Plasma effects on the passive external thermal control coating of Space Station Freedom

Carruth, Ralph; Vaughn, Jason A.; Holt, James M.; Werp, Richard; Sudduth, Richard D.

doi:10.2514/6.1992-1685

Cited by 6 publications

(3 citation statements)

References 2 publications

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“…(1)(2)(3)(4)(5) resultsin an electron temperaturein the ori ce of about 2 eV for a wide range of hollow cathode parameters. Figure 3 shows electron temperature in the ori ce as a function of gas ow rate.…”

Section: Electron Temperaturementioning

confidence: 99%

of Plasma Contactor Performance

Katz

Gardner

Mandell

et al. 1997

Journal of Spacecraft and Rockets

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A hollow cathode-based plasma contactor will be own on the international space station to control the station's potential to within 40 V of the local ionosphere. Extensive testing of the plasma contactor has been conducted in vacuum facilities at the NASA Lewis Research Center. Signi cant performance differences were observed between tests of the same plasma contactor in different facilities. Why measured plasma contactor performance differs in the laboratory in different tank environments and how the plasma contactor performance measured in the laboratory relates to expected performance in space is addressed. Presented are models of plasma contactor plasma generation and interaction in a laboratory environment, including anode area limiting. These models were integrated using the Space Station Environment Work Bench to predict plasma contactor operation, and the results are compared with the laboratory measurements. Nomenclature F= gas ow rate, standard cubic centimeter per minute I D = total ori ce electron current, A I emission = ori ce current emitted, A I keeper = keeper electrode current, A I loss = ion loss rate, A I max = maximum possible electron current, A I prod = total ion production rate, A J e = electron current density, A m 2 L = ori ce length, m m = neutral atom mass, kg m e = electron mass, kg m i = ion mass, kg N n = neutral density, m 3 r = ori ce radius, m W conv = power loss by electron convection, W W ion = power loss by ionization, W W rad = power loss by radiation, W e = ori ce electron temperature, eV i = ion temperature, eV in = insert region electron temperature, eV n = neutral gas temperature, eV = electrical conductivity, ohm m 1 ion = ionization cross section, m 3 rad = inelastic cross section, m 3 p = electron plasma frequency, rad s 1

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Section: Electron Temperaturementioning

confidence: 99%

of Plasma Contactor Performance

Katz

Gardner

Mandell

et al. 1997

Journal of Spacecraft and Rockets

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“…[1][2][3][4][5][6][7][8]. As a result of evaluation of these effects, the decision was made to add a plasma contactor system to ISS to control the voltage between the ISS structure and the local plasma, thereby preventing any voltage driven interactions.…”

Section: Figure 1 Iss Assembly Complete Configurationmentioning

confidence: 99%

ISS and space environment interactions without operating plasma contactor

Carruth

Ferguson

Suggs

et al. 2001

39th Aerospace Sciences Meeting and Exhibit

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Solar arrays on the International Space Station operate at 160 volts. The negative side of the power system is grounded to ISS structure. The high voltage solar arrays coupled with ISS design and materials properties can lead to detrimental interactions with the ionospheric plasma. A plasma contactor on ISS provides a "ground wire" to control the voltage between the ISS structure and local plasma and prevents such interactions. An evaluation of possible effects that could result in the event of plasma contactor failure was undertaken and is reported in this paper. In general, any identified impacts on ISS function take several months of contactor malfunction to develop. Possible hazard to crewmembers on EVA are addressed and sufficient controls have been put in place. NOMENCLATURE ASurface Area AC Assembly Complete

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“…Xenon atoms and ions will be emitted by the plasma eontactor which will be operated on ISS. Its purpose is to ground the ISS structure relative to the local plasma (Carruth, 1992). Also, thrusters used for attitude control and station reboost will contribute to the neutral and plasma environment when they are operational.…”

Section: Iss External Environmentmentioning

confidence: 99%

An environment monitoring package for the international space station

Carruth¹,

Clifton²

1999

AIP Conference Proceedings

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Abstract. The first elements of the International Space Station (ISS) will soon be launched into space and over the next few years ISS will be assembled on orbit into its final configuration. Experiments will be performed on a continuous basis both inside and outside the station. External experiments will be mounted on attached payload locations specifically designed to accommodate experiments, provide data and supply power from ISS. From the beginning of the space station program it has been recognized that experiments will require knowledge of the external local environment which can affect the science being performed and may impact lifetime and operations of the experiment hardware. Recently an effort was initiated to design and develop an Environment Monitoring Package (EMP). This paper describes the derivation of the requirements for the EMP package, the type of measurements that the EMP will make and types of instruments which will be employed to make these measurements.

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Plasma effects on the passive external thermal control coating of Space Station Freedom

Cited by 6 publications

References 2 publications

of Plasma Contactor Performance

of Plasma Contactor Performance

ISS and space environment interactions without operating plasma contactor

An environment monitoring package for the international space station

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