United States and Russian Thermal Control Coating Results in Low Earth Orbit

Tribble, Alan C.; Lukins, R.; Watts, Ed; Borisov, V. A.; Demidov, S. A.; Denisenko, V. A.; Gorodetskiy, A. A.; Grishin, V. K.; Nauma, S. F.; Sergeev, V. K.; Sokolova, S. P.

doi:10.2514/3.55722

Cited by 39 publications

(9 citation statements)

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“…Atomic oxygen (AO) with high activity is dominant species in the LEO space environment and can cause the oxidation and performance deterioration of space materials [1,2]. Therefore, for the space materials used in the LEO, the AO effect must be took into discreet consideration.…”

Section: Introductionmentioning

confidence: 99%

Changes in the structure and tribological property of Ag film by LEO space environment exposure

Gao¹,

Hu²,

Sun³

et al. 2014

Applied Surface Science

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Section: Introductionmentioning

confidence: 99%

Changes in the structure and tribological property of Ag film by LEO space environment exposure

Gao¹,

Hu²,

Sun³

et al. 2014

Applied Surface Science

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“…The ions are accelerated in a negative-potential sheath on a solar array, and the current generated by the solar array is leaked by the impact of the ions; the solar array is still degraded by sputtering and arcing due to the collected ions [2], [3]. Accordingly, the environmental factors cause changes in the chemical structures of the spacecraft materials and their optical and/or electrical properties [4]- [6]. In GEO satellites, it is well known that the electrical breakdown of negative charging on their insulating surfaces causes intensive damages in the systems.…”

Section: Introductionmentioning

confidence: 99%

Ground-Based Experiment of Electric Breakdown of Spacecraft Surface Insulator in an Ambient Plasma Environment

Tahara

Masuyama

2006

IEEE Trans. Plasma Sci.

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In the future, LEO spacecraft will be larger and higher powered. Because of the balance of the leakage currents through the ambient space plasma, their main conductive body will have a higher negative potential without plasma contactor operation. When the spacecraft operates with a higher voltage, more intensive arcing is suspected to occur on the surface. In this study, a ground-based experiment was carried out to understand the arcing phenomenon and to examine the influences of the ambient space plasma on the arcing process. Simulating plasmas were generated by electron-cyclotron-resonance discharge. When arcing occurred on negatively biased anodized-aluminum-sample (AAS) plates in the plasma environment, the time variations in the arc current and bias voltage were measured. The arc-spot diameter was also measured. The single-arcing characteristics showed that both the peak arc current and the total charge emitted by arcing increased with the initial-charging voltage and neutralparticle number density. The diameter of the arc spot increased with the initial-charging voltage although it was almost constant regardless of the neutral-particle density. The repetitive-arcing characteristics showed that the arc rate gradually increased with the arcing number. Lots of overlapping arc spot were observed after 1000 arcings, and its number increased with the arcing number. The influences of the initial-charging energy on arcing characteristics were also examined by widely changing the capacitance and the initial-charging voltage. The arc-spot diameter intensively increased with the initial-charging energy, and the fitting line could be evaluated. Accordingly, a high-voltage operation of the LEO spacecraft might bring a drastic degradation of AAS by arcing, depending on the ambient plasma conditions and spacecraft capacitance.Index Terms-Anodized aluminum, arc plasma, arc spot, discharge characteristics, electric breakdown, ground-based experiment, insulator surface, spacecraft environment, space-plasma environment.

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“…However, for some applications, it must withstand exposure to some extreme operation conditions in low earth orbit (LEO, 200-1000 km) space environment, where atomic oxygen (AO) is a dominant species and exhibits a high activity, flux (~10 13 -10 15 atoms·cm −2 ·s − 1 ) as well as kinetic energy (~5 eV) for an orbit vehicle surface with an orbital velocity of 8 km·s −1 [5,6] and can cause the oxidation and performance deterioration of metallic Ag [7][8][9][10][11][12][13][14][15].…”

Section: Introductionmentioning

confidence: 99%

LEO space environment exposure resistant behavior of Ag–Cu films

Gao

et al. 2015

Surface and Coatings Technology

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United States and Russian Thermal Control Coating Results in Low Earth Orbit

Cited by 39 publications

References 1 publication

Changes in the structure and tribological property of Ag film by LEO space environment exposure

Changes in the structure and tribological property of Ag film by LEO space environment exposure

Ground-Based Experiment of Electric Breakdown of Spacecraft Surface Insulator in an Ambient Plasma Environment

LEO space environment exposure resistant behavior of Ag–Cu films

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