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Atomic oxygen interaction at defect sights in protective coatings on polymers flown on ldef
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Gebauer, Linda Auer, Bruce M. Banks, Bruce A. Degroh, Kim K. Lamoreaux, Cynthia |
| Copyright Year | 1993 |
| Description | Although the Long Duration Exposure Facility (LDEF) has exposed materials with a fixed orientation relative to the ambient low-Earth-orbital environment, arrival of atomic oxygen is angularly distributed as a result of the atomic oxygen's high temperature Maxwellian velocity distribution and the LDEF's orbital inclination. Thus, atomic oxygen entering defects in protective coatings on polymeric surfaces can cause wider undercut cavities than the size of the defect in the protective coating. Because only a small fraction of atomic oxygen reacts upon first impact with most polymeric materials, secondary reactions with lower energy thermally accommodated atomic oxygen can occur. The secondary reactions of scattered and/or thermally accommodated atomic oxygen also contribute to widening the undercut cavity beneath the protective coating defect. As the undercut cavity enlarges, exposing more polymer, the probability of atomic oxygen reacting with underlying polymeric material increases because of multiple opportunities for reaction. Thus, the effective atomic oxygen erosion yield for atoms entering defects increases above that of the unprotected material. Based on the results of analytical modeling and computational modeling, aluminized Kapton multilayer insulation exposed to atomic oxygen on row 9 lost the entire externally exposed layer of polyimide Kapton, yet based on the results of this investigation, the bottom surface aluminum film must have remained in place, but crazed. Atomic oxygen undercutting at defect sites in protective coatings on graphite epoxy composites indicates that between 40 to 100 percent of the atomic oxygen thermally accommodates upon impact, and that the reaction probability of thermally accommodated atomic oxygen may range from 7.7 x 10(exp -6) to 2.1 x 10(exp -3), depending upon the degree of thermal accommodation upon each impact. |
| File Size | 962094 |
| Page Count | 16 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19940026519 |
| Archival Resource Key | ark:/13960/t3615z81c |
| Language | English |
| Publisher Date | 1993-12-01 |
| Access Restriction | Open |
| Subject Keyword | Nonmetallic Materials Temperature Distribution Earth Orbital Environments Kapton Trademark Aluminum Probability Theory Maxwell-boltzmann Density Function Velocity Distribution High Temperature Defects Cavities Oxygen Atoms Metal Films Polyimides Graphite-epoxy Composites Mathematical Models Multilayer Insulation Protective Coatings Long Duration Exposure Facility Erosion Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
