Electric Propulsion
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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. -
An Assessment of Aerocapture and Applications to Future Missions
Post-Exit Atmospheric Flight Cruise Approach An Assessment of Aerocapture and Applications to Future Missions February 13, 2016 National Aeronautics and Space Administration An Assessment of Aerocapture Jet Propulsion Laboratory California Institute of Technology Pasadena, California and Applications to Future Missions Jet Propulsion Laboratory, California Institute of Technology for Planetary Science Division Science Mission Directorate NASA Work Performed under the Planetary Science Program Support Task ©2016. All rights reserved. D-97058 February 13, 2016 Authors Thomas R. Spilker, Independent Consultant Mark Hofstadter Chester S. Borden, JPL/Caltech Jessie M. Kawata Mark Adler, JPL/Caltech Damon Landau Michelle M. Munk, LaRC Daniel T. Lyons Richard W. Powell, LaRC Kim R. Reh Robert D. Braun, GIT Randii R. Wessen Patricia M. Beauchamp, JPL/Caltech NASA Ames Research Center James A. Cutts, JPL/Caltech Parul Agrawal Paul F. Wercinski, ARC Helen H. Hwang and the A-Team Paul F. Wercinski NASA Langley Research Center F. McNeil Cheatwood A-Team Study Participants Jeffrey A. Herath Jet Propulsion Laboratory, Caltech Michelle M. Munk Mark Adler Richard W. Powell Nitin Arora Johnson Space Center Patricia M. Beauchamp Ronald R. Sostaric Chester S. Borden Independent Consultant James A. Cutts Thomas R. Spilker Gregory L. Davis Georgia Institute of Technology John O. Elliott Prof. Robert D. Braun – External Reviewer Jefferey L. Hall Engineering and Science Directorate JPL D-97058 Foreword Aerocapture has been proposed for several missions over the last couple of decades, and the technologies have matured over time. This study was initiated because the NASA Planetary Science Division (PSD) had not revisited Aerocapture technologies for about a decade and with the upcoming study to send a mission to Uranus/Neptune initiated by the PSD we needed to determine the status of the technologies and assess their readiness for such a mission. -
Gravity-Assist Trajectories to Jupiter Using Nuclear Electric Propulsion
AAS 05-398 Gravity-Assist Trajectories to Jupiter Using Nuclear Electric Propulsion ∗ ϒ Daniel W. Parcher ∗∗ and Jon A. Sims ϒϒ This paper examines optimal low-thrust gravity-assist trajectories to Jupiter using nuclear electric propulsion. Three different Venus-Earth Gravity Assist (VEGA) types are presented and compared to other gravity-assist trajectories using combinations of Earth, Venus, and Mars. Families of solutions for a given gravity-assist combination are differentiated by the approximate transfer resonance or number of heliocentric revolutions between flybys and by the flyby types. Trajectories that minimize initial injection energy by using low resonance transfers or additional heliocentric revolutions on the first leg of the trajectory offer the most delivered mass given sufficient flight time. Trajectory families that use only Earth gravity assists offer the most delivered mass at most flight times examined, and are available frequently with little variation in performance. However, at least one of the VEGA trajectory types is among the top performers at all of the flight times considered. INTRODUCTION The use of planetary gravity assists is a proven technique to improve the performance of interplanetary trajectories as exemplified by the Voyager, Galileo, and Cassini missions. Another proven technique for enhancing the performance of space missions is the use of highly efficient electric propulsion systems. Electric propulsion can be used to increase the mass delivered to the destination and/or reduce the trip time over typical chemical propulsion systems.1,2 This technology has been demonstrated on the Deep Space 1 mission 3 − part of NASA’s New Millennium Program to validate technologies which can lower the cost and risk and enhance the performance of future missions. -
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. -
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 -
Study of a Crew Transfer Vehicle Using Aerocapture for Cycler Based Exploration of Mars by Larissa Balestrero Machado a Thesis S
