Composite materials application on FORMOSAT-5 remote sensing instrument structure

  • Author(s): Jen-Chueh Kuo, Heng-Chuan Hung, Mei-Yi Yang, Chia-Ray Chen, and Jer Lin
  • DOI: 10.3319/TAO.2016.04.17.01(EOF5)
  • Keywords: CTE CFRP RSI
  • Citation: Kuo, J. C., H. C. Hung, M. Y. Yang, C. R. Chen, and J. Lin, 2017: Composite materials application on FORMOSAT-5 remote sensing instrument structure. Terr. Atmos. Ocean. Sci., 28, 157-165, doi: 10.3319/TAO.2016.04.17.01(EOF5)
  • Manufacturing process of CFRP materials on FORMOSAT-5 RSI structure was verified
  • Launch load impacts on RSI structure integrity were assessed and verified
  • RSI structure moisture desorption methodology has been effectively applied

Composite material has been widely applied in space vehicle structures due to its light weight and designed stiffness modulus. Some special mechanical properties that cannot be changed in general metal materials, such as low CTE (coefficient of thermal expansion) and directional material stiffness can be artificially adjusted in composite materials to meet the user’s requirements. Space-qualified Carbon Fiber Reinforced Plastic (CFRP) composite materials are applied In the FORMOSAT-5 Remote Sensing (RSI) structure because of its light weight and low CTE characteristics. The RSI structural elements include the primary mirror supporting plate, secondary mirror supporting ring, and supporting frame. These elements are designed, manufactured, and verified using composite materials to meet specifications. The structure manufacturing process, detailed material properties, and CFRP structural element validation methods are introduced in this paper.

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