| 摘要 |
The invention relates to an optical recording device in a spacecraft, comprising a detector (14) that is actively cooled by means of a cooling element (32), a lens system that focusses on the detector, an electronic evaluating device, and a housing having a base plate (10) that accommodates the lens system and the matrix detector (14). In order to be able to sufficiently cool the detector (14) and nevertheless arrange the detector in a calibrated manner relative to the lens system, the detector (14) comprises a first connection segment (33) having a first thermal conductivity (41) and a first mechanical stiffness (37), a second connection segment (34) having an intermediately connected cooling element (32), a second thermal conductivity (42) and a second mechanical stiffness (38) between the detector (14) and the cooling element (32), and a third thermal conductivity (44) and a third mechanical stiffness (40) between the cooling element (32) and the base plate (10), wherein the first thermal conductivity (41) is less than the second and third thermal conductivities (42, 44) and the first mechanical stiffness (37) is greater than at least one of the second and third mechanical stiffnesses (38, 40). |
