Method for Designating a Target for a Weapon Having Terminal Guidance Via Imaging

A method for designating a target in an area, intended for a weapon having terminal guidance via imaging, by means of an airborne optronic system comprising an imager associated with geolocation means and a processing unit. It comprises the steps of: acquisition of an image of the area by the imager of the system, and geolocation of this image by the geolocation means; extraction from a database of an orthoimage of the geolocated area, called the reference virtual image; designation of the position of the target in the reference virtual orthoimage; extraction from the reference virtual orthoimage of primitives around the position of the target, called virtual primitives; determination of the position of the target with respect to these virtual primitives; transferring the virtual primitives and the position of the target to the weapon having terminal guidance via imaging.

Optical device

An optical device forms a beam path between an optical end element at a beam path end and an object scene into which the beam path is directed via a field of view of the end element. The optical device contains an alignment device for pivoting the field of view relative to a predetermined direction, an end optical unit and an optical articulation for guiding the beam path from the pivoted field of view into the end optical unit. In order to achieve good shielding against spurious radiation, the device has a shielding unit containing a shielding element led partly around the optical articulation, which shielding unit shields the optical articulation against incident radiation that is not incident through the entrance or exit aperture of the optical articulation.

View-point guided weapon system and target designation method

A passive guidance system including a viewpoint capture system (VCS) including a first processor in communication with first memory and a first SWIR imager for creating a viewpoint image database having a plurality of images, at least one of the images having a target point. A weapon guidance module is in communication with the VCS and coupled to a weapon. The weapon guidance module includes a second processor in communication with second memory and a second SWIR imager for storing the viewpoint image database and correlating in-flight images from the second SWIR imager to provide guidance commands directing the weapon to the target point.

Method for automatically managing a homing device mounted on a projectile, in particular on a missile

According to the invention, the projectile ( 1 ) is provided with a strapdown homing device ( 2 ), said device having a lock-on phase during which the latter attempts to detect a target (C), and including an viewing direction ( 3 ), said viewing direction ( 3 ) being fixed with respect to the projectile ( 1 ) and extending along the longitudinal axis ( 4 ) of the latter, said projectile ( 1 ) further comprising control means ( 8 ) for automatically controlling said projectile ( 1 ) so as to cause the longitudinal axis ( 4 ) thereof, in flight and during the lock-on phase of the homing device ( 2 ), to trace a circle, the radius of which increases in time, until the target (C) is detected.

MISSILE GUIDANCE SYSTEM

A hypersonic self-guided missile system is described. Particularly, embodiments describe missiles whose trajectories are controlled by an on-board control unit that decrease the effect of damaging heat to sensitive internal components by employing one or more annular windows, internal mirrors, lenses, and/or cameras. Embodiments may have an internal camera oriented substantially toward or away from the nose of the missile. 1. A missile system comprising:a missile body comprising a nose cone tapering to a tip;an annular window formed in at least a portion of the nose cone;a camera oriented away from the tip;a mirror positioned to direct light from the annular window into the camera; anda control unit operable to adjust a trajectory of the missile based on an image formed by light captured by the camera.2. The system of claim 1 , wherein distance from the camera to the tip is greater than the distance from the annular window to the tip.3. The system of claim 1 ,wherein the annular window is a first annular window; andfurther comprising a second annular window disposed in the nose cone,wherein the mirror is further positioned to direct light from the second annular window into the camera.4. The system of claim 1 ,wherein the annular window is a first annular window and the mirror is a first mirror; andfurther comprising a second annular window and a second mirror,wherein the first mirror is positioned to direct light from the first annular window into the camera and the second mirror is positioned to direct light from the second annular window into the camera.5. The system of claim 1 , wherein the camera generates images from light having a wavelength in a range from three to five micrometers.6. The system of claim 1 , wherein the mirror is at least a portion of a parabolic mirror.7. The system of claim 1 , wherein the mirror has a length and a width corresponding to a length and a width of the annular window.8. The system of claim 1 , wherein the annular window ...

UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION

A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value. 120- (canceled)21. A method comprising:determining, by a processor, an orientation of an unmanned aerial vehicle (UAV) to obtain a terminal homing trajectory towards a target in consideration of at least one of: a crosswind and a motion of the target;effecting, by the processor, a movement of one or more UAV control surfaces to achieve the determined orientation of the UAV;determining, by the processor, at a predefined distance away from the target, an angle offset of the UAV relative to the target so that an ejection of a mass from the UAV will be directed substantially towards the target; andeffecting, by the processor, the ejection of the mass from the UAV towards the target.22. The method of wherein the angle offset is based on a distance between a target point and a boresight point of a body-fixed image frame.23. The method of further comprising:effecting, by the processor, the angle offset of the UAV relative to the target by a movement of the one or more UAV control surfaces.24. The method of claim 23 , wherein the effected angle offset comprises an angular roll component to translate the target point in the body-fixed image frame to thereby maintain an offset angle via the boresight offset angle correction value.25. The method of further comprising:effecting, by the processor, a movement of the ...

MIDBODY CAMERA/SENSOR NAVIGATION AND AUTOMATIC TARGET RECOGNITION

A guidance assembly and method for guiding an ordnance to a target. The assembly can operated in navigation and targeting modes and has an imager/seeker including an objective lens assembly and an imaging sensor array which provide image data for mapping and terminal seeker performance. The imager/seeker is pivotally mounted on the ordnance. An actuator is coupled to the imager/seeker and can be actuated to pivot the imager/seeker relative to a longitudinal axis of the ordnance from a navigation position to a targeting position. A flight control unit communicates with the imager/seeker and the actuator, and has a processor which analyses the image data to provide navigation flight control signals for guiding the ordnance in the navigation mode of operation and determining a target direction via automatic target recognition or aimpoint algorithms for directing the ordnance to the target in the targeting mode of operation. 1. A guidance assembly being operable in a navigation mode and targeting mode for guiding an ordnance to a target , the guidance assembly comprising:an imager/seeker having an objective lens assembly and an imaging sensor array which capture light energy and provide image data for the navigation and targeting modes of operation, the imager/seeker being pivotally mounted on the ordnance;an actuator being coupled to the imager/seeker and actuatable to pivot the imager/seeker relative to a longitudinal axis of the ordnance from a navigation position to a targeting position;a flight control unit communicating with the imager/seeker, the flight control unit having a processor which analyses the image data and provides navigation flight control signals for guiding the ordnance in the navigation mode of operation and determines a target direction via automatic target recognition algorithms for directing the ordnance to the target in the targeting mode of operation.2. The guidance assembly according to claim 1 , wherein the imager/seeker being arranged in ...

UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION

A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value. 1: A method of unmanned aerial vehicle (UAV) body re-orientation comprising:determining, by a processor, a boresight offset angle error correction value based on a distance between a target point and a boresight point of a body-fixed image frame; andeffecting, by the processor, an onboard control surface actuation maneuver comprising an angular roll component to translate the target point in the body-fixed image frame to thereby maintain an offset angle via the boresight offset angle correction value.2: The method of UAV body re-orientation of further comprising:effecting, by the processor, an onboard control surface actuation maneuver comprising a pitch component to translate the target point in the body-fixed image frame to thereby maintain the offset angle via the boresight offset angle correction value.3: The method of UAV body re-orientation of wherein the onboard control surface actuation maneuver further comprises orienting the target point in the body-fixed image frame below a boresight point in the body-fixed image frame.4: The method of UAV body re-orientation of wherein the onboard control surface actuation maneuver further comprises actuating one or more aileron actuators.5: The method of UAV body re-orientation of wherein the onboard control surface actuation maneuver is by one of: a bank-to- ...

Visual guidance system for barrel-fired projectiles

A winged external guidance frame placed on the muzzle that can couple with a projectile while exiting the barrel utilizing the kinetic energy of the projectile to travel to the target while the accuracy is provided by on board electronics and corrected using the wings. Alternately a reusable unmanned aerial system that travels in the speed and direction of the projectile and couples with the projectile as it exits the barrel.