Study of a Crew Transfer Vehicle Using Aerocapture for Cycler Based Exploration of Mars by Larissa Balestrero Machado A thesis submitted to the College of Engineering and Science of Florida Institute of Technology in partial fulfillment of the requirements for the degree of Master of Science in Aerospace Engineering Melbourne, Florida May, 2019 © Copyright 2019 Larissa Balestrero Machado. All Rights Reserved The author grants permission to make single copies ____________________ We the undersigned committee hereby approve the attached thesis, “Study of a Crew Transfer Vehicle Using Aerocapture for Cycler Based Exploration of Mars,” by Larissa Balestrero Machado. _________________________________________________ Markus Wilde, PhD Assistant Professor Department of Aerospace, Physics and Space Sciences _________________________________________________ Andrew Aldrin, PhD Associate Professor School of Arts and Communication _________________________________________________ Brian Kaplinger, PhD Assistant Professor Department of Aerospace, Physics and Space Sciences _________________________________________________ Daniel Batcheldor Professor and Head Department of Aerospace, Physics and Space Sciences Abstract Title: Study of a Crew Transfer Vehicle Using Aerocapture for Cycler Based Exploration of Mars Author: Larissa Balestrero Machado Advisor: Markus Wilde, PhD This thesis presents the results of a conceptual design and aerocapture analysis for a Crew Transfer Vehicle (CTV) designed to carry humans between Earth or Mars and a spacecraft on an Earth-Mars cycler trajectory. The thesis outlines a parametric design model for the Crew Transfer Vehicle and presents concepts for the integration of aerocapture maneuvers within a sustainable cycler architecture. The parametric design study is focused on reducing propellant demand and thus the overall mass of the system and cost of the mission. This is accomplished by using a combination of propulsive and aerodynamic braking for insertion into a low Mars orbit and into a low Earth orbit. -
Ionization Within a Plasma for the Purpose Investigating Space Propulsion and the Vasimr Plasma Rocket Engine
Ionization within a Plasma for the Purpose Investigating Space Propulsion and the Vasimr Plasma Rocket Engine A project present to The Faculty of the Department of Aerospace Engineering San Jose State University in partial fulfillment of the requirements for the degree Master of Science in Aerospace Engineering By Jeffrey Meadows May, 2016 approved by Dr. Marcus Murbach Faculty Advisor Abstract This paper investigates 2 key methods of ionization; Electron bombardment and RF bombardment, for plasma production in space as it relates to propulsion applications. The Paschen curve for air was measured experimentally and a 2mm wide region of <10% error was measured from those results. Ionization costs of between 8,000 and 15,000 electron Volts were calculated within the 2mm gap region. From these results, it was determined that electron bombardment could not provide efficient ionization for thrusting applications above 0.1 Newtons. From previously published data the ratio of ionization potential to atomic mass was a determined to be a key design parameter limiting propellant selection to the noble gases. The elements specifically investigated were Argon, Xenon & Krypton. More importance was placed on investigating Argon owing to the abundance of previously published data. Furthermore, a novel solution was proposed relying on published data and experimental investigation, to fill the design space between VASIMR and ion/hall thrusters. The theoretical results of this solution are a thrust of 0.6 N operating on 25 kW of power at total efficiency of just 10%. A future experiment was proposed for investigating RF bombardment ionization efficiencies of the 3 elements to better estimate their ionization efficiencies within the Helicon antenna to improve this 10% total efficiency. -
Degree at Master at Science Floyd J. Ruble, B.Sc
