Abstract: An airborne vehicle (1, 2, 10) which is equipped with an extinguishant container (12) for mist extinguishing is specified for efficient firefighting. A detonator (18) which is located on the extinguishant container (12) can be detonated via a fuze (19). The detonator (18) is attached to the airborne vehicle (1, 2, 10) such that, on firing the extinguishant which is contained in the extinguishant container (12) produces an extinguishant mist.

Abstract: An attitude sensing apparatus for determining the attitude of a mobile unit is provided that can reliably estimate an alignment angle between a GPS antenna coordinate system and an IMU coordinate system with good accuracy regardless of the magnitude of the alignment angle. Based on observation of the difference between a GPS angular velocity and an IMU angular velocity, an alignment angle estimating section estimates an alignment angle and sensor errors. An alignment angle adder and a sensor error adder cumulatively add and update the estimated alignment angle and sensor errors, respectively. The estimated alignment angle is fed back to an inertia data converter while the estimated sensor errors are fed back to an inertia data correcting section. The apparatus repeatedly performs estimation until the estimated alignment angle gradually approaches a true alignment angle by successively feeding back estimated values to a flow of alignment angle estimation process.

Abstract: A system for determining the distance between a target (4) and a laser guided weapon traveling towards the target (4). The system (1) comprises a laser designator (5) on a remote platform (2) for radiating a first train of pulses (l1) on a set wavelength in the direction of the target (4). In the weapon (3) a receiver (6) is arranged to receive and detect pulses on the set wavelength reflected from the target (4). There is also a direction sensing means in the weapon (3) for determining the direction of the target (4). A transmitter (7) is arranged in the weapon (3) to periodically transmit a second train of pulses (l2) on the set wavelength in the direction of the target (4). There are means in the receiver (6) to extract a reflection from the target (4) of the second train of pulses (l2). There are further timing means to determine the period of time from transmitting the second train of pulses (l2) to receiving the reflection from the target (4) of the second train of pulses (l2).

Abstract: The invention concerns a laser pointing sighting system comprising a designator range finder (19) including means (E) for emitting a designating laser beam and reception means (R) for detecting and processing the reflection of a hot spot formed by said beam on a target, said reception means (R) are capable in the absence of designating beam emission by the range finder, of detecting the reflection of a hot spot formed on a target by a third designating device, the system comprising means capable, when the reception means detect such a hot spot, of being automatically oriented relative to the direction defined by said spot.

Abstract: Applicants' ATR system is weather-agile because it is comprised of a primary target sensing means that is capable of surveilling the target scene in foul or fair weather, and a secondary target sensing means that is also capable of sensing targets in various weather. The primary and secondary sensing means communicate through a control center so that ultimately, among several weapons available, the most strategically located and equipped weapon is activated for the destruction of a selected target, given the weather. The control center accomplishes the communication by receiving the sensed target signature from the primary sensing means, processing the signature using database already resident in the center and transmitting the processed target signature to the weapon possessing the greatest potential for successfully destroying the target.

Abstract: The present invention relates to a projectile seeker which comprises: (a) A hollow in the projectile for accommodating a light sensor; (b) A light sensor located within said hollow for sensing light which is emitted or reflected from a target, and for producing an electronic signal upon sensing such emitted light; and (c) A longitudinal shaped opening at the slanted front-side surface of the projectile for enabling a shaped field of view to said light sensor which is limited by the boundaries of said opening, the opening width varies in a direction from the front to the back of the projectile in order to cause said electronic signal to depend on the spinning of the projectile and to be proportional to the orientation of the projectile with respect to the object.

Abstract: A plurality of sensor vehicles collect imaging data from an assigned location of a target region having targets and non-targets. The imaging data may be combined based on its location and the combined data is matched to a threat object map to identify the actual targets from the non-targets. In some embodiments, the sensor vehicles may be redirected to collect velocity and/or range information on the identified targets.

Abstract: A method of mapping a first array to a second array is useful where (1) each of the arrays has pixels in sequential columns and rows and the first array has sequential integers identifying each row of pixels, (2) sequential integers identify each column of pixels, and a numerical value is associated with each pixel, (3) the first and second arrays have (or can be made to have) a one to one pairing between columns of the first and second arrays, and (4) groups of four unique pixels in the same column of the first array are paired one to one with a pixel in the paired column of the second array.

