Abstract
Several concepts for improvement of the current Class 2 Space Shuttle Orbiter RCG coating were investigated experimentally under NASA Contract, NAS2-9809. Coatings, which are applied to LI-900 or LI-2200 tiles were prepared to provide increased performance in the areas of thermal expansion, impact, residual strain and increased viscosity. Turbulent duct arc-plasma tests at NASA/Ames Research Center are continuing on two candidates that show improved low residual strain and increased high temperature viscosity. In the course of this investigation, a coating system with lower fusion-temperature (1950 degree F) was identified. This coating has the potential of significantly improving tile yield through reduced LI-900 shrinkage and distortion since it can be fused at 250 degree F lower than the present Class 2 coating.
| Original language | English |
|---|---|
| Title of host publication | National SAMPE Technical Conference |
| Publisher | SAMPE (v 11) |
| Pages | 82-93 |
| Number of pages | 12 |
| Publication status | Published - 1979 |
| Event | Natl SAMPE Tech Conf 11th, New Horiz - Mater and Processes for the Eighties - Boston, Mass Duration: Nov 13 1979 → Nov 15 1979 |
Other
| Other | Natl SAMPE Tech Conf 11th, New Horiz - Mater and Processes for the Eighties |
|---|---|
| City | Boston, Mass |
| Period | 11/13/79 → 11/15/79 |
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ASJC Scopus subject areas
- Engineering(all)
Cite this
STUDIES FOR IMPROVED HIGH TEMPERATURE COATINGS FOR SPACE SHUTTLE APPLICATION. / Creedon, J.; Banas, R.; Garofalini, Steve.
National SAMPE Technical Conference. SAMPE (v 11), 1979. p. 82-93.Research output: Chapter in Book/Report/Conference proceeding › Chapter
}
TY - CHAP
T1 - STUDIES FOR IMPROVED HIGH TEMPERATURE COATINGS FOR SPACE SHUTTLE APPLICATION.
AU - Creedon, J.
AU - Banas, R.
AU - Garofalini, Steve
PY - 1979
Y1 - 1979
N2 - Several concepts for improvement of the current Class 2 Space Shuttle Orbiter RCG coating were investigated experimentally under NASA Contract, NAS2-9809. Coatings, which are applied to LI-900 or LI-2200 tiles were prepared to provide increased performance in the areas of thermal expansion, impact, residual strain and increased viscosity. Turbulent duct arc-plasma tests at NASA/Ames Research Center are continuing on two candidates that show improved low residual strain and increased high temperature viscosity. In the course of this investigation, a coating system with lower fusion-temperature (1950 degree F) was identified. This coating has the potential of significantly improving tile yield through reduced LI-900 shrinkage and distortion since it can be fused at 250 degree F lower than the present Class 2 coating.
AB - Several concepts for improvement of the current Class 2 Space Shuttle Orbiter RCG coating were investigated experimentally under NASA Contract, NAS2-9809. Coatings, which are applied to LI-900 or LI-2200 tiles were prepared to provide increased performance in the areas of thermal expansion, impact, residual strain and increased viscosity. Turbulent duct arc-plasma tests at NASA/Ames Research Center are continuing on two candidates that show improved low residual strain and increased high temperature viscosity. In the course of this investigation, a coating system with lower fusion-temperature (1950 degree F) was identified. This coating has the potential of significantly improving tile yield through reduced LI-900 shrinkage and distortion since it can be fused at 250 degree F lower than the present Class 2 coating.
UR - http://www.scopus.com/inward/record.url?scp=0018711632&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=0018711632&partnerID=8YFLogxK
M3 - Chapter
AN - SCOPUS:0018711632
SP - 82
EP - 93
BT - National SAMPE Technical Conference
PB - SAMPE (v 11)
ER -