits with exactly to a certain object or in a certain direction. traditional cold gas systems in being simple in Other obviously desirable properties include design, clean, safe, and robust. They do not generate design simplicity, cleanliness, safety, robustness, net charge to the spacecraft, and typically operate on low-power operation, no net charge generation to low-power. The minute size is suitable not only for the craft, together with low mass, and a wide inclusion on high-performance nanosatellites but dynamic range. Cold gas micropropulsion has also for high-demanding future space missions of those merits and in the present paper, larger sizes. technological solutions will be treated By using differently sized nozzles in parallel emphatically, at the same time the mentioned systems the dynamic range of a cold gas merits will be brought out clearly.
  • Breakthrough Propulsion Study Assessing Interstellar Flight Challenges and Prospects

    Breakthrough Propulsion Study Assessing Interstellar Flight Challenges and Prospects

    Breakthrough Propulsion Study Assessing Interstellar Flight Challenges and Prospects NASA Grant No. NNX17AE81G First Year Report Prepared by: Marc G. Millis, Jeff Greason, Rhonda Stevenson Tau Zero Foundation Business Office: 1053 East Third Avenue Broomfield, CO 80020 Prepared for: NASA Headquarters, Space Technology Mission Directorate (STMD) and NASA Innovative Advanced Concepts (NIAC) Washington, DC 20546 June 2018 Millis 2018 Grant NNX17AE81G_for_CR.docx pg 1 of 69 ABSTRACT Progress toward developing an evaluation process for interstellar propulsion and power options is described. The goal is to contrast the challenges, mission choices, and emerging prospects for propulsion and power, to identify which prospects might be more advantageous and under what circumstances, and to identify which technology details might have greater impacts. Unlike prior studies, the infrastructure expenses and prospects for breakthrough advances are included. This first year's focus is on determining the key questions to enable the analysis. Accordingly, a work breakdown structure to organize the information and associated list of variables is offered. A flow diagram of the basic analysis is presented, as well as more detailed methods to convert the performance measures of disparate propulsion methods into common measures of energy, mass, time, and power. Other methods for equitable comparisons include evaluating the prospects under the same assumptions of payload, mission trajectory, and available energy. Missions are divided into three eras of readiness (precursors, era of infrastructure, and era of breakthroughs) as a first step before proceeding to include comparisons of technology advancement rates. Final evaluation "figures of merit" are offered. Preliminary lists of mission architectures and propulsion prospects are provided.
  • A "Green Cold-Gas" Propulsion System for Cubesats

    A "Green Cold-Gas" Propulsion System for Cubesats

    A "Green Cold-Gas" Propulsion System for Cubesats John Lee1, Adam Huang2 1 Department of Mechanical Engineering, University of Arkansas, [email protected] 2 Department of Mechanical Engineering, University of Arkansas, [email protected] Background – Cubesat Maneuvering Propellant Characterization Thrust Generated • Current Cubesat maneuvering techniques are mainly passive, with little to no • Vaporizing a propellant via nanochannels to vacuum was • Experiments were conducted in a vacuum HD Lifecam ability to change orbits. studied as a means of propulsion for small satellites. chamber that maintained a milliTorr • Specific impulse (Isp) - measure of propellant efficiency • Basic attitude control primarily using Earth’s magnetic field or gravity. Black Out Bell Jar Curtain pressure to simulate space conditions 훾+1 훾푅푇 ∗ ∗ • Very low torque, long time-constant stability (hours), and low accuracy. 푐 훾 2 2 훾−1 푐 = 훾+1 • Various trials were conducted to 퐼푠푝 = where 2 2훾−1 푔 훾 − 1 훾 + 1 훾 • Near-term flights with momentum wheels. Need momentum dumping. 0 훾 + 1 determine properties of vapor phase Light Source • Available technologies aqueous propylene glycol by varying: Test Apparatus • Using Aqueous PG Isp and nanochannel array dimensions • Magnets, Magnetorquers, Momentum wheels (needs dump), Conventional 250μm • Temperature – controlled with a bang- Mass Scale the theoretical thrust was calculated thrusters (solid, fluid thrusters), Gravity gradient, Drag, Electric Thrusters bang thermostat • Thrust is tuned by adjusted the nanochannel dimensions
  • DESIGN and DEVELOPMENT of a 30-Ghz MICROWAVE ELECTROTHERMAL THRUSTER

