PURPOSE: To improve tracking, guiding capacity of a guided missile by preventing saturation of a sensor due to introduction of a solar light to an optical sensor, variably setting a solar light inhibit angle according to a state of a weather, and so flying the missile as to eliminate introduction of a solar light within the inhibit angle.
CONSTITUTION: Effective and reactive solar inhibit angle are previously set to a solar light inhibit angle setter 17 according to a state of a weather, a daytime, a night, etc., and a direction of an optical sensor 1 and a flying route are so controlled by an orbit correction signal generator 18 as not to introduce a solar light into the inhibit angle of the sensor 1 when the inhibit angle is to be effective. Simultaneously, even when the solar light is incident on the sensor 1, if a reception level of the sensor 1 exceeds a redetermined level, a flying route is steered to a route in which the light is not incident on the sensor 1 by a bias signal generator 13.
KIMOTO KENJI
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