Space Demonstration of Bare Electrodynamic Tape-Tether Technology on the Sounding Rocket S520-25
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Lunar Space Elevator Infrastructure
Lunar Space Elevator Infrastructure A Cost Saving Approach to Human Spaceflight within a 15-year Constrained NASA Budget White Paper Submitted at the Open Invitation of the National Research Council 2013 Lunar Space Elevator Infrastructure In Response to the National Research Council’s Study on the Benefits, Challenges and Ramifications of America’s Human Spaceflight Program. LiftPort Group presents a Cost-Effective Approach to Human Spaceflight within a 15-year Constrained NASA Budget. | MICHAEL LAINE – PRESIDENT, LIFTPORT GROUP | CHARLES RADLEY MSC., – ADVISOR, LIFTPORT GROUP | MARSHALL EUBANKS MSC., – ADVISOR, LIFTPORT GROUP | JEROME PEARSON MSC., – ADVISOR, LIFTPORT GROUP | PETER SWAN PHD., – ADVISOR, LIFTPORT GROUP | LEE GRAHAM (NASA – HIS VIEWS DO NOT REFLECT HIS EMPLOYER) | | 8 JULY 2013 | LIFTPORT GROUP | 1307 Dogwood Hill RD SW, Port Orchard, WA, 98366 | www.liftport.com | (862) 438-5383 | [email protected] LiftPort’s Lunar Space Elevator Infrastructure: Affordable Response to Human Spaceflight What are the important benefits provided to the United States and other countries by human spaceflight endeavors? The ability to place humans in space is exciting to the public, and demonstrates the technological maturity and stature of each spacefaring nation. Such a visible and peaceful demonstration of cutting edge technology fosters foreign policy by showing Page | 1 strength without engaging in conflicti. Human spaceflight sparks the imagination and serves an instinctive need to explore. Astronauts are ambassadors for all of humanity in a very personal way. Men and women in space suits inspire people – of all cultures and demographics – to achieve excellence, to believe in a common cause and to pursue a noble goal. -
Modular Spacecraft with Integrated Structural Electrodynamic Propulsion
NAS5-03110-07605-003-050 Modular Spacecraft with Integrated Structural Electrodynamic Propulsion Nestor R. Voronka, Robert P. Hoyt, Jeff Slostad, Brian E. Gilchrist (UMich/EDA), Keith Fuhrhop (UMich) Tethers Unlimited, Inc. 11807 N. Creek Pkwy S., Suite B-102 Bothell, WA 98011 Period of Performance: 1 September 2005 through 30 April 2006 Report Date: 1 May 2006 Phase I Final Report Contract: NAS5-03110 Subaward: 07605-003-050 Prepared for: NASA Institute for Advanced Concepts Universities Space Research Association Atlanta, GA 30308 NAS5-03110-07605-003-050 TABLE OF CONTENTS TABLE OF CONTENTS.............................................................................................................................................1 TABLE OF FIGURES.................................................................................................................................................2 I. PHASE I SUMMARY ........................................................................................................................................4 I.A. INTRODUCTION .............................................................................................................................................4 I.B. MOTIVATION .................................................................................................................................................4 I.C. ELECTRODYNAMIC PROPULSION...................................................................................................................5 I.D. INTEGRATED STRUCTURAL -
W, A. Pavj-.:S VA -R,&2. ~L
