Electrodynamic Tethers For Planetary And De-orbiting Missions

Nuevas aplicaciones tecnológicas y científicas mediante amarras electrodinámicas son analizadas para misiones planetarias. i) Primero, se considera un conjunto de amarras cilíndricas en paralelo (veleros electrosolares) para una misión interplanetaria. Los iones provenientes del viento solar son repelidos por el alto potencial de dichas amarras generando empuje sobre el velero. Para conocer el intercambio de momento que provocan los iones sobre las amarras se ha considerado un modelo de potencial estacionario. Se ha analizado la transferencia orbital de la Tierra a Júpiter siguiendo un método de optimización de trayectoria indirecto. ii) Una vez que el velero se encuentra cerca de Júpiter, se ha considerado el despliegue de una amarra para diferentes objetivos científicos. iia) Una amarra podría ser utilizada para diagnóstico de plasmas, al ser una fuente efectiva de ondas, y también como un generador de auroras artificiales. Una amarra conductora que orbite en la magnetosfera jovial es capaz de producir ondas. Se han analizado las diferentes ondas radiadas por un conductor por el que circula una corriente constante que sigue una órbita polar de alta excentricidad y bajo apoápside, como ocurre en la misión Juno de la NASA. iib) Además, se ha estudiado una misión tentativa que sigue una órbita ecuatorial (LJO) por debajo de los intensos cinturones de radiación. Ambas misiones requiren potencia eléctrica para los sistemas de comunicación e instrumentos científicos. Las amarras pueden generar potencia de manera más eficiente que otros sistemas que utlizan paneles solares o sistemas de potencia de radioisótopos (RPS). La impedancia de radiación es necesaria para determinar la corriente que circula por todo el circuito de la amarra. En un modelo de plasma frío, la radiación ocurre principalmente en los modos de Alfven y magnetosónica rápida, mostrando un elevado índice de refracción. Se ha estudiado la impedancia de radiación en amarras con recubrimiento aislante para los dos modos de radiación y cada una de las misiones. A diferencia del caso ionosférico terrestre, la baja densidad y el intenso campo magnético que aparecen en el entorno de Júpiter consiguen que la girofrecuencia de los electrones sea mucho mayor que la frecuencia del plasma; esto hace que el espectro de potencia para cada modo se modifique substancialmente, aumentando la velocidad de Alfven. Se ha estimado también la impedancia de radiación para amarras sin aislante conductor. En la misión LJO, un vehículo espacial bajando lentamente la altitud de su órbita permitiría estudiar la estructura del campo magnético y composición atmosférica para entender la formación, evolución, y estructura de Júpiter. Adicionalmente, si el contactor (cátodo) se apaga, se dice que la amarra flota eléctricamente, permitiendo emisión de haz de electrones que generan auroras. El continuo apagado y encendido produce pulsos de corriente dando lugar a emisiones de señales, que pueden ser utilizadas para diagnóstico del plasma jovial. En Órbita Baja Jovial, los iones que impactan contra una amarra polarizada negativamente producen electrones secundarios, que, viajando helicoidalmente sobre las líneas de campo magnético de Júpiter, son capaces de alcanzar su atmósfera más alta, y, de esta manera, generar auroras. Se han identificado cuáles son las regiones donde la amarra sería más eficiente para producir auroras. iic) Otra aplicación científica sugerida para la misión LJO es la detección de granos cargados que orbitan cerca de Júpiter. Los electrones de alta energía en este ambiente pueden ser modelados por una distribucción no Maxwelliana conocida como distribución kappa. En escenarios con plasmas complejos, donde los campos eléctricos en Júpiter pueden acelerar las cargas hasta velocidades que superen la velocidad térmica, este tipo de distribuciones son muy útiles. En este caso las colas de las distribuciones de electrones siguen una ley de potencias. Se han estudiado las fluctuaciones de granos cargados para funciones de distribución kappa. iii) La tesis concluye con el análisis para deorbitar satélites con amarras electrodinámicas que siguen una Órbita Baja Terrestre (LEO). Una amarra debe presentar una baja probabilidad de corte por pequeño debris y además debe ser suficientemente ligero para que el cociente entre la masa de la amarra y el satélite sea muy pequeño. En este trabajo se estiman las medidas de la longitud, anchura y espesor que debe tener una amarra para minimizar el producto de la probabilidad de corte por el cociente entre las masas de la amarra y el satélite. Se presentan resultados preliminares del diseño de una amarra con forma de cinta para deorbitar satélites