A split-chord deployable wing for aerial vehicles such as missiles, UAVs, MALDs and SDBs that require both longer wing span and increased chord length. Such split-chord deployable wings must address unique problems such as synchronized deployment and integrity of the deployed wing to both vertical and sheer loads. Each wing comprises a pair of wing sections stowed fore and aft along the fuselage. Complementary gear teeth synchronize deployment of the wing sections. A deployment mechanism synchronizes deployment of the wings. Complementary tongue and groove surface portions of the wing sections progressive engage as the wing sections pivot away from the fuselage. The surface portions are segmented so that tongue segments are nested within complementary groove segments to provide both vertical and sheer stability.

A split-chord deployable wing for aerial vehicles such as missiles, UAVs, MALDs and SDBs that require both longer wing span and increased chord length. Such split-chord deployable wings must address unique problems such as synchronized deployment and integrity of the deployed wing to both vertical and sheer loads. Each wing comprises a pair of wing sections stowed fore and aft along the fuselage. Complementary gear teeth synchronize deployment of the wing sections. A deployment mechanism synchronizes deployment of the wings. Complementary tongue and groove surface portions of the wing sections progressive engage as the wing sections pivot away from the fuselage. The surface portions are segmented so that tongue segments are nested within complementary groove segments to provide both vertical and sheer stability.

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.

The invention relates to an artillery projectile (1) which is intended to have a trajectory comprising a ballistic phase and a piloted phase. This projectile (1) has at least one means ensuring its aerodynamic stabilization on part or all of its trajectory and a means (9) intended to ensure a piloting during the piloted phase. This projectile is characterized in that the aerodynamic stabilization means comprises a wing system having at least two wings (16) which are able to positioned with respect to the axis (26) of the projectile, at least during the piloted phase, with their sweepback angles being negative, that is, with the free ends (16b) of the wings (16) being oriented towards the front of the projectile (1).

The invention relates to an artillery projectile (1) which is intended to have a trajectory comprising a ballistic phase and a piloted phase. This projectile (1) has at least one means ensuring its aerodynamic stabilization on part or all of its trajectory and a means (9) intended to ensure a piloting during the piloted phase. This projectile is characterized in that the aerodynamic stabilization means comprises a wing system having at least two wings (16) which are able to positioned with respect to the axis (26) of the projectile, at least during the piloted phase, with their sweepback angles being negative, that is, with the free ends (16b) of the wings (16) being oriented towards the front of the projectile (1).

A airborne vehicle comprising a fuselage, a folding wing-like structure which is movable from a stowed position to a deployed position, and a hinge mechanism which couples the folding wing-like structure to the fuselage in a manner so that the folding wing-like structure displaces and rotates during movement from the stowed position to the deployed position. The hinge mechanism is housed within an outer mold line of the fuselage and folding wing-like structure to decrease the signature of the airborne vehicle.

A airborne vehicle comprising a fuselage, a folding wing-like structure which is movable from a stowed position to a deployed position, and a hinge mechanism which couples the folding wing-like structure to the fuselage in a manner so that the folding wing-like structure displaces and rotates during movement from the stowed position to the deployed position. The hinge mechanism is housed within an outer mold line of the fuselage and folding wing-like structure to decrease the signature of the airborne vehicle.

The present invention is a canister-launched pyrotechnically actuated folding wing UAV. The invention features a method for reliable and irreversible locking of a foldable wing, while enabling compact storage, cost reduction, ease of deployment and aerodynamic performance unattainable in current folding-wing designs. In a specific embodiment, the UAV is pre-packaged in a deployment canister for single-button deployment. The UAV can be offered in a rental system in which part or the entirety of the device can be returned for refurbishing. Additionally, the device can be provided as a fully expendable unit.

An elongate cylindrical projectile including processing circuitry, a head assembly, a tail section assembly, a mid body section positioned between the head assembly and tail assembly, and a wing assembly, the wing assembly including a deployable wing which is stored in a closed position entirely within the mid body section and is deployed, using an actuator, to outside the mid body section in an open position in response to a command from the processing circuitry.