W, A. PaVJ-.:s VA -r,&2._~L NATIONAL ACADEMIES OF SCIENCE AND ENGINEERING NATIONAL RESEARCH COUNCIL of the UNITED STATES OF AMERICA UNITED STATES NATIONAL COMMITTEE International Union of Radio Science, National Radio Science Meeting 5-8 January 1993 Sponsored by USNC/URSI in cooperation with Institute of Electrical and Electronics Engineers University of Colorado Boulder, Colorado U.S.A. National Radio Science Meeting 5-8 January 1993 Condensed Technical Program Monday, 4 January 2000-2400 USNC-URSI Meeting Broker Inn Tuesday, 5 January 0835-1200 B-1 ANTENNAS CRZ-28 0855-1200 A-1 MICROWAVE MEASUREMENTS CRl-46 D-1 MICROWAVE, QUASisOPTICAL, AND ELECTROOPTICAL DEVICES CRl-9 G-1 COORDINATED CAMPAIGNS AND ACTIVE EXPERIMENTS CR0-30 J/H-1 RADIO AND RADAR ASTRONOMY OF THE SOLAR SYSTEM CRZ-26 1335-1700 B-2 SCATIERING CR2-28 F-1 SENSING OF ATMOSPHERE AND OCEAN CRZ-6 G-2 IONOSPHERIC PROPAGATION CHANNEL CR0-30 J/H-2 RADIO AND RADAR ASTRONOMY OF THE SOLAR SYSTEM CR2-26 1355-1700 A-2 EM FIELD MEASUREMENTS CRl-46 D-2 OPTOELECTRONICS DEVICES AND APPLICATION CRl-9 1700-1800 Commission A Business Meeting CRl-46 Commission C Business Meeting CRl-40 Commission D Business Meeting CRl-9 Commission G Business Meeting CR0-30 Wednesday, 6 January 0815-1200 PLENARY SESSION MATH 100 1335-1700 B-3 EM THEORY CRZ-28 D-3 MICROWAVE AND MILLIMETER AND RELATED DEVICES CRl-9 F-2 PROPAGATION MODELING AND SCATTERING CRZ-6 H-1 PLASMA WAYES IN THE IONOSPHERE AND THE MAGNETOSPHERE CRl-42 J-1 FIBER OPTICS IN RADIO ASTRONOMY CR2-26 1355-1700 E-1 HIGH POWER ELECTROMAGNETICS (HPE) AND INTERFERENCE PROBLEMS CRl-40 United States National Committee INTERNATIONAL UNION OF RADIO SCIENCE PROGRAM AND ABSTRACTS National Radio Science Meeting 5-8 January 1993 Sponsored by USNC/URSI in cooperation with IEEE groups and societies: Antennas and Propagation Circuits and Systems Communications Electromagnetic Compatibility Geoscience Electronics Information Theory ,. -
1 Using Eletrodynamic Tethers to Perform Station
USING ELETRODYNAMIC TETHERS TO PERFORM STATION-KEEPING MANEUVERS IN LEO SATELLITES Thais Carneiro Oliveira(1), and Antonio Fernando Bertachini de Almeida Prado(2) (1)(2) National Institute for Space Research (INPE), Av. dos Astronautas 1758 São José dos Campos – SP – Brazil ZIP code 12227-010,+55 12 32086000, [email protected] and [email protected] Abstract: This paper analyses the concept of using an electrodynamic tether to provide propulsion to a space system with an electric power supply and no fuel consumption. The present work is focused on orbit maintenance and on re-boost maneuvers for tethered satellite systems. The analyses of the results will be performed with the help of a practical tool called “Perturbation Integrals” and an orbit integrator that can include many external perturbations, like atmospheric drag, solar radiation pressure and luni-solar perturbation. Keywords: Electromagnetic Tether, Station-Keeping Maneuver, Orbital Maneuver, Tether Systems, Disturbing Forces. 1. Introduction Space tether is a promising and innovating field of study, and many articles, technical reports, books and even missions have used this concept through the recent decades. An overview of the space tethered flight tests missions includes the Gemini tether experiments, the OEDIPUS flights, the TSS-1 experiments, the SEDS flights, the PMG, TiPs, ATEx missions, etc [1-6]. This paper analyses the potential of using an electrodynamic tether to provide propulsion to a space system with an electric power supply and no fuel consumption. The present work is focused on orbit maintenance and re-boosts maneuvers for tethered satellite systems (TSS). This type of system consists of two or more satellites orbiting around a planet linked by a cable or a tether [7]. -
Tethers in Space Handbook - Second Edition
Tethers In Space Handbook - Second Edition - (NASA-- - I SECOND LU IT luN (Spectr Rsdrci ystLSw) 259 P C'C1 ? n: 1 National Aeronautics and Space Administration Office of Space Flight Advanced Program Development NASA Headquarters Code MD Washington, DC 20546 This document is the product of support from many organizations and individuals. SRS Technologies, under contract to NASA Headquarters, compiled, updated, and prepared the final document. Sponsored by: National Aeronautics and Space Administration NASA Headquarters, Code MD Washington, DC 20546 Contract Monitor: Edward J. Brazil!, NASA Headquarters Contract Number: NASW-4341 