Abstract: A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude control motors is disposed in each cavity of the plurality of cavities.

Abstract: A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude motors is disposed in each cavity of the plurality of cavities.

Abstract: A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude motors is disposed in each cavity of the plurality of cavities.

Abstract: A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude control motors is disposed in each cavity of the plurality of cavities.

Abstract: A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude control motors is disposed in each cavity of the plurality of cavities.

Abstract: Recoil forces of a launched missile and the moment force imposed on the launch platform can be reduced by use of a recoil abatement element in communication with a launch tube. The recoil abatement element includes at least one nozzle configured to receive therethrough exhaust gasses from a missile when launched. The nozzle can be canted or otherwise configured to direct the exhaust gasses in a desired direction to thereby offset moment force imposed on the platform by the exhaust gasses.

Abstract: A combination conductor-antenna apparatus is provided comprising a surface that defines a passage for use as a receptor for a second conductor and for use as a waveguide. The surface is at least partially formed of an electrically conductive material, thus allowing the apparatus to serve as a medium by which an electrical signal can be transferred from a second conductor. Disposed within the passage is a pickup element for sensing and/or injecting electromagnetic energy in the passage, thus allowing the apparatus to serve as a medium for wireless communications.

Abstract: An apparatus for selectively affecting a launch trajectory of a projectile from a canister includes means for selectively positioning the projectile with respect to the canister and a sabot operably associated with the projectile and the means for selectively positioning the projectile. A projectile launch system includes a canister, a projectile disposed in the canister, and means for selectively positioning the projectile with respect to the canister. A method for affecting a launch trajectory of a projectile includes providing a canister and a projectile disposed in the canister and adjusting a position of the projectile with respect to the canister.

Abstract: An apparatus for selectively affecting a launch trajectory of a projectile from a canister includes means for selectively positioning the projectile with respect to the canister and a sabot operably associated with the projectile and the means for selectively positioning the projectile. A projectile launch system includes a canister, a projectile disposed in the canister, and means for selectively positioning the projectile with respect to the canister. A method for affecting a launch trajectory of a projectile includes providing a canister and a projectile disposed in the canister and adjusting a position of the projectile with respect to the canister.

Abstract: Systems and methods are disclosed for emitting electromagnetic (EM) energy. A source emits EM energy that is incident on a first material. The first material transmits EM energy to a second material. The second material can have a first surface adjacent to the first material and a thickness and shape selected to stimulate surface plasmon polaritons on the first surface of the second material to resonate the EM energy transmitted from the first material such that the resonated EM energy has an EM wavelength in a narrow field of view with substantially no sidelobes.

Abstract: A combination conductor-antenna apparatus is provided comprising a surface that defines a passage for use as a receptor for a second conductor and for use as a waveguide. The surface is at least partially formed of an electrically conductive material, thus allowing the apparatus to serve as a medium by which an electrical signal can be transferred from a second conductor. Disposed within the passage is a pickup element for sensing and/or injecting electromagnetic energy in the passage, thus allowing the apparatus to serve as a medium for wireless communications.

Abstract: A pusher plate assembly for launching a projectile includes a pusher plate, a pressure seal circumferentially extending about the pusher plate, a cage extending from an aft side of the pusher plate, and a plurality of propellant portions disposed in the cage. A projectile system includes a launching tube, a projectile disposed in the launching tube, a pusher plate assembly disposed between an aft end of the projectile and the launching tube, a fuze, a charge igniter operatively associated with the fuze and the plurality of propellant portions, and a retainer disposed within the launching tube proximate a mouth of the launching tube. The pusher plate assembly includes a pusher plate, a pressure seal circumferentially extending about the pusher plate to seal an annulus between the pusher plate and the launching tube, a cage extending from an aft side of the pusher plate, and a plurality of propellant portions disposed in the cage.

