NOSES OF SPIN-STABILIZED MISSILES Russian patent published in 2024 - IPC F42B10/16 

FIELD: rocket engineering.

SUBSTANCE: used in the development of noses of the spin-stabilized missiles. The nose of the spin-stabilized missiles contains a warhead, a fuse, a control system, a satellite navigation unit, inertial sensors, a power source, steering actuators, four aerodynamic rudders located in the body of the nose, and a mechanism for their deployment at the command of the control system. The length of the tip chord of the rudder is equal to (0.03-0.18)D, where D is the calibre of the rocket. The distance between the leading edges of the rudders in the folded position is (0.2-0.6)D. The steering wheel mounting axes are mounted at a distance L from the front end of the nose, equal to (2.1-4.2) D, and the length of the trailing edge is equal to (0.1-0.4) L.

EFFECT: providing the specified control parameters of a rotating missile while maintaining the weight and size characteristics, as well as ensuring the required reliability parameters of the nose.

3 cl, 3 dwg