FIELD: missile guidance systems.
SUBSTANCE: present method for guidance of a spinning missile consists in forming a modulated emission by a launcher, receiving said emission by the missile, generating vertical and horizontal steering control signals, forming three-position relay periodical signals depending on the missile roll angle and forming a two-position relay signal. Said two-position relay signal is formed during each period of the missile's spinning about the roll axis on the basis of the vertical and horizontal steering control signals according to the specified dependences.
EFFECT: enhancement of the guidance accuracy of missiles spinning about their roll axis and having relay controlled steering devices.
2 cl, 7 dwg
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