Contractor: SRS Technologies Washington Operations Division 1500 Wilson Boulevard, Suite 800 Arlington, Virginia 22209 Project Manager: Dr. Rodney W. Johnson, SRS Technologies Handbook Editors: Dr. Paul A. Penzo, Jet Propulsion Laboratory Paul W. Ammann, SRS Technologies Tethers In Space Handbook - Second Edition - May 1989 Prepared For: National Aeronautics and Space Administration Office of Space Flight Advanced Program Development NASA National Aeronautics and Space Administration FOREWORD The Tethers in Space Handbook Second Edition represents an update to the initial volume issued in September 1986. As originally intended, this handbook is designed to serve as a reference manual for policy makers, program managers, educators, engineers, and scientists alike. It contains information for the uninitiated, providing insight into the fundamental behavior of tethers in space. For those familiar with space tethers, it summarizes past and ongoing studies and programs, a complete bibliography of tether publications, and names, addresses, and phone numbers of workers in the field. Perhaps its most valuable asset is the brief description of nearly 50 tether applications which have been proposed and analyzed over the past 10 years. -
Arxiv:2003.07985V1
Tether Capture of spacecraft at Neptune a,b b, J. R. Sanmart´ın , J. Pel´aez ∗ aReal Academia de Ingenier´ıa of Spain bUniversidad Polit´ecnica de Madrid, Pz. C.Cisneros 3, Madrid 28040, Spain Abstract Past planetary missions have been broad and detailed for Gas Giants, compared to flyby missions for Ice Giants. Presently, a mission to Neptune using electrodynamic tethers is under consideration due to the ability of tethers to provide free propulsion and power for orbital insertion as well as additional exploratory maneuvering — providing more mission capability than a standard orbiter mission. Tether operation depends on plasma density and magnetic field B, though tethers can deal with ill-defined density profiles, with the anodic segment self-adjusting to accommodate densities. Planetary magnetic fields are due to currents in some small volume inside the planet, magnetic-moment vector, and typically a dipole law approximation — which describes the field outside. When compared with Saturn and Jupiter, the Neptunian magnetic structure is significantly more complex: the dipole is located below the equatorial plane, is highly offset from the planet center, and at large tilt with its rotation axis. Lorentz-drag work decreases quickly with distance, thus requiring spacecraft periapsis at capture close to the planet and allowing the large offset to make capture efficiency (spacecraft-to-tether mass ratio) well above a no-offset case. The S/C might optimally reach periapsis when crossing the meridian plane of the dipole, with the S/C facing it; this convenient synchronism is eased by Neptune rotating little during capture. Calculations yield maximum efficiency of approximately 12, whereas a 10◦ meridian error would reduce efficiency by about 6%. -
Optimal Control of Electrodynamic Tethers
Air Force Institute of Technology AFIT Scholar Theses and Dissertations Student Graduate Works 6-1-2008 Optimal Control of Electrodynamic Tethers Robert E. Stevens Follow this and additional works at: https://scholar.afit.edu/etd Part of the Aerospace Engineering Commons Recommended Citation Stevens, Robert E., "Optimal Control of Electrodynamic Tethers" (2008). Theses and Dissertations. 