CLeanliness Support of the Launch Vehicle for Putting into Orbit the Spacecraft Meteor-3M with the “Sage-III” Instrument
Abstract
Care should be taken in order to avoid any contamination sources in the design and construction of the fairings. Such sources as the outgassing of organic materials used in the design including fiberglass, heat-shielded fiberglass, etc. as well as the contamination with particulates always remains a problem when dealing with cleanliness issues. A special production process was designed to maintain the required cleanliness levels on the fabrication stage of the fairing. The developed process provided for the cleaning of separate parts and units and preservation of the reached level of cleanliness during the transportation and in-process storage. The requirements to the cleanliness and the developed methodology are described in this paper.
Keywords
Clean Room Solar Array Nonmetallic Material Particulate Contamination Launch SitePreview
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References
- 1.V.G. Tikhii, “About some aspects of changing optical properties of glass in solar arrays and other space materials on exposure to LEO space environment”, eds. J.I. Kleiman and R.C. Tennyson, in: Proceedings of the 3rd International Space Conference, ICPMSE-3, Toronto, Canada, April 25–26, 1996, pp. 203–206.Google Scholar
- 2.V.G. Sitalo, V. G. Tikhiy, “Cleanliness support of vehicle fairing for spacecrafts launch” in: Protection of Materials from the Space Environment, eds. J.I. Kleiman and R.C. Tennyson, Proceedings of the 4th International Conference, ICPMSE-4, Toronto, Canada, April 23–24, 1998, pp. 95–102.Google Scholar
- 3.J. Kleiman, “Surface Modification of Polymers Used in the Low Earth Orbit Space Environment”, Metallized Plastics 5/6, Fundamental and Applied Science, ed. K. Mittal, (1998) 331–351.Google Scholar
- 4.J.I. Kleiman, Z.A. Iskanderova, Y.I. Gudimenko, W.D. Morison, and R.C. Tennyson, “Polymers and Composites in the Low Earth Orbit Space Environment: Interaction and Protection”, Canadian Aeronautic and Space Journal, v.45, No.2, (June 1999), 148–160.Google Scholar