Target recognition and tracking for a salvo environment

A follow-on object for use in a salvo mission in which one or more lead objects (LO) and a follow-on object track a target. A track state of a tracked object within a sensor field-of-view (FOV) of the follow-on object is initialized. Target-state estimator (TSE) processing based on sensor measurements from the sensor FOV is performed to maintain the track state of the tracked object. Kinematic characteristics of the tracked object are evaluated based on the sensor measurements to compute a probability that the tracked object is an LO based on the evaluated kinematic characteristics. If the probability is not greater than a threshold, the tracked object is designated as the target and TSE processing is resumed. Otherwise, the tracked object is designated as an LO and the track state is re-initialized and the track of the LO is excluded from some intercept task considerations.

PAYLOAD ACTIVATION DEVICE

The present disclosure provides a payload activation device. The payload activation device comprises a camera having a fixed focal length, arranged to capture an image of an object on a platform for carrying a payload having the payload activation device, wherein, when the payload is in a first position relative to the platform, the image of the object is in a first focused state and, when the payload is in a second position relative to the platform, the image of the object is in a second focused state. The payload activation device also comprises a processor configured to determine whether the image of the object is in the first focused state or the second focused state and to cause actuation of an activation mechanism within the payload when the image of object is in the second focused state to activate the payload. The present disclosure also provides a deployable payload having the payload activation device and an aircraft for carrying the deployable payload. 1. A payload activation device , the payload activation device comprising:a camera having a fixed focal length, the camera being arranged to capture an image of an object on a platform for carrying a payload having the payload activation device, wherein, when the payload is in a first position relative to the platform, the image of the object is in a first focused state and, when the payload is in a second position relative to the platform, the image of the object is in a second focused state; anda processor configured to determine whether the image of the object is in the first focused state or the second focused state and to cause actuation of an activation mechanism within the payload, when the image of object is in the second focused state, to activate the payload.2. The payload activation device according to claim 1 , further comprising a servo for actuating the activation mechanism claim 1 , the processor being configured to cause actuation of the servo to actuate the activation mechanism when the ...

Unmanned aircraft turn and approach system

An aircraft including a wing system, a plurality of control surfaces, a camera mounted on a camera pod, and a control system. The camera pod is configured to vary the orientation of the camera field of view only in yaw, relative to the aircraft, between a directly forward-looking orientation and a side-looking orientation. The control system controls the control surfaces such that they induce a significant aircraft yaw causing an identified target to be within the field of view of the camera with the camera in the directly forward-looking orientation.

UNMANNED AIRCRAFT TURN AND APPROACH SYSTEM

An aircraft including a wing system, a plurality of control surfaces, a camera mounted on a camera pod, and a control system. The camera pod is configured to vary the orientation of the camera field of view only in yaw, relative to the aircraft, between a directly forward-looking orientation and a side-looking orientation. The control system controls the control surfaces such that they induce a significant aircraft yaw causing an identified target to be within the field of view of the camera with the camera in the directly forward-looking orientation. 1. An unmanned aircraft system including an aircraft , comprising:a wing system configured to carry the majority of the aircraft weight when in flight;a plurality of control surfaces configured to control aircraft pitch, aircraft roll and aircraft yaw in flight;a camera characterized by a field of view, the camera being mounted on a camera pod, wherein the camera pod is configured to vary the orientation of the camera field of view only in yaw, relative to the aircraft, between a directly forward-looking orientation and a directly side-looking orientation; anda control system configured to control the control surfaces, and further configured to control the camera pod to change the camera position in yaw relative to the aircraft;wherein the control system is programmed with a commit function for use when the camera is observing an identified target that is not directly in front of the aircraft; andwherein the commit function controls the camera position in yaw such that the camera continuously maintains the identified target within its lateral field of view.2. An unmanned aircraft system including an aircraft , comprising:a wing system configured to carry the majority of the aircraft weight when in flight;a plurality of control surfaces configured to control aircraft pitch, aircraft roll and aircraft yaw in flight;a camera characterized by a field of view, the camera being mounted on a camera pod, wherein the camera pod ...

