Tungsten Trioxide-based Variable Reflectivity Radiation Coatings for Optical Propulsion Applications

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.