DOCSLIB.ORG

Plasma and Nuclear Propulsion

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Plasma and Nuclear Propulsion Plasma and Nuclear Propulsion 1 Thrust and Specific Impulse • Thrust is defined as the force generated by an engine or rocket • For rockets Fthrust = ce*dm; dm = fuel mass flow rate • Specific Impulse measures the efficiency of a rocket engine (not a physical quanFty). • It is effecFvely equal to the thrust divided by the amount of fuel used per unit Fme. • It is measured by a quanFty called Isp = ce/g 2 Types of Electric Propulsion 1. Electrothermal – uses electricity to heat a neutral gas examples: arcjet 2. Electrosta/c – uses a stac electric field to accelerate a plasma. Stac magneFc field are someFmes used to help confine the plasma, but they are not used for acceleraon. examples: gridded ion thruster 3. Electromagne/c – uses electric and magneFc fields to accelerate a plasma. examples: hall thruster, pulsed plasma thruster 3 Electrothermal: Arcjet How they work: 1. Neutral gas flows through the propellant flow. 2. An electrical arc forms between the anode and cathode. 3. A small amount of the neutral gas is ionized to form the arc. 4. The remaining gas is heated as it passes through the arc. Propellant: Hydrazine Ammonia Exhaust speed: 4-10 km/s Thrust range: 200-1000 mN* Power required: 400 W – 3 kW Efficiency: 30-50% * 1 mN is about the weight of a sheet of paper. 4 Electrostac: Gridded Ion Thruster Electrostac: Gridded Ion Thruster Vital Stats: Propellant: Argon, Krypton, Xenon Exhaust speed: 15-50 km/s Thrust range: 0.01-200 mN* Power 1-10 kW required: Efficiency: 60-80% * 1 mN is about the weight of a sheet of paper. Advantages: Disadvantages: Uses: 1. High exhaust speed 1. Complex power processing 1. Staon keeping 2. High efficiency 2. Low thrust 2. Orbital change 3. Inert propellant 3. Grid and cathode lifeFme LEO to GEO issues 3. Primary propulsion 4. High voltages 5. Thrust density is limited 6 Electrostac: Gridded Ion Thruster Gridded Ion Thrusters have been flown as the primary propulsion of several satellites: Deep Space 1 (NASA; Braille, Borrelly) Dawn (NASA; Ceres & Vesta) Hayabusa (jAXA; sample from Itokawa) Deep Space 1’s NSTAR Thruster: 1. Exhaust speed 35 km/s 2. Used 74 kg of Xenon fuel 3. Low thrust (92 mN) over a long Fme (678 days) 4. Δv due to thruster (4.3 km/s) DAWN’s Ion Engine: 1. Exhaust speed 31 km/s 2. Low thrust (90 mN) over a long Fme (longer than DS1) 3. Larger Δv than DS1 7 ElectromagneFc: Pulsed Plasma Thruster (PPT) How they work: 1. Arc ablates material off the Teflon surface. a. Material is ionzied b. Current flows through the arc. 2. Current generates a magneFc field. 3. MagneFc field and current interact to accelerate the plasma. Propellant: Solid Teflon Exhaust speed: 6 - 20 km/s Thrust range: 0.05 - 10 mN* Power required: 5 -500 W Efficiency: 10% * 1 mN is about the weight of a sheet of paper. 8 ElectromagneFc: Pulsed Plasma Thruster (PPT) Advantages: 1. Simple design 2. Low power 3. Solid fuel a. No propellant tanks/plumbing b. No zero-g effects on propellant Disadvantages: 1. Low thrust 2. Low efficiency 3. Toxic products Uses (flown in space): Staon keeping Precision poinFng 9 ElectromagneFc: Hall Thruster How they work: 1. Cathode releases electrons which ionize propellant. 2. Electrons from ionizaon move in a circular paern (create current). 3. Current interacts with radial magneFc field to produce ion acceleraon. 4. Cathode electrons neutralize the beam. Propellant: Xenon or Argon Exhaust speed: 15 - 20 km/s Thrust range: 0.01 - 2000 mN* Power required: 1 W - 200 kW Efficiency: 30-50% * 1 mN is about the weight of a sheet of paper. 10 ElectromagneFc: Hall Thruster Advantages: 1. High exhaust velocity 2. Simple power supply 3. Inert propellant 4. High efficiency 5. Desirable exhaust velocity Disadvantages: 1. High beam divergence 2. Lifeme issues (erosion) Uses (flown in space): Staon keeping Orbital transfer (LEO to GEO) Primary Propulsion (SMART-1) 11 Variable Specific Impulse Magnetoplasma Rocket (VASIMR) How it works (VX-200): 1. Helicon ionizes neutral gas (30 kW). 