relativamente ligeros como Cryosat y pesados como Envisat. Las misiones espaciales a planetas exteriores y en el ámbito terrestre plantean importantes retos científico-tecnológicos que deben ser abordados y solucionados. Por ello, desde el inicio de la era espacial se han diseñando novedosos métodos propulsivos, sistemas de guiado, navegación y control más robustos, y nuevos materiales para mejorar el rendimiento de los vehículos espaciales (SC). En un gran número de misiones interplanetarias y en todas las misiones a planetas exteriores se han empleado sistemas de radioisótopos (RPS) para generar potencia eléctrica en los vehículos espaciales y en los rovers de exploración. Estos sistemas emplean como fuente de energía el escaso y costoso plutonio-238. La NASA, por medio de un informe de la National Academy of Science (5 de Mayo del 2009), expresó una profunda preocupación por la baja cantidad de plutonio almacenado, insuficiente para desarrollar todas las misiones de exploración planetaria planeadas en el futuro [81, 91]. Esta circustancia ha llevado a dicha Agencia tomar la decisión de limitar el uso de estos sistemas RPS en algunas misiones de especial interés científico y una recomendación de alta prioridad para que el Congreso de los EEUU apruebe el reestablecimiento de la producción de plutonio-238, -son necesarios cerca de 5 kg de este material radiactivo al año-, para salvaguardar las misiones que requieran dichos sistemas de potencia a partir del año 2018. Por otro lado, la Agencia estadounidense ha estado considerando el uso de fuentes de energía alternativa; como la fisión nuclear a través del ambicioso proyecto Prometheus, para llevar a cabo una misión de exploración en el sistema jovial (JIMO). Finalmente, dicha misión fue desestimada por su elevado coste. Recientemente se han estado desarrollando sistemas que consigan energía a través de los recursos naturales que nos aporta el Sol, mediante paneles solares -poco eficientes para misiones a planetas alejados de la luz solar-. En este contexto, la misión JUNO del programa Nuevas Fronteras de la NASA, cuyo lanzamiento fue realizado con éxito en Agosto de 2011, va a ser la primera misión equipada con paneles solares que sobrevolará Júpiter en el 2015 siguiendo una órbita polar. Anteriormente se habían empleado los antes mencionados RPS para las misiones Pioneer 10,11, Voyager 1,2, Ulysses, Cassini-Huygens y Galileo (todas sobrevuelos excepto Galileo). Dicha misión seguirá una órbita elíptica de alta excentricidad con un periápside muy cercano a Júpiter, y apoápside lejano, evitando que los intensos cinturones de radiación puedan dañar los instrumentos de navegación y científicos. Un tether o amarra electrodinámica es capaz de operar como sistema propulsivo o generador de potencia, pero también puede ser considerado como solución científicotecnológica en misiones espaciales tanto en LEO (Órbita Baja Terrestre) como en planetas exteriores. Siguiendo una perspectiva histórica, durante las misiones terrestres TSS-1 (1992) y TSS-1R (1996) se emplearon amarras estandard con recubrimiento aislante en toda su longitud, aplicando como terminal anódico pasivo un colector esférico para captar electrones. En una geometría alternativa, propuesta por J. R. Sanmartín et al. (1993) [93], se consideró dejar la amarra sin recubrimiento aislante (“bare tether”), y sin colector anódico esférico, de forma que recogiera electrones a lo largo del segmento que resulta polarizado positivo, como si se tratara de una sonda de Langmuir de gran longitud. A diferencia de la amarra estandard, el “bare tether” es capaz de recoger electrones a lo largo de una superficie grande ya que este segmento es de varios kilómetros de longitud. Como el radio de la amarra es del orden de la longitud de Debye y pequeño comparado con el radio de Larmor de los electrones, permite una recolección eficiente de electrones en el régimen OML (Orbital Motion Limited) de sondas de Langmuir. La corriente dada por la teoría OML varía en función del perímetro y la longitud. En el caso de una cinta delgada, el perímetro depende de la anchura, que debe ser suficientemente grande para evitar cortes producidos por debris y micrometeoritos, y suficientemente pequeño para que la amarra funcione en dicho régimen [95]. En el experimento espacial TSS-1R mencionado anteriormente, se identificó una recolección de corriente más elevada que la que predecía el modelo teórico de Parker- Murphy, debido posiblemente a que se utilizaba un colector esférico de radio bastante mayor que la longitud de Debye [79]. En el caso de una amarra “bare”, que recoge electrones a lo largo de gran parte de su longitud, se puede producir un fenómeno conocido como atrapamiento adiabático de electrones (adiabatic