An unmanned aerial vehicle (UAV) adapted for transit in and deployment from a projectile casing is provided. The UAV includes a wing assembly coupled to the projectile casing and the wing assembly moveable between a closed position and a deployed position. The UAV further includes a propulsion system including at least one rotor disposed on the wing assembly to generate lift, wherein in the closed position, the wing assembly is substantially integral with the projectile casing and in the deployed position, the wing assembly is extended outwards from the projectile casing.

A mortar shell including: a metallic inner layer defining an interior of the mortar, the metallic inner layer having a grid formed on an outer surface to define a plurality of metallic fragments separated by grooves; a polymer having first reinforcing fibers disposed within the grooves; and a polymer outer layer, the polymer outer layer having second reinforcing fibers dispersed therein. The grid can be a square grid to define square shaped metallic fragments. The polymer outer layer can include a pattern of dimples formed on an outer surface. The polymer outer layer can include a solid lubricant.

A projectile with selectable angle of attack for increased impact on a target includes an active charge and controllable initiation device for initiation of the active charge, wherein the projectile also includes at least one side-acting impulse motor for tilting the projectile relative to its trajectory from a substantially vertical position, in which the front face of the projectile is directed toward the target, into a more horizontal position, in which the outer surface of the projectile is directed toward the target.

A mortar shell including: a metallic inner layer; a polymer outer layer having reinforcing fibers dispersed therein; and at least one layer of metallic fragments disposed between the inner and outer layers, the layer of metallic fragments including a plurality of individual metallic fragments unconnected to each other. In a variation, the mortar shell including: a metallic inner layer, the metallic inner layer having a grid formed on an outer surface to define a plurality of metallic fragments separated by grooves; a polymer having first reinforcing fibers disposed within the grooves; and a polymer outer layer having second reinforcing fibers dispersed therein. In another variation, the mortar shell including a polymer outer layer having reinforcing fibers dispersed therein; and a metallic inner layer having a plurality of metallic fragments with a shape to interlock to each of the other and assembled together into the metallic inner layer.

Systems and methods for providing location and guidance are herein described, and more particularly for providing location and guidance in environments where global position systems (GPS) are unavailable or unreliable (GPS denied and/or degraded environments). The systems and methods herein utilize inertial measurement units (IMUs) to provide such location and guidance. More particularly, the systems and methods herein utilize a series of low-accuracy or low-resolution IMUs, in combination, to provide high-accuracy or high-resolution location and guidance results.

An unmanned aerial vehicle (UAV) adapted for transit in and deployment from a projectile casing is provided. The UAV includes a wing assembly coupled to the projectile casing and the wing assembly moveable between a closed position and a deployed position. The UAV further includes a propulsion system including at least one rotor disposed on the wing assembly to generate lift, wherein in the closed position, the wing assembly is substantially integral with the projectile casing and in the deployed position, the wing assembly is extended outwards from the projectile casing.

An unmanned aerial vehicle (UAV) adapted for transit in and deployment from a projectile casing is provided. The UAV includes a wing assembly coupled to the projectile casing and the wing assembly moveable between a closed position and a deployed position. The UAV further includes a propulsion system including at least one rotor disposed on the wing assembly to generate lift, wherein in the closed position, the wing assembly is substantially integral with the projectile casing and in the deployed position, the wing assembly is extended outwards from the projectile casing.

The invention relates to a penetrating and explosive projectile (1) provided with a trajectory-stabilizing fin assembly (8) which is secured to a body of the projectile by a mechanical connection. The fin assembly (8) includes a tapped tube (14) which engages on a threaded rear cylindrical shank (10) of a tail (9) connected to the projectile body (2), thereby forming a threaded mechanical connection (13) between the tail unit (8) and the body (2). This projectile (1) is characterized in that it includes means ensuring the fragilization of the threaded connection (13) on impact on a target, the fin assembly then separating from the projectile body.

The invention relates to a penetrating and explosive projectile (1) provided with a trajectory-stabilizing fin assembly (8) which is secured to a body of the projectile by a mechanical connection. The fin assembly (8) includes a tapped tube (14) which engages on a threaded rear cylindrical shank (10) of a tail (9) connected to the projectile body (2), thereby forming a threaded mechanical connection (13) between the tail unit (8) and the body (2). This projectile (1) is characterized in that it includes means ensuring the fragilization of the threaded connection (13) on impact on a target, the fin assembly then separating from the projectile body.

A closed, self-contained ballistic apogee detection module for use in a projectile, such as a rocket, mortar round, or artillery round, fuses data from multiple built-in sensors, such as an accelerometer, a magnetometer, and a gyroscope, and processes the data using a microprocessor through a custom quaternion extended Kalman filter to provide accurate state and orientation information about the projectile so as to accurately predict apogee. The module outputs a signal indicating apogee detection or prediction which they projectile uses to initiate fuze arming, targeting control, airbody transformation, maneuvering, flow effector deployment or activation, payload exposure or deployment, and/or other mission activity. Because the system and method of the invention does not rely on external environmental data to detect apogee, it need not use a pressure sensor and can be completely sealed in and closed without requiring access to air from outside the projectile for barometric readings.