THE ORG!NIWION AND DEVELOPMENT OF YOUNG MEN'S FARMING CLUBS IN OHIO A fheaia Preaented for the :Degree at Master at Science by Floyd J. Ruble, B.Sc. ~he Ohio State University 1930 Approved bya TA.BLE OF CO:tnENTS Page INTRODUC~ION i Statement of the Problem 11 Source material ii FARill ORGANIZATIONS 1 ACTIVITIES FOR CHILDREN AND YOUTH 2 BEGINNING OF THE FARMING CLUB MOV&ililll! 3 ITS POSSIBILITIES FOR lilEMBEB.SllIP 4 THE ORGANIUTION OF A TY.Piilli.L CLUB 5 PART-TIME COURSES ESSENTIAL TO 1!13TABLISHING FARMING CLUBS 10 INT~TS OF THE OBGA.Niz.ATION 12 MEM.BlmSHIP 14 THE CONSTITUTION OF A CLUB 18 INITIATION 19 .PROGRAM OF WORK 20 ATHLE'rIOS 27 SOCIALS 28 PIAYS 29 PFB.l! HUNTS 30 PAlJJlft-SON .BANQ.Ums 31 PA!lf-TIKE COURSil> 31 O.BJ:00!.rIVBS OP' PART-TIME INSTRUCTION 35 PROJ:OOT WORK 37 :eROJ:OOTS AND SUPERVISED .PRACTICE IN THE GROVE CITY C01A1UNITY TABLE OF CONTE!il'lS page CASES OF INDIVIDUAL PROJJOOT WOBK 46 THE YOUNG MEN'S FAru.ilNG CLUB AS A COM.WNITY ASS~~ 50 BEIA.TIONSHIPS AND R.EaPONSIBILITI.12 OP T~CH.l:lib OP VOCA.TIONA.L AGRICUL'...'URE 51 THE FU'i'URE OF YOUNG MEN'S FAmllNG CLUBS 52 STATUS OF YOUNG MEN'S F.Alli:iilNG CLUBS IN O'.i:HAR STAT.Ea 53 SUMhlARY 54 BIBLIOGRAHIY 56 APPENDIX 57 LIST OF TAB~ Page I GROWTH OF THE GROVE CITY YOU. MEN'S FARM.ING CLUBS 6 II THE GRC1NTH OF YOUNG .MEN'S ~~Rii:llNG CLUBS SHOWING THE REJ'ATION OF THE NUMBER OF llEPAR'.i:.:J..~~S OF VOCATIONA.L AGRICULTURE AND THE WllB~ OF .PART-TIU COURS.:l3 FOR NINE Y.FARS, 1922 TO 1930 10 III 11IE REIATIONSHIP BEfJ.'WEEN F.AlUoUNG CLUB l4EM.B..iBS AND PART-TIME -
1 Iac-06-C4.4.7 the Innovative Dual-Stage 4-Grid Ion
IAC-06-C4.4.7 THE INNOVATIVE DUAL-STAGE 4-GRID ION THRUSTER CONCEPT – THEORY AND EXPERIMENTAL RESULTS Cristina Bramanti, Roger Walker, ESA-ESTEC, Keplerlaan 1, 2201 AZ Noordwijk, The Netherlands [email protected], Roger. Walker @esa.int Orson Sutherland, Rod Boswell, Christine Charles Plasma Research Laboratory, Research School of Physical Sciences and Engineering, The Australian National University, Canberra, ACT 0200, Australia [email protected], [email protected], [email protected]. David Fearn EP Solutions, 23 Bowenhurst Road, Church Crookham, Fleet, Hants, GU52 6HS, United Kingdom [email protected] Jose Gonzalez Del Amo, Marika Orlandi ESA-ESTEC, Keplerlaan 1, 2201 AZ Noordwijk, The Netherlands [email protected], [email protected] ABSTRACT A new concept for an advanced “Dual-Stage 4-Grid” (DS4G) ion thruster has been proposed which draws inspiration from Controlled Thermonuclear Reactor (CTR) experiments. The DS4G concept is able to operate at very high specific impulse, power and thrust density values well in excess of conventional 3-grid ion thrusters at the expense of a higher power-to-thrust ratio. A small low-power experimental laboratory model was designed and built under a preliminary research, development and test programme, and its performance was measured during an extensive test campaign, which proved the practical feasibility of the overall concept and demonstrated the performance predicted by analytical and simulation models. In the present paper, the basic concept of the DS4G ion thruster is presented, along with the design, operating parameters and measured performance obtained from the first and second phases of the experimental campaign. -
Single-Stage Drag Modulation GNC Performance for Venus Aerocapture Demonstration
See discussions, stats, and author profiles for this publication at: https://www.researchgate.net/publication/330197775 Single-Stage Drag Modulation GNC Performance for Venus Aerocapture Demonstration Conference Paper · January 2019 DOI: 10.2514/6.2019-0016 CITATIONS READS 5 32 3 authors, including: Evan Roelke University of Colorado Boulder 9 PUBLICATIONS 18 CITATIONS SEE PROFILE Some of the authors of this publication are also working on these related projects: Multi-Event Drag Modulated Aerocapture Guidance View project All content following this page was uploaded by Evan Roelke on 14 September 2020. The user has requested enhancement of the downloaded file. Single-Stage Drag Modulation GNC Performance for Venus Aerocapture Demonstration Roelke, E.∗, Braun, R.D.†, and Werner, M.S.‡ University of Colorado Boulder The future of space exploration is heavily reliant on innovative Entry, Descent, and Landing (EDL) technologies. One such innovation involves aeroassist technology, mainly aerocapture, which involves a single pass through the upper atmosphere of a planetary body from an incom- ing hyperbolic trajectory to capture into an elliptical orbit. Previous aerocapture guidance studies focused on lift modulation using reaction-control system (RCS) thrusters. This pa- per investigates the guidance law performance of drag-modulated aerocapture for a single, discrete, jettison event. Venus is selected as the target planet to observe performance in the most challenging environment. Three different guidance algorithms are studied, including a deceleration curve-fit, a pure state-predictor, and a numerical predictor-corrector utilizing both bisection and Newton-Raphson root-finding methods. The performance is assessed us- ing Monte Carlo simulation methods. The deceleration curve-fit achieves a capture rate of over 55% for a 2000km apoapsis target and 1000km tolerance. -
