A protection covering for folded tail fins of a projectile. The protection covering is installed to surround outer portion of the folded tail fins of the projectile and protects the tail fins against external high pressure, whereby the tail fins are not damaged even at high pressure generated in a launching process of the projectile. After the launch of the projectile, the protection covering is separated from the projectile by the pressure applied on the inner side surface of the circular plate portion of the protection covering by the accumulated combustion gas inside the air pocket. The protection covering is automatically separated from the projectile without providing any other mechanical structure immediately after the launch of the projectile, thereby providing an effect to allow the tail fins to be deployed quickly and economically.

A projectile includes a housing and a slot formed in the housing. A deployable flight surface is inside the housing. A cover is attached to the housing and covers the slot. A cutter is adjacent the cover and moves in the slot and slices the cover to open the slot and allow deployment of the flight surface through the slot.

A projectile includes a housing and a slot formed in the housing. A deployable flight surface is inside the housing. A cover is attached to the housing and covers the slot. A cutter is adjacent the cover and moves in the slot and slices the cover to open the slot and allow deployment of the flight surface through the slot.

Embodiments include active protection systems and methods for an aerial platform. An onboard system includes one or more radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the plurality of 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 a rocket motor to accelerate the eject vehicle along an intercept vector, alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, and divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector. The eject vehicle activates at least one of the alignment thrusters responsive to the intercept vector.

Embodiments include active protection systems and methods for an aerial platform. An onboard system includes one or more radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the plurality of 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 a rocket motor to accelerate the eject vehicle along an intercept vector, alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, and divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector. The eject vehicle activates at least one of the alignment thrusters responsive to the intercept vector.

A folding wing for a missile comprises a wing root, an upper wing part foldably supported at the wing root around a swiveling axis, at least one first elastically pre-stressed force element and a latching device. The at least one first elastically pre-stressed force element is coupled with the wing root and the upper wing part and is designed for permanently urging the upper wing part into a working position relative to the wing root through introducing a torque. The latching device is designed for arresting the upper wing part on reaching the working position automatically.

A folding wing for a missile comprises a wing root, an upper wing part foldably supported at the wing root around a swiveling axis, at least one first elastically pre-stressed force element and a latching device. The at least one first elastically pre-stressed force element is coupled with the wing root and the upper wing part and is designed for permanently urging the upper wing part into a working position relative to the wing root through introducing a torque. The latching device is designed for arresting the upper wing part on reaching the working position automatically.

A deployable airfoil airborne body such as missiles, bombs, guided projectiles, MALDs and UAVs includes first and second rigid airfoil sections stowed end-to-end along the airborne body. The airfoil sections have first and second interior edges of equal lengths, abutting ends connected at the first and second interior edges by a free-floating pivot, a distant end of the first rigid airfoil section coupled to a fixed pivot on the airborne body, and a distant end of the second rigid airfoil section having a translation point. The first and second rigid airfoil sections are configured to rotate in opposite directions to move the translation point axially along the airborne body to abut the fixed pivot driving the free-floating pivot radially away from the airborne body to join the first and second interior edges in a deployed position transverse to the airborne body to form a rigid airfoil.

A deployable airfoil airborne body such as missiles, bombs, guided projectiles, MALDs and UAVs includes first and second rigid airfoil sections stowed end-to-end along the airborne body. The airfoil sections have first and second interior edges of equal lengths, abutting ends connected at the first and second interior edges by a free-floating pivot, a distant end of the first rigid airfoil section coupled to a fixed pivot on the airborne body, and a distant end of the second rigid airfoil section having a translation point. The first and second rigid airfoil sections are configured to rotate in opposite directions to move the translation point axially along the airborne body to abut the fixed pivot driving the free-floating pivot radially away from the airborne body to join the first and second interior edges in a deployed position transverse to the airborne body to form a rigid airfoil.

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).