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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. -
Arxiv:2002.12686V1 [Physics.Pop-Ph] 28 Feb 2020 SOI Sphere of Influence VEV Variable Ejection Velocity
Achieving the required mobility in the solar system through Direct Fusion Drive Giancarlo Genta1 and Roman Ya. Kezerashvili2;3;4, 1Department of Mechanical and Aerospace Engineering, Politecnico di Torino, Turin, Italy 2Physics Department, New York City College of Technology, The City University of New York, Brooklyn, NY, USA 3The Graduate School and University Center, The City University of New York, New York, NY, USA 4Samara National Research University, Samara, Russian Federation (Dated: March 2, 2020) To develop a spacefaring civilization, humankind must develop technologies which enable safe, affordable and repeatable mobility through the solar system. One such technology is nuclear fusion propulsion which is at present under study mostly as a breakthrough toward the first interstellar probes. The aim of the present paper is to show that fusion drive is even more important in human planetary exploration and constitutes the natural solution to the problem of exploring and colonizing the solar system. Nomenclature Is specific impulse m mass mi initial mass ml mass of payload mp mass of propellant ms structural mass mt mass of the thruster mtank mass of tanks t time td departure time ve ejection velocity F thrust J cost function P power of the jet α specific mass of the generator γ optimization parameter ∆V velocity increment DFD Direct Fusion Drive IMLEO Initial Mass in Low Earth Orbit LEO Low Earth Orbit LMO Low Mars Orbit NEP Nuclear Electric Propulsion NTP Nuclear Thermal Propulsion SEP Solar Electric Propulsion arXiv:2002.12686v1 [physics.pop-ph] 28 Feb 2020 SOI Sphere of Influence VEV Variable Ejection Velocity I. -
The Space to Lead
Washington University in St. Louis Washington University Open Scholarship All Theses and Dissertations (ETDs) Summer 8-1-2013 The pS ace to Lead Mack A. Bradley Washington University in St. Louis Follow this and additional works at: https://openscholarship.wustl.edu/etd Part of the International Relations Commons Recommended Citation Bradley, Mack A., "The pS ace to Lead" (2013). All Theses and Dissertations (ETDs). 1172. https://openscholarship.wustl.edu/etd/1172 This Thesis is brought to you for free and open access by Washington University Open Scholarship. It has been accepted for inclusion in All Theses and Dissertations (ETDs) by an authorized administrator of Washington University Open Scholarship. For more information, please contact [email protected]. WASHINGTON$UNIVERSITY$IN$ST.$LOUIS University$College InternaSonal$Affairs The$Space$to$Lead by Mack$A.$Bradley A$thesis$presented$to the of$Washington$University$in$ partial$fulfillment$of$the$ requirements$for$the$degree$of$ Master$of$Arts August$2013 St.$Louis,$Missouri i © 2013$MACK$A.$BRADLEY ii TABLE$OF$CONTENTS Acknowledgements iii Dedication v Abstract vi Chapter 1: Leading from Behind p.1 Chapter 2: Shuttle, Station, and International Space p. 8 Chapter 3: We Need Our Space p. 23 Chapter 4: Economy of Space p. 30 Chapter 5: Space for Sale or Lease p. 38 Chapter 6: Space Security p. 49 Chapter 7: Houston, We Have Problems p. 56 America in search of a mission p. 57 Russia’s launch program needs a boost p. 72 Trouble in the debris belt p. 74 Living in a dangerous neighborhood p. 78 Chapter 8: Conclusions and Recommendations p. -
DIRECT FUSION DRIVE for Interstellar Exploration S.A
