Characterization of plasma-sprayed alumina as thermal control coating for micro-satellite applications

2005 ◽  
Vol 219 (2) ◽  
pp. 111-119
Author(s):  
R M Li ◽  
S C Joshi ◽  
H W Ng
Keyword(s):  
Thermal Control ◽  
Processing Parameters ◽  
Thermal Design ◽  
Space Environment ◽  
Solar Arrays ◽  
Barrier Coating ◽  
Satellite Applications ◽  
Good Potential ◽  
Plasma Sprayed

Conventional thermal control materials (TCMs) used in satellites tend to deteriorate in the severe space environment, many times leading to unanticipated mission problems. New and better TCMs are constantly sought to reduce difficulties in satellite thermal design. In this paper, the possibility of using plasma-sprayed alumina (PSA) coating for thermal control of a satellite is examined. Such PSA coatings have proved to be a good thermal barrier coating material for hot section components in aircraft engines. Panels of aluminum alloys such as 2024-T3, 6061-T6, 7075, and so on which are commonly used for satellite applications, form a very compatible substrate for PSA coatings. Various physical and processing parameters and simulated in-service behaviour for PSA were studied analytically and experimentally. Preliminary investigations reveal that the PSA coatings have good potential as a substitute to conventional TCMs for micro-satellite panels, including solar arrays.

Solar Effects on Tensile and Optical Properties of Hubble Space Telescope Silver-Teflon Insulation

2006 ◽  
Vol 929 ◽  
Author(s):  
Kim K. de Groh ◽  
Joyce A. Dever ◽  
Aaron Snyder ◽  
Sharon Kaminski ◽  
Catherine E. McCarthy ◽  
...  
Keyword(s):  
Radiation Effects ◽  
Hubble Space Telescope ◽  
Strong Dependence ◽  
Thermal Control ◽  
Space Environment ◽  
Solar Array ◽  
Solar Absorptance ◽  
Space Telescope ◽  
Solar Arrays ◽  
Solar Exposure

ABSTRACTDuring the fourth servicing mission of the Hubble Space Telescope (HST), the second set of solar arrays (SA-II) was replaced with a third set and the SA-II was brought back to Earth. A section of the retrieved SA-II solar array drive arm (SADA) multilayer insulation (MLI), which experienced 8.25 years of space exposure, was provided to NASA Glenn Research Center for environmental durability analyses of the top layer of silver-Teflon fluorinated ethylene propylene (Ag-FEP). Because the SADA MLI had solar and anti-solar facing surfaces and was exposed to the space environment for a long duration, it provided a unique opportunity to study solar effects on environmental degradation of Ag-FEP, a commonly used spacecraft thermal control material. Therefore, the objective of this research was to characterize the degradation of retrieved HST SADA Ag-FEP with particular emphasis on solar radiation effects. Data obtained included tensile properties, solar absorptance, surface morphology and chemistry. The solar facing surface of the SADA was found to be extremely embrittled and contained numerous through-thickness cracks. Tensile testing indicated that the solar facing surface lost 60% of its mechanical strength and 90% of its elasticity while the anti-solar facing surface had ductility similar to pristine FEP. The solar absorptance of both the solar facing surface (0.155 ± 0.032) and the anti-solar facing surface (0.208 ± 0.012) were found to be greater than pristine Ag-FEP (0.074). Solar facing and anti-solar facing surfaces were microscopically textured, and locations of isolated contamination were present on the anti-solar surface resulting in increased localized texturing. Yet, the overall texture was significantly more pronounced on the solar facing surface indicating a synergistic effect of combined solar exposure and increased heating with atomic oxygen erosion. The results indicate a very strong dependence of degradation, particularly embrittlement, upon solar exposure with orbital thermal cycling having a significant effect.

scholarly journals 3D characterization of porosity in an air plasma-sprayed thermal barrier coating and its effect on thermal conductivity

2018 ◽  
Vol 101 (6) ◽  
pp. 2482-2492 ◽  
Author(s):  
Xun Zhang ◽  
Justyna Kulczyk-Malecka ◽  
James Carr ◽  
Ping Xiao ◽  
Philip  J. Withers
Keyword(s):  
Thermal Conductivity ◽  
Thermal Barrier Coating ◽  
Thermal Barrier ◽  
Air Plasma ◽  
Barrier Coating ◽  
Plasma Sprayed

Atomic Oxygen Resistant Films for Multi-Layer Insulation

2000 ◽  
Vol 12 (1) ◽  
pp. 113-123 ◽  
Author(s):  
Peter Schuler ◽  
H Bob Mojazza ◽  
Ross Haghighat
Keyword(s):  
Atomic Oxygen ◽  
Vacuum Ultraviolet ◽  
Thermal Control ◽  
Radiation Stability ◽  
Low Earth Orbit ◽  
Space Environment ◽  
Advanced Materials ◽  
Validation Tests ◽  
Atomic Oxygen Erosion

