Abstract: The coolant supply to a cooler for the detector of an optical seeker in a missile is to be controlled; the missile is arranged in a launcher attached to an aircraft. A caging device for caging the movable seeker optical system of the seeker is provided in the seeker. For target tracking, this caging device is releasable, before operation of the missile, by a release signal through a control line extending from the cockpit of the aircraft to the launcher. This control line is simultaneously used for controlling the coolant supply by providing a bistable circuit on the missile side of the control line, activation of the coolant supply being effected by setting the bistable circuit, the setting and resetting of the bistable circuit being determined by the variation in time of the release signal.

Abstract: An optical seeker comprises a rotor (16) mounted on a bearing sleeve (42) to pivot about a pivot point (26) and to rotate about an axis of rotation (28). The rotor (16) carries an imaging system having a concave mirror (50) and a secondary mirror (52). The optical axis of concave mirror (50) and secondary mirror (52) form an angle with the axis of rotation (28). A sunshade (54) is connected to the rotor (16). The bearing sleeve (42) carries an optical element (56). An axle portion (58) is provided on the element (56), on which axle portion the secondary mirror (52) is mounted. The secondary mirror (52) is connected to the sunshade (54) through a stepping-up planetary gear having internal toothing (72), planet wheel (76) and external toothing (78). The planet wheel (76) is mounted on a carrier (74) connected with the axle portion (58).