A projectile is disclosed, having: a longitudinal axis, a steering assembly, a shell body, an attitude control system, a despin module, an electromagnetic receiver and/or emitter system, and a controller. The attitude control system includes a ram air inlet in selective open fluid communication with an exhaust assembly, which includes a plurality of exhaust outlets to selectively generate each of a plurality of thrust jets from a ram air inflow provided by the ram air inlet, each thrust jet being selectively controllable via the controller. The despin module is configured for selectively de-spinning the steering assembly with respect to the shell body about the longitudinal axis. The electromagnetic receiver and/or emitter system is configured for receiving and/or emitting electromagnetic energy, and for cooperating with the controller for operating the exhaust assembly to thereby selectively provide steering control moments. Systems and methods for steering the projectile are also disclosed.

A device produces an arming criterion for a fuze for a partly spinning munition. The munition has a first part which spins and a second part without or with little spin during flight of the munition. The device includes a sensor for outputting a characteristic variable for a relative rotation between the first part and the second part and a control unit for producing the arming criterion when the characteristic variable fulfils a flying criterion. The fuze for the partly spinning munition, which has at least one arming criterion, includes the device for providing the arming criterion or one of the arming criteria. The partly spinning munition includes the fuze with the device.

A guided projectile having a nose portion, a body portion, a tail portion, and a central axis. In various embodiments the projectile includes a control support portion and a collar assembly pivotally mounted to the control support portion. In various embodiments the collar assembly includes a collar having an exterior sidewall with a plurality of fixed aerodynamic surfaces thereon for spinning the collar and a plurality of variable sweep wings for directional control of the projectile. In various embodiments the plurality of variable sweep wings each have a first end coupled to a wing actuator configured to rotate a second end portion between and including a first position, where the wings are oriented generally parallel to the central axis of the projectile to a second position, where the lengthwise wing axis of the plurality of wings are oriented generally perpendicular to the central axis of the projectile.

A guided projectile having a nose portion, a body portion, a tail portion, and a central axis. In various embodiments the projectile includes a control support portion and a collar assembly pivotally mounted to the control support portion. In various embodiments the collar assembly includes a collar having an exterior sidewall with a plurality of fixed aerodynamic surfaces thereon for spinning the collar and a plurality of variable sweep wings for directional control of the projectile. In various embodiments the plurality of variable sweep wings each have a first end coupled to a wing actuator configured to rotate a second end portion between and including a first position, where the wings are oriented generally parallel to the central axis of the projectile to a second position, where the lengthwise wing axis of the plurality of wings are oriented generally perpendicular to the central axis of the projectile.

A fin deployment mechanism for a projectile. The mechanism includes at least one fin and at least one actuator. The fin is arranged in a deployable and retractable manner on the projectile. The fin and at least one balance weight are arranged so that, when the fin is deployed, the weight is displaced towards a center of the projectile and, when the fin is retracted, the weight is displaced from the center of the projectile. A method for deploying and retracting fins on a projectile. At least one fin is arranged in a deployable and retractable manner on the projectile. The fin is fitted to at least one balance weight such that when the fin is displaced from the center of the projectile the weight is displaced towards the center, and when the fin is displaced towards the center of the projectile the weight is displaced from the center.

A fin deployment mechanism for a projectile. The mechanism includes at least one fin and at least one actuator. The fin is arranged in a deployable and retractable manner on the projectile. The fin and at least one balance weight are arranged so that, when the fin is deployed, the weight is displaced towards a center of the projectile and, when the fin is retracted, the weight is displaced from the center of the projectile. A method for deploying and retracting fins on a projectile. At least one fin is arranged in a deployable and retractable manner on the projectile. The fin is fitted to at least one balance weight such that when the fin is displaced from the center of the projectile the weight is displaced towards the center, and when the fin is displaced towards the center of the projectile the weight is displaced from the center.

A non-lethal, non-impact smart projectile fired from a suitable launcher and equipped with a digital camera, CPU microprocessor and computer vision programming that can recognize a designated target and track a moving target, while moving at high speed. An image dataset of the target stored in memory of the CPU that enables the projectile to recognize a human or small UAV drone in real time within fractions of a second. A steering and braking system comprising several fins/air brakes, controlled by the CPU and MEMS micro-actuators, that enable the projectile to track a moving target or slow the projectile down. A projectile equipped with actuators that dispenses a non-lethal, non-impact payload or payloads as the projectile approaches the target.

A guided projectile having a nose portion, a body portion, a tail portion, and a central axis. In various embodiments the projectile includes a control support portion and a collar assembly pivotally mounted to the control support portion. In various embodiments the collar assembly includes a collar having an exterior sidewall with a plurality of fixed aerodynamic surfaces thereon for spinning the collar and a plurality of variable sweep wings for directional control of the projectile. In various embodiments the plurality of variable sweep wings each have a first end coupled to a wing actuator configured to rotate a second end portion between and including a first position, where the wings are oriented generally parallel to the central axis of the projectile to a second position, where the lengthwise wing axis of the plurality of wings are oriented generally perpendicular to the central axis of the projectile.

A guided projectile having a nose portion, a body portion, a tail portion, and a central axis. In various embodiments the projectile includes a control support portion and a collar assembly pivotally mounted to the control support portion. In various embodiments the collar assembly includes a collar having an exterior sidewall with a plurality of fixed aerodynamic surfaces thereon for spinning the collar and a plurality of variable sweep wings for directional control of the projectile. In various embodiments the plurality of variable sweep wings each have a first end coupled to a wing actuator configured to rotate a second end portion between and including a first position, where the wings are oriented generally parallel to the central axis of the projectile to a second position, where the lengthwise wing axis of the plurality of wings are oriented generally perpendicular to the central axis of the projectile.

A projectile is disclosed, having: a longitudinal axis, a steering assembly, a shell body, an attitude control system, a despin module, an electromagnetic receiver and/or emitter system, and a controller. The attitude control system includes a ram air inlet in selective open fluid communication with an exhaust assembly, which includes a plurality of exhaust outlets to selectively generate each of a plurality of thrust jets from a ram air inflow provided by the ram air inlet, each thrust jet being selectively controllable via the controller. The despin module is configured for selectively de-spinning the steering assembly with respect to the shell body about the longitudinal axis. The electromagnetic receiver and/or emitter system is configured for receiving and/or emitting electromagnetic energy, and for cooperating with the controller for operating the exhaust assembly to thereby selectively provide steering control moments. Systems and methods for steering the projectile are also disclosed.