FIELD: weapons and ammunition.
SUBSTANCE: invention relates to guided spinning missiles. The small-sized guided spinning missile comprises the electronic control equipment, control units, and an inertial measurement unit. The inertial measurement unit comprises three micromechanical gyroscopes (MMG) and a biaxial linear acceleration sensor (LAS) placed on a common panel mounted perpendicular to the longitudinal axis X of the missile rotation. The electronic control equipment comprises a microcontroller of preliminary treatment and conversion of signals of three MMG and biaxial LAS into signals corresponding to the transverse axes Y and Z, and a non-volatile reprogrammable memory device for storing the calibration coefficients.
EFFECT: improving the accuracy of targeting and increasing the firing range with the guided missile.
2 dwg
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Authors
Dates
2015-08-27—Published
2014-04-25—Filed