2656. https://scholar.afit.edu/etd/2656 This Dissertation is brought to you for free and open access by the Student Graduate Works at AFIT Scholar. It has been accepted for inclusion in Theses and Dissertations by an authorized administrator of AFIT Scholar. For more information, please contact [email protected]. OPTIMAL CONTROL OF ELECTRODYNAMIC TETHER SATELLITES DISSERTATION Robert E. Stevens, Commander, USN AFIT/DS/ENY/08-13 DEPARTMENT OF THE AIR FORCE AIR UNIVERSITY AIR FORCE INSTITUTE OF TECHNOLOGY Wright-Patterson Air Force Base, Ohio APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED The views expressed in this dissertation are those of the author and do not reflect the official policy or position of the United States Air Force, Department of Defense, or the United States Government. AFIT/DS/ENY/08-13 OPTIMAL CONTROL OF ELECTRODYNAMIC TETHER SATELLITES DISSERTATION Presented to the Faculty Graduate School of Engineering and Management Air Force Institute of Technology Air University Air Education and Training Command in Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy Robert E. Stevens, BS, MS Commander, USN June 2008 APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED AFIT/DS/ENY/08-13 OPTIMAL CONTROL OF ELECTRODYNAMIC TETHER SATELLITES Robert E. Stevens, BS, MS Commander, USN Approved: Date ____________________________________ William E. -
Electrodynamic Tethers in Space
Electrodynamic Tethersin Space By Enrico Lorenzini and Juan Sanmartín 50 SCIENTIFIC AMERICAN AUGUST 2004 COPYRIGHT 2004 SCIENTIFIC AMERICAN, INC. ARTIST’S CONCEPTION depicts how a tether system might operate on an exploratory mission to Jupiter and its moons. As the apparatus and its attached research instruments glide through space between Europa and Callisto, the tether would harvest power from its interaction with the vast magnetic field generated by Jupiter, which looms in the background. By manipulating current flow along the kilometers-long tether, mission controllers could change the tether system’s altitude and direction of flight. By exploiting fundamental physical laws, tethers may provide low-cost electrical power, drag, thrust, and artificial gravity for spaceflight www.sciam.com SCIENTIFIC AMERICAN 51 COPYRIGHT 2004 SCIENTIFIC AMERICAN, INC. There are no filling stations in space. Every spacecraft on every mission has to carry all the energy Tethers are systems in which a flexible cable connects two sources required to get its job done, typically in the form of masses. When the cable is electrically conductive, the ensemble chemical propellants, photovoltaic arrays or nuclear reactors. becomes an electrodynamic tether, or EDT. Unlike convention- The sole alternative—delivery service—can be formidably al arrangements, in which chemical or electrical thrusters ex- expensive. The International Space Station, for example, will change momentum between the spacecraft and propellant, an need an estimated 77 metric tons of booster propellant over its EDT exchanges momentum with the rotating planet through the anticipated 10-year life span just to keep itself from gradually mediation of the magnetic field [see illustration on opposite falling out of orbit. -
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 _________________________________________________________________________________________ -
05, Military, Aerospace, Space & Homeland
------------------------------------------------------------- [コンフェレンス紹介] May 3-5, 2005 MASH '05, Military, Aerospace, Space & Homeland Security Sacramento Marriott Rancho Cordova http://www.imaps.org/mash ------------------------------------------------------------- 2005 年 4 月 28 日 19:12 WIRED NEWS (2005/04/28) NASA、量子ワイヤ研究を援助――宇宙エレベータも射程 http://hotwired.goo.ne.jp/news/20050428301.html NASA はライス大学の量子ワイヤ研究に対する$11M の資金援助 く、宇宙船軽量化やプロセッサ高速化につながる。「宇宙エレベ を発表。2010 年までに長さ 1m の電線を完成させるのが目標。カ ータ」への応用も含め、ナノチューブは人類を宇宙へと送出すの ーボン・ナノチューブで作る量子ワイヤは軽量で電気伝導度が高 に大きな役割を果たすと期待されている。 ------------------------------------------------------------- 2005 年 4 月 28 日 19:12 WIRED NEWS (2005/04/28) ロケット燃料による飲料水汚染、米国の 36 州で http://hotwired.goo.ne.jp/news/20050428305.html 米の 36 の州で、ロケット燃料や兵器の製造に使われた化学 巨額の費用がかかるため、現在米環境保護局(EPA)では強制 薬品によって、飲料水が汚染されていることが判明。浄化に 力のない安全基準しか定めていない。 ------------------------------------------------------------- 2005 年 4 月 26 日 9:28 ジェトロ 半導体パッケージングの大型投資相次ぐ(中国) 上海発 半導体製造は前工程生産能力が急成長し、最近は後工程とい 体パッケージングへの大規模投資が相次いでいる。 われる半導体パッケージング需要が高まっている。このため半導 ------------------------------------------------------------- 2005 年 4 月 25 日 9:24 ジェトロ EU 憲法条約の批准、最初のヤマ場近づく(EU) ブリュッセル発 ギリシャ議会が 4 月 19 日、EU 憲法条約を賛成多数(賛成:268 となるもので、2006 年秋ごろの発効を目指している。発効には全 票、反対:17 票)で承認し、ギリシャは EU25 ヵ国中 5 番目の批准 加盟国の批准が必要で、5 月 29 日に実施予定のフランスの国民 国となった。EU 憲法条約は EU の拡大に伴い、新たな基本条約 投票が最初のヤマ場となる。 ------------------------------------------------------------- 2005 年 4 月 22 日 19:10 WIRED NEWS (2005/04/22) 狙った相手だけに聞かせる音声伝送システムに MIT 発明賞 http://hotwired.goo.ne.jp/news/20050422301.html 米マサチューセッツ工科大学(MIT)『レメルソン -
