METHOD FOR SEPARATION OF GUIDED MISSILE NOSE BLOCK WITH HOMING HEAD AND DEVICE FOR ITS REALIZATION Russian patent published in 2003 - IPC

FIELD: military equipment, in particular, guided ammunition. SUBSTANCE: communication element of the nose block with the missile body are destructed, the nose block is displaced in the axial direction, and the side force acts on it for deflection from the flight trajectory. Deflection is effected due to the turn of the control surfaces about the axis at the instant of separation and subsequent turn of the block by the control surfaces through the angle of attack with the incoming flow of air. The missile nose block body is made in the form of a thin-walled ogival-shaped fairing, rigidly fastened to the cylinder, whose longitudinal axis coincides with the missile axis. A pair of control surfaces is installed on a common axle in the plane of symmetry of the nose block for angular displacements. The axle of the control surfaces is in front of the nose block center of gravity, but behind the own aerodynamic center of pressure of the control surfaces, it is provided with a limiter of angular displacements and fixed from turning by a rod. The rod is rigidly fastened to a stop fixed on the piston and installed coaxially with the missile longitudinal axis in front of the cylinder. EFFECT: enhanced reliability of functioning of the guided missile at the instant of separation of the nose block at an expanded range of flight velocities and probable angles of attack. 2 cl, 3 dwg