2. Plasma flows along field lines and is compressed. 3. Ion Cyclotron Resonance Heang (ICRH) is used to heat the ions (170 kW). 4. MagneFc nozzle converts temperature into directed flow. 5. Plasma detaches from the magneFc field. VASIMR Advantages: 1. Variable exhaust speed 2. High exhaust speed 3. Variable thrust 4. High thruster 5. No grids or anode/cathode 6. Variety of fuels (H, Ar, Ne) Disadvantages: 1. SuperconducFng magnets required 2. PotenFal detachment issues 3. PotenFal energy conversion issues 4. Requires nuclear reactor EP Summary Types of EP: Electrothermal: resistojet, arcjet Electrosta/c: gridded ion thruster Electromagne/c: Hall thruster, PPT, MPD thruster, VASIMR Advantages: High exhaust velocity High propellant efficiency High spacecra speeds Disadvantages: Power intensive Very low thrust (in space only) Acceleraon takes Fme PotenFal lifeFme issues 14 Nuclear Propulsion 15 Radioisotope Thermal Generator (RTG): How they work: AddiFonal informaon: • RadioacFve decay (oqen 238Pu) • 10s-100s of Was • Heat generated in decay • 3-7% efficient • Thermocouples convert heat to • Well suited to deep space roboFc electricity missions • US has Flown 45 RTGs in 25 missions • Voyager 1& 2 • Cassini (870 W - shown leq) • Galileo (570 W) • Viking 1 & 2 • Pioneer • Ulysses RadioacFve Heater Units: • 1 Wa of heat power • Used to keep spacecra warm • US has flown more than 240 RTGs have a good service history, but are still controversial. 16 Nuclear Propulsion Now we’re really geng into the border of science ficFon. However, real research is being done or has been done to seriously invesFgate several nuclear propulsion concepts. Types of nuclear propulsion: 1. Nuclear pulse propulsion – uses nuclear explosions to propel a spacecra 2. Nuclear thermal propulsion – uses the heat of a nuclear reactor to heat a gas which is expelled for thrust 3. Nuclear electric propulsion – uses electrical power from a nuclear reactor to power an electric thruster 17 Nuclear Pulse Propulsion Also called external pulsed plasma propulsion. Uses nuclear explosions to generate thrust. Programs: 1. Project Orion (1958 – 1963) 2. Project Daedalus (1973 – 1978) 3. Project Longshot (1987-1988) 18 Project Orion Study by General Atomics led by Ted Taylor and Freeman Dyson Goal: High thrust with high exhaust speeds How it works: 1. Drop nuclear bomb out the back of the spacecra 2. Nuclear bomb detonates about 60 m behind the spacecra 3. Explosion hits a steel plate, which propels the spacecra forward. Note: shock absorber is required for human payload due to the high g involved. 19 Project Orion Performance: EsFmated thrust > 1 mega-newton EsFmated exhaust velocity: 20 – 30,000 km/s EsFmated spacecra speed: 0.03c – 0.1c (c = speed of light) PotenFal Missions: Fast travel through solar system with massive payloads Single stage to Mars Saturn’s moons jupiter’s moons PotenFal Problems: Asteroid deflecFon Plate ablaon/damage Interstellar travel Nuclear fallout on Earth High acceleraon rate Project Orion was terminated by the Crew shielding ParFal Test Ban Treaty of 1963. 20 Orion 21 Commercializing Human Space Flight New Commercial Space • NASA COTS/CRS • Space Tourism – Orbital Sciences – Bigelow Aerospace – SpaceX – Space Adventures • NASA CCDev Partners – Virgin GalacFc – Blue Origin – XCor – Boeing – Paragon – Sierra Nevada – United Launch Alliance Falcon 1/1e: • 2 stages: LOX-Kerosene • 670 kg (1010 kg) to LEO • Achieved orbit: Sept., 28, 2008 • 2/5 successes • $10.9 M Falcon 9: • 2 stages: LOX-Kerosene • 10,450 kg to LEO • 4,540 kg to GTO • Dragon Capability • Maiden Flight: june 4, 2010 Placed test payload in orbit • Cost: $45.8 – $55.1 M • Flight 2: Tuesday, Dec 7, 2010 – First Dragon test flight – First private company to return a capsule from orbit. • Next launch with docking to ISS soon (5/19?) .
