Patent ID: 6758435
Filing Date: 2004-07-06
Classification: F42B

Abstract:
A missile comprising(a) a missile body having a longitudinal axis and (b) a guide assembly mounted on said missile body; said guide assembly including (1) a plurality of pivots; (2) a plurality of vanes mounted on respective said pivots for a swinging motion about a pivotal axis between a folded position of rest and a deployed flight position; each said vane having a length dimension; said vanes being arranged for free pivotal motion during flight in response to forces acting thereon to determine said flight position; each said vane having a center of gravity that, in said folded position of each vane, is at a greater distance from said longitudinal axis than said pivotal axis of each vane; and (3) abutments limiting said flight position of said vanes to a maximum angle between said length dimension and said longitudinal axis; said maximum angle being greater than 90Â°. wherein the abutments limit said maximum angle to an angle that is greater than positional angle of the vanes in a state of force equilibrium during flight.