Correlation of predicted and observed optical properties of multilayer thermal control coatings

Abstract

Thermal control coatings on spacecraft will be increasingly important, as spacecraft grow smaller and more compact. New thermal control coatings will be needed to meet the demanding requirements of next generation spacecraft. Computer programs are now available to design optical coatings and one such program was used to design several thermal control coatings consisting of alternating layers of W0 3 and S102. The coatings were subsequently manufactured with electron beam evaporation and characterized with both optical and thermal techniques. Optical data were collected in both the visible region of the spectrum and the infrared. Predictions of solar absorptance and infrared emittance were successfully correlated to the observed thermal control properties. Functional performance of the coatings was verified in a bench top thermal vacuum chamber.

Black Ceramic Thermal Control Coating Prepared by Microarc Oxidation

“…This causes a large temperature change on the vehicle, which is in the range of −200° to 200°C. Hence, the thermal system of the spacecraft must be carefully designed to ensure that the spacecraft and their parts have the fullest working efficiency 1,2 …”

“…Hence, the thermal system of the spacecraft must be carefully designed to ensure that the spacecraft and their parts have the fullest working efficiency. 1,2 The heat exchanged in the spacecraft is limited to radiation in the absence of atmosphere. The equilibrium temperature of any subsystem is controlled by the solar absorptance (a s ) and infrared emittance (e) of its surface.…”

Characterization of Silicon thin Film Deposited by E-Beam Evaporator for Flexible Display

“…[1,2] However this method would be limited by the hydrogen eruption during excimer laser irradiation. [4,5] Our experiment shows that the silicon thin film deposited by e-gun evaporator have a poly-silicon structure. However, some amount of sputter source gases such as Ar and He incorporated in silicon film may cause abruption during the laser annealing process.…”

White anodized thermal control coating on LY12 aluminum alloy

“…spacecraft and the parts of spacecraft are working at their fullest efficiency (Jaworske, 1998(Jaworske, , 1996. The equilibrium temperature of any subsystem of the spacecraft is controlled by the solar absorptance (˛s) and infrared emittance (ε) of its surface (Taylor et al, 1999;Warnes and Schilbe, 2001;Cernuschi et al, 2005).…”