Load more

Recommended publications
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • Deuterium – Tritium Pulse Propulsion with Hydrogen As Propellant and the Entire Space-Craft As a Gigavolt Capacitor for Ignition
    Deuterium – Tritium pulse propulsion with hydrogen as propellant and the entire space-craft as a gigavolt capacitor for ignition. By F. Winterberg University of Nevada, Reno Abstract A deuterium-tritium (DT) nuclear pulse propulsion concept for fast interplanetary transport is proposed utilizing almost all the energy for thrust and without the need for a large radiator: 1. By letting the thermonuclear micro-explosion take place in the center of a liquid hydrogen sphere with the radius of the sphere large enough to slow down and absorb the neutrons of the DT fusion reaction, heating the hydrogen to a fully ionized plasma at a temperature of ~ 105 K. 2. By using the entire spacecraft as a magnetically insulated gigavolt capacitor, igniting the DT micro-explosion with an intense GeV ion beam discharging the gigavolt capacitor, possible if the space craft has the topology of a torus. 1. Introduction The idea to use the 80% of the neutron energy released in the DT fusion reaction for nuclear micro-bomb rocket propulsion, by surrounding the micro-explosion with a thick layer of liquid hydrogen heated up to 105 K thereby becoming part of the exhaust, was first proposed by the author in 1971 [1]. Unlike the Orion pusher plate concept, the fire ball of the fully ionized hydrogen plasma can here be reflected by a magnetic mirror. The 80% of the energy released into 14MeV neutrons cannot be reflected by a magnetic mirror for thermonuclear micro-bomb propulsion. This was the reason why for the Project Daedalus interstellar probe study of the British Interplanetary Society [2], the neutron poor deuterium-helium 3 (DHe3) reaction was chosen.
    [Show full text]
  • 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.
    [Show full text]
  • Cave-73-02-Fullr.Pdf
    EDITORIAL Production Changes for Future Publication of the Journal of Cave and Karst Studies SCOTT ENGEL Production Editor The Journal of Cave and Karst Studies has experienced December 2011 issue, printed copies of the Journal will be budget shortfalls for the last several years for a multitude automatically distributed to paid subscribers, institutions, of reasons that include, but are not limited to, increased and only those NSS members with active Life and cost of paper, increased costs of shipping through the Sustaining level memberships. The remainder of the NSS United State Postal Service, increased submissions, and membership will be able to view the Journal electronically stagnant funding from the National Speleological Society online but will not automatically receive a printed copy. Full (NSS). The cost to produce the Journal has increased 5 to content of each issue of the Journal will be available for 20 percent per year for the last five years, yet the budget for viewing and downloading in PDF format at no cost from the the Journal has remained unchanged. To offset rising costs, Journal website www.caves.org/pub/journal. the Journal has implemented numerous changes over recent Anyone wishing to receive a printed copy of the Journal years to streamline the production and printing process. will be able to subscribe for an additional cost separate However, the increasing production costs, combined with from normal NSS dues. The cost and subscription process the increasing rate of good-quality submissions, has were still being determined at the time of this printing. resulted in the number of accepted manuscripts by the Once determined, the subscription information will be Journal growing faster than the acquisition of funding to posted on the Journal website.
