A deployment system, such as for deploying wings, includes a pair of hub assemblies that transmit linear motion provided by an actuator into a combination of rotational and axial motion. The actuator works on both hub assemblies, rotating (for each wing) a slew ring that is coupled to a lift bar that acts as a follower, following a pair of cam slots, to allow the wings to follow their desired course. In one embodiment the wings move axially away from a fuselage at the beginning of the deployment movement, followed by a primarily rotational movement, with the wings pulling in toward the fuselage at the end of the deployment process. The actuator includes a pair of threaded shafts (threaded in opposite directions) that rotate along with a pinion gear, driven by a motor, to translate a pair of retractor links that are coupled to the slew rings.

A deployment system, such as for deploying wings, includes a pair of hub assemblies that transmit linear motion provided by an actuator into a combination of rotational and axial motion. The actuator works on both hub assemblies, rotating (for each wing) a slew ring that is coupled to a lift bar that acts as a follower, following a pair of cam slots, to allow the wings to follow their desired course. In one embodiment the wings move axially away from a fuselage at the beginning of the deployment movement, followed by a primarily rotational movement, with the wings pulling in toward the fuselage at the end of the deployment process. The actuator includes a pair of threaded shafts (threaded in opposite directions) that rotate along with a pinion gear, driven by a motor, to translate a pair of retractor links that are coupled to the slew rings.

A method of increasing the performance of an aircraft, missile, munition or ground vehicle with plasma actuators, and more particularly of controlling fluid flow across their surfaces or other surfaces which would benefit from such a method, includes the design of an aerodynamic plasma actuator for the purpose of controlling airflow separation over a control surface of a aircraft, missile, or a ground vehicle, and a method of determining a modulation frequency for the plasma actuator for the purpose of fluid flow control over these vehicles. Various embodiments provide steps to increase the efficiency of aircraft, missiles, munitions and ground vehicles. The method of flow control reduces the power requirements of the aircraft, missile, munition or ground vehicle. These methods also provide alternative aerodynamic control using low-power hingeless plasma actuator devices.

A method of increasing the performance of an aircraft, missile, munition or ground vehicle with plasma actuators, and more particularly of controlling fluid flow across their surfaces or other surfaces which would benefit from such a method, includes the design of an aerodynamic plasma actuator for the purpose of controlling airflow separation over a control surface of a aircraft, missile, or a ground vehicle, and a method of determining a modulation frequency for the plasma actuator for the purpose of fluid flow control over these vehicles. Various embodiments provide steps to increase the efficiency of aircraft, missiles, munitions and ground vehicles. The method of flow control reduces the power requirements of the aircraft, missile, munition or ground vehicle. These methods also provide alternative aerodynamic control using low-power hingeless plasma actuator devices.

A bullet including a drag-reducing assembly provided about its main body, and configured for being triggered upon a blast from a cartridge, in order to reduce a resulting base drag of the bullet during flight trajectory. The drag-reducing assembly includes at least one cavity being configured for receiving and containing a portion of gun gas from the cartridge and corresponding blast, and at least one peripheral orifice for releasing gun gas from the at least one cavity during the flight trajectory of the bullet, in order to fill a partial vacuum behind the bullet during flight trajectory, and thus reduce the resulting base drag, for an improved overall ballistic performance of the bullet.

An integrated propulsion and warhead system for an artillery round includes a propulsion, such as a solid rocket motor and/or an air-breathing jet engine, and an annular explosive concentrically arranged around at least a portion of the propulsion system. The integrated propulsion and warhead system is included in a propulsion section of the artillery round so that space in an adjacent guidance section is increased and the space allocation for the propulsion system and annular explosive is optimized.

An elongate cylindrical projectile including processing circuitry, a head assembly, a tail section assembly, a mid body section positioned between the head assembly and tail assembly, and a wing assembly, the wing assembly including a deployable wing which is stored in a closed position entirely within the mid body section and is deployed, using an actuator, to outside the mid body section in an open position in response to a command from the processing circuitry.

An elongate cylindrical projectile including processing circuitry, a head assembly, a tail section assembly, a mid body section positioned between the head assembly and tail assembly, and a wing assembly, the wing assembly including a deployable wing which is stored in a closed position entirely within the mid body section and is deployed, using an actuator, to outside the mid body section in an open position in response to a command from the processing circuitry.

In some embodiments, an arrow comprises a shaft comprising a tubular wall comprising a cavity and a nock comprising a notch arranged to engage a bowstring. An intake inlet is in fluid communication with the cavity and an exhaust outlet is in fluid communication with the cavity.

A streamlined projectile is disclosed that includes a base or rear having a plurality of concentric sections located within each other at the aft of the projectile and in successively smaller sizes. Within each concentric section is a chamber having a wall perpendicular to expanding combustion gasses, with the total area of these walls being greater than an area of the rear of the projectile itself. This creates a larger projectile base for a propellant to push against and for that explosion to be held within the section chamber for a longer period than that of a standard boattail or flat-tail projectile. In addition, the concentric sections at least partially negate atmospheric drag by occupying the region behind the projectile where a partial vacuum forms, resulting in a projectile that will go faster and further for a given propellant charge.