On the expansion of ionospheric plasma into the near‐wake of the space shuttle orbiter

Stone, N. H.; Wright, K. H.; Samir, Uri; Hwang, K. S.

doi:10.1029/gl015i010p01169

Cited by 19 publications

(15 citation statements)

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“…Counterstreaming ion beams are present in the wake [Stone et al, 1988], and ion heating could occur as a result of the two-stream ion-ion instability, which would convert part of the directed energy of the accelerated ion streams into thermal energy [Singh et al, 1986]. The fact that ion density increases monotonically as a function of separation distance in the midwake suggests that the two-stream ion-ion instability, and subsequent ion heating, may occur only when the ion streams have a density above a critical value.…”

Section: Discussionmentioning

confidence: 99%

“…Ions are accelerated toward the wake axis along their entire trajectory, beginning when they first pass the body and ending when they reach the wake axis. Singh et al [ 1989] showed that for the ion streams crossing the wake axis observed by Stone et al [1988] on Spacelab 2, a model based on the plasma expansion process could account for the experimental observations with good quantitative agreement.…”

Section: Introductionmentioning

confidence: 99%

“…Qualitatively, the near wake is the region immediately behind the obstacle and is characterized by an absence of particles, the midwake is the region where distinct converging ion streams cross the wake axis, and the far wake is where ion streams, if they can be distinguished, diverge from the wake axis. For the Orbiter, a floating body with a radius much larger than the sheath thickness, crossing streams are present as close as 13.7 m downstream [Stone et al, 1988], which gives an upper bound to the start of the midwake. At a downstream distance of 40 m, distinct ion streams were not seen by the differential ion flux probe (DIFP), so this point is taken as the beginning of the far wake.…”

Section: Introductionmentioning

confidence: 99%

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Change in ion distribution function while crossing the space shuttle wake

Sorensen¹,

Stone²,

Wright³

1997

J. Geophys. Res.

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Section: Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Change in ion distribution function while crossing the space shuttle wake

Sorensen¹,

Stone²,

Wright³

1997

J. Geophys. Res.

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“…0148-0227/99/1998JA900071 $09.00 Stone et al, 1988], and, recently, measurements have been made of the Moon's plasma wake [Ogilvie et al, 1996]. Both electrostatic and thermal processes contribute to filling the wake [Crow et al, 1975].…”

Section: Paper Number 1998ja900071mentioning

confidence: 99%

High‐voltage interactions in plasma wakes: Simulation and flight measurements from the Charge Hazards and Wake Studies (CHAWS) experiment

Davis¹,

Mandell²,

Cooke³

et al. 1999

J. Geophys. Res.

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Abstract. The Charge Hazards and Wake Studies (CHAWS) flight experiment flew on the Wake Shield Facility (WSF) aboard STS-60 and STS-69. The experiment studied highvoltage current collection within the spacecraft wake. The wake-side sensor was a 45-cmlong, biasable cylindrical probe mounted on the 3.66-m-diameter WSF. Operations were performed in free flight and at various attitudes while on the shuttle orbiter remote manipulator system (RMS) arm. Preflight and postflight simulations were performed using the programs Potentials of Large Objects in the Auroral Region (POLAR) and Dynamic Plasma Analysis Code (DynaPAC) and are compared here with the flight results. Both programs perform three-dimensional, self-consistent, steady state plasma simulations. During high-voltage operations the wake-side probe collected current consistent with preflight predictions. In both the flight data and the steady state simulations the current collected has a power law dependence on the potential and has a less than linear dependence on density. Growth of the sheath beyond the WSF edge controls the highvoltage current collection, and kinematic and space charge effects both play important roles in attracting ions into the wake region. Measurements made at low voltage differ from the calculations. The preflight calculations for a pure oxygen plasma predict a collection threshold at -100 V bias. The flight data show little or no threshold, implying a source of ions not accounted for in the simulations. Possible sources for these ions are discussed. BackgroundLow-Earth-orbiting spacecraft have velocities higher than the thermal speed of the ions and lower than the thermal speed of the electrons of the surrounding plasma. Figure 1 shows the basic structure of a spacecraft wake. The ion and electron densities immediately behind the spacecraft are dramatically reduced because only ions with velocities comparable to the spacecraft velocity (corresponding to an energy of about 5 eV) can exist in this "deep wake" region. The electron density would be near uniform were it not for the negative potential due to electron space charge. Samir et al.

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“…The investigations, shown in Table 1 Satellite-ionospheric interactions under controlled conditions unique to the TSS-1R can also be used to study the collisionless expansion of plasma into the void region of the satellite's wake [Stone et al, 1988]. This process has many potential applications in space and was suggested as a mechanism for closure of the wake of the Moon in the solar wind plasma by Samir et al [1983].…”

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The TSS‐1R Mission: Overview and scientific context

Stone

Bonifazi

1998

Geophysical Research Letters

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Mission BackgroundThe Tethered Satellite System (TSS) program is a binational collaboration between NASA and the Italian Space Agency (ASI) with NASA providing the Shuttle-based deployer and tether and ASI providing a satellite especially designed for tethered deployment. Twelve science investigations (see Table 1) were supported by NASA, ASI, or the Air Force Philips Laboratory. The goals of the TSS-1R mission, which was the second flight of the TSS hardware, were to provide unique opportunities to explore (1) certain space plasma-electrodynamic processes--particularly those involved in the generation of ionospheric currents, and (2) the orbital mechanics of a gravity-gradient stabilized system of two satellites linked by a long conducting tether.TSS-1R was launched February 22, 1996 on STS-75 into a 300-km, circular orbit at 28.5 ø inclination. Satellite flyaway occurred at MEF 3/00:27 and a unique data set was obtained over the next 5 hours as the tether was deployed to a length of 19,695 m. At MET 3/05:11, during a day pass, the tether suddenly broke near the top of the deployer boom. The break resulted from a flaw in the tether insulation which allowed the ignition of a strong electrical discharge that melted the tether. The operations that had begun at satellite flyaway, however, allowed significant science to be accomplished. Instrumentation and MeasurementsThe TSS converted mechanical energy into electrical energy in a classical demonstration of Faraday's law. The configuration was such that the satellite received a positive bias and collected electrons from the ionosphere, which conducted through the tether to the orbiter where the circuit could be closed back to the ionosphere (see Fig. 1 sphere. An electrical schematic is shown in Figure 3 of Dobrowolny and Stone [1994].The TSS was instrumented to control the tether current (as described above) and diagnose the environmental space plasma properties under highly nonequilibrium conditions. The investigations, shown in Table 1

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On the expansion of ionospheric plasma into the near‐wake of the space shuttle orbiter

Cited by 19 publications

References 9 publications

Change in ion distribution function while crossing the space shuttle wake

Change in ion distribution function while crossing the space shuttle wake

High‐voltage interactions in plasma wakes: Simulation and flight measurements from the Charge Hazards and Wake Studies (CHAWS) experiment

The TSS‐1R Mission: Overview and scientific context

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