Abstract
In the present study, long term durability of the candidate material for the next radio astronomy satellite under space environment were investigated. The materials were high modulus PAN based carbon fiber reinforced polycyanate ester and epoxy. In order to simulate the space environment, thermal cycle tests between -197 and 120 ℃ were conducted. Surface observations and bending modulus measurements were also conducted. Transverse cracks in 90 ° plies were observed at 1 cycle and the number of crack increased with cycles. Bending modulus, however remain constant during thermal cycles. Microscopic damage in carbon fiber reinforced polycyanate ester was suppressed at the late stage of the thermal cycle. This result indicated the long term durability for carbon fiber reinforced polycyanate ester was superior.
