An effector having an extendible range and a method for extending the range of an effector includes using an axially translatable center body that is movable from a stowed position, in which the center body is stowed in an outer body of the effector, to a deployed position in which the center body extends out of the outer body to extend the axial length of the effector. The effector includes a ramjet assembly and the subsystems of the effector are contained in the center body. The movement of the center body exposes radially positioned ramjet fuel in the outer body, such that the air entering the ramjet inlet may be heated by combusting the air with the fuel for additional fuel and propulsion of the effector.

A control surface restraining system for variably preventing movement of a control surface imparted by a control actuation shaft of a control actuation section of a tactical flight vehicle includes a power take-off shaft operably connected to the control actuation shaft with a power take-off gear train and a control surface restraint. The control surface restraint is configured to variably engage the power take-off shaft, thereby locking the power take-off gear train and preventing the control actuation shaft from imparting the movement of the control surface. The control surface restraint is also configured to variably disengage the power take-off shaft, thereby unlocking power take-off gear train and allowing the control actuation shaft from imparting the movement of the control surface.

A control surface restraining system for variably preventing movement of a control surface imparted by a control actuation shaft of a control actuation section of a tactical flight vehicle includes a power take-off shaft operably connected to the control actuation shaft with a power take-off gear train and a control surface restraint. The control surface restraint is configured to variably engage the power take-off shaft, thereby locking the power take-off gear train and preventing the control actuation shaft from imparting the movement of the control surface. The control surface restraint is also configured to variably disengage the power take-off shaft, thereby unlocking power take-off gear train and allowing the control actuation shaft from imparting the movement of the control surface.

A projectile incorporates one or more spoiler-tabbed spinning disks to effect flow around the projectile and thus impart steering forces and/or moments. The spoiler tabs may be deployed only during steering phases of travel thus minimizing the drag penalty associated with steering systems. The disks are driven by motors and informed and controlled by sensors and electronic control systems. The spoiler tabs protrude through the surface of the projectile only for certain angles of spin of the spinning disk. For spin-stabilized projectiles, the disks spin at substantially the same rate as the projectile, but the disks may function in fin-stabilized projectiles as well. Any number of such spinning flow effector disks may be incorporated in a projectile, with the manner of functional coordination differing slightly for even and odd numbers of disks.

A projectile incorporates one or more spoiler-tabbed spinning disks to effect flow around the projectile and thus impart steering forces and/or moments. The spoiler tabs may be deployed only during steering phases of travel thus minimizing the drag penalty associated with steering systems. The disks are driven by motors and informed and controlled by sensors and electronic control systems. The spoiler tabs protrude through the surface of the projectile only for certain angles of spin of the spinning disk. For spin-stabilized projectiles, the disks spin at substantially the same rate as the projectile, but the disks may function in fin-stabilized projectiles as well. Any number of such spinning flow effector disks may be incorporated in a projectile, with the manner of functional coordination differing slightly for even and odd numbers of disks.

A lock and release mechanism includes a primary ring with a first surface and a second surface, each surface including a plurality of channels of varying depths. A secondary ring has first and second surfaces, the first surface including a plurality of channels of varying depths. The channels of the secondary ring are aligned with a portion of an opposing channel of the primary ring. Arranged between the primary and secondary rings are a plurality of low friction elements partially arranged within a channel of the primary ring and partially arranged within an opposing channel of the secondary ring. In order to lock and release the mechanism, the primary ring translates relative to the secondary ring such that the bearing balls move within each channel from a first depth to a second depth greater than the first depth.

A lock and release mechanism includes a primary ring with a first surface and a second surface, each surface including a plurality of channels of varying depths. A secondary ring has first and second surfaces, the first surface including a plurality of channels of varying depths. The channels of the secondary ring are aligned with a portion of an opposing channel of the primary ring. Arranged between the primary and secondary rings are a plurality of low friction elements partially arranged within a channel of the primary ring and partially arranged within an opposing channel of the secondary ring. In order to lock and release the mechanism, the primary ring translates relative to the secondary ring such that the bearing balls move within each channel from a first depth to a second depth greater than the first depth.

Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.

A telescoped type ammunition including a case inside which is housed a sub-calibre projectile equipped with a segmented discarding sabot, a propellant charge and an igniting device for the propellant charge, wherein the sub-calibre projectile incorporates a prolonged part receiving a tail fin able to move between a folded position against the prolonged part and a deployed position, the sabot retaining the tail fin in the folded position, the sabot encloses the tail fin to isolate it so as to prevent any contact between the tail fin and the propellant charge.

A projectile including at least one pair of airfoil sections, deployable from housings located inside the body and emerging toward the outside of the projectile. The projectile includes a casing surrounding the body of the projectile and outer surface of which is in profile continuity with the body. The casing can pivot around body along longitudinal axis and includes, for each section, an opening having two zones. A first zone is indented to be positioned, by pivoting of the casing, so as to face a housing in order to allow the section to pass to allow it to be deployed, and second zone located as a recess lateral to the first zone, the recess being oriented along a direction substantially perpendicular to the first zone's longitudinal direction, the second zone having a width allowing the passage of a foot of the deployed section.