FIELD: guidance systems; self-guidance systems of aircraft on ground targets. SUBSTANCE: relative bearing and angular velocity of target sight line in horizontal plane are determined by means of relative relationships depending on mode of operation of on-board radar system from moment of detection till use of destructive means. Signal of control in horizontal plane is shaped in form of algebraic sum of lateral acceleration of guided aircraft and guidance error at respective coefficients by relative bearing and angular velocity of target sight line in horizontal plane by law given in Specification. Proposed method makes it possible to use one law of aircraft control for bringing the aircraft to point at given range at preset relative bearing and at required angular velocity of target sight line for use of different destructive means at any mode of operation of on-board radar system. Besides that, required linear resolving power is ensure. EFFECT: enhanced accuracy of guidance; proper engagement of various modes of operation. 14 dwg
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