    DESIGN and DEVELOPMENT of a 30-Ghz MICROWAVE ELECTROTHERMAL THRUSTER

    The Pennsylvania State University The Graduate School College of Engineering DESIGN AND DEVELOPMENT OF A 30-GHz MICROWAVE ELECTROTHERMAL THRUSTER A Thesis in Aerospace Engineering by Erica E. Capalungan ©2011 Erica E. Capalungan Submitted in Partial Fulfillment of the Requirements for the Degree of Master of Science August 2011 The thesis of Erica E. Capalungan was reviewed and approved* by the following: Michael M. Micci Professor of Aerospace Engineering Director of Graduate Studies Thesis Advisor Sven G. Bilén Associate Professor of Engineering Design, Electrical Engineering, and Aerospace Engineering George A. Lesieutre Professor of Aerospace Engineering Head of the Department of Aerospace Engineering *Signatures are on file in the Graduate School. ii ABSTRACT Research has been conducted on the microwave electrothermal thruster at The Pennsylvania State University since the 1980’s. Each subsequent thruster incorporated modifications that resulted in improvements in thruster performance compared to previous generations. Operational frequencies evaluated thus far include 2.45 GHz, 7.5 GHz, 8 GHz, and 14.5 GHz. As each thruster increased in operational frequency, plasmas have been ignited with successively lower amounts of input power. With higher frequency and lower power requirements, the physical sizes of the thruster and the power supply have been reduced. Decreased size results in a lighter propulsion system, which is ideal for space missions. This thesis concerns the design and development of a thruster operating at 30 GHz. Electromagnetic modeling was used in the design of the thruster to determine the optimal input antenna size and length. A 2.4-mm antenna size was chosen with a length that is flush with the bottom of the cavity.
  • Magnetoshell Aerocapture: Advances Toward Concept Feasibility

    Magnetoshell Aerocapture: Advances Toward Concept Feasibility

    Magnetoshell Aerocapture: Advances Toward Concept Feasibility Charles L. Kelly A thesis submitted in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics & Astronautics University of Washington 2018 Committee: Uri Shumlak, Chair Justin Little Program Authorized to Offer Degree: Aeronautics & Astronautics c Copyright 2018 Charles L. Kelly University of Washington Abstract Magnetoshell Aerocapture: Advances Toward Concept Feasibility Charles L. Kelly Chair of the Supervisory Committee: Professor Uri Shumlak Aeronautics & Astronautics Magnetoshell Aerocapture (MAC) is a novel technology that proposes to use drag on a dipole plasma in planetary atmospheres as an orbit insertion technique. It aims to augment the benefits of traditional aerocapture by trapping particles over a much larger area than physical structures can reach. This enables aerocapture at higher altitudes, greatly reducing the heat load and dynamic pressure on spacecraft surfaces. The technology is in its early stages of development, and has yet to demonstrate feasibility in an orbit-representative envi- ronment. The lack of a proof-of-concept stems mainly from the unavailability of large-scale, high-velocity test facilities that can accurately simulate the aerocapture environment. In this thesis, several avenues are identified that can bring MAC closer to a successful demonstration of concept feasibility. A custom orbit code that dynamically couples magnetoshell physics with trajectory prop- agation is developed and benchmarked. The code is used to simulate MAC maneuvers for a 60 ton payload at Mars and a 1 ton payload at Neptune, both proposed NASA mis- sions that are not possible with modern flight-ready technology. In both simulations, MAC successfully completes the maneuver and is shown to produce low dynamic pressures and continuously-variable drag characteristics.
  • IAF Space Propulsion Symposium 2019