Abstract: A projectile navigation system operable within an extremely high G-shock loading environment during the launch phase may include a set of Kalman filters configured to repeatedly calculate a navigational solution by solving a set of non-linear equations of motions of the projectile utilizing a current parameter vector, position, velocity, and attitude of the projectile. The system may include a suite of solid state sensors to calibrate the Kalman filter equations. If desired, the system may also include a satellite based positioning-determining (SBPD) attitude determination system configured to update the state of the host projectile by making real time attitude measurements of the projectile, and a parameter estimator configured to estimate and update a parameter vector of the host projectile. An external guidance and control processor may be used to generate guidance and control signals, enabling real time navigation of the host projectile.

Abstract: Systems and methods for contiguously and accurately updating target object information during an entire target engagement period are provided. The target tracking system includes a database for storing starfield information, an optical beam source configured to illuminate one or more optical beam pulses, first and second camera systems, and a processor. The processor instructs the first camera system to track the object based on recordation of the tracked object, instructs the second camera system to stabilize the tracking image based on the instructions sent to the first camera system, and determines inertial reference information of the tracked object based on the stabilized image and starfield information associated with the stabilized image.

Abstract: A system and method for performing in-orbit alignment calibration using on-board attitude sensors to improve reflector alignment after deployment to improve spacecraft pointing.

Abstract: A target tracking device for target tracking missiles having an electro-optical seeker assembly mounted in a missile structure through gimbals. The seeker assembly responds to target radiation and provides target deviation signals. Actuators, controlled by the target deviation signals, cause the seeker assembly to track the target. The electro-optical seeker assembly is pivotally mounted in the missile structure about a roll axis and a pitch axis only, the pitch axis being orthogonal to the roll axis. First and second pick-offs, providing pick-off signals, are provided for picking off angles of rotation of the seeker assembly about the roll and pitch axes. A structure-fixed inertial sensor unit is provided for measuring the angular rates about three mutually orthogonal axes and providing angular rate signals.

Abstract: A dual servo system for a seeker actuator comprises a seeker head gimballed on a platform and driven in the pitch and yaw senses by respective fast, i.e. high bandwidth low ambit, servo sub-systems, the platform being pivotally mounted with respect to a base and driven in the pitch and yaw senses by respective slow, i.e. low bandwidth high ambit, servo systems. The pivotal mounting between the platform and the base is configured to provide a spherical bearing of relatively large area (typically about 85° solid angle) to provide good resistance to high acceleration loads.

Abstract: A projectile comprises an imaging seeker at a front of the projectile; a front warhead behind the imaging seeker; a power supply; an electronics unit connected to the power supply and comprising a microprocessor circuit board, a voltage regulator circuit board, an inertial measurement circuit board and a fuze and safe and arm circuit board, all electrically connected to each other, the microprocessor circuit board also being connected to the imaging seeker; a rear warhead, the front and rear warheads being electrically connected to the safe and arm circuit board; a rocket motor electrically connected to the electronics unit; foldable fins mounted at the rear of the projectile; a shell that encases the front warhead, the power supply, the electronics unit, the rear warhead and the rocket motor; and a maneuver mechanism disposed in the shell and electrically connected to the microprocessor circuit board.

Abstract: A proximity sensor for use with a guidance system of a smart bomb including a ranging radar proximity sensor configured for mounting on a smart bomb and a radome connected to the ranging radar proximity sensor. A laser radiation sensor system is attached to the proximity sensor, which is configured and arranged to detect laser radiation reflected from a target which passes through the radome and output the azimuth and elevation angles to the target to the guidance system.

Abstract: The invention concerns a procedure for emission of jamming signals for jamming of laser-based measuring instruments as a result of which systems for distance or speed measurement of targets using laser reflection receive further signals (jamming signals) in addition to the laser signals emitted by the measuring system itself and then reflected at the target. The invention is applicable to affect the distance or speed measurement of targets by means of laser-based measuring instruments, where the measurement procedure of the respective laser-based measuring system is jammed or even prevented.