Space Propulsion Technology for Small Spacecraft
Space Propulsion Technology for Small Spacecraft The MIT Faculty has made this article openly available. Please share how this access benefits you. Your story matters. Citation Krejci, David, and Paulo Lozano. “Space Propulsion Technology for Small Spacecraft.” Proceedings of the IEEE, vol. 106, no. 3, Mar. 2018, pp. 362–78. As Published http://dx.doi.org/10.1109/JPROC.2017.2778747 Publisher Institute of Electrical and Electronics Engineers (IEEE) Version Author's final manuscript Citable link http://hdl.handle.net/1721.1/114401 Terms of Use Creative Commons Attribution-Noncommercial-Share Alike Detailed Terms http://creativecommons.org/licenses/by-nc-sa/4.0/ PROCC. OF THE IEEE, VOL. 106, NO. 3, MARCH 2018 362 Space Propulsion Technology for Small Spacecraft David Krejci and Paulo Lozano Abstract—As small satellites become more popular and capa- While designations for different satellite classes have been ble, strategies to provide in-space propulsion increase in impor- somehow ambiguous, a system mass based characterization tance. Applications range from orbital changes and maintenance, approach will be used in this work, in which the term ’Small attitude control and desaturation of reaction wheels to drag com- satellites’ will refer to satellites with total masses below pensation and de-orbit at spacecraft end-of-life. Space propulsion 500kg, with ’Nanosatellites’ for systems ranging from 1- can be enabled by chemical or electric means, each having 10kg, ’Picosatellites’ with masses between 0.1-1kg and ’Fem- different performance and scalability properties. The purpose tosatellites’ for spacecrafts below 0.1kg. In this category, the of this review is to describe the working principles of space popular Cubesat standard [13] will therefore be characterized propulsion technologies proposed so far for small spacecraft. -
Ion Propulsion
NASA Facts National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio 44135–3191 FS–2004–11–021–GRC Ion Propulsion Plasma is an electrically neutral gas in which all positive and negative charges—from neutral atoms, negatively charged electrons, and positively charged ions—add up to zero. Plasma exists everywhere in nature; it is designated as the fourth state of matter (the others are solid, liquid, and gas). It has some of the properties of a gas but is affected by electric and magnetic fields and is a good conductor of electricity. Plasma is the building block for all types of electric propulsion, where electric and/or magnetic fields are used to push on the electrically charged ions and electrons to provide thrust. Examples of plasmas seen every day are lightning and fluorescent light bulbs. The conventional method for ionizing the propellant atoms in an ion thruster is called electron bombardment. The majority of NASA’s research consists of electron NASA Evolutionary Xenon Thruster (NEXT) ion bombardment ion thrusters. When a high-energy electron thruster in operation. (negative charge) collides with a propellant atom (neutral charge), a second electron is released, yielding two Introduction negative electrons and one positive ion. The propulsion of choice for science fiction writers has become the propulsion of choice for scientists and An alternative method of ionization called electron engineers at NASA. The ion propulsion system’s efficient cyclotron resonance (ECR) is also being researched use of fuel and electrical power enable modern spacecraft at NASA. This method uses high-frequency radiation to travel farther, faster, and cheaper than any other (usually microwaves), coupled with a high magnetic field propulsion technology currently available.