A system of missile control surfaces includes a control surface housing, a control surface shaft which is rotatably mounted in the control surface housing, a control surface secured on the control surface shaft, a control surface drive and a coupling unit. The coupling unit couples the control surface drive to the control surface shaft in such a way that a movement of the control surface drive produces a rotation of the control surface shaft. To enable high forces to be applied reliably to a guided missile control surface, it is proposed that the coupling unit has at least one flexible tension element, which is secured on the control surface drive and is rolled up onto the control surface shaft to a certain extent.

Launch vehicles with ring-shaped external elements, and associated systems and methods are disclosed. An aerospace system in accordance with a particular embodiment includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction. A propulsion system can be carried by the launch vehicle, and can have at least one nozzle positioned toward the first end of the vehicle to launch the vehicle. A controller can be in communication with the launch vehicle and programmed to direct the vehicle in the first direction during vehicle ascent, and in the second direction during vehicle descent.

A missile including an upper stage and at least one lower stage is provided. The upper stage includes a primary flight computer configured to control a flight of the upper stage along a missile flight path such that, for example, it reaches a predetermined target. The lower stage is mounted to the upper stage and includes a propellant for initially propelling the upper stage along the missile flight path. The lower stage is configured to be jettisoned from the upper stage when the propellant is spent. The lower stage includes a secondary flight computer configured to receive data from the primary flight computer prior to the propellant of the lower stage being spent, and to control a flight of the lower stage along a jettisoned stage flight path of the jettisoned lower stage such that, for example, the jettisoned lower stage glides to a predetermined safe landing zone

A battlefield weapon system is proposed to counter the threat posed by small drones. The main system element is an aerodynamically guided missile that is compatible with existing multipurpose shoulder launched weapon systems. The system is fully portable for dispersed deployment among infantry.

A battlefield weapon system is proposed to counter the threat posed by small drones. The main system element is an aerodynamically guided missile that is compatible with existing multipurpose shoulder launched weapon systems. The system is fully portable for dispersed deployment among infantry.

A munition including: a control surface actuation device including: an actuator having two or more pistons, each of the pistons being movable between an extended and retracted position, the retracted position resulting from an activation of each of the two or more pistons; and a movable rack having a pocket corresponding to each of the two or more pistons, each pocket being engageable with a corresponding portion of each of the two or more pistons, a distance between the pockets being different than a distance between the portions of the two or more pistons, such that activation of the portion into the corresponding pocket sequentially translates the rack; and a control surface operatively connected to the rack such that translation of the rack rotates the control surface.

A munition including: a control surface actuation device including: an actuator having two or more pistons, each of the pistons being movable between an extended and retracted position, the retracted position resulting from an activation of each of the two or more pistons; and a movable rack having a pocket corresponding to each of the two or more pistons, each pocket being engageable with a corresponding portion of each of the two or more pistons, a distance between the pockets being different than a distance between the portions of the two or more pistons, such that activation of the portion into the corresponding pocket sequentially translates the rack; and a control surface operatively connected to the rack such that translation of the rack rotates the control surface.

A device for blocking a fin of a projectile, the fin including a fin base pivoting about a pivot pin secured to the body of the projectile between a withdrawn fin position and a deployed fin position, wherein the device includes at least one recess housing at least one shape of revolution pushed by a resilient means between a first surface borne by the fin and a second surface borne by the body of the projectile, at least one of the two surfaces forming a ramp that converges toward the other surface to tend to cause jamming of the shape of revolution between the two surfaces.

A device for blocking a fin of a projectile, the fin including a fin base pivoting about a pivot pin secured to the body of the projectile between a withdrawn fin position and a deployed fin position, wherein the device includes at least one recess housing at least one shape of revolution pushed by a resilient means between a first surface borne by the fin and a second surface borne by the body of the projectile, at least one of the two surfaces forming a ramp that converges toward the other surface to tend to cause jamming of the shape of revolution between the two surfaces.

A method for deploying a control surface from an exterior surface of a spinning projectile during flight is provided. The method including: at least partially retracting the control surface into an interior of the projectile for a portion of a full revolution of the spinning projectile and extending the control surface from the interior of the projectile for another portion of the full revolution of the spinning projectile; and maintaining the control surface in a same plane during the full revolution of the spinning projectile.