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Development of mechanical structure for the compact space IR camera MIRIS

2010; SPIE; Volume: 7731; Linguagem: Inglês

10.1117/12.856364

1996-756X

Bongkon Moon, Woong-Seob Jeong, Sang-Mok Cha, Young‐Sik Park, Chang H. Ree, Dae‐Hee Lee, Sung‐Joon Park, Uk‐Won Nam, Jang‐Hyun Park, Nung Hyun Ka, Mi Hyun Lee, Duk-Hang Lee, Jeonghyun Pyo, Seung-Woo Rhee, Jong‐Oh Park, Hyung Mok Lee, Toshio Matsumoto, Sun Choel Yang, Wonyong Han,

Calibration and Measurement Techniques

MIRIS is a compact near-infrared camera with a wide field of view of 3.67°×3.67° in the Korea Science and Technology Satellite 3 (STSAT-3). MIRIS will be launched warm and cool the telescope optics below 200K by pointing to the deep space on Sun-synchronous orbit. In order to realize the passive cooling, the mechanical structure was designed to consider thermal analysis results on orbit. Structural analysis was also conducted to ensure safety and stability in launching environments. To achieve structural and thermal requirements, we fabricated the thermal shielding parts such as Glass Fiber Reinforced Plastic (GFRP) pipe supports, a Winston cone baffle, aluminum-shield plates, a sunshade, a radiator and 30 layers of Multi Layer Insulation (MLI). These structures prevent the heat load from the spacecraft and the earth effectively, and maintain the temperature of the telescope optics within operating range. A micro cooler was installed in a cold box including a PICNIC detector and a filter-wheel, and cooled the detector down to a operating temperature range. We tested the passive cooling in the simulated space environment and confirmed that the required temperature of telescope can be achieved. Driving mechanism of the filter-wheel and the cold box structure were also developed for the compact space IR camera. Finally, we present the assembly procedures and the test result for the mechanical parts of MIRIS.