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Mechanical Assessment of Sun Sensors for Launch Environment
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DOI：10.1007/s42496-024-00242-4.png)
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Abstract
En 中文
Sun sensors are widely utilized in satellite attitude determination, particularly within Attitude Determination and Control Systems (ADCS), where accurate characterization of the satellite's orientation stability is crucial. This study aims to qualify sun sensors for new applications, focusing on their positioning and inclination to satisfy mission-specific requirements. The operational environment involves a Polar Satellite Launch Vehicle (PSLV) launcher, with dynamic loads from random vibrations being the predominant stress factor. To align with the ADCS mission requirements of ALSAT 1B observation satellite, the position and inclination angle of the sun sensors were modified, ranging from 70 degrees to 50 degrees. Through a combination of simulations and experimental validation, it was observed that the sun sensors exhibited significant responses due to their location on the satellite. However, subsequent verification procedures revealed no damage to the sensor modules, demonstrating their robustness under these conditions. The results confirm that the sun sensors are adequately qualified for flight, ensuring reliable performance without the risk of failure.
Keywords:
Sun sensors
Random vibration
Experimental test
FEM
Launch environment
Qualification
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