Journal of the British Interplanetary Society VOLUME 72 NO.2 FEBRUARY 2019 General interstellar issue DIRECT FUSION DRIVE for Interstellar Exploration S.A. Cohen et al. INTERMEDIATE BEAMERS FOR STARSHOT: Probes to the Sun’s Inner Gravity Focus James Benford & Gregory Matloff REALITY, THE BREAKTHROUGH INITIATIVES and Prospects for Colonization of Space Edd Wheeler A GRAVITATIONAL WAVE TRANSMITTER A.A. Jackson and Gregory Benford CORRESPONDENCE www.bis-space.com ISSN 0007-084X PUBLICATION DATE: 29 APRIL 2019 Submitting papers International Advisory Board to JBIS JBIS welcomes the submission of technical Rachel Armstrong, Newcastle University, UK papers for publication dealing with technical Peter Bainum, Howard University, USA reviews, research, technology and engineering in astronautics and related fields. Stephen Baxter, Science & Science Fiction Writer, UK James Benford, Microwave Sciences, California, USA Text should be: James Biggs, The University of Strathclyde, UK ■ As concise as the content allows – typically 5,000 to 6,000 words. Shorter papers (Technical Notes) Anu Bowman, Foundation for Enterprise Development, California, USA will also be considered; longer papers will only Gerald Cleaver, Baylor University, USA be considered in exceptional circumstances – for Charles Cockell, University of Edinburgh, UK example, in the case of a major subject review. Ian A. Crawford, Birkbeck College London, UK ■ Source references should be inserted in the text in square brackets – [1] – and then listed at the Adam Crowl, Icarus Interstellar, Australia end of the paper. Eric W. Davis, Institute for Advanced Studies at Austin, USA ■ Illustration references should be cited in Kathryn Denning, York University, Toronto, Canada numerical order in the text; those not cited in the Martyn Fogg, Probability Research Group, UK text risk omission. -
Nuclear Fusion–Propelled Missions to Mars
the tube, it puts a million amps of current down the the U.S. government are committed to building the fa- tube. These were always unstable when you tried to do cilities necessary to do this quickly. So, building the that, but they’ve got the idea that if you just put a little facilities that you need, and building them quickly, and twist on the pinch as you make it, it won’t go unstable, having the money to do that makes a total difference in or at least it won’t go unstable very fast. And maybe the schedule. I still have no doubt that if we got that you can get enough fusion out of that. money, we could be doing this in 15-20 years. That’s an extremely simple idea, but if it works, and There’s also a management issue. Right now in the you can keep it stable for a long enough time with that U.S., the fusion program is being funded as a science geometry, it’s extremely simple. One of the things elec- program. That’s like when we decided to go to the tric utilities are looking for are technologies that aren’t Moon, astrophysics was a science program. But you so complicated that they’ve never used before, that had to build up a whole infrastructure and management they’ve got to figure out how to make them work on a commitment to go to the Moon. So, what we’d have to very reliable basis to make electricity for months and get in addition to the money, would be a management years on end without having to do a lot of maintenance. -
Fusion Rocket Engines for Planetary Defense
J Fusion Energ (2016) 35:123–133 DOI 10.1007/s10894-015-0034-1 ORIGINAL RESEARCH A New Vision for Fusion Energy Research: Fusion Rocket Engines for Planetary Defense 1 1 2 3 3 G. A. Wurden • T. E. Weber • P. J. Turchi • P. B. Parks • T. E. Evans • 4 5 6 S. A. Cohen • J. T. Cassibry • E. M. Campbell Published online: 16 November 2015 Ó The Author(s) 2015. This article is published with open access at Springerlink.com Abstract We argue that it is essential for the fusion comes to discussing future energy production. Is there energy program to identify an imagination-capturing crit- another, more urgent, unique, and even more important ical mission by developing a unique product which could application for fusion? command