Abstract: Controlling an in-flight spin-rate of a spin-stabilized guided projectile is disclosed. In various embodiments, the projectile includes a despun control portion configured for despinning relative to a projectile chassis and for directional control of the projectile. In various embodiments, controlling the in-flight spin-rate includes determining a gyroscopic stability factor for the guided projectile using the in-flight spin rate and a forward velocity of the guided projectile, determining that the gyroscopic stability factor exceeds a stability threshold, and spin-braking the guided projectile, in response to determining that the gyroscopic stability factor exceeds a threshold value, by braking rotation of the despun control portion by which the gyroscopic stability factor of the guided projectile is reduced to a second gyroscopic stability factor.

Abstract: A projectile and a method of launching a projectile from a barrel. The projectile of the present invention may be matched to a pre-selected barrel rifling to produce a controlled spin rate. Controlled spin rate is characterized by substantially balanced forward and axial deceleration. Substantially balanced forward and axial deceleration is characterized by an axial speed that decreases in relationship to the decrease in forward speed. Substantially balanced forward and axial deceleration produces a trajectory that is characterized by a gyroscopic stability factor that remains highly stable over a given distance of a trajectory. Gyroscopic stability is controlled during the projectile's flight by controlling the spin damping moment as a design element. Control of the spin damping moment may be achieved by incorporating physical features in the projectile's design and manufacture and/or may result from the incorporation of physical features imparted upon the projectile during launch.

Abstract: A projectile and a method of launching a projectile from a barrel. The projectile of the present invention may be matched to a pre-selected barrel rifling to produce a controlled spin rate. Controlled spin rate is characterized by substantially balanced forward and axial deceleration. Substantially balanced forward and axial deceleration is characterized by an axial speed that decreases in relationship to the decrease in forward speed. Substantially balanced forward and axial deceleration produces a trajectory that is characterized by a gyroscopic stability factor that remains highly stable over a given distance of a trajectory. Gyroscopic stability is controlled during the projectile's flight by controlling the spin damping moment as a design element. Control of the spin damping moment may be achieved by incorporating physical features in the projectile's design and manufacture and/or may result from the incorporation of physical features imparted upon the projectile during launch.

Abstract: A projectile having a body including a waist segment having a diameter substantially equal to a caliber of the projectile, and a fore segment continuous to and extending forward from the waist segment. The body includes a bore formed along a longitudinal axis of the projectile and extending from a leading edge of the fore segment through the body to a floor of the bore located at a first depth from the leading edge of the fore segment. The projectile also includes a tip segment having a which is inserted within the bore. A void is formed between a butt end of the tip segment and the floor of the bore. Upon impact, the tip segment is displaced rapidly through the body causing rapid expansion of the projectile followed by fragmentation as the tip segment is displaced through the body of the projectile.

Abstract: A projectile including a body having a land segment, a tapered body segment continuous to and extending forward from the land segment and a conical nose segment continuous to and extending forward from the tapered body segment. The projectile may include a tapered tail segment continuous to and extending rearward from the land segment. The conical nose segment may be configured as a conical nose segment. The projectile may include an angular transition between the conical nose segment and the tapered body segment.