electron trapping) [25, 40, 60, 73, 74, 97]. En el caso terrestre (LEO) se da la condición mesotérmica en la que la amarra se mueve con una velocidad muy superior a la velocidad térmica de los iones del ambiente y muy inferior a la velocidad térmica de los electrones. J. Laframboise y L. Parker [57] mostraron que, para una función de distribución quasi-isotrópica, la densidad de electrones debe entonces ser necesariamente inferior a la densidad ambiente. Por otra parte, debido a su flujo hipersónico y a la alta polarización positiva de la amarra, la densidad de los iones es mayor que la densidad ambiente en una vasta región de la parte “ram” del flujo, violando la condición de cuasi-neutralidad,-en una región de dimensión mayor que la longitud de Debye-. La solución a esta paradoja podría basarse en el atrapamiento adiabático de electrones ambiente en órbitas acotadas entorno al tether. ABSTRACT New technological and scientific applications by electrodynamic tethers for planetary missions are analyzed: i) A set of cylindrical, parallel tethers (electric solar sail or e-sail) is considered for an interplanetary mission; ions from the solar wind are repelled by the high potential of the tether, providing momentum to the e-sail. An approximated model of a stationary potential for a high solar wind flow is considered. With the force provided by a negative biased tether, an indirect method for the optimization trajectory of an Earth-to-Jupiter orbit transfer is analyzed. ii) The deployment of a tether from the e-sail allows several scientific applications in Jupiter. iia) It might be used as a source of radiative waves for plasma diagnostics and artificial aurora generator. A conductive tether orbiting in the Jovian magnetosphere produces waves. Wave radiation by a conductor carrying a steady current in both a polar, highly eccentric, low perijove orbit, as in NASA’s Juno mission, and an equatorial low Jovian orbit (LJO) mission below the intense radiation belts, is considered. Both missions will need electric power generation for scientific instruments and communication systems. Tethers generate power more efficiently than solar panels or radioisotope power systems (RPS). The radiation impedance is required to determine the current in the overall tether circuit. In a cold plasma model, radiation occurs mainly in the Alfven and fast magnetosonic modes, exhibiting a large refraction index. The radiation impedance of insulated tethers is determined for both modes and either mission. Unlike the Earth ionospheric case, the low-density, highly magnetized Jovian plasma makes the electron gyrofrequency much larger than the plasma frequency; this substantially modifies the power spectrum for either mode by increasing the Alfven velocity. An estimation of the radiation impedance of bare tethers is also considered. iib) In LJO, a spacecraft orbiting in a slow downward spiral under the radiation belts would allow determining magnetic field structure and atmospheric composition for understanding the formation, evolution, and structure of Jupiter. Additionally, if the cathodic contactor is switched off, a tether floats electrically, allowing e-beam emission that generate auroras. On/off switching produces bias/current pulses and signal emission, which might be used for Jovian plasma diagnostics. In LJO, the ions impacting against the negative-biased tether do produce secondary electrons, which racing down Jupiter’s magnetic field lines, reach the upper atmosphere. The energetic electrons there generate auroral effects. Regions where the tether efficiently should produce secondary electrons are analyzed. iic) Other scientific application suggested in LJO is the in-situ detection of charged grains. Charged grains naturally orbit near Jupiter. High-energy electrons in the Jovian ambient may be modeled by the kappa distribution function. In complex plasma scenarios, where the Jovian high electric field may accelerate charges up superthermal velocities, the use of non-Maxwellian distributions should be considered. In these cases, the distribution tails fit well to a power-law dependence for electrons. Fluctuations of the charged grains for non-Mawellian distribution function are here studied. iii) The present thesis is concluded with the analysis for de-orbiting satellites at end of mission by electrodynamic tethers. A de-orbit tether system must present very small tether-to-satellite mass ratio and small probability of a tether cut by small debris too. The present work shows how to select tape dimensions so as to minimize the product of those two magnitudes. Preliminary results of tape-tether design are here discussed to minimize that function. Results for de-orbiting Cryosat and Envisat are also presented.