the marketplace. We lay out the logic that this product is a fusion rocket engine, to enable a rapid response capable of deflecting an incoming comet, to prevent its impact on the planet Earth, in defense of our population, infrastructure, and civilization. As a side ben- Fusion’s Unique Application efit, deep space solar system exploration, with greater speed and orders-of-magnitude greater payload mass would As an on-board power source and thruster for fast propul- also be possible. sion in space [4], a fusion reactor would provide unparal- leled performance (high specific impulse and high specific Keywords Fusion research Á Fusion rocket engine Á power) for a spacecraft. To begin this discussion, we need Comet deflection Á Planetary defense Á Nuclear explosive some rocket terminology. Specific impulse is defined as Isp ¼ ve=g, where g is the usual Earth’s gravitational The US Department of Energy’s magnetic fusion research acceleration constant and ve is the rocket propellant’s program, based in its Office of Science, focuses on plasma exhaust velocity. -
Fusions-Enabled Pluto Orbiter and Lander
Princeton Satellite Systems Fusion-Enabled Pluto Orbiter and Lander Phase I Final Report Award Title: Fusion-Enabled Pluto Orbiter and Lander Report Type: Phase I Final Report Principal Investigator: Ms. Stephanie Thomas Period of Performance: May 13, 2016 through May 12, 2017 Institution: Princeton Satellite Systems, Inc. 6 Market St. Suite 926 Plainsboro, NJ 08536 Award Number: NNX16AK28G 1 Princeton Satellite Systems Fusion-Enabled Pluto Orbiter and Lander Phase I Final Report Executive Summary The Pluto orbiter mission proposed here is credible and exciting. The benefits to this and all outer-planet and interstellar-probe missions are difficult to overstate. The enabling technology, Direct Fusion Drive, is a unique fusion engine concept based on the Princeton Field-Reversed Configuration (PFRC) fusion reactor under development at the Princeton Plasma Physics Laboratory. The truly game-changing levels of thrust and power in a modestly sized package could integrate with our current launch infrastructure while radically expanding the science capability of these missions. During this Phase I effort, we made great strides in modeling the engine efficiency, thrust, and specific impulse and analyzing feasible trajectories. Based on 2D fluid modeling of the fusion reactor’s outer stratum, its scrape-off-layer (SOL), we estimate achieving 2.5 to 5 N of thrust for each megawatt of fusion power, reaching a specific impulse, Isp, of about 10,000 s. Supporting this model are particle-in-cell calculations of energy transfer from the fusion products to the SOL electrons. Subsequently, this energy is transferred to the ions as they expand through the magnetic nozzle and beyond. -
Direct Fusion Drive for the Gravitational Lens Mission
PrincetonFUSION SYSTEMS Direct Fusion Drive For the Gravitational Lens Mission Artist’s rendering of DFD concept PFRC-2 in operation at PPPL Outline DFD background Deep space SGL mission DFD/PFRC research update PrincetonFUSION 2 SYSTEMS 6/24/19 PRINCETON FIELD REVERSED CONFIGURATION (PFRC) PrincetonFUSION 3 SYSTEMS 6/24/19 PFRC Technology is Simple, Small, and Clean Field Shaping RF Heating Ø Simple Coils Fuel Antenna Mirror Coil - Linear array of magnetic coils Ø Small D-3He Fusion - FRC: Field-Reversed Configuration, a compact toroid - Size limited to 1-10 MW Coolant Ø Clean Exhaust Cool Plasma Energy Absorbed Heat and Ash Extraction - Very feW damaging particles generated PFRC Schematic - No radioactive or hazardous fuels required Result: cheaper and faster to develop than other fusion concepts Electrolysis D2O Auxiliary Power O2 - Fusion poWer has only been generated in large Unit Startup Tokamaks (PPPL TFTR, JET) RF Generator Coil Radiator Refrigerator