Satellite

Client: Taiwan Space Agency (TASA)

Keywords: Satellite; Optical payload; Carbon Fiber Cylinder; Low Moisture Absorption; Rigidity; Strength; Thermal Deformation; Natural Frequency and Modal Shapes.

This project focuses on the design analysis, prototyping, and test validation of a carbon fiber composite cylinder for a satellite optical payload. The Formosat-5 satellite, developed by the Taiwan Space Agency (TASA), utilized a composite truss structure to support its optical payload. In contrast, the Formosat-8 aims to design a simpler, easier-to-assemble composite cylinder.

TOPU uses low-moisture-absorption carbon fiber prepreg in the laminate design to meet the required rigidity, strength, and thermal deformation specifications. Due to the extremely high precision requirements of the satellite optical payload, it must endure harsh conditions from assembly and installation on the ground to placement in the rocket fairing, rocket launch, high-speed flight, and entry into Earth's orbit. These conditions include rocket ignition, separation, structural impact and vibration induced by aerodynamics, and drastic changes in temperature and humidity. Even during the prototype manufacturing stage, the effects of molds and processes must be considered in the design phase.

Finally, after autoclave curing, the composite cylinder prototype undergoes testing validation. The structural weight, natural frequency, modal shapes, and thermal deformation data all meet TASA's specifications.