    [Show full text]
  • Performance of the NASA 30 Cm Ion Thruster
    https://ntrs.nasa.gov/search.jsp?R=19940020297 2020-06-16T16:39:35+00:00Z /-^- E-S^L^ NASA Technical Memorandum 106426 IEPC-93-108 Performance of the NASA 30 cm Ion Thruster Michael J. Patterson and Thomas W. Haag Lewis Research Center Cleveland, Ohio and Scot A. Hovan University of Dayton Dayton, Ohio Prepared for the 23rd International Electric Propulsion Conference cosponsored by the AIAA, AIDAA, DGLR, and BASS Seattle, Washington, September 13-16, 1993 NASA IEPC-93-108 Performance of the NASA 30 cm Ion Thruster Michael J. Patterson' and Thomas W. Haag' National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio Scot A. Hovan Department of Mechanical Engineering University of Dayton Dayton, Ohio A 30 cm diameter xenon ion thruster is under development at NASA to provide an ion propulsion option for missions of national interest, and is being proposed for use on the USAF/TRW Space Surveillance, Tracking and Autonomous Repositioning (SSTAR) platform to validate ion propulsion. The thruster incorporates innovations in design, materials, and fabrication techniques compared to those employed in conventional ion thrusters. Specific development efforts include thruster design optimizations, component life testing and validation, vibration testing, and performance characterizations. Under this test program, the ion thruster will be brought to engineering model development status. This paper discusses the performance and power throttling test data for the NASA 30 cm diameter xenon ion thruster over an input power envelope
    [Show full text]
  • Space Propulsion.Pdf
    Deep Space Propulsion K.F. Long Deep Space Propulsion A Roadmap to Interstellar Flight K.F. Long Bsc, Msc, CPhys Vice President (Europe), Icarus Interstellar Fellow British Interplanetary Society Berkshire, UK ISBN 978-1-4614-0606-8 e-ISBN 978-1-4614-0607-5 DOI 10.1007/978-1-4614-0607-5 Springer New York Dordrecht Heidelberg London Library of Congress Control Number: 2011937235 # Springer Science+Business Media, LLC 2012 All rights reserved. This work may not be translated or copied in whole or in part without the written permission of the publisher (Springer Science+Business Media, LLC, 233 Spring Street, New York, NY 10013, USA), except for brief excerpts in connection with reviews or scholarly analysis. Use in connection with any form of information storage and retrieval, electronic adaptation, computer software, or by similar or dissimilar methodology now known or hereafter developed is forbidden. The use in this publication of trade names, trademarks, service marks, and similar terms, even if they are not identified as such, is not to be taken as an expression of opinion as to whether or not they are subject to proprietary rights. Printed on acid-free paper Springer is part of Springer Science+Business Media (www.springer.com) This book is dedicated to three people who have had the biggest influence on my life. My wife Gemma Long for your continued love and companionship; my mentor Jonathan Brooks for your guidance and wisdom; my hero Sir Arthur C. Clarke for your inspirational vision – for Rama, 2001, and the books you leave behind. Foreword We live in a time of troubles.
    [Show full text]
  • A New Vision for Fusion Energy Research: Fusion Rocket Engines for Planetary Defense Abstract We Argue That It Is Essential Fo
    LA-UR-15-23198 A New Vision for Fusion Energy Research: Fusion Rocket Engines for Planetary Defense G. A. Wurden1, T. E. Weber1, P. J. Turchi2, P. B. Parks3, T. E. Evans3, S. A. Cohen4, J. T. Cassibry5, E. M. Campbell6 1Los Alamos National Laboratory 2Santa Fe, NM 3General Atomics 4Princeton Plasma Physics Laboratory 5University of Alabama, Huntsville 6Sandia National Laboratory Abstract We argue that it is essential for the fusion energy program to identify an imagination- capturing critical mission by developing a unique product which could 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 benefit, deep space solar system exploration, with greater speed and orders-of-magnitude greater payload mass would also be possible. The US Department of Energy’s magnetic fusion research program, based in its Office of Science, focuses on plasma and fusion science1 to support the long term goal of environmentally friendly, socially acceptable, and economically viable electricity production from fusion reactors.2 For several decades the US magnetic fusion program has had to deal with a lack of urgency towards and inconsistent funding for this ambitious goal. In many American circles, fusion isn’t even at the table3 when it comes to discussing future energy production. Is there another, more urgent, unique, and even more important application for fusion? Fusion’s unique application As an on-board power source and thruster for fast propulsion in space,4 a fusion reactor would provide unparalleled performance (high specific impulse and high specific power) for a spacecraft.
