Raytheon Company

Hughes Missile Systems Company

Other

Arthur J Schneider

James G Small

Wayne V Spate

Andrew J Hinsdale

Michael B McFarland

Michael J Kaiserman

Stanton L Winetrobe

Henry August

Robert W Adams

Ralph H Klestadt

David A Faulkner

Kenneth R Johnson

Douglas E Elerath

Paul D Shubert

Donald E French

Guy B Coleman

Michael T Rodack

Jennifer B Weesner

Jeffrey S Supp

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.

Methods for inductively transferring data and power to a plurality of guided projectiles to provide a lock-on-before-launch capability

The present invention generally concerns systems and methods for supplying electric power using supercapacitors; and more particularly, representative and exemplary embodiments of the present invention generally relate to improved methods and systems for supplying power to a guided rocket.

Launcher for a projectile having a supercapacitor power supply

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.

Inductive power transfer

The disclosed system, device and method for guiding a hypersonic kinetic penetrator projectile () generally includes a kinetic penetrator body () and a slip-over electronic guidance unit (), 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.

Guided kinetic penetrator

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. The projectile placed into the bore is fired by producing a traveling sequence of propulsive currents in the electrical excitation coils moving in a direction from the breech end toward the muzzle end of the barrel, so that a traveling propulsive magnetic field produced by the electrical excitation coils interacts with the armature of the projectile to propel the projectile in the direction from the breech end toward the muzzle end of the barrel. Simultaneously, a traveling sequence of field-nulling currents in the electrical excitation coils moves in the direction from the breech end toward the muzzle end of the barrel but closer to the muzzle end of the barrel than the traveling sequence of propulsive currents and spatially leading the traveling sequence of propulsive currents. The field-nulling currents are in a circumferential direction opposite to the propulsive currents, thereby at least partially nulling the traveling propulsive magnetic field at the nose end of the projectile.

Magnetic field protection for the projectile of an electromagnetic coil gun system

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.

RF attitude measurement system and method

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.

System and method for locating a target and guiding a vehicle toward the target

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.

Missile system with multiple submunitions

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. In accordance with the present teachings, the guidance system includes a transceiver system mounted on the projectile. The transceiver system includes a low-power continuous wave, millimeter wavelength wave emitter. A system is included at the launch platform for communicating with the projectile. The platform system sends a blinking command to the projectile and measures the round trip delay thereof to ascertain the range of the projectile. Velocity is determined by conventional Doppler techniques or differentiation. Azimuth and elevation are then determined by a monopulse antenna on the launch platform. As a consequence, the platform ascertains the location of the projectile and the impact point thereof. The platform generates a command to the projectile which is received by the projectile and used to actuate control surfaces to adjust the trajectory and impact point thereof as necessary.

Precision-guided hypersonic projectile weapon system

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.

Modular missile and method of assembly

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.

Propulsive torque motor

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. The waveform is reflected from the antenna which spins with the projectile and reflects a relatively strong signal when the electric field pulse of the asymmetric waveform is aligned along a conduction direction of the diode, a relatively weak reflected signal when the antenna and diode are aligned orthogonal to the electric field pulse, and a small, non-zero, signal when the diode is aligned anti-parallel to the electric field pulse and the diode is back-biased so that respective halves of the antenna are disconnected. The radar or tracker measures the instantaneous roll angle of the spinning projectile during its flight as a function of the state of the reflected signal. The projectile has a maneuvering device, and a receiver that receives commands that causes the maneuvering device to actuate at one or more specific roll-angles to deflect the flight direction of the projectile at a target.

Impulse radar guidance apparatus and method for use with guided projectiles

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 (,). A GPS receiver (,) is mounted on each of the three vehicles (,) to receive signals transmitted from spaceborne satellites (,). Each vehicle (,) acts as a pseudo-satellite or 'pseudolite'. The received GPS signals are processed by a processor (,) to provide a first intermediate signal indicating the position of the vehicle (,). 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. Because the pseudolites are relatively close to the targets compared to a satellite in high altitude orbit and because the pseudolites would be able to transmit a kilowatt or more power, the signal strength may be improved significantly. To succeed as a jammer, a jammer, successful against GPS satellites, would need considerably more power to succeed against aircraft carried pseudolites. The pseudolite system delivers GPS signals into the target area 40-70 dB stronger than signals coming directly from GPS satellites. By timing the signals for 100% time coverage, enemy C/A code receivers will be jammed because they are limited to a J/S capability of 30 dB.

Airborne GPS guidance system for defeating multiple jammers

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. The inertial line of sight rate is driven to zero or a low fixed value by a control system to accurately track a target. The control system and missile dynamics generate a body angle signal that is input to a difference circuit along with a camera pointing angle signal output by the pointing angle adjustment apparatus. The difference circuit generates a desired camera pointing angle that is input to the pointing angle adjustment apparatus to point the camera at the target.

Guidance system having a body fixed seeker with an adjustable look angle

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. The controller (44) then changes the velocity vector of the missile as necessary to maintain the error signal within a predetermined value. The processor (40) also provides an estimate of missile travel time to the target. When the travel time to target drops below a predetermined threshold, terminal guidance is effected by an inertial measurement unit (46).

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Tucson, AZ, United States of America

Arthur J Schneider