The radiation impedance of electrodynamics tethers in a polar Jovian orbit

Juno, the second mission in the NASA New Frontiers Program, will both be a polar Jovian orbiter, and use solar arrays for power, moving away from previous use of radioisotope power systems (RPSs) in spite of the weak solar light reaching Jupiter. The power generation at Jupiter is critical, and a conductive tether could be an alternative source of power. A current-carrying tether orbiting in a magnetized ionosphere/plasmasphere will radiate waves. A magnitude of interest for both power generation and signal emission is the wave impedance. Jupiter has the strongest magnetic field in the Solar Planetary System and its plasma density is low everywhere. This leads to an electron plasma frequency smaller than the electron cyclotron frequency, and a high Alfven velocity. Unlike the low Earth orbit (LEO) case, the electron skin depth and the characteristic size of plasma contactors affect the Alfven impedance.

An extended electron beam for auroral studies

An electrically floating metallic bare tether in a low Earth orbit would be highly negative with respect to the ambient plasma over most of its length, and would be bombarded by ambient ions. This would liberate secondary electrons, which, after acceleration through the same voltage, would form a magnetically guided two-sided planar e-beam. Upon impact on the atmospheric E-layer, at about 120-140 Km altitude auroral effects (ionization and light emission) can be expected. This paper examines in a preliminary way the feasibility of using this effect as an upper atmospheric probe. It is concluded that significant perturbations can be produced along the illuminated planar sheet of the atmosphere, with ionization rates of several thousand cm-3 sec1. Observation of the induced optical emission is made difficult by the narrowness and high moving speed of the illuminated zone, but it is shown that vertical resolution of single spectral lines is possible, as is wider spectral coverage with no vertical resolution.

Expectations from EMET and OESEE ground listening of possible EM events generated by the TSS 1R

On 22nd February '96, the space mission STS 75 started ,from the NASA facilities at Cape Canaveral. Such a mission consists in the launch of the shuttle Columbia in order to carry out two experiments in the space: the TSS 1R (Tethered Satellite Sistem 1 Refliight) and the USMP (United States Microgravity Payload). The TSS 1R is a replica of a similar mission TSS 1 '92. The TSS space programme is a bilateral scientific cooperation between the USA space agency NASA (National Aeronautics and Space Agency) and the ASI (Italian Space Agency. The TSS 1R system consists on the shuttle Columbia which deploys, up-ward, by means a conducting tether 20 km long, a spherical satellite (1.5 mt diameter) containing scientific instrumentation. This system, orbiting at about 300 km from the Earth's surface, represents, presently, the largest experimental space structure, Due to its dimensions, flexibility and conducting properties of the tether, the system interacts, in a quite complex manner, wih the earth magnetic field and the ionospheric plasma, in a way that the total system behaves as an electromagnetic radiating antenna as well as an electric power generator. Twelve scientific experiments have been assessed by US and Italian scientists in order to study the electro dynamic behaviour of the structure orbiting in the ionos phere. Two experiments have been prepared in the attempt to receive on the Earth's surface possible electromagnetic events radiated by the TSS 1R. The project EMET (Electro Magnetic Emissions from Tether),USA and the project OESEE (Observations on the Earth Surface of Electromagnetic Emissions) Italy, consist in a coordinated programme of passive detection of such possible EM emissions. This detection will supply the verification of some thoretical hypotheses on the electrodynamic interactions between the orbiting system, the Earth's magnetic field and the ionospheric plasma with two principal aims as the technological assesment of the system concept as well as a deeper knowledge of the ionosphere properties for future space applications. A theoretical model that keeps the peculiarities of tether emissionsis being developed for signal prediction at constant tether current. As a step previous to the calculation of the expected ground signal , the Alfven-wave signature left by the tether far back in the ionosphere has been determined. The scientific expectations from the combined effort to measure the entity of those perturbations will be outlined taking in to account the used ground track sensor systems.

An upper atmospheric probe for auroral effects

An electrically floating bare tether in LEO orbit may serve as upper atmospheric probe. Ambient ions bombard the negatively biased tether and liberate secondary electrons, which accelerate through the same voltage to form a magnetically guided planar e-beam resulting in auroral effects at the E-layer. This beam is free from the S/C charging and plasma interaction problems of standard e-beams. The energy flux is weak but varies accross the large beam cross section, allowing continuous observation from the S/C. A brightness scan of line-integrated emissions, that mix emitting altitudes and tether points originating the electrons, is analysed. The tether is magnetically dragged at nighttime operation, when power supply and plasma contactor at the S/C are off for electrical floating; power and contactor are on at daytime for partial current reversal, resulting in thrust. System requirements for keeping average orbital height are discussed.