Gas - Large machines are expensive to develop and only D Box Plasma HTS Coil Blanket useful for large centralized poWer plants, ex. ITER Coil Cooling 3He Space Thermal Conversion PFRC is based on plasma heating experiments neutrons Bremsstrahlung Generator Synchotron Brayton taking place at Princeton Plasma Physics Lab Shielding Coolant Radiator Heat Engine - PFRC-1, complete, PFRC-2, noW operating Space version subsystems PFRC = Princeton Field-Reversed Configuration PrincetonFUSION 4 SYSTEMS 6/24/19 Dual-Use Technology: PFRC becomes Direct Fusion Drive Field Shaping RF Heating -
Journal of Space Law
JOURNAL OF SPACE LAW VOLUME 22, NUMBERS 1 & 2 1994 JOURNAL OF SPACE LAW A journal devoted to the legal problems arising out of human activities in outer space VOLUME 22 1994 NUMBERS I &2 EDITORIAL BOARD AND ADVISORS BERGER, HAROLD GALLOWAY, Ell.ENE Philadelphia, Pennsylvania Washington, D.C. B6CKSTlEGEL, KARL-HEINZ GOEDHUIS, D. Cologne, Germany London, England, BOUREr.. Y, MICHEL G. HE,QIZHI Luzille par Blere, France Beijing, China COCCA, ALDO ARMANDO JASENTULIYANA, NANDASIRI Buenes Aires, Argentina Vienna, Austria DEMBLING, PAUL G. KOPAL, VLADIMIR Washington, D. C. Prague, Czechoslovakia DlEDERIKS-VERSCHOOR, I.H. PH. MCDOUGAL, MYRES S. Baarn, Holland New Haven, Connecticut FASAN, ERNST VERESHCHETIN, V.s. Neunkirchen, Austria Moscow, U.S.S.R. FINCH, EDWARD R., JR. ZANOTTI, ISIDORO New York, N.Y. Washington, D.C. STEPHEN GOROVE, Chainnan University, Mississippi All correspondance should be directed to the JOURNAL OF SPACE LAW, P.O. Box 308, University, Mississippi 38677. Tel. 601-234-2391. Fax: 601-232-7010. The subscription rate for 1994 is $74.45 (doinestic) and $79.95· (foreign) for two isSues combined. Single issues for other years may be ordered at $40 per issue (postage and handling included). Copyright © JOURNAL OF SPACE LAW 1994 Suggested abbreviation: J. SPACE L. JOURNAL OF SPACE LAW A journal devoted to the legal problems arising out of human activities in outer space VOLUME 22 1994 NUMBERS 1 &2 CONTENTS Announcement iv Judge Manfred Lachs: An Obituary (I.H.Ph. Diederiks-Verschoor) 1 ARTICLES Regulation of Space Salvage Operations: Possibilities for the Future (N. Jasenruliyana) 5 The International Telecommunication Union and Development Francis Lyall) 23 Judge Manfred Lachs and the Principle of Jus Cog/ms (Carl Q. -
Papers of Wernher Von Braun
Wernher Von Braun A Register of His Papers in the Library of Congress Prepared by Allan J. Teichroew Manuscript Division, Library of Congress Washington, D.C. 1978 Contact information: http://lcweb.loc.gov/rr/mss/address.html Text converted and initial EAD tagging provided by Apex Data Services, 1999 January; encoding completed by Manuscript Division, 1999 2004-12-06 converted from EAD 1.0 to EAD 2002 Collection Summary Title: Papers of Wernher Von Braun Span Dates: 1796-1970 Bulk Dates: (bulk 1950-1970) ID No.: MSS44172 Creator: Von Braun, Wernher, 1912-1977 Extent: 20,000 items; 56 containers plus 5 oversize; 22.8 linear feet Language: Collection material in English and German Repository: Manuscript Division, Library of Congress, Washington, D.C. Abstract: German aerospace engineer. Correspondence, fan mail, speeches and writings, public relations material, subject files, scrapbooks, and printed material. The papers relate to Wernher Von Braun's career in rocketry and aerospace engineering from his early work on the V-2 rocket in Germany to his work for the United States Department of Defense, the Redstone Arsenal, and the National Aeronautics and Space Administration George C. Marshall Space Flight Center in Huntsville, Ala. Selected Search Terms The following terms have been used to index the description of this collection in the Library's online catalog. They are grouped by name of person or organization, by subject or location, and by occupation and listed alphabetically therein. Names: Von Braun, Wernher, 1912-1977 Bechtle, Otto Wolfgang--Correspondence Brucker, Wilber Marion, 1894-1968--Correspondence Durant, Frederick C., 1916- --Correspondence Gartmann, Heinz, 1917- --Correspondence Gerhards, Jupps--Correspondence Grosse, Aristid von, 1905- --Correspondence Kölle, Heinz Hermann, 1917- --Correspondence Ley, Willy, 1906-1969--Correspondence Loeser, G.--Correspondence Medaris, John B. -