Abstract: An aircraft formation/refueling guidance system guides a follower aircraft relative to a leader aircraft. A datalink provides a position hold and a bias command from the leader aircraft to the follower aircraft. An optical tracker onboard the follower aircraft takes an image of the leader aircraft when receiving the hold command, tracks the leader aircraft using the image, and provides optical tracker movement outputs. A resolver resolves the optical tracker movement outputs to provide resolver control signals. A vernier control receives the bias command to change a position of the follower aircraft by biasing the resolver control signals with a bias signal. A sum circuit connected to the resolver and to the vernier control receives the resolver control signals and the bias signal to provide a sum circuit output signal. An autopilot and autothrottle receives the sum circuit output signal and the position hold command to control the follower aircraft.

Abstract: A technique is provided that uses a dual mode seeker (IR and LADAR) for precise target dynamics measurement, which extends stripping to a much higher altitude than ground based radar. Initial results show that this approach works to altitudes in excess of 100 km. Stripping becomes a reliable way to discriminate lighter weight decoys from reentry vehicles at altitudes and ranges consistent with planned divert capabilities for terminal phase missile defense. It is a finding of this invention that the LADAR will improve the spatial resolution by a factor of five over typical missile defense IR seekers using a common aperture. The LADAR provides a 3D angle, angle, range (AAR) image for each laser pulse which is used to extract the precise target state vectors.

Abstract: A system for automatically correcting flight path of an aircraft onto a predetermined trajectory is provided. A sensor is configured to sense speed and direction of air relative to the aircraft at a predetermined distance in front of the aircraft. A navigation system is configured to determine displacement of a flight path of the aircraft from a predetermined trajectory. A processor is coupled to receive the sensed speed and direction of air from the sensor and the displacement of the flight path from the navigation system. The processor includes a first component that is configured to determine whether the speed of the air at the predetermined distance is indicative of turbulence, and a second component that is configured to automatically generate control signals to correct the flight path of the aircraft from the displacement onto the predetermined trajectory by a time when the aircraft enters the turbulence.

Abstract: A system includes an optical system having a curved window with anamorphic symmetry about a first plane and a second plane perpendicular to the first plane. The window may be, for example, in a flight vehicle such as a missile. An optical corrector is adjacent to a curved inner surface of the window and has an optical corrector shape responsive to a shape of the window. The optical corrector has anamorphic symmetry about the first plane and the second plane. A sensor is disposed to receive an optical ray passing sequentially through the window and the optical corrector.

Abstract: A method, apparatus, article of manufacture, and a memory structure for compensating for optical sensor data corrupted by angular acceleration is disclosed. The method comprises the steps of determining an angular acceleration of the optical sensor and modifying the optical sensor data according to the determined angular acceleration of the optical sensor. The apparatus comprises a sensor for determining an angular acceleration of the optical sensor and a navigation system for modifying the optical sensor data according to the determined angular acceleration of the optical sensor.

Abstract: A method and apparatus for finding a relative direction of received radiation is described. The received radiation is incident upon a window system at an angle and is transmitted therethrough. The magnitude of the transmitted radiation decreases as a continuous function of increasing angle of incidence, known as Fresnel transmittance. Opposing radiation detectors then detect this transmitted radiation, thereby creating a pair of detection signals, By dividing the difference of the detection signals by the sum of the detection signals, a processor generates a beta angle error curve and finds the relative direction of the radiation. Based upon this beta angle error curve, the processor generates an appropriate error correction signal for guiding an object based upon the relative direction of the received radiation. The method and apparatus are readily applicable to guiding munitions using a laser monopulse to designate a target.

Abstract: The invention concerns a procedure for emission of jamming signals for jamming of laser-based measuring instruments as a result of which systems for distance or speed measurement of targets using laser reflection receive further signals (jamming signals) in addition to the laser signals emitted by the measuring system itself and then reflected at the target. The invention is applicable to affect the distance or speed measurement of targets by means of laser-based measuring instruments, where the measurement procedure of the respective laser-based measuring system is jammed or even prevented.

Abstract: A fuzing system for non-spinning or substantially non-spinning weapons is implemented by means of wide angle optics providing at least forward-hemisphere coverage, an array of infrared detectors and a microprocessor for image and data processing, aim-point selection, directional-warhead aiming and skewed-cone fuzing. The skewed-cone fuzing has a generatrix which is the vector sum of missile velocity, warhead velocity and the negative of target velocity.