A "Free-Lunch" tour of the Jovian System

An ED-tether mission to Jupiter is presented. A bare tether carrying cathodic devices at both ends but no power supply, and using no propellant, could move 'freely' among Jupiter's 4 great moons. The tour scheme would have current naturally driven throughout by the motional electric field, the Lorentz force switching direction with current around a 'drag' radius of 160,00 kms, where the speed of the jovian ionosphere equals the speed of a spacecraft in circular orbit. With plasma density and magnetic field decreasing rapidly with distance from Jupiter, drag/thrust would only be operated in the inner plasmasphere, current being near shut off conveniently in orbit by disconnecting cathodes or plugging in a very large resistance; the tether could serve as its own power supply by plugging in an electric load where convenient, with just some reduction in thrust or drag. The periapsis of the spacecraft in a heliocentric transfer orbit from Earth would lie inside the drag sphere; with tether deployed and current on around periapsis, magnetic drag allows Jupiter to capture the spacecraft into an elliptic orbit of high eccentricity. Current would be on at succesive perijove passes and off elsewhere, reducing the eccentricity by lowering the apoapsis progressively to allow visits of the giant moons. In a second phase, current is on around apoapsis outside the drag sphere, rising the periapsis until the full orbit lies outside that sphere. In a third phase, current is on at periapsis, increasing the eccentricity until a last push makes the orbit hyperbolic to escape Jupiter. Dynamical issues such as low gravity-gradient at Jupiter and tether orientation in elliptic orbits of high eccentricity are discussed.

Spherical collectors versus bare tethers for drag, thrust, and power generation

Performances of ED-tethers using either spherical collectors or bare tethers for drag, thrust, or power generation, are compared. The standard Parker-Murphy model of current to a full sphere, with neither space-charge nor plasmamotion effects considered, but modified to best fit TSS1R results, is used (the Lam, Al'pert/Gurevich space-charge limited model will be used elsewhere) In the analysis, the spherical collector is assumed to collect current well beyond its random-current value (thick-heath). Both average current in the bare-tether and current to the sphere are normalized with the short-circuit current in the absence of applied power, allowing a comparison of performances for all three applications in terms of characteristic dimensionless numbers. The sphere is always substantially outperformed by the bare-tether if ohmic effects are weak, though its performance improves as such effects increase.

A theory of electron collection by a grid sphere

Use of a spherical grid as electron collector at the anodic end of a tether, as recently proposed, is considered. The standard analysis of space-charge limited current to a solid sphere (with neither magnetic nor plasma-motion effects), which has been shown to best fit TSS1R in-orbit results at very high bias, is used to determine effects from grid transparency on current collected; the analysis is first reformulated in the formalism recently introduced in the two-dimensional analysis of bare-tethers. A discussion of the electric potential created by a spherical grid in vacuum is then carried out; it is shown that each grid-wire collects current well below its maximum OML current, the effective grid transparency being close to its optical value. Formulae for the current to a spherical grid, showing the effects of grid transparency, is determined. A fully consistent analysis of electric potential and electron density, outside and inside the grid, is completed.

Propellantless de orbiting of space debris by bare electrodynamic tethers

A 3-year Project started on November 1 2010, financed by the European Commision within the FP-7 Space Program, and aimed at developing an efficient de-orbit system that could be carried on board by future spacecraft launched into LEO, will be presented. The operational system will deploy a thin uninsulated tape-tether to collect electrons as a giant Langmuir probe, using no propellant/no power supply, and generating power on board. This project will involve free-fall tests, and laboratory hypervelocity-impact and tether-current tests, and design/Manufacturing of subsystems: interface elements, electric control and driving module, electron-ejecting plasma contactor, tether-deployment mechanism/end-mass, and tape samples. Preliminary results to be presented involve: i) devising criteria for sizing the three disparate tape dimensions, affecting mass, resistance, current-collection, magnetic self-field, and survivability against debris itself; ii) assessing the dynamical relevance of tether parameters in implementing control laws to limit oscillations in /off the orbital plane, where passive stability may be marginal; iii) deriving a law for bare-tape current from numerical simulations and chamber tests, taking into account ambient magnetic field, ion ram motion, and adiabatic electron trapping; iv) determining requirements on a year-dormant hollow cathode under long times/broad emission-range operation, and trading-off against use of electron thermal emission; v) determining requirements on magnetic components and power semiconductors for a control module that faces high voltage/power operation under mass/volume limitations; vi) assessing strategies to passively deploy a wide conductive tape that needs no retrieval, while avoiding jamming and ending at minimum libration; vii) evaluating the tape structure as regards conductive and dielectric materials, both lengthwise and in its cross-section, in particular to prevent arcing in triple-point junctions.

