ThermoVideoSystem for Installation on Spacecraft

Abstract

The termovideosystem with possibility of use of thermoprotection and protection of objectives and devices with charging communication from influence of radiating factors for videocameras, the space vehicles located near to thermoloaded elements and carrier rockets for tracing of thermoconditions by means of video telemetry is considered. The thermocasing model, its key parametres and characteristics is presented. Expressions for selection of a thickness of a thermolayer depending on flying time of carrier rockets, and also a thickness of a thermolayer for preset time of influence of temperature are received. The example of thermoprotection videocameras with the set diameter of a eye of an objective and flying time of carrier rockets for a basic orbit is resulted. It is offered to use the periscopic device for protection against influence of radiating factors of lenses of objectives and devices with charging communication. Expressions for the size of mirrors of a periscope, and also for an angle of rotation of mirrors of periscopes are resulted at simultaneous use of two videocameras directed on one image box of object.