A spaceborne cooler micro-vibration isolation system with capability of launch vibration attenuation according to the present invention comprises a fixated shaft having one end fixated and connected to a vibration generating source mounted on a satellite; a fixated shaft cover installed to wrap the fixated shaft in an axial direction; a displacement restraint block (20) through which a shaft body (32) of the fixated shaft cover (30) penetrates, forming an in-plane displacement restraint hole for preventing penetration of a shaft displacement restraint body (31) and having one side coming into contact with an end of the shaft displacement restraint body (31); a support bracket (10) coupled to the displacement restraint block (20) and including a head (11) forming a housing space for housing the shaft displacement restraint body (31) of the fixated shaft cover (30) therein and a left and right leg (13,14) extended to make a regular angle from the head (11); and a damper unit (40) including a string (45) installed on an outer side of the head (11) of the support bracket (10) to be radially arranged with respect to the shaft displacement restraint body (31) of the fixated shaft cover (30), wrapping the outer surface of the shaft displacement restraint body (31) in a circumferential direction and having a regular tensile force, and a damper part connected to the string (45) passing through a string penetration hole formed in the head (11) of the support bracket (10) for absorbing vibration generated at the fixated shaft (100).
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