Abstract: A method of mapping a first array to a second array is useful where (1) each of the arrays has pixels in sequential columns and rows and the first array has sequential integers identifying each row of pixels, (2) sequential integers identify each column of pixels, and a numerical value is associated with each pixel, (3) the first and second arrays have (or can be made to have) a one to one pairing between columns of the first and second arrays, and (4) groups of four unique pixels in the same column of the first array are paired one to one with a pixel in the paired column of the second array.

Abstract: External armament apparatus, including a machine gun, an associated ammunition box for supplying belted ammunition to the gun, a flare dispenser, a missile launcher or other external stores apparatus, and a forward looking infrared sensor (FLIR), is exteriorly supported on a landing gear sponson tow plate of a helicopter, adjacent a cabin area gunner's window. The external mounting of the gun and other armament apparatus frees up cabin space, permits the gunner's window to be closed with the gun in a ready position, and permits a 0.50 caliber machine gun to be used an alternative to either a 7.62 mm mini-gun or a single barrel 7.62 mm machine gun adjacent the gunner's window.

Abstract: A method for operating a short range, air-to-air missile carried by an aircraft flown by a pilot. The missile includes a seeker operative to track a target. The method comprises providing a first indication to the pilot when the seeker is tracking a target, providing a second indication to the pilot when a rate of angular motion of the seeker falls below a given value for a predefined period.

Abstract: A device for detecting attacking guided missiles with optical seeker head and for generating a laser beam directed to such guided missile has an all-around seeker with a detector responding to thermal radiation from the guided missile, and a laser which points to the guided missile detected by the all-around seeker. A roll and pitch gimbal system is provided. A roll gimbal is rotatable relative to the structure about a roll axis. A pitch gimbal is rotatable relative to the roll gimbal about a pitch axis orthogonal to the roll axis. The detector is structure-fixed. An imaging optical system is mounted on the roll and pitch gimbal system. The optical system with its optical axis can point to an object scenario. With each position of the gimbal system, an image of this object scenario is generated on the detector. The laser is also structure-fixed.

Abstract: A guidance seeker system for a projectile includes a plurality of photoconductive sensing elements symmetrically disposed about a central axis of the projectile. When a target is illuminated with a light source, a lens transmits light reflected from the target to one or more of the photoconductive sensing elements. Dependent on which photoconductive sensing element is irradiated, a variance between the line of flight of the projectile and the target is determined. A voltage impulse resulting from irradiation of the photoconductive sensing element triggers actuation of a course corrector, such as a diverter, to nudge the line of flight of the projectile to increase the likelihood of the projectile reaching the desired target. This guidance seeking system is particularly effective when the target is designated with a pulsed laser.

Abstract: An imaging fuse comprising a housing fixable within a receptacle at a fore end of a projectile, a coaxial support frame rotatably supported within the housing and fitted with an imaging assembly. The support frame is axially displaceable with respect to the housing. An axial shock absorbing system is provided intermediate the housing and the support frame, and a spin suppressing mechanism is associated with the support frame, for suppressing rotation of the support frame with respect to the housing.

Abstract: A method of maneuvering target tracing is disclosed. The present invention relates to the field of target tracking and more generally to a method of employing multiple model and variable sampling rate technique, which achieve good tracking performance for a high-g maneuvering target. The results show that the present invention can handle the missile sudden maneuver better and are accurate.

Abstract: A device for generating a laser beam in a LADAR system has a master oscillator with a laser-active medium and an amplifier stage in the form of a fiber optic power amplifier. This power amplifier amplifies the power of the oscillator. A carrier body is provided, on which a length of fiber of the power amplifier is coiled. The carrier body consists of a material of high thermal conductivity. The master oscillator may be a microchip laser. Diode lasers are used as pump light sources for the fiber optic power amplifier. This assembly can be made lightweight and compact, whereby it is particularly suitable for use in missiles.