    IAF Space Propulsion Symposium 2019

    IAF Space Propulsion Symposium 2019 Held at the 70th International Astronautical Congress (IAC 2019) Washington, DC, USA 21 -25 October 2019 Volume 1 of 2 ISBN: 978-1-7138-1491-7 Printed from e-media with permission by: Curran Associates, Inc. 57 Morehouse Lane Red Hook, NY 12571 Some format issues inherent in the e-media version may also appear in this print version. Copyright© (2019) by International Astronautical Federation All rights reserved. Printed with permission by Curran Associates, Inc. (2020) For permission requests, please contact International Astronautical Federation at the address below. International Astronautical Federation 100 Avenue de Suffren 75015 Paris France Phone: +33 1 45 67 42 60 Fax: +33 1 42 73 21 20 www.iafastro.org Additional copies of this publication are available from: Curran Associates, Inc. 57 Morehouse Lane Red Hook, NY 12571 USA Phone: 845-758-0400 Fax: 845-758-2633 Email: [email protected] Web: www.proceedings.com TABLE OF CONTENTS VOLUME 1 PROPULSION SYSTEM (1) BLUE WHALE 1: A NEW DESIGN APPROACH FOR TURBOPUMPS AND FEED SYSTEM ELEMENTS ON SOUTH KOREAN MICRO LAUNCHERS ............................................................................ 1 Dongyoon Shin KEYNOTE: PROMETHEUS: PRECURSOR OF LOW-COST ROCKET ENGINE ......................................... 2 Jérôme Breteau ASSESSMENT OF MON-25/MMH PROPELLANT SYSTEM FOR DEEP-SPACE ENGINES ...................... 3 Huu Trinh 60 YEARS DLR LAMPOLDSHAUSEN – THE EUROPEAN RESEARCH AND TEST SITE FOR CHEMICAL SPACE PROPULSION SYSTEMS ....................................................................................... 9 Anja Frank, Marius Wilhelm, Stefan Schlechtriem FIRING TESTS OF LE-9 DEVELOPMENT ENGINE FOR H3 LAUNCH VEHICLE ................................... 24 Takenori Maeda, Takashi Tamura, Tadaoki Onga, Teiu Kobayashi, Koichi Okita DEVELOPMENT STATUS OF BOOSTER STAGE LIQUID ROCKET ENGINE OF KSLV-II PROGRAM .......................................................................................................................................................
  • The Development of a Pulsed Plasma Thruster As a Solid Fuel Plasma Source for a High Power Helicon

    The Development of a Pulsed Plasma Thruster As a Solid Fuel Plasma Source for a High Power Helicon

    The Development of a Pulsed Plasma Thruster as a Solid Fuel Plasma Source for a High Power Helicon Ian Kronheim Johnson A thesis submitted in partial fulfillment of the requirements for the degree of Master of Science The University of Washington 2011 Program authorized to offer degree: Aeronautics and Astronautics University of Washington Graduate School This is to certify that I have examined this copy of a master’s thesis by Ian Kronheim Johnson and have found that is it complete and satisfactory in all respects, and that any and all revisions required by the final examining committee have been made. Committee Members: Professor Robert Winglee, Department of Earth and Space Sciences, Chair Professor Tom Jarboe, Department of Aeronautics and Astronautics Date: The University of Washington ii In presenting this thesis in partial fulfillment of the requirements for a master’s degree at the University of Washington, I agree that the Library shall make its copies freely available for inspection. I further agree that extensive copying of this thesis is allowable only for scholarly purposes, consistent with “fair use” as prescribed in the U.S. Copyright Law. Any other reproduction for any purposes or by any means shall not be allowed without my written permission. Signature: Date: The University of Washington iii University of Washington Abstract The Development of a Pulsed Plasma Thruster as a Solid Fuel Plasma Source for a High Power Helicon Ian Kronheim Johnson Chair of the Supervisory Committee: Professor Robert Winglee Earth and Space Sciences As space exploration shifts to lower mass and lower cost missions, the need for improved on-board propulsion systems is growing.