| 摘要 |
FIELD: defense equipment, in particular, guided projectiles and rockets spin-stabilized flight. ^ SUBSTANCE: the projectile has a body and a control section with a control actuator positioned in it, warhead, tail section with aerodynamic stabilizers and a gyroscope with a contactless transmitter in the form of a photon-coupled pair with radiators and photodiodes secured in it in pairs, and a raster installed in the slot between them, fastened on the axle of the outer frame of the gyroscope. The prelaunch angular position of the photon-coupled pair of the transmitter is shifted relative to the plane passing through the axis of the control surfaces if the control actuator and the projectile longitudinal axis towards the direction of projectile spinning by an angle equal to the angle of its turn in flight during the time of delayed execution of control commands by the control actuator. The working section of the raster is divided into four sectors, one of which is transparent, the second one opposite to it is non-transparent, an the two others are positioned symmetrically between the first and second ones, and made in the form of alternating transparent and non-transparent sections positioned concentrically to the raster axis and radially to it. The surface of the working section of the raster and the slot of the photon-coupled pair of the transmitter, between the elements of the opton-coupled pairs, have a low reflectivity, and the dimensions of the transparent and non-transparent sections of the raster exceed the dimensions of the sensitive surface of the photodiodes of the opton-coupled pairs. ^ EFFECT: enhanced accuracy of projectile hitting of the target by reducing its vibration relative to the sight line during flight in the trajectory. ^ 3 cl, 4 dwg |