PURITY MONITOR

A purity monitor is provided. The purity monitor includes a cryo-cooler and a piezo-electric crystal microbalance that may have a matte finish. The cryo-cooler includes a nozzle and plumbing components disposed to supply a fluid having a working pressure of up to 10,000 psig to the nozzle. The nozzle provides for locating substantially all of a pressure drop of the cryo-cooler near an exit thereof. The nozzle sprays fluid onto the piezo-electric crystal microbalance and the piezo-electric crystal microbalance measures a mass of non-volatile residue (NVR) left thereon by the spraying. Respective temperatures of the fluid and the piezo-electric crystal microbalance are controllable based on a type of the NVR. 1. A purity monitor , comprising:a cryo-cooler comprising a nozzle and plumbing components disposed to supply a fluid having a working pressure of up to 10,000 psig to the nozzle,the nozzle being configured to provide for locating substantially all of a pressure drop of the cryo-cooler near an exit thereof; anda piezo-electric crystal microbalance onto which the nozzle sprays fluid and which is configured to measure a mass of non-volatile residue (NVR) left thereon by the spraying,respective temperatures of the fluid and the piezo-electric crystal microbalance being controllable based on a type of the NVR.2. The purity monitor according to claim 1 , wherein the fluid comprises high pressure fluid drawn from a radiation detection system.3. The purity monitor according to claim 1 , wherein the cryo-cooler comprises:a first end receptive of the fluid;a second end coupled to the nozzle;a cooler configured to lower a temperature of the fluid prior to spraying; anda filtering system fluid interposed between the first end and the cooler.4. The purity monitor according to claim 1 , wherein the exit of the nozzle comprises a nozzle orifice and a vena contracta downstream from the nozzle orifice.5. The purity monitor according to claim 1 , wherein the piezo-electric ...

LOW COST SEEKER WITH MID-COURSE MOVING TARGET CORRECTION

A targeting system for guidance correction of a projectile along a flight path toward a target. The targeting system includes seeker/guidance system mounted on the projectile which controls guidance of the projectile along the flight path toward the target. A remote fire control system receives and displays a survey image of a battlefield and enables an operator to mark location coordinates of the target in the survey image. Based on the location coordinates, the fire control system defines a reference image and transmits the reference image and location coordinates to the seeker/guidance system for use in guiding the projectile toward the target. If the target moves as the projectile travels toward the target, the remote fire control system enables the operator to update the location coordinates and transmit only an offset of the coordinates to the seeker/guidance system which then adjusts or corrects the flight path of the projectile. 1. A targeting system for guidance correction of a projectile along a flight path toward an intended target , the targeting system comprising:a seeker/guidance control system coupled to the projectile, the seeker/guidance control system controlling guidance of the projectile along the flight path, the seeker/guidance control system being electrically coupled to an onboard communication link for receiving information;a remote imaging device providing a survey image of a battlefield region about the intended target; anda fire control system comprising a communication link electrically coupled to an input device, a display device and a processor, wherein the communication link facilitates receiving the survey image, the display device displays at least some portion of the survey image, the input device facilitates identifying location coordinates of the intended target, and the processor identifies a reference image about the location coordinates;wherein the communication link of the fire control system facilitates transmission of at ...

