STUDIES FOR IMPROVED HIGH TEMPERATURE COATINGS FOR SPACE SHUTTLE APPLICATION.

J. Creedon; R. Banas; Steve Garofalini

STUDIES FOR IMPROVED HIGH TEMPERATURE COATINGS FOR SPACE SHUTTLE APPLICATION.

Rutgers University

Research output: Chapter in Book/Report/Conference proceeding › Chapter

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

ASJC Scopus subject areas

Engineering(all)

Access to Document

Fingerprint Dive into the research topics of 'STUDIES FOR IMPROVED HIGH TEMPERATURE COATINGS FOR SPACE SHUTTLE APPLICATION.'. Together they form a unique fingerprint.

Cite this

@inbook{0637659e108b4c3db39ac723f5ab295a,

title = "STUDIES FOR IMPROVED HIGH TEMPERATURE COATINGS FOR SPACE SHUTTLE APPLICATION.",

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.",

author = "J. Creedon and R. Banas and Steve Garofalini",

year = "1979",

language = "English",

pages = "82--93",

booktitle = "National SAMPE Technical Conference",

publisher = "SAMPE (v 11)",

note = "Natl SAMPE Tech Conf 11th, New Horiz - Mater and Processes for the Eighties ; Conference date: 13-11-1979 Through 15-11-1979",

}

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)

T2 - Natl SAMPE Tech Conf 11th, New Horiz - Mater and Processes for the Eighties

Y2 - 13 November 1979 through 15 November 1979

ER -