Short tethers for electrodynamic thrust

The operational advantages of electrodynamic tethers of moderate length are becoming evident from studies of collision avoidance. Although long tethers (of order of 10 kilometers) provide high efficiency and good adaptability to varying plasma conditions, boosting tethers of moderate length (- 1 kilometer) and suitable design might still operate at acceptable efficiencies and adequate adaptability to a changing environment. In this paper we carry out a parametric analysis of the performance of 1-km long boosting tethers, to maximize their efficiency. We also discuss the possible use of multiple, parallel such tethers for keeping thrust high when length is decreased. We then estimate the survivability of short tethers to micrometeoroids and orbital debris. Finally, a few considerations are made on the dynamic stability of electrodynamic tether systems versus length.

BETs: Propellant less de orbiting of space debris by bare electrodynamic tethers

As a fundamental contribution to limiting the increase of debris in the Space environment, a three-year project started on 1 November 2010 financed by the European Commission under the FP-7 Space Programme. It aims at developing a universal system to be carried on board future satellites launched into low Earth orbit (LEO), to allow de-orbiting at end of life. The operational system involves a conductive tape-tether left bare of insulation to establish anodic contact with the ambient plasma as a giant Langmuir probe. The project will size the three disparate dimensions of a tape for a selected de-orbit mission and determine scaling laws to allow system design for a general mission. It will implement control laws to restrain tether dynamics in/off the orbital plane; and will carry out plasma chamber measurements and numerical simulations of tether-plasma interaction. The project also involves the design and manufacturing of subsystems: electron-ejecting plasma contactors, an electric control and power module, interface elements, tether and deployment mechanisms, tether tape/end-mass as well as current collection plus free-fall, and hypervelocity impact tests.

Bare wire anodes for electrodynamic tethers

The collection of electrons from the ionosphere is the major problem facing high-power electrodynamic tethers. This article discusses a simple electron-collection concept which is free of most of the physical uncertainties associated with plasma contactors in the rarefied, magnetized environment of an orbiting tether. The idea is to leave exposed a fraction of the tether length near its anodic end, such that, when a positive bias develops locally with respect to the ambient plasma, and for a tether radius small compared with both thermal gyroradius and Debye length, electrons are collected in an orbital-motion-limited regime. It is shown that large currents can be drawn in this way with only moderate voltage drops. The concept is illustrated through a discussion of performance characteristics for generators and thrusters.

Propulsive small expendable deployer system experiment

Relatively short electrodynamic tethers can extract orbital energy to "push" against a planetary magnetic field to achieve propulsion without the expenditure of propellant. The Propulsive Small Expendable Deployer System experiment will use the flight-proven Small Expendable Deployer System to deploy a 5-km bare aluminum tether from a Delta II upper stage to achieve ~0.4-N drag thrust, thus lowering the altitude of the stage. The experiment will use a predominantly bare tether for current collection in lieu of the endmass collector and insulated tether used on previous missions. The flight experiment is a precursor to a more ambitious electrodynamic tether upper-stage demonstration mission that will be capable of orbit-raising,lowering, and inclination changes, all using electrodynamic thrust. The expected performance of the tether propulsion system during the experiment is described.

Bare Tethers for Electrodynamic Spacecraft Propulsion

Electrodynamic tether thrusters can use the power provided by solar panels to drive a current in the tether and then the Lorentz force to push against the Earth's magnetic field, thereby achieving propulsion without the expenditure of onboard energy sources or propellant. Practical tether propulsion depends critically on being able to extract multiamp electron currents from the ionosphere with relatively short tethers (10 km or less) and reasonably low power. We describe a new anodic design that uses an uninsulated portion of the metallic tether itself to collect electrons. Because of the efficient collection of this type of anode, electrodynamic thrusters for reboost of the International Space Station and for an upper stage capable of orbit raising, lowering, and inclination changes appear to be feasible. Specifically, a 10-km-long bare tether, utilizing 10 kW of the space station power could save most of the propellant required for the station reboost over its 10-year lifetime. The propulsive small expendable deployer system experiment is planned to test the bare-tether design in space in the year 2000 by deploying a 5-km bare aluminum tether from a Delta II upper stage to achieve up to 0.5-N drag thrust, thus deorbiting the stage.