PROTECTIVE DOME FOR A DUAL MODE ELECTROMAGNETIC DETECTION SYSTEM

A dual mode electromagnetic detection system and a protective dome for the electromagnetic detection system are described. The protective dome includes a substrate having a portion transparent to both infrared radiation and radio frequency radiation. The portion of the substrate includes a macromolecular material including a polymer selected from a family of polyolefins and an antistatic additive. 1. A protective dome for an electromagnetic detection system , comprising a substrate having a portion transparent to both infrared radiation and radio frequency radiation , characterized in thatsaid portion of the substrate comprises a macromolecular material including a polymer selected from a family of polyolefins and an antistatic additive.2. The protective dome of claim 1 , wherein said polymer material is polyethylene.3. The protective dome of claim 1 , wherein said polymer material is polypropylene.4. The protective dome of any one of the preceding claims claim 1 , wherein said substrate has a uniform thickness.5. The protective dome of any one of to claim 1 , wherein said substrate has a variable thickness.6. The protective dome of any one of the preceding claims claim 1 , wherein said substrate comprising another portion claim 1 , wherein said another portion includes stiffening members.7. The protective dome of claim 6 , wherein said another portion is includes a material transparent at least to radio frequency radiation.8. The protective dome of claim 6 , wherein said stiffening members include a stiffening grid.9. The protective dome of claim 6 , wherein said stiffening elements includes stiffening ribs.10. A dual mode electromagnetic detection system comprising:an infrared seeker having an infrared camera;a radio frequency radar having an antenna arrangement; anda protective dome housing the infrared camera and the antenna arrangement, said protective dome comprising a substrate having a portion transparent to both infrared radiation and radio frequency ...

SYSTEM AND METHOD FOR INTERCEPTING AN EXO-ATMOSPHERIC TARGET USING PASSIVE RANGING ESTIMATION

A target intercept system for guiding an interceptor to a target using passive ranging includes an EO/IR sensor that provides target azimuth and elevation angles, target irradiance, target area and target length. A dual Kalman Filter architecture is implemented where, prior to a target image becoming resolved, i.e., prior to endgame, a first Kalman Filter provides guidance as a function of target azimuth and elevation angles and target irradiance measurements. After the target image becomes resolved, i.e., at endgame, a second Kalman Filter provides guidance as a function of target azimuth and elevation angles, target area and, optionally, target length, instead. The dual Kalman Filter approach improves the estimates of time-to-go by optimizing the on-board EO/IR sensor measurements at the optimal times. 1. A system for guiding an interceptor toward a target using passive ranging estimation , the system comprising: detect the target and output corresponding target azimuth information, target elevation information, target irradiance information, target length information, target area information and a respective validity indicator for each of the target azimuth information, target elevation information, target irradiance information, target length information and target area information;', 'determine that the target irradiance information is valid and the target area information is invalid only when the target is detected as a point source; and', 'determine that the target irradiance information is invalid and the target area information is valid only when an image of the target has been resolved,', 'wherein the target area information and the target irradiance information cannot both be indicated as being valid at a same time;, 'an EO/IR sensing device configured to a first Kalman Filter configured to generate the interceptor guidance information as a function of the target azimuth information, the target elevation information and the target irradiance information; ...

UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION

A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value. 1. A method of unmanned aerial vehicle (UAV) body re-orientation comprising:determining, by a processor, a boresight offset angle error correction value based on a distance between a target point and a boresight point of a body-fixed image frame; andeffecting, by the processor, an onboard control surface actuation maneuver comprising an angular roll component to translate the target point in the body-fixed image frame to thereby maintain an offset angle via the boresight offset angle correction value.2. The method of UAV body re-orientation of further comprising:effecting, by the processor, an onboard control surface actuation maneuver comprising a pitch component to translate the target point in the body-fixed image frame to thereby maintain the offset angle via the boresight offset angle correction value.3. The method of UAV body re-orientation of wherein the onboard control surface actuation maneuver further comprises orienting the target point in the body-fixed image frame below a boresight point in the body-fixed image frame.4. The method of UAV body re-orientation of wherein the onboard control surface actuation maneuver further comprises actuating one or more aileron actuators.5. The method of UAV body re-orientation of wherein the onboard control surface actuation maneuver is by one of: a bank-to- ...

