Patent ID: 6981672

Claim:
A projectile guidance system comprising: a body portion; a nose portion connected to the body portion by a spin control coupling; said spin control coupling being constructed and arranged so that when the body portion is spinning in a first rotational direction, the nose portion will spin in a second rotational direction; the nose portion including first and second aerodynamic surfaces fixedly attached to the nose portion and configured and arranged to cause the nose portion to spin in the second rotational direction during projectile flight; the nose portion including third and fourth aerodynamic surfaces fixedly attached to the nose portion and being configured and arranged such that when nose portion is spinning the third and fourth aerodynamic surfaces have no net effect on projectile flight, but when the nose portion is despun using the spin control coupling, the third and fourth aerodynamic surfaces induce both a moment and a lateral force to the nose, causing the projectile flight path to change.