고열전도성 그라파이트 시트의 열 스트랩을 이용한 소형 위성용 적외선 카메라의 열 설계 및 검증
Thermal design and validation ofIR camera for the small satellite using thermal strap with high-thermal-conductive graphite sheet
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This study presents a passive thermal control system employing a high thermal conductivity graphite sheet thermal strap, designed for a small satellite infrared camera. The strap was fabricated by sandwiching a pre-cut graphite sheet between aluminum flanges and bonding the interface with adhesive to prevent damage from clamping pressure. Orbital thermal analysis was conducted using commercial software (Hypermesh for the geometrical mathematical model and Thermal Desktop’s Radcad and SINDA/FLUINT for the thermal mathematical model), simulating worst hot and cold cases. The simulation verified that the optical components (maintained at 25±5 °C) and the infrared detector (kept below 35 °C) remain within their allowable temperature ranges. Thermal balance tests in a thermal vacuum chamber at –150 °C and pressures below 1×10⁻⁵ Torr confirmed effective heat conduction through the thermal strap (~1.7 W/°C). These results demonstrate the suitability of the thermal strap with graphite sheet for enhanced thermal management in small satellites.
Abstract
This study presents a passive thermal control system employing a high thermal conductivity graphite sheet thermal strap, designed for a small satellite infrared camera. The strap was fabricated by sandwiching a pre-cut graphite sheet between aluminum flanges and bonding the interface with adhesive to prevent damage from clamping pressure. Orbital thermal analysis was conducted using commercial software (Hypermesh for the geometrical mathematical model and Thermal Desktop’s Radcad and SINDA/FLUINT for the thermal mathematical model), simulating worst hot and cold cases. The simulation verified that the optical components (maintained at 25±5 °C) and the infrared detector (kept below 35 °C) remain within their allowable temperature ranges. Thermal balance tests in a thermal vacuum chamber at –150 °C and pressures below 1×10⁻⁵ Torr confirmed effective heat conduction through the thermal strap (~1.7 W/°C). These results demonstrate the suitability of the thermal strap with graphite sheet for enhanced thermal management in small satellites.