Navigation System with Monocentric Lens and Curved Focal Plane Sensor

A navigation system includes a monocentric lens and one or more curved image sensor arrays disposed parallel and spaced apart from the lens to capture respective portions, not all, of the field of view of the lens. 1. A navigation system comprising:a monocentric objective lens; anda first curved image sensor array disposed parallel to, and spaced apart from, the lens.2. A navigation system according to claim 1 , wherein:the lens has a focal length; andthe first curved image sensor array is spaced apart from the lens by the focal length.3. A navigation system according to claim 1 , wherein:the lens has a field of view; andthe first curved image sensor array is sized to receive light from less than 80% of the field of view.4. A navigation system according to claim 1 , wherein:the lens has a field of view; andthe first curved image sensor array is sized to receive light from less than 25% of the field of view.5. A navigation system according to claim 1 , wherein:the lens has a field of view; andthe first curved image sensor array is sized to receive light from a first portion, less than all, of the field of view; the navigation system further comprising:a plurality of optical fibers optically coupling the first curved image sensor array to the monocentric objective lens.6. A navigation system according to claim 1 , further comprising a controller communicatively coupled to the first curved image sensor array and configured to use image data from the first curved image sensor array to automatically determine a location of the navigation system.7. A navigation system according to claim 6 , wherein:the first curved image sensor array is configured to send the image data in a compressed form; andthe controller is configured to use the image data in the compressed form to determine the location of the navigation system, without decompressing the image data.8. A navigation system according to claim 1 , wherein:the lens has a field of view; andthe first curved image sensor ...

Missile system with navigation capability based on image processing

The present invention relates to electro-optic guided missile systems and, in particular, it concerns systems and methods providing enhanced navigation capabilities based on ego-motion processing of seeker images. The missile system comprising: a missile; a seeker located at a nose portion of said missile, said seeker comprising an electro-optic imaging sensor; and a control arrangement for steering the missile along a flight path to a target, characterized in that the missile system further comprises: a navigation subsystem receiving images from said imaging sensor, said navigation subsystem being configured to: co-process a plurality of said images from said imaging sensor to derive ego-motion of said missile relative to a region viewed by said imaging sensor; derive from said ego-motion a calculated target direction from said missile to a target.

MODULAR UNDERWATER TORPEDO SYSTEM

A torpedo apparatus comprises a propulsion module operable to propel the torpedo apparatus through water and a steering module operatively coupled to the propulsion module. The steering module including a plurality of fins which are controllable for controlling a direction of travel of the torpedo apparatus through water. A plurality of head modules are removably and interchangeably attachable to the torpedo apparatus, wherein each of the head modules houses at least one guidance assembly and at least one utility assembly. A power supply module is configured to provide power to the propulsion module, the steering module, and an attached one of the head modules. 1. A torpedo apparatus , comprising:a propulsion module operable to propel the torpedo apparatus through water;a steering module operatively coupled to the propulsion module, the steering module including a plurality of fins which are controllable for controlling a direction of travel of the torpedo apparatus through water;a plurality of head modules removably and interchangeably attachable to the torpedo apparatus, wherein each of the head modules houses at least one guidance assembly and at least one utility assembly; anda power supply module configured to provide power to the propulsion module, the steering module, and an attached one of the head modules.2. The torpedo apparatus of claim 1 , wherein the guidance assembly includes an optical receiver for detecting light reflected from a target claim 1 , the optical receiver cooperating with the steering module to direct the torpedo apparatus to the target.3. The torpedo apparatus of claim 2 , wherein the guidance assembly is configured to follow an ultraviolet (UV) laser designator beam.4. The torpedo apparatus of claim 1 , wherein the guidance assembly includes an acoustic transducer for detecting sound waves emanating from a target claim 1 , the acoustic transducer cooperating with the steering module to direct the torpedo apparatus to the target.5. The ...

Systems, Methods and Computer-Readable Media for Improving Platform Guidance or Navigation Using Uniquely Coded Signals

A spatially-distributed architecture (SDA) of antennas transmits respective uniquely coded signals. A first receiver having a known position in a coordinate system defined by the SDA receives reflected versions of the uniquely coded signals. A first processor receives