Abstract: An active mirror guidance system for a vehicle is disclosed. The guidance system includes active mirrors to track a target. The mirrors are moved in response to disturbances detected by sensors or manually via remote control. The image provided from the mirrors is sent to a focus device for processing. A signature signal processing device and additional optics may also be used. A control system connects each of the components of the guidance system. The guidance system is also connected to the vehicle control equipment to steer the vehicle toward the target.

Abstract: A camera system for tracking a target from an aircraft includes a camera with a moveable head, a user interface, and a control circuit. The target has target data indicative of a position of the target, and the aircraft includes a navigation system for generating aircraft data indicative of a current position of the aircraft. The user interface generates the target data, and the control circuit generates pointing data based on the aircraft data and the target data. The pointing data is provided to the camera to cause the camera to direct the camera head at the target. A video display within the aircraft may then display the images from the camera.

Abstract: The present invention relates to a method and an arrangement for guiding a missile. In accordance with the prior art, the angle position of a target (9) when the missile (3) is expected to reach the target is predicted on the basis of the angular velocity determined in a preceding time period. In order to improve the strike accuracy, the operator, in a second subsequent time period, tracks the actual position of the missile in relation to the predicted angle position of the target. If a deviation is observed, a correction command is transmitted to the missile in order to correct the missile trajectory. For this purpose, a communications link is provided to transmit the correction command given by the operator.

Abstract: A missile tracking and deflection system for protecting a platform includes a missile warning system for detecting the presence of a missile and generating a warning signal. A countermeasure processor receives the warning signal and analyzes characteristics of the missile to prioritize a trajectory signal. A track processor receives the trajectory signal and generates a pointer signal. The system also includes a receiver, which is positioned by a pointer that receives the pointer signal, for receiving a passive and/or active signature of the missile to confirm the presence thereof. The countermeasure processor then directs a laser beam at the missile to determine its operational parameters and receives an active signature from the missile.

Abstract: Sight head with integrated laser designator for use in an aircraft such as a rotorcraft. The laser designator (32) is integrated into a zone of a main external assembly of the pod (14) of the sight head (12), enclosed externally in an existing fairing (34). It comprises a laser transmitter (36), a power supply (38) and a radio receiver (40). The laser transmitter (36) is fitted to the site head structure using adjusting screws (46) which allows the alignment to be modified.

Abstract: A camera system for tracking a target from an aircraft includes a camera with a moveable head, a user interface, and a control circuit. The target has target data indicative of a position of the target, and the aircraft includes a navigation system for generating aircraft data indicative of a current position of the aircraft. The user interface generates the target data, and the control circuit generates pointing data based on the aircraft data and the target data. The pointing data is provided to the camera to cause the camera to direct the camera head at the target. A video display within the aircraft may then display the images from the camera.

Abstract: A scanning device, typically ultrasonic, can make a volumetric scan of a conical scanning field. A transducer having a permanent magnet at its back end is gimbal mounted in a housing. Behind the permanent magnet is a hemispheric electromagnet coil assembly having at least two wound electromagnet coils. The coils are energized in turn with an alternating current signal, with the signal applied to any coil being out of phase with the signal applied to any other coil by 180°/n, where n is the number of coils in the hemispheric electromagnet coil assembly. Volumetric scanning is possible by periodically modulating the magnitude or frequency of the signals applied to the coils.

Abstract: A method for guiding an intercepting missile to a body-to-body contact with an airborne target in the atmosphere. The method includes the steps of guiding the intercepting missile to within an appropriate distance from the airborne target, illuminating the airborne target, using an illuminator carried by the intercepting missile, acquiring an image of the illuminated airborne target and, steering the missile in accordance with an aimpoint on the image.

Abstract: A pitot tube cover that is arranged with a cavity to encompass the pitot tube, a central vertical split separates the cover and allows it to separate from the pitot tube. A wind surfaces channel the wind into the split, and a spring holds the cover onto the pitot tube. Once the aircraft reaches a predetermined speed, the wind is forced by the front angled wind surfaces into the split, thus separating the cover from the pitot tube and exposing the tube's opening to the oncoming wind pressure.

