A non-lethal projectile comprises a rear portion in the form of a cylinder (2) coupled to at least two symmetrical petal-like impact elements (1) which are capable of opening upon leaving a bore and are designed to form, in a closed configuration, a cylinder having an outside diameter equal to the diameter of the cylindrical rear portion and also having an axial cylindrical opening which transitions into an axial opening in the cylindrical rear portion of the projectile. The petal-like elements have an asymmetrical cross section and an inner conical groove, the base of which is disposed at the rear portion-end of the projectile, wherein, in the front portion, each petal-like element has a unidirectional relief.

Embodiments of the present invention relate to a launch vehicle fairing recovery system and method using inflatable bags and fairing repositioning mechanisms. Embodiments of the present invention also relate to providing a system or mechanism to flip the fairing into the proper floating position. In some embodiments, the fairing has an inner surface and an outer surface, where the outer surface is exposed to the atmosphere when the fairing is interconnected to a spacecraft, and one or more inflatable bags interconnected to the outer surface of the fairing, where when the fairing is interconnected to the spacecraft the one or more inflatable bags is empty, and after the fairing separates from the spacecraft the one or more airbags are filled with pressurized gas and/or hydraulic liquids.

Embodiments of the present invention relate to a launch vehicle fairing recovery system and method using inflatable bags and fairing repositioning mechanisms. Embodiments of the present invention also relate to providing a system or mechanism to flip the fairing into the proper floating position. In some embodiments, the fairing has an inner surface and an outer surface, where the outer surface is exposed to the atmosphere when the fairing is interconnected to a spacecraft, and one or more inflatable bags interconnected to the outer surface of the fairing, where when the fairing is interconnected to the spacecraft the one or more inflatable bags is empty, and after the fairing separates from the spacecraft the one or more airbags are filled with pressurized gas and/or hydraulic liquids.

The invention relates to a brake panel (3, 3) for a projectile (1), in which those surfaces (A) of the brake panel (3, 3) which are facing in the direction of travel of the projectile are wholly or partially angled in such a way that the normal from the said surfaces (A) is not parallel with the center line (C) of the projectile (1) in order to reduce or counteract the Magnus torque generated during and after the extension of the brake panel (3, 3). The invention further relates to a detonator (2) for a projectile (1) and a projectile (1) comprising such a brake panel.

The invention relates to a brake panel (3, 3) for a projectile (1), in which those surfaces (A) of the brake panel (3, 3) which are facing in the direction of travel of the projectile are wholly or partially angled in such a way that the normal from the said surfaces (A) is not parallel with the center line (C) of the projectile (1) in order to reduce or counteract the Magnus torque generated during and after the extension of the brake panel (3, 3). The invention further relates to a detonator (2) for a projectile (1) and a projectile (1) comprising such a brake panel.

A mechanism secures and then deploys a rotationally coupled rigid member to and from a frame. One end of a curved member is pinned to the rigid member and the other end is on or in a reaction guiding element. In a closed state, the curved member is straightened from its originally manufactured or free state curvature and the other end is secured to the frame via a latch mechanism. The tension in the straightened curved member serves to preload the rigid member against the frame. To move to an open state, the latch mechanism is released allowing the other end of the curved member to move with or within the reaction guiding element along a constrained path towards its free state curvature. The curved member reacts against the frame, the pinned end in the rigid member and the reaction guiding element to rotate the rigid member away from the frame.

A mechanism secures and then deploys a rotationally coupled rigid member to and from a frame. One end of a curved member is pinned to the rigid member and the other end is on or in a reaction guiding element. In a closed state, the curved member is straightened from its originally manufactured or free state curvature and the other end is secured to the frame via a latch mechanism. The tension in the straightened curved member serves to preload the rigid member against the frame. To move to an open state, the latch mechanism is released allowing the other end of the curved member to move with or within the reaction guiding element along a constrained path towards its free state curvature. The curved member reacts against the frame, the pinned end in the rigid member and the reaction guiding element to rotate the rigid member away from the frame.

A projectile and ammunition round are provided for disabling unmanned aerial vehicles (UAVs) or drones while reducing risks to people and property on the ground. The projectile includes a penetrator body and a plurality of wings that are folded during firing and deploy after discharge. In the deployed configuration, the wings slow and stabilize the projectile by generating drag and imparting rotation. The body may include grooves and a recessed forward end to enable multiple projectiles to be stacked in a nested configuration within a casing. An ammunition round may contain multiple stacks of the projectiles for compact storage and sequential deployment.

A projectile and ammunition round are provided for disabling unmanned aerial vehicles (UAVs) or drones while reducing risks to people and property on the ground. The projectile includes a penetrator body and a plurality of wings that are folded during firing and deploy after discharge. In the deployed configuration, the wings slow and stabilize the projectile by generating drag and imparting rotation. The body may include grooves and a recessed forward end to enable multiple projectiles to be stacked in a nested configuration within a casing. An ammunition round may contain multiple stacks of the projectiles for compact storage and sequential deployment.