    [Show full text]
  • Fast Transit: Mars & Beyond
    Fast Transit: mars & beyond final Report Space Studies Program 2019 Team Project Final Report Fast Transit: mars & beyond final Report Internationali l Space Universityi i Space Studies Program 2019 © International Space University. All Rights Reserved. i International Space University Fast Transit: Mars & Beyond Cover images of Mars, Earth, and Moon courtesy of NASA. Spacecraft render designed and produced using CAD. While all care has been taken in the preparation of this report, ISU does not take any responsibility for the accuracy of its content. The 2019 Space Studies Program of the International Space University was hosted by the International Space University, Strasbourg, France. Electronic copies of the Final Report and the Executive Summary can be downloaded from the ISU Library website at http://isulibrary.isunet.edu/ International Space University Strasbourg Central Campus Parc d’Innovation 1 rue Jean-Dominique Cassini 67400 Illkirch-Graffenstaden France Tel +33 (0)3 88 65 54 30 Fax +33 (0)3 88 65 54 47 e-mail: [email protected] website: www.isunet.edu ii Space Studies Program 2019 ACKNOWLEDGEMENTS Our Team Project (TP) has been an international, interdisciplinary and intercultural journey which would not have been possible without the following people: Geoff Steeves, our chair, and Jaroslaw “JJ” Jaworski, our associate chair, provided guidance and motivation throughout our TP and helped us maintain our sanity. Øystein Borgersen and Pablo Melendres Claros, our teaching associates, worked hard with us through many long days and late nights. Our staff editors: on-site editor Ryan Clement, remote editor Merryl Azriel, and graphics editor Andrée-Anne Parent, helped us better communicate our ideas.
    [Show full text]
  • Hyperspace  NASA BPP Program  Books 8
    Advanced Space Propulsion Concepts for Interstellar Travel Gregory V. Meholic [email protected] Planets HR 8799 140 LY 11/14/08 Updated 9/25/2019 1 Presentation Objectives and Caveats ▪ Provide a high-level, “evolutionary”, information-only overview of various propulsion technology concepts that, with sufficient development (i.e. $), may lead mankind to the stars. ▪ Only candidate concepts for a vehicle’s primary interstellar propulsion system will be discussed. No attitude control No earth-to-orbit launch No traditional electric systems No sail-based systems No beamed energy ▪ None of the following will be given, assumed or implied: Recommendations on specific mission designs Developmental timelines or cost estimates ▪ Not all propulsion options will be discussed – that would be impossible! 2 Chapters 1. The Ultimate Space Mission 2. The Solar System and Beyond 3. Challenges of Human Star Flight 4. “Rocket Science” Basics 5. Conventional Mass Ejection Propulsion Systems State-of-the-Art Possible Improvements 6. Alternative Mass Ejection Systems Nuclear Fission Nuclear Fusion Matter/Antimatter Other Concepts 7. Physics-Based Concepts Definitions and Things to Remember Space-Time Warp Drives Fundamental Force Coupling Alternate Dimension / Hyperspace NASA BPP Program Books 8. Closing Information 3 Chapter 1: The Ultimate Space Mission 4 The Ultimate Space Mission For humans to travel to the stars and return to Earth within a “reasonable fraction” (around 15 years) of a human lifetime. ▪ Why venture beyond our Solar System? Because we have to - humans love to explore!!! Visit the Kuiper Belt and the Oort Cloud – Theoretical home to long-period comets Investigate the nature of the interstellar medium and its influence on the solar system (and vice versa) – Magnetic fields, low-energy galactic cosmic rays, composition, etc.
    [Show full text]