A series of advanced polymer films from Triton Systems is being developed to meet the challenges of harsh space environmental effects, lighter weight requirements and superior thermal control performance demands. With support from NASA, Triton Systems Inc has developed advanced new materials for thermal control films with exceptional properties and durability in the space environment. These films known as TOR™ and TOR-LM™ are amber coloured, mechanically sound, produced in continuous rolls and have undergone substantial ground-based simulation and confirming space validation tests. These films are highly resistant to atomic oxygen erosion, and have excellent vacuum ultraviolet radiation stability in ground-based simulation tests. Two applications for these films include large inflatable structures that are either deployed in low earth orbit (LEO) or travel through a LEO orbit into higher orbits, and as outer metallized layers in multi-layer insulation (MLI) blankets. This paper discusses the processing of these advanced materials into thin films, metallization of the films and characterization of their environmental durability as well as other physical, optical, thermal and mechanical properties.

Development, Manufacturing and Verification of Micro-Electro-Mechanical (MEM) Louvres

2006 ◽  
Author(s):  
Klaus Reichenberger ◽  
Jovan Matovic
Keyword(s):  
Control Systems ◽  
European Space Agency ◽  
Thermal Control ◽  
Thermal Design ◽  
Space Technology ◽  
External Radiation ◽  
Space Agency ◽  
Satellite Applications ◽  
Low Mass ◽  
New Generation

MAGNA STEYR Space Technology was authorised by the European Space Agency (ESA) to develop to breadboard level a low mass micro engineered device able to change the heat rejection capability of a radiator and to protect it against external radiation variations. Previous works of MAGNA in the field of thermal control systems was the thermal design, manufacturing and verification of the ROSETTA thermal Louvres [5]. Thermal Louvres in satellite applications are used for thermal control to avoid overheating of the new generation satellites by exposed or shadowed radiator area. The closing and opening of the louvers wings is performed by thermal controlled actuators. The Louvres system is designed to be controlled by solar radiation. The challenge in the project was the design, manufacturing and verification of louvers with less mass but higher efficiency than current louvers.

CHARACTERIZATION OF AS-SPRAYED AND LASER-TREATED ZIRCONIA-BASED PLASMA SPRAYED COATINGS

1990 ◽  
Vol 51 (C5) ◽  
pp. C5-393-C5-402
Author(s):  
A. FERRIERE ◽  
G. FLAMANT ◽  
J.-F. ROBERT ◽  
P. PEKSHEV ◽  
I. SMUROV ◽  
...  
Keyword(s):  
Plasma Sprayed Coatings ◽  
Plasma Sprayed ◽  
Sprayed Coatings

HOT CORROSION OF CERIA-YTTRIA STABILIZED ZIRCONIA PLASMA SPRAYED THERMAL BARRIER COATING BY EUTECTIC VANDIUM PENTAOXIDE-SODIUM SULFATE

2018 ◽  
Vol 18 (1) ◽  
pp. 182-192 ◽  
Author(s):  
Mohammed J Kadhim ◽  
Mohammed H Hafiz ◽  
Maryam A Ali Bash
Keyword(s):  
Thermal Barrier Coating ◽  
Hot Corrosion ◽  
Monoclinic Phase ◽  
Volume Fraction ◽  
High Volume ◽  
Thermal Barrier ◽  
Air Plasma ◽  
Plan View ◽  
Barrier Coating ◽  
Plasma Sprayed

The high temperature corrosion behavior of thermal barrier coating (TBC) systemconsisting of IN-738 LC superalloy substrate, air plasma sprayed Ni24.5Cr6Al0.4Y (wt%)bond coat and air plasma sprayed ZrO2-20 wt% ceria-3.6 wt% yttria (CYSZ) ceramic coatwere characterized. The upper surfaces of CYSZ covered with 30 mg/cm2 , mixed 45 wt%Na2SO4-55 wt% V2O5 salt were exposed at different temperatures from 800 to 1000 oC andinteraction times from 1 up to 8 h. The upper surface plan view of the coatings wereidentified for topography, roughness, chemical composition, phases and reaction productsusing scanning electron microscopy, energy dispersive spectroscopy, talysurf, and X-raydiffraction. XRD analyses of the plasma sprayed coatings after hot corrosion confirmed thephase transformation of nontransformable tetragonal (t') into monoclinic phase, presence ofYVO4 and CeVO4 products. Analysis of the hot corrosion CYSZ coating confirmed theformation of high volume fraction of YVO4, with low volume fractions of CeOV4 and CeO2.The formation of these compounds were combined with formation of monoclinic phase (m)from transformation of nontransformable tetragonal phase (t').

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