Siewnarine Vishal 2015 Masters
THE IMPACT OF ATMOSPHERIC MODELS ON THE DYNAMICS OF SPACE TETHER SYSTEMS Vishal Siewnarine A THESIS SUBMITTED TO THE FACULTY OF GRADUATE STUDIES IN PARTIAL FULFILMENT OF THE REQUIREMENTS FOR THE DEGREE OF MASTER OF SCIENCE Graduate Program in Physics and Astronomy York University Toronto, Ontario September 2015 Vishal Siewnarine, 2015 Abstract Space debris has become an increasingly larger concern for aerospace travel and exploration. One idea to control the space debris population is to de-orbit defunct satellites using a space tether system. A space tether system is often made up of three parts: the main satellite, the tether and the sub-satellite. The tether connects the main satellite and the sub-satellite. Space tether systems make use of the Lorentz force as an electrodynamic drag for de-orbit. We use an established model of a space tether system to observe how satellites de- orbit. This model was constructed in MATLAB (Simulink) and uses the 1976 U.S. Standard Atmosphere. However, we wish to investigate how the model behaves using newer and more accurate atmospheric models, namely, the Jacchia-Bowman 2008 model and the Drag Temperature Model 2013. We also investigate the effect of controlling the tether's libration energy under the three aforementioned atmospheric models. ii Acknowledgements First of all, I would like to thank God for bringing me to this point. Without her, nothing is possible. Next, I would like to thank Professor Zheng Hong Zhu for his enduring patience and effort in being my supervisor and mentor whose sincerity, encouragement, late nights and tireless efforts helped shape my focus and inspire me as I hurdle all the obstacles and barriers in the completion of this work. -
Applications of the Electrodynamic Tether to Interstellar Travel
s .I 1 7 Matloff/Johnson “Tether Applications paper,” for JBIS Applications of the Electrodynamic Tether to Interstellar Travel GREGORY L. MATLOFF Dept. of Physical & Biological Sciences, New York City College of Technology, CUNU, 300 Jay Street, Brooklyn, NY 11201, USA Gray Research Inc., 675 Discovery Drive, Suite 302, Huntsville, AL, 35806, USA Email: [email protected] and LES JOHNSON In-Space Propulsion Technology Project, NASA Marshall Space Flight Center, NP40, AL, 35812, USA Emai 1: C. Les.Johnson @ nasa. gov ABSTRACI’: After considering relevant properties of the local interstellar medium and defining a sample interstellar mission, this paper considers possible interstellar applications of the electrodynamic tether, or EDT. These include use of the EDT to provide on-board power and affect trajectory modifications and direct application of the EDT to starship acceleration. It is demonstrated that comparatively modest EDTs can provide substantial quantities of on-board power, if combined with a large-area electron- collection device such as the Cassenti toroidal-field ramscoop. More substantial tethers can be used to accomplish large-radius thrustless turns. Direct application of the EDT to starship acceleration is apparently infeasible. Keywords: interstellar travel, tethers, world ships, ramscoops, thrustless turning, on- board power sources 1. Introduction: The Electrodynamic Tether, or EDT, is conceptually one of the simplest in-space propulsion concepts. The tether consists of a long, conducting strand. Electrons are collected from the ambient plasma at one end, flow along the tether, and are emitted at the other end of the tether. In certain cases, the tether itself collects electrons from the local plasma, and a dedicated electron-collection device is not required.