An aeromechanically stable sabot system that includes a center of gravity that is placed forward of an aerodynamic center of the aeromechanically stable sabot system when in steady-state flight. By placing the center of gravity forwards of the aerodynamic center, the sabot system exhibits positive longitudinal and directional stability. To illustrate, the sabot system and/or portions thereof will return to stable flight after being disturbed in pitch (vertically or about a transverse horizontal axis) or yaw (side to side or about a vertical axis) when traveling horizontally.

A guidance system for a projectile having a mid-body. The guidance system having a mid-body semi-active laser seeker. The seeker has an objective lens assembly and a sensor array that reads laser energy and transmits data to determine the direction of the laser energy. A glint management unit is connected to mid-body in such a manner that glint laser energy is prevented from passing to the objective lens assembly and sensor array so as to enhance determination of the location of the target.

A rear slip base plate for a round carrying a guidance and control unit payload, which round is launched from a rifled launch tube. To prevent the guidance and control unit payload from also being rapidly spun with the round, the slip base plate unit mechanically isolates the guidance and control unit payload from the round spin rate.

A tail kit assembly of a guided munition having a tail kit base connected to a trailing end of a projectile body. The tail kit base is rotatable relative to the projectile body. A trimmable rudder has forward and rearward ends. The forward end is pivotally coupled to the tail kit base, such that the trimmable rudder can, relative to the tail kit base, between retracted and extended orientations. An actuator is fixed between the tail kit base and the rearward end of the trimmable rudder. The actuator is electrically coupled to an onboard guidance system that controls actuation of the actuator to pivot the trimmable rudder between the retracted orientation and the extended orientation.

A tail kit assembly of a guided munition having a tail kit base connected to a trailing end of a projectile body. The tail kit base is rotatable relative to the projectile body. A trimmable rudder has forward and rearward ends. The forward end is pivotally coupled to the tail kit base, such that the trimmable rudder can, relative to the tail kit base, between retracted and extended orientations. An actuator is fixed between the tail kit base and the rearward end of the trimmable rudder. The actuator is electrically coupled to an onboard guidance system that controls actuation of the actuator to pivot the trimmable rudder between the retracted orientation and the extended orientation.

The present invention is directed to a bendable projectile having a forebody unit, a rearbody unit and an articulating joint unit connecting the two units. The articulating joint unit is composed of a spherical shape body, a receiving socket and a sphere-gear assembly. The spherical shape body is fitted into the receiving socket whereby movement of the spherical shape body about the receiving socket is permitted without release of the spherical shape body from the socket. Movement of the spherical shape body inside the receiving socket is effectuated by the sphere gear assembly. The sphere-gear assembly engages the concentric grooves along the surface of the spherical shape body or the concave surface of the receiving socket. Such sphere-gear assembly is comprised of electric board, powersource, powertrain, guidance control system and gears having teeth and grooves that complement the plurality of concentric grooves on the spherical shape body.

The present invention is directed to a bendable projectile having a forebody unit, a rearbody unit and an articulating joint unit connecting the two units. The articulating joint unit is composed of a spherical shape body, a receiving socket and a sphere-gear assembly. The spherical shape body is fitted into the receiving socket whereby movement of the spherical shape body about the receiving socket is permitted without release of the spherical shape body from the socket. Movement of the spherical shape body inside the receiving socket is effectuated by the sphere gear assembly. The sphere-gear assembly engages the concentric grooves along the surface of the spherical shape body or the concave surface of the receiving socket. Such sphere-gear assembly is comprised of electric board, powersource, powertrain, guidance control system and gears having teeth and grooves that complement the plurality of concentric grooves on the spherical shape body.

The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to flow control system involving different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The active flow control device or activatable flow effectors of these various embodiments are adapted to be activated, controlled, and deactivated based on signals from the sensors to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.

The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to flow control system involving different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The active flow control device or activatable flow effectors of these various embodiments are adapted to be activated, controlled, and deactivated based on signals from the sensors to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.

A guiding kit for guiding a projectile to a target comprises a front part and a rear part. The front part and the rear part are rotatably connected to each other to enable relative rotation about a common central longitudinal axis of rotation. The front part comprises a front transceiver (T/X) unit that is disposed next to the rear end of the front part and coinciding with the longitudinal central axis of rotation and adapted to transmit signals towards the rear part. A rear transceiver unit is disposed against the front transceiver unit and adapted to communicate with front transceiver unit when the front part and the rear part are rotating with respect to each other.