Abstract: Embodiments of an inductive power transfer method are generally described herein. In some embodiments, a method of transferring data and power to a plurality of guided projectiles located in launcher tubes on a helicopter is described herein. In some embodiments, power and data are inductively transferred across the launcher windings to the projectile windings to configure the control systems of the guided projectiles to provide a lock-on-before-launch capability.

Abstract: Embodiments of an inductive power transfer method are generally described herein. In some embodiments, a method of transferring data and power to a plurality of guided projectiles located in launcher tubes on a helicopter is described herein. In some embodiments, power and data are inductively transferred across the launcher windings to the projectile windings to configure the control systems of the guided projectiles to provide a lock-on-before-launch capability.

Abstract: The present invention generally concerns inductive power transfer systems and their components. More particularly, representative and exemplary embodiments of the present invention generally relate to systems, devices and methods for transferring modulated current between a launcher and at least one guided missile.

Abstract: The present invention generally concerns inductive power transfer systems and their components. More particularly, representative and exemplary embodiments of the present invention generally relate to systems, devices and methods for transferring modulated current between a launcher and at least one guided missile.

Abstract: The disclosed system, device and method for guiding a hypersonic kinetic penetrator projectile (300) generally includes a kinetic penetrator body (110, 230) and a slip-over electronic guidance unit (120, 220), where the kinetic penetrator body slidably mounts through the slip-over electronic guidance unit. Disclosed features and specifications may be variously controlled, adapted or otherwise optionally modified to improve accuracy and control of a hypersonic projectile. Exemplary embodiments of the present invention generally provide multi-use slip-over electronic guidance units for hypersonic kinetic penetrator projectiles in 105 mm and 120 mm munition rounds, surface-to-surface missiles, and air-to-surface missiles.

Abstract: An electromagnetic coil gun system includes a launcher having a barrel with a longitudinal bore therethrough, and a plurality of longitudinally extending electrical excitation coils arranged circumferentially around the bore of the barrel so that a magnetic field produced by an electrical current in each electrical excitation coil penetrates into the bore. Each electrical excitation coil is independently activated by the electrical current passed therethrough. There is a projectile sized to be received within the bore of the barrel and having a circumferential armature at a tail end thereof, and a nose end.

Abstract: A simple RF system tracks a missile, bullet or artillery round and determines the instantaneous attitude of the spinning projectile while in flight. The system is particularly useful in command-guided weapons systems where line-of-sight is maintained from the launch platform to the target. The system includes a first pair of linearly polarized transmit antennas spaced apart on the projectile for transmitting a signal and a harmonic of that signal. A receiver on the launch platform determines the roll angle and either the yaw or pitch angle from the received signals. To determine the remaining angle, either the receiver samples the received signals ninety degrees out of phase or a second pair of transmit antennas are mounted on the projectile, preferably ninety degrees from the first pair, for transmitting another pair of harmonic signals.

Abstract: A vehicle guidance system. The system includes a first mechanism for tracking a vehicle based on time-of-arrival information associated with energy emanating from the vehicle and providing vehicle position information in response thereto. A second mechanism steers the vehicle based on the vehicle position information. In a specific embodiment, the system of further includes a third mechanism for locating the target based on time-of-arrival information associated with energy radiating from the target and providing target location information in response thereto. The second the second mechanism steers the vehicle based on the target location information and the vehicle position information.

Abstract: A multi-staged missile includes a booster and a submunition delivery vehicle that has one or more submunitions. The booster rapidly accelerates the submunition vehicle, and then separates from the submunition vehicle. The submunition delivery vehicle is then maneuvered to approach a target. Individual submunitions finally separate, and are individually guided to the target. By providing multiple, independently-targeted submunitions, the missile greatly increases the chances of hitting the target.

Abstract: A multi-staged missile includes a booster and a submunition delivery vehicle that has one or more submunitions. The booster rapidly accelerates the submunition vehicle, and then separates from the submunition vehicle. The submunition delivery vehicle is then maneuvered to approach a target. Individual submunitions finally separate, and are individually guided to the target. By providing multiple, independently-targeted submunitions, the missile greatly increases the chances of hitting the target.

Abstract: A precision-guided hypersonic projectile weapon system. The inventive system includes a first subsystem for determining a target location and providing data with respect thereto. A second subsystem calculates trajectory to the target based on the data. The projectile is then launched and guided in flight along the trajectory to the target. In the illustrative application, the projectile is a tungsten rod and the first subsystem includes a forward-looking infrared imaging system and a laser range finder. The second subsystem includes a fire control system. The fire control system includes an optional inertial measurement unit and predicts target location. The projectile is mounted in a missile launched from a platform such as a vehicle. After an initial burn, the missile launches the projectile while in flight to the target. The missile is implemented with a rocket with a guidance system and a propulsion system.

Abstract: A modular missile assembly includes a pair of modules which are separately transported and handled until just prior to firing, when they are coupled together. A forward payload-carrying module includes a forward canister which encloses a missile payload section, for example, consisting of a penetrator rod, fins, and ancillary subassemblies. An aft booster module includes a missile propulsion section, encased in an aft canister. Prior to firing, suitable forward and aft modules are selected, are individually loaded into a launch tube, and are coupled together. In this coupling the missile payload section and the missile propulsion section are coupled together to form a missile, and the forward and aft canisters are likewise coupled together to form a combined canister assembly. Division of the missile into separate payload and booster modules facilitates handling as compared to unitary missiles. The modular design also allows increased flexibility.

