Abstract
The study was made on a MEMS-based thermal emissivity variable micro-thermal control device to meet the requirements of the thermal control system of the spacecraft. An emissivity adjustment model for louvers was established. Main parameters that influence the equivalent emissivity of the louver were also investigated. Characteristics such as the electrostatic torque driven by parallel electrodes were modeled and analyzed. As a result, curves of the relationship between angles driven by parallel electrodes and electrostatic torques were obtained. Based on theoretical analysis, the adjustment range of the thermal emissivity was obtained for torsional micro-thermal control devices. The results showed that the properties meet the requirements for the control of space thermal emissivity.
Publisher
Trans Tech Publications, Ltd.
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