MITTEILUNGEN 5/2008 Deutsche Gesellschaft Für Luft- Und Raumfahrt – Lilienthal-Oberth E.V
... ...Mitteilungen... ...Mitteilungen... ...Mitteilun MITTEILUNGEN 5/2008 Deutsche Gesellschaft für Luft- und Raumfahrt – Lilienthal-Oberth e.V. Sehr geehrte Mitglieder, die Sommerpause und damit die ruhige und Prandtl-Ring erstmals nach 1996 an einen zogen wird. Für das Vortragsprogramm hat erholsame Phase des Jahres ist vorbei, und Wissenschaftler aus dem Außereuro- diese Änderung so gut wie keine man kann schon fast von einem Endspurt päischen Raum verliehen. Professor Dr. Auswirkungen. Durch die nicht mehr inte- für das Jahr 2008 sprechen. Für die DGLR Yuri Semyonovich Kachanov von dem grierte Mitgliederversammlung (gesonderte steht der Höhepunkt des Jahres allerdings Institute of Theoretical and Applied Einladung für die Mitgliederversammlung noch vor der Tür, der Deutsche Luft- und Mechanics (ITAM) der Rusischen Akade- entnehmen Sie bitte der Beilage) wird der Raumfahrtkongress in Darmstadt. mie der Wissenschaften in Novosibirsk, nicht mehr für Fachvorträge zur Verfügung Wie jedes Jahr wird die höchste Aus- Russland, ist der zu Ehrende für 2008. stehende Dienstagvormittag fast gänzlich zeichnung der DGLR, der Ludwig- Wichtig für alle treuen Besucher des kompensiert. Auch das Rahmenprogramm Prandtl-Ring, während der feierlichen Er- Kongresses ist, dass die Eröffnung nicht am ist von der Änderung nicht betroffen. öffnungsveranstaltung überreicht. Montag, sondern erst am Dienstag stattfin- Ich würde mich freuen, Sie möglichst zahl- Im Darmstadtium, der neuen Kongresshal- det und damit die schon seit längerem ange- reich in Darmstadt -
Arxiv:2009.12633V1 [Physics.Space-Ph] 26 Sep 2020
Exploration of trans-Neptunian objects using the Direct Fusion Drive Paolo Aimea,b, Marco Gajeria,b, Roman Ya. Kezerashvilib,c,d aPolitecnico di Torino, Torino, Italy bNew York City College of Technology, The City University of New York, New York, USA cThe Graduate School and University Center, The City University of New York, New York, USA dSamara National Research University, Samara, Russian Federation Abstract The Direct Fusion Drive (DFD) is a nuclear fusion engine that will provide thrust and electrical power for any spacecraft. It is a compact engine, based on the D -3He aneutronic fusion reaction that uses the Princeton field reversed configuration for the plasma confinement and an odd parity rotating magnetic field as heating method to achieve nuclear fusion (Cohen et al., 2019), which will heat the deuterium, also used as propellant. In this work we present possibilities to explore the solar system outer border using the DFD. The objective is to reach some trans-Neptunian object, such as the dwarf planets Makemake, Eris and Haumea in less than 10 years with a payload mass of at least of 1500 kg, so that it would enable all kind of missions, from scientific observation to in-situ operations. For each mission a thrust-coast-thrust profile is considered. For this reason, each mission is divided into 3 phases: i. the spiral trajectory to escape Earth gravity; ii. the interplanetary travel, from the exit of Earth sphere of influence to the end of the coasting phase; iii. maneuvers to rendezvous with the dwarf planet. Propellant mass consumption, initial and final masses, velocities and ∆V for each maneuver are presented.