Satellite Positive-Ion-Beam System

Masek, T. D.; Cohen, H. A.

doi:10.2514/3.57284

Cited by 16 publications

(3 citation statements)

References 7 publications

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“…An ion gun was installed on the SCATHA spacecraft to investigate the efficiency of an ion emission system in modifying satellite potentials [Masek and Cohen, 1978]. The Air Force Geophysics Laboratory ion gun experiment (SC4-2) was successfully used to develop negative voltages on the vehicle [Werner, 1988].…”

Section: Ion Gunmentioning

confidence: 99%

Spacecraft‐generated ions

Olsen¹,

Norwood²

1991

J. Geophys. Res.

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Electrostatic analyzer measurements of ions on the SCATHA satellite show evidence of locally generated ions. These measurements come during periods of large negative charging (~-100 to -10,000 V) at or near geosynchronous altitude. Ions are observed at energies below the satellite potential, which, in the absence of scattering, must have been generated on or near the satellite surface. Differential charging measurements from the Surface Satellite Potential Monitor indicated that there were surfaces with the proper magnitude of differential charging to provide a source for the observed ions. Application of the Sigmund-Thompson theories on sputtering show that ambient 10-to100-keV O+ on glass should provide a yield of 0.5 to 1.0 particles per incident ion. Roughly 2-4% of this yield is ionized. This is sufficient to explain the flux levels observed. Particle tracking using the NASA Charging Analyzer Program (NASCAP) showed that the energies measured provided a sweep of trajectories along the satellite surface, but no specific source was identified.

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Section: Ion Gunmentioning

confidence: 99%

Spacecraft‐generated ions

Olsen¹,

Norwood²

1991

J. Geophys. Res.

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“…An ion source, designated SC4-2, was provided to emit neutralized and nonneutral beams, at energies of 1 and 2 kV, at nominal currents of 0.3, 1.0, and 2.0 mA. Xenon propellant was utilized in the hollow cathode based system [Masek and Cohen, 1978]. The beam neutralization was provided by filament neutralizers, which could be biased in voltage and set at fixed current levels.…”

Section: The Scatha Programmentioning

confidence: 99%

Plasma wave observations during Ion Gun Experiments

Olsen¹,

Weddle²,

Roeder³

1990

J. Geophys. Res.

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Experiments in charge control on the AF/NASA P78‐2 (SCATHA) satellite were conducted with a plasma/ion source in the inner magnetosphere. These experiments were monitored with plasma wave instruments capable of high temporal and frequency resolution in the 0–6 kHz frequency range. Ion gun experiments revealed two distinct classes of behavior. Nonneutralized ion beam operation at 1 mA, 1 kV resulted in arcing signatures (spiky in time, broad frequency range), coincident with induced satellite potentials of −600 to −900 V. This signature disappeared when the accelerating voltage was switched off or the beam was neutralized (at which time the satellite body approached potentials of a few volts). The signal is attributed to arcing between differentially charged surfaces. An additional feature was noted in the 100‐kHz channel of the wave receiver. During emission of dense, low‐energy plasma, a signal is generated which may be at the upper hybrid, or plasma frequency for the local plasma.

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“…Various options to generate and control the charge were considered in [27]. Electron or ion beam emissions [30][31][32][33] are the most common methods to generate charge on-board. However, the net charge that can be generated is controlled by spacecraft charging, which can attract some of the emitted charged particles back, as well as the space charge limit of the beam, which will form a virtual electrode at the beam exit to cap the transmission of an un-neutralized beam at the space charge limit [32][33][34].…”

Section: Introductionmentioning

confidence: 99%

Hovering of an Electrically Actuated Spacecraft in a Small-Body Plasma Field

Bechini

Quadrelli

Lavagna

et al. 2021

Journal of Spacecraft and Rockets

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The paper presents simulation models and an analysis of the hovering capability of an electrostatic spacecraft around a small celestial body. The hovering capabilities of an electrically actuated spacecraft are evaluated by combining orbital dynamics analysis with threedimensional fully kinetic particle-in-cell simulations of asteroid/spacecraft interactions with the solar wind plasma. The zero velocity curves obtained from the analysis allow the identification of the equilibrium points for different levels of charge. The analysis of the system equilibria indicates the presence of equilibrium points in the combined gravitational, electrostatic, and solar illumination field, most of which can be obtained by charging the spacecraft negatively. The charge-to-mass ratio needed to hover is obtained for different orbital positions, and an analysis of the sensitivity of the equilibria with respect to the spacecraft equivalent radius and with respect to the Sun-to-Main Body distance provides additional insight into the system dynamics. Nomenclature d Main-Body-to-Sun distance, m h Angular Momentum, m 2 /s a Semi-Major Axis, m e Eccentricity, -

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Satellite Positive-Ion-Beam System

Cited by 16 publications

References 7 publications

Spacecraft‐generated ions

Spacecraft‐generated ions

Plasma wave observations during Ion Gun Experiments

Hovering of an Electrically Actuated Spacecraft in a Small-Body Plasma Field

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