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Description
Advancements in thermal interface materials (TIMs) allows for the creation of new and more powerful electronics as they increase the heat transfer from the component to the heat sink. Current industrial options provide decent heat transfer, but the creation of TIMs with higher thermal conductivities is needed. In addition, if these TIMs are elastic in nature, their effectiveness can greatly increase as they can deal with changing interfaces without degradation of their properties. The research performed delves into this idea, creating elastic TIMs using liquid metal (LM), in this case galinstan, along with other matrix particles embedded in Polydimethylsiloxane (PDMS) to create an easy to use, relatively inexpensive, thermally conductive, but electrically insulative, pad with increased thermal conductivity from industrial solutions.
The pads were created using varying amounts of LM and matrix materials ranging from copper microspheres to diamond powder mixed into PDMS using a high-speed mixer. The material was then cast into molds and cured to create the pads. Once the pads were created, the difficulty came in quantifying their thermal properties. A stepped bar apparatus (SBA) following ASTM D5470 was created to measure the thermal resistance of the pads but it was determined that thermal conductivity was a more usable metric of the pads’ performance. This meant that the pad’s in-situ thickness was needed during testing, prompting the installation of a linear encoder to measure the thickness. The design and analysis of the necessary modification and proposed future design is further detailed in the following paper.
The pads were created using varying amounts of LM and matrix materials ranging from copper microspheres to diamond powder mixed into PDMS using a high-speed mixer. The material was then cast into molds and cured to create the pads. Once the pads were created, the difficulty came in quantifying their thermal properties. A stepped bar apparatus (SBA) following ASTM D5470 was created to measure the thermal resistance of the pads but it was determined that thermal conductivity was a more usable metric of the pads’ performance. This meant that the pad’s in-situ thickness was needed during testing, prompting the installation of a linear encoder to measure the thickness. The design and analysis of the necessary modification and proposed future design is further detailed in the following paper.
ContributorsKemme, Nicholas (Author) / Rykaczewski, Konrad (Thesis advisor) / Wang, Robert (Thesis advisor) / Wang, Liping (Committee member) / Arizona State University (Publisher)
Created2017
Description
This research focuses mainly on employing tunable materials to achieve dynamic radiative properties for spacecraft and building thermal management. A secondary objective is to investigate tunable materials for optical propulsion applications. The primary material investigated is vanadium dioxide (VO2), which is a thermochromic material with an insulator-to-metal phase transition. VO2 typically undergoes a dramatic shift in optical properties at T = 341 K, which can be reduced through a variety of techniques to a temperature more suitable for thermal control applications. A VO2-based Fabry-Perot variable emitter is designed, fabricated, characterized, and experimentally demonstrated. The designed emitter has high emissivity when the radiating surface temperature is above 345 K and low emissivity when the temperature is less than 341 K. A uniaxial transfer matrix method and Bruggeman effective medium theory are both introduced to model the anisotropic properties of the VO2 to facilitate the design of multilayer VO2-based devices. A new furnace oxidation process is developed for fabricating high quality VO2 and the resulting thin films undergo comprehensive material and optical characterizations. The corresponding measurement platform is developed to measure the temperature-dependent transmittance and reflectance of the fabricated Fabry-Perot samples. The variable heat rejection of the fabricated samples is demonstrated via bell jar and cryothermal vacuum calorimetry measurements. Thermal modeling of a spacecraft equipped with variable emittance radiators is also conducted to elucidate the requirements and the impact for thermochromic variable emittance technology.
The potential of VO2 to be used as an optical force modulating device is also investigated for spacecraft micropropulsion. The preliminary design considers a Fabry-Perot cavity with an anti-reflection coating which switches between an absorptive “off” state (for insulating VO2) and a reflective “on” state (for metallic VO2), thereby modulating the incident solar radiation pressure. The visible and near-infrared optical properties of the fabricated vanadium dioxide are examined to determine if there is a sufficient optical property shift in those regimes for a tunable device.
The potential of VO2 to be used as an optical force modulating device is also investigated for spacecraft micropropulsion. The preliminary design considers a Fabry-Perot cavity with an anti-reflection coating which switches between an absorptive “off” state (for insulating VO2) and a reflective “on” state (for metallic VO2), thereby modulating the incident solar radiation pressure. The visible and near-infrared optical properties of the fabricated vanadium dioxide are examined to determine if there is a sufficient optical property shift in those regimes for a tunable device.
