A precision guided munition with a fin assembly comprising a free spinning hub to which the fins attach addresses the need to roll control a projectile while eliminating the problems of the fin kit. The fin hub, to which the fins are attached, is radially decoupled from the mortar tail boom thus allowing it and the fins to spin freely relative to the body without coupling any of the spin. Advantageously, the need for a bearing between the hub and the tail boom is negated.

A propellant driven disrupter (PDD) for disrupting an explosive target, comprising: a disrupter barrel having a breech and muzzle end; a projectile liquid or gas positioned in the barrel and extending a longitudinal distance in the disrupter barrel. The projectile liquid distal end is located farthest from the disrupter barrel breech end. A jet stabilizing projectile (JSP) is at least partially positioned in the barrel and operably contacts the projectile liquid distal end. The JSP has a JSP proximal end facing toward the disrupter barrel breech end and a distal end opposed to the JSP proximal end, wherein some or all of the JSP is positioned in the barrel. The PDD may contain the JSP, with an air region between the JSP distal end and the muzzle end, or an air region in an adapter that is connected to the muzzle end. Also provided are JSP's having improved flight stability for use with liquid or air-filled disrupters and methods of disrupting a target.

A propellant driven disrupter (PDD) for disrupting an explosive target, comprising: a disrupter barrel having a breech and muzzle end; a projectile liquid or gas positioned in the barrel and extending a longitudinal distance in the disrupter barrel. The projectile liquid distal end is located farthest from the disrupter barrel breech end. A jet stabilizing projectile (JSP) is at least partially positioned in the barrel and operably contacts the projectile liquid distal end. The JSP has a JSP proximal end facing toward the disrupter barrel breech end and a distal end opposed to the JSP proximal end, wherein some or all of the JSP is positioned in the barrel. The PDD may contain the JSP, with an air region between the JSP distal end and the muzzle end, or an air region in an adapter that is connected to the muzzle end. Also provided are JSP's having improved flight stability for use with liquid or air-filled disrupters and methods of disrupting a target.

A color marker projectile, which is intended as a non-lethal projectile to mark a hit with color, is located in the projectile itself and is poured over the target on impact. The projectile is launched from a conversion kit (new barrel and bolt) of a real weapon. The color marker projectile includes a front part, a rear part, an inserted element and a color filler. The front part is formed as a semicircular cylindrical part with vertical ribs. The inserted element is positioned to complete the concluded cylindrical part of the front part. The color filler and the inserted element are positioned on the inside of the front part. The color filler is located at the contact point between the front part and the rear part.

A projectile (10) for firing from a barrel (12) of a firearm has an elongated tubular body (14) with a leading end (16), a trailing end (18) and a passage (100) extending through the body (14) and opening onto the leading end (16). An insert (102) is disposed in the passage (100). A cavity (20) is formed in the body (14) between the insert (102) and the trailing end (18) for holding a volume of propellant. A seal arrangement (22) is formed on the body (14) and located between and in-board of the leading end (16) and the trailing end (18). The seal arrangement (22) extends circumferentially about body to form a substantial seal against an inner circumferential surface of the barrel (12). A driving band (28) is supported on the body (14) between the seal arrangement (22) and the trailing end (18) and arranged to maintain substantial coaxial alignment of the body (14) of the projectile and the barrel (12) of the firearm while the projectile travels along the barrel (12). The driving band (28) has one or more flow paths (38) that enable fluid communication between opposite axial ends of the driving band (28).

A projectile (10) for firing from a barrel (12) of a firearm has an elongated tubular body (14) with a leading end (16), a trailing end (18) and a passage (100) extending through the body (14) and opening onto the leading end (16). An insert (102) is disposed in the passage (100). A cavity (20) is formed in the body (14) between the insert (102) and the trailing end (18) for holding a volume of propellant. A seal arrangement (22) is formed on the body (14) and located between and in-board of the leading end (16) and the trailing end (18). The seal arrangement (22) extends circumferentially about body to form a substantial seal against an inner circumferential surface of the barrel (12). A driving band (28) is supported on the body (14) between the seal arrangement (22) and the trailing end (18) and arranged to maintain substantial coaxial alignment of the body (14) of the projectile and the barrel (12) of the firearm while the projectile travels along the barrel (12). The driving band (28) has one or more flow paths (38) that enable fluid communication between opposite axial ends of the driving band (28).

Launching an aeronautical system can comprise applying force or energy to the system in connection with accelerating the system. Responsive to the force or energy, an element of the system can move along a defined path within the system. The system can comprise a drive that converts motion along the defined path into rotational motion. The drive can rotate a mass within the system, which can be supported by a gas bearing. The rotating mass can comprise the moving element, a different system element, or the entire system. The rotating mass can produce angular momentum and can support gyroscopic stabilization of the aeronautical system. Rotational energy can be selectively imparted to and transferred between system elements in connection with stabilization management. System elements can moderate the system's response to impulsive stimuli associated with rotation and acceleration. A gas bearing can support an external surface of the system during launch.

A guided projectile including a precision guidance munition assembly utilizes angular rate sensors to sample a first angular velocity of the precision guidance munition assembly from the first angular rate sensor at a first time, sample a second angular velocity of the precision guidance munition assembly from the second angular rate sensor at the first time, generate a coning command based, at least in part, on the first angular velocity and the second angular velocity, and apply the coning command to the canard assembly. The range may be decreased or increased based on the coning commands.

The present invention relates to projectiles and munitions, and more specifically to such in flight. More particularly the present invention relates to projectiles and munitions in flight equipped with one or more image sensors adapted for acquiring image data of the environment surrounding the projection or munition in flight. The present invention further relates to systems and methods for correcting or stabilizing motion effects and artifacts present in the image data related to the movement or motion of the projectile or munition in flight, including spin or rotation of the projectile or munition.

The present invention relates to projectiles and munitions, and more specifically to such in flight. More particularly the present invention relates to projectiles and munitions in flight equipped with one or more image sensors adapted for acquiring image data of the environment surrounding the projection or munition in flight. The present invention further relates to systems and methods for correcting or stabilizing motion effects and artifacts present in the image data related to the movement or motion of the projectile or munition in flight, including spin or rotation of the projectile or munition.