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

Author:

CARRUTH, JR. RALPH1,VAUGHN JASON1,HOLT JAMES1,WERP RICHARD2,SUDDUTH RICHARD2

Affiliation:

1. NASA, Marshall Space Flight Center, Huntsville, AL

2. Boeing Defense and Space Group, Huntsville, AL

Publisher

American Institute of Aeronautics and Astronautics

Reference23 articles.

1. Table 111 Flight Configurations Evaluated

2. process, BAC 5884 Type I Class 1. Prior to anodizing, the panels were degreased, alkaline cleaned, and acid deoxidized per specification prior to being immersed in the anodize bath. The anodize bath operated at 95 OF and coatings were applied at 40 volts with a 5 minute ramp time to full voltage. Five different anodizing conditions were evaluated in this study as indicated in Table IV. These different anodizing conditions produced a variation in a and E as well as the thickness of the coating which varied from 1 pm to 3 pm. The anodizing conditions tested ranged on either side of the beginning of life values of a and E for the space station for this study which were: Test Configuration and Experimental Measurements

3. specimens were performed. The test facility consisted of a large cylindrical diffusion pumped vacuum vessel, a hollow cathode plasma source, and the necessary electronics needed to support testing. The chamber is 1.2 m in diameter and 1.8 m long with two cold trapped 8" diffusion pumps. The vacuum facility is capable of a base pressure of 10-7 Torr. Because of the gas load required to operate the plasma source, the operating pressure was in the low 10-4 Torr range during testing.

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1. Ground-Based Experiment of Arcing on Spacecraft Surfaces in Ambient Plasma Environments;JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES;2004

2. ISS and space environment interactions without operating plasma contactor;39th Aerospace Sciences Meeting and Exhibit;2001-01-08

3. Space environmental effects testing in support of the International Space Station;38th Aerospace Sciences Meeting and Exhibit;2000-01-10

4. A model of plasma contactor behavior in the laboratory;34th Aerospace Sciences Meeting and Exhibit;1996-01-15

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