FIELD: astronautics.
SUBSTANCE: invention relates to space navigation and can be used for rapid accurate determination of spacecraft orientation relative to inertial coordinate system. Device for determining celestial orientation of object includes a housing, an optical system, a lens hood, a matrix radiation receiver, a computing device, electronic memory with onboard navigation catalogue stars. Well arrangement of the sensor is used, wherein the optical system and blind are combined into central module, partially located inside the housing of the sensor, the blind is holder of the optical system, and central module is the housing cover. Around the central module there is a single electronic board which is fixed to side walls and case base with screws. Board comprises flexible sections, at which the Board is bent so that the main fuel elements are pressed to side walls of the housing and matrix radiation receiver to case base. Note here that heat release from the walls and base of the housing is conducted by heat exchange due to heat conductivity through at least three fastening lugs of the body base and partially by radiant heat exchange with inner surface of the built-in blind. In the board under lower surface of the radiation detector array is arranged thermoelectric cooler Peltier in contact with housing base through a heat-conducting paste or gasket.
EFFECT: reduced weight and overall dimensions, as well as high heat removal.
3 cl, 6 dwg
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Authors
Dates
2016-03-20—Published
2015-02-04—Filed