ContributorsTaylor, Sydney June (Author) / Wang, Liping (Thesis advisor) / Wells, Valana (Committee member) / Yu, Hongbin (Committee member) / Wang, Robert (Committee member) / Thangavelautham, Jekanthan (Committee member) / Massina, Christopher J (Committee member) / Arizona State University (Publisher)
Created2020
Tungsten Trioxide-based Variable Reflectivity Radiation Coatings for Optical Propulsion Applications
Description
This thesis explores the potential application of the phase change material tungsten trioxide (WO3) in optical force modulation for spacecraft and satellites. It starts with a literature review of past space optical force applications as well as potential phase change materials for optical force modulation. This is followed by the theoretical model and discussions of the optical properties of a variety of materials used in the structures explored thereafter. Four planar structures were analyzed in detail. Two of the structures were opaque and the other two were semi-transparent.
The first of the opaque structures was a tungsten trioxide film on aluminum substrate (WO3/Al). It was found to have a 26% relative change in radiation pressure with WO3 thickness of 200 nm. The second opaque structure was a tungsten trioxide film on silicon spacer on aluminum substrate (WO3/Si/Al). This structure was found to have a 25% relative change in radiation pressure with 180 nm WO3 and 20 nm Si.
The semitransparent structures were tungsten trioxide film on undoped silicone substrate (WO3/Si), and a tungsten trioxide film on a silicone spacer on tungsten trioxide (WO3/Si/WO3). The WO3/Si structure was found to have an 8% relative change in radiation pressure with 200 nm WO3 and 50 nm Si. The WO3/Si/WO3 structure had a relative change in radiation pressure of 20% with 85 nm WO3 and 90 nm Si.
These structures show promise for attitude control in future solar sailing space missions. The IKAROS mission proved the functionality of using phase change material in order to steer a space craft. This was accomplished with a 7.8% relative change in radiation pressure. However, this only occurred at a pressure change of 0.11 µN/m2 over a range of 0.4 to 1.0 µm which is approximately 77.1% of the solar spectrum energy. The proposed structure (WO3/Al) with a 26% relative change in radiation pressure with a pressure change of 1.4 µN/m2 over a range 0.4 to 1.6 µm which is approximately 80% of the solar spectrum energy. The magnitude of radiation pressure variation in this study exceeds that used on the IKAROS, showing applicability for future mission.
The first of the opaque structures was a tungsten trioxide film on aluminum substrate (WO3/Al). It was found to have a 26% relative change in radiation pressure with WO3 thickness of 200 nm. The second opaque structure was a tungsten trioxide film on silicon spacer on aluminum substrate (WO3/Si/Al). This structure was found to have a 25% relative change in radiation pressure with 180 nm WO3 and 20 nm Si.
The semitransparent structures were tungsten trioxide film on undoped silicone substrate (WO3/Si), and a tungsten trioxide film on a silicone spacer on tungsten trioxide (WO3/Si/WO3). The WO3/Si structure was found to have an 8% relative change in radiation pressure with 200 nm WO3 and 50 nm Si. The WO3/Si/WO3 structure had a relative change in radiation pressure of 20% with 85 nm WO3 and 90 nm Si.
These structures show promise for attitude control in future solar sailing space missions. The IKAROS mission proved the functionality of using phase change material in order to steer a space craft. This was accomplished with a 7.8% relative change in radiation pressure. However, this only occurred at a pressure change of 0.11 µN/m2 over a range of 0.4 to 1.0 µm which is approximately 77.1% of the solar spectrum energy. The proposed structure (WO3/Al) with a 26% relative change in radiation pressure with a pressure change of 1.4 µN/m2 over a range 0.4 to 1.6 µm which is approximately 80% of the solar spectrum energy. The magnitude of radiation pressure variation in this study exceeds that used on the IKAROS, showing applicability for future mission.
ContributorsVlastos, Joseph Niko (Author) / Wang, Liping (Thesis advisor) / Wang, Robert (Committee member) / Calhoun, Ron (Committee member) / Arizona State University (Publisher)
Created2020