1 Iac-06-C4.4.7 the Innovative Dual-Stage 4-Grid Ion
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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. -
9.0 BACKGROUND “What Do I Do First?” You Need to Research a Card (Thruster Or 9.1 DESIGNER’S NOTES Robonaut) with a Low Fuel Consumption
9.2 TIPS FOR INEXPERIENCED ROCKET CADETS 9.0 BACKGROUND “What do I do first?” You need to research a card (thruster or 9.1 DESIGNER’S NOTES robonaut) with a low fuel consumption. A “1” is great, a “4” The original concept for this game was a “Lords of the Sierra Madre” in is marginal. The PRC player*** can consider an dash to space. With mines, ranches, smelters, and rail lines all purchased and claim Hellas Basin on Mars, using just his crew card. He controlled by different players, who have to negotiate between them- needs 19 fuel steps (6 WT) along the red route to do this. selves to expand. But space does not work this way. “What does my rocket need?” Your rocket needs 4 things: Suppose you have a smelter on one main-belt asteroid, powered by a • A card with a thruster triangle (2.4D) to act as a thruster. • A card with an ISRU rating, if its mission is to prospect. beam-station on another asteroid, and you discover platinum on a third • A refinery, if its mission is to build a factory. nearby asteroid. Unfortunately for long-term operations, next year these • Enough fuel to get to the destination. asteroids will be separated by 2 to 6 AUs.* Furthermore, main belt Decide between a small rocket able to make multiple claims, Hohmann transfers are about 2 years long, with optimal transfer opportu- or a big rocket including a refinery and robonaut able to nities about 7 years apart. Jerry Pournelle in his book “A Step Farther industrialize the first successful claim. -
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. -
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. -
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 -
Mass Driver CDR March 10, 2020 Mission Profile (Mars → Phobos)
Mass Driver CDR March 10, 2020 Mission Profile (Mars → Phobos) ● Launch windows are defined by phobos position and tether sling spin up time ○ Phobos must be -29.033° from Olympus Mons (right ascension) ○ Max turnover = 3 launches/sol ● Acceleration Profile ○ 4.77 km/s Launch Velocity ○ 4.47 km/s Velocity past atmosphere ○ 2 G’s net ● Total Orbital Flight Time 14.69 hrs Orbital Trajectory ΔV (km/s) Time (hrs) Launch 4.77 6.17 Burn 1 0.286 8.52 Burn 2 0.375 RNDVZ Total 0.661 14.69 Considerations & Deviations ● Acceleration modification ○ Make time and distance shorter ○ Launch Velocity includes drag and rotation ● Orbital analysis ○ No perturbations ○ No eccentricity/inclinations ● Risk Assessment ○ If launch fails, more ΔV is required ○ If burn 1 fails, the taxi will return to Olympus Mons ○ If burn 2 fails, no return possibility without significant ΔV Mass Driver Objectives • Handle loads of our magnitude (passenger trains) • Allows us to more easily decelerate the cradle for reusability • Located at the base of Olympus Mons • Using Null-Flux Coils for Repulsive Levitation Mass Driver Objectives • Updated battery sizing, spacing and model • Two 1x1x1 m battery banks every 409 meters down the track Mass Driver Overview Important Parameters • Track Length: 635 km (for taxi + cradle acceleration) 106 km (for cradle deceleration) • Launch Duration: 4 minutes 14 seconds • 2g constant acceleration • Force required: 6.49 MN (propulsion) 1.11 MN (levitation) • Propellant saved: 477 Mg Maglev System Diagram 0.31 m 0.55 m HTS Magnets: 80 magnets -
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. -
A Rapid and Scalable Approach to Planetary Defense Against Asteroid Impactors
THE LEAGUE OF EXTRAORDINARY MACHINES: A RAPID AND SCALABLE APPROACH TO PLANETARY DEFENSE AGAINST ASTEROID IMPACTORS Version 1.0 NASA INSTITUTE FOR ADVANCED CONCEPTS (NIAC) PHASE I FINAL REPORT THE LEAGUE OF EXTRAORDINARY MACHINES: A RAPID AND SCALABLE APPROACH TO PLANETARY DEFENSE AGAINST ASTEROID IMPACTORS Prepared by J. OLDS, A. CHARANIA, M. GRAHAM, AND J. WALLACE SPACEWORKS ENGINEERING, INC. (SEI) 1200 Ashwood Parkway, Suite 506 Atlanta, GA 30338 (770) 379-8000, (770)379-8001 Fax www.sei.aero [email protected] 30 April 2004 Version 1.0 Prepared for ROBERT A. CASSANOVA NASA INSTITUTE FOR ADVANCED CONCEPTS (NIAC) UNIVERSITIES SPACE RESEARCH ASSOCIATION (USRA) 75 5th Street, N.W. Suite 318 Atlanta, GA 30308 (404) 347-9633, (404) 347-9638 Fax www.niac.usra.edu [email protected] NIAC CALL FOR PROPOSALS CP-NIAC 02-02 PUBLIC RELEASE IS AUTHORIZED The League of Extraordinary Machines: NIAC CP-NIAC 02-02 Phase I Final Report A Rapid and Scalable Approach to Planetary Defense Against Asteroid Impactors Table of Contents List of Acronyms ________________________________________________________________________________________ iv Foreword and Acknowledgements___________________________________________________________________________ v Executive Summary______________________________________________________________________________________ vi 1.0 Introduction _________________________________________________________________________________________ 1 2.0 Background _________________________________________________________________________________________ -
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