A Carbon Fiber Reinforced Polymer (CFRP) optical bench has been developed for the Tunable Magnetograph instrument (TuMag) for the SUNRISE III mission. This mission is within the NASA Long Duration Balloon Program and it consists of 1-meter aperture telescope with three post-focal instruments to study the solar dynamics. One of them is TuMag: a diffraction-limited imager, a high sensitivity polarimeter and a high-resolution spectrometer. The composite material has been selected for the optical bench due to its lightweight, low sensitivity to thermal gradients and low coefficient of thermal expansion (CTE). Additionally, to the flight model optical bench, a breadboard model identical to the flight model has been manufactured including optical fiber Bragg temperature and strains sensors embedded in its upper skin. The goal is to demonstrate that the use of distributed fiber Bragg gratings (FBGs) can provide valuable information for strain and temperature mapping of an optical instrument onboard a payload, during its operation and its on-ground testing. Furthermore, surface mounted strain FBG sensors and thermocouples have been installed in the optical bench for intercomparison purposes. In this paper the results obtained for a thermal-vacuum test are presented. It consists of three thermal cycles with stabilization steps at 100ºC, 60ºC, 20ºC and -20ºC. The FBG embedded temperature sensors results have been compared with the surface mounted thermocouples; the FBG embedded strain sensor results have been compared to the surface mounted strain sensors.
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