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|Title:||Outgassing studies on thermal control coatings for micro‐satellites||Authors:||Joshi, Sunil Chandrakant||Keywords:||Coatings
|Issue Date:||2011||Source:||Joshi, S. C. (2011). Outgassing studies on thermal control coatings for micro‐satellites. Aircraft Engineering and Aerospace Technology, 83(2), 69-74.||Series/Report no.:||Aircraft Engineering and Aerospace Technology||Abstract:||Purpose – With the advent of micro‐satellites technology, passive thermal controls in the form of surface coatings have become important for onboard thermal management. The thermal coatings, however, suffer outgassing and mass loss due to their direct exposure to harsh thermal environment and high vacuum in space. The purpose of this paper is to discuss testing and evaluation on outgassing of AA6061‐T6 specimen surfaces treated with various types of anodized coatings of different thicknesses and the related mass loss before and after thermal exposure. Design/methodology/approach – Samples of chromic acid, polytetrafluroethylene polymer, and black‐ and brown‐colour anodized aluminum coupons were subjected to high vacuum (∼1×10−6 mbar), before and after thermal baking at 120°C. Spectrum analysis of the outgassed material to know their quantities and proportion was conducted subsequently using a Quadrupole mass analyzer. Findings – The surface coatings under study complied with the spacecraft requirements for the mass loss of less than 1 percent of the total mass of the coating material used for that surface. The mass spectrum analysis of the outgassed material indicated that the majority of the coating mass loss was on account of water vapours and organic solvents like ethylene. Practical implications – These results provided a good insight into the reliability of the coating materials studied and the bonding between the aluminum substrates and the coatings. Originality/value – The coatings and the technology needed for their application on aluminum are readily available. The present work on outgassing and mass loss in a simulated space environment will provide useful insight on their usage for micro‐satellites.||URI:||https://hdl.handle.net/10356/81013
|ISSN:||0002-2667||DOI:||10.1108/00022661111120953||Rights:||© 2011 Emerald Group Publishing Limited. This is the author created version of a work that has been peer reviewed and accepted for publication by Aircraft Engineering and Aerospace Technology, Emerald Group Publishing Limited. It incorporates referee’s comments but changes resulting from the publishing process, such as copyediting, structural formatting, may not be reflected in this document. The published version is available at: [http://dx.doi.org/10.1108/00022661111120953].||Fulltext Permission:||open||Fulltext Availability:||With Fulltext|
|Appears in Collections:||MAE Journal Articles|
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