Abstract: A lethality device includes a penetrator structure configured to penetrate a target and an incendiary material disposed near the penetrator structure. The incendiary material self-ignites and is injected into the target after penetration of the target. A projectile includes a penetrator structure configured to penetrate a target, an incendiary material disposed near the penetrator structure, and one or components other than the penetrator structure and the incendiary material disposed aft of the penetrator structure. Loads from the one or more components are transferred to the penetrator structure upon impact with the target. The incendiary material self-ignites and is injected into the target after penetration of the target. A method for defeating a target containing an ignitable material includes broaching or puncturing an outer skin of the target, self-igniting an incendiary material, injecting the ignited incendiary material into the target, and igniting a material disposed within the target.

Abstract: Systems and methods are disclosed for emitting electromagnetic (EM) energy. A source emits EM energy that is incident on a first material. The first material transmits EM energy to a second material. The second material can have a first surface adjacent to the first material and a thickness and shape selected to stimulate surface plasmon polaritons on the first surface of the second material to resonate the EM energy transmitted from the first material such that the resonated EM energy has an EM wavelength in a narrow field of view with substantially no sidelobes.

Abstract: A method and apparatus for use in determining the range in a single time sample from a platform to a target are disclosed. The method includes receiving radiation emanating from the target at two points on the platform in a common time sample; detecting the received radiation and generating a signal representative thereof; and processing the signal. The signal is processed to determine a respective angle to target from two points on the platform by using a correlation between received signal amplitude and respective angle; and determine the range from the platform to the target from the respective angles and the separation distance between said two points in a single signal-to-noise sufficient sample. The apparatus includes a plurality of optical channels through which the apparatus can receive radiation emanating from the target, the optical channels and a plurality of electronics.

Abstract: The invention is, in its various embodiments and implementations, a method and apparatus for planar actuation of a flared surface to control a vehicle. In one aspect, the invention comprises an apparatus for controlling a vehicle capable of moving through a fluid medium. The apparatus includes a flare; a planar yoke operably associated with the flare; a plurality of actuators capable of moving the planar yoke to manipulate the flare through the operable association between the planar yoke and the flare; and a load bearing structure through which the translating means imparts a moment from the flare to the vehicle. In a second aspect, the invention comprises a method for controlling the maneuvering of a vehicle capable of moving through a fluid medium. The method includes moving a planar yoke to deflect at least a portion of a flare.

Abstract: The invention is, in its various embodiments and implementations, a method and apparatus for planar actuation of a flared surface to control a vehicle. In one aspect, the invention comprises an apparatus for controlling a vehicle capable of moving through a fluid medium. The apparatus includes a flare; a planar yoke operably associated with the flare; a plurality of actuators capable of moving the planar yoke to manipulate the flare through the operable association between the planar yoke and the flare; and a load bearing structure through which the translating means imparts a moment from the flare to the vehicle. In a second aspect, the invention comprises a method for controlling the maneuvering of a vehicle capable of moving through a fluid medium. The method includes moving a planar yoke to deflect at least a portion of a flare.

Abstract: In a first aspect, the invention uses the thrust and axial aerodynamic forces of and on the missile system as the primary mechanism for altering the missile system's flight path as opposed to the missile system's aerodynamic normal force. In accordance with this first aspect, a first embodiment is a method for changing the direction of travel of a vehicle moving through a fluid medium to a desired direction of travel measured in the vehicle's inertial frame of reference, the vehicle comprising a body including a nose, a moment generating control device, and an axial propulsive device. The method comprises actuating the moment generating control device to align the nose substantially with the desired direction of travel, and applying the axial propulsive device as the primary mechanism to redirect the vehicle's velocity to the desired direction of travel. In a second aspect, the invention provides a missile control system implementing the first aspect of the invention.

Abstract: A comparative dual-control strategy actuates forward and aft control devices simultaneously to significantly improve a missile's maneuverability/dynamic capability. A substantial, and measurable, operational effect of the inventive control strategy is a dramatic improvement in a missile's divert capability. To effect a maneuver in accordance with the inventive strategy, a missile's aft fins are initially deflected to generate a force OPPOSITE that conventionally used (pushing the missile's tail in the direction of the commanded maneuver) which simultaneously actuating forward thrusters to also push the missile's nose in the direction of the commanded maneuver but at a faster rate than the tail section. This causes the missile body to simultaneously rotate and translate in the direction of the commanded maneuver.