Abstract: A modular missile assembly includes a pair of modules which are separately transported and handled until just prior to firing, when they are coupled together. A forward payload-carrying module includes a forward canister which encloses a missile payload section, for example, consisting of a penetrator rod, fins, and ancillary sub-assemblies. An aft booster module includes a missile propulsion section, encased in an aft canister. Prior to firing, suitable forward and aft modules are selected, are individually loaded into a launch tube, and are coupled together. In this coupling the missile payload section and the missile propulsion section are coupled together to form a missile, and the forward and aft canisters are likewise coupled together to form a combined canister assembly. Division of the missile into separate payload and booster modules facilitates handling as compared to unitary missiles. The modular design also allows increased flexibility.

Abstract: A precision-guided hypersonic projectile weapon system. The inventive system includes a first subsystem for determining a target location and providing data with respect thereto. A second subsystem calculates trajectory to the target based on the data. The projectile is then launched and guided in flight along the trajectory to the target. In the illustrative application, the projectile is a tungsten rod and the first subsystem includes a forward-looking infrared imaging system and a laser range finder. The second subsystem includes a fire control system. The fire control system includes an optional inertial measurement unit and predicts target location. The projectile is mounted in a missile launched from a platform such as a vehicle. After an initial burn, the missile launches the projectile while in flight to the target. The missile is implemented with a rocket with a guidance system and a propulsion system.

Abstract: A spin-stabilized missile includes two or more spin nozzles along a perimeter of the missile, the nozzles being operatively coupled to a pressurized gas source. The pressurized gas source provides pressurized gas which passes through the nozzles and external to the missile, thereby providing circumferential thrust which causes a torque on the missile that results in the missile rolling or spinning. The pressurized gas source may be a pressure container containing solid rocket fuel. The pressurized gas source for spinning the missile may be the same as that for the missile's main propulsion system.

Abstract: An impulse radar guidance system and method for use with a spinning projectile. The system and method tracks the flight of the spinning projectile using an all-weather radar or tracker. A linearly polarized asymmetric waveform is transmitted at the projectile that comprises a series of repeating pulses having a relatively strong, short, positive electric field pulse followed by a relatively weak, long, negative electric-field baseline. The projectile contains a dipole antenna having a switching diode disposed between respective halves thereof.

Abstract: A missile guidance system designed to operate on GPS signals in an anti-jamming environment. The inventive system includes first, second and third airborne vehicles (20). A GPS receiver (24) is mounted on each of the three vehicles (20) to receive signals transmitted from spaceborne satellites (14). Each vehicle (20) acts as a pseudo-satellite or ‘pseudolite’. The received GPS signals are processed by a processor (26) to provide a first intermediate signal indicating the position of the vehicle (20). This signal is retransmitted from each vehicle and received by a GPS receiver mounted on a missile. The received intermediate signal is processed on the missile to provide an output signal indicating the position thereof. The pseudolites would be airborne in the vicinity of a target area.

Abstract: A missile guidance system with a fixed body missile seeker having an adjustable look angle. The missile seeker has a fixed camera whose look angle is adjustable to keep a moving target within the field of view of the camera. The target is tracked by a tracker to generate target angle and line of sight rate signals. The target angle signal is input to pointing angle adjustment apparatus which adjusts the look angle of the camera. The pointing angle adjustment apparatus may comprise a stepper motor that controls the angular position of a gimbal on which the camera is mounted. Alternatively, the pointing angle adjustment apparatus may comprise one or more stepper motors that control an adjustable zoom lens or a plurality of optical wedges, respectively. A body angular rate output signal of a body-fixed inertial measurement system is summed with the line of sight rate signals from the tracker to determine the inertial line of sight rate of the moving target.

Abstract: A guidance system (30) for a missile comprising a sensor (20) mounted on the missile and having a fixed line-of-sight relative thereto. The body fixed sensor (20) provides a first signal representing frames of image data. A processor (40) identifies a target in the frames of image data and provides a second signal representative of the location of the centroid thereof. A conventional tracker (36) follows the target and provides a third signal representative of an aim point of the missile. A controller (44) then changes the velocity vector of the missile in response to the second and third signals. In a specific embodiment, the body fixed sensor (20) provides first and second frames of image data. The system (32, 34) subtracts the first and second frames of image data and ascertains a growth center of the target. The processor (40) compares the image growth center to the aim point and provides an error signal in response thereto.

Abstract: A system for guiding the flight of a projectile to a target. The system comprises a tracking and guidance system, the projectile, and a projectile reference and control system that is part of the projectile. The tracking and guidance system includes a target tracker, a projectile tracker for providing a projectile-tracking laser beam, and a target designator for designating the target using a target-tracking laser beam, and for providing range data indicative of the range to the target. A processor is coupled to the target designator, the target tracker, and the projectile tracker for processing target and projectile return signals and target range signals to generate an actuator command signal that is transmitted by the projectile tracker using the projectile-tracking laser beam and that is used to alter the flight of the projectile.