Abstract: The present invention provides a ship self-defense missile (SSDM) weapon system for launching a plurality of light weight missiles from an existing vertical tube launch infrastructure. The system for vertically launching missiles from a ship comprises a plurality of tiers having a top tier and a bottom tier in which tier supports a plurality of missiles. The tiers are set into a launch canister having an interior wall to form a vertical stack in the launch canister. A launch means is used for selectively launching at least one of the plurality of missiles from the top tier. A means for ejecting ejects the top tier is depleted of missiles. A vertical movement means raises and lowers the tiers within the launch tube and the vertical movement means raises next tier in the vertical stack into a position to launch.

Abstract: A method and system for pointing and stabilizing a device that needs to be pointed and stabilized with a desired direction, are disclosed, wherein current attitude measurement and attitude rate measurement of the device measured by an attitude producer, which includes an inertial measurement unit, and the desired direction information measured by a target coordinates producer are processed by a pointing controller to compute rotation commands to an actuator. An actuator rotates and stabilizes the device at the desired direction according to the rotation commands in the presence of disturbances and parametric uncertainties to account for the undesired vibration due to disturbances. A visual and voice device provide an operator with visualization and voice indication of the pointing and stabilization procedure of the device.

Abstract: A system for underwater vehicles for detecting and countering laser threats includes laser detectors and associated equipment to be placed in an underwater vehicle for providing protection of underwater vehicles. Detectors for detecting lasers are arranged on the surface of the underwater vehicle and controlled by a laser warning receiver and a signal processor. The risk of detection of the underwater submarine by laser radiation is reduced as a result thereof. Equipment for detecting and diverting objects are also arranged on the surface of the vehicle. The equipment for detecting and diverting objects are connected together and controlled by a laser control processor. The laser control processor directly communicates with a system for guiding weapons and with the laser warning receiver and signal processor.

Abstract: A method for boresighting of a designation system, including a tracker responsive to a detector with reference to an indicator, including the step of directing a beam of light at a target, using a light source, so that the beam of light is reflected from a spot on the target while a temperature of the spot remains substantially constant. The method further includes focusing at least part of the reflected light as an image on the detector and determining a misalignment of the indicator and the image.

Abstract: A background rejection circuit uses the harmonic content of an angularly narrow target to produce a signal. The signal is used to modulate an externally derived audio signal to produce a target indication signal free of background noise.

Abstract: A device for detecting attacking guided missiles with optical seeker head and for generating a laser beam directed to such guided missile has an all-around seeker with a detector responding to thermal radiation from the guided missile, and a laser which points to the guided missile detected by the all-around seeker. A roll and pitch gimbal system is provided. A roll gimbal is rotatable relative to the structure about a roll axis. A pitch gimbal is rotatable relative to the roll gimbal about a pitch axis orthogonal to the roll axis. The detector is structure-fixed. An imaging optical system is mounted on the roll and pitch gimbal system. The optical system with its optical axis can point to an object scenario. With each position of the gimbal system, an image of this object scenario is generated on the detector. The laser is also structure-fixed.

Abstract: A system for guiding projectiles to a target. More particularly, a system for the guidance of projectiles toward a target using a photo detector array (18) and an arrangement of single use thrusters (22). The system is capable of guiding projectile to targets after firing from extended distances.

Abstract: A reconnaissance pod for viewing a scene has a structural backbone extending generally parallel to a pod axis, a forward housing affixed to the backbone, and an aft housing affixed to the backbone. The aft housing is separated from the forward housing along the pod axis. A central housing is mounted between the forward housing and the aft housing along the pod axis. The central housing includes a central body, a window through the central body, and at least a portion of a sensor assembly supported within the central housing from the forward housing and/or the aft housing. A rotational drive assembly has a forward support rotationally supporting the central body from the forward housing, with a forward bearing oriented to permit rotation of the central housing about the pod axis. The rotational drive assembly also includes an aft support rotationally supporting the central body from the aft housing, with an aft bearing oriented to permit rotation of the central housing about the pod axis.

Abstract: An interceptor missile including an infrared radiation detection subsystem and a window assembly in the hull of the missile optically coupled to the infrared radiation detection subsystem. The window assembly includes an inner window, an outer window, and a support subsystem between the inner and the outer windows defining a plurality of infrared transparent fluid flow cooling channels between the inner and outer windows. A source of fluid coupled to the cooling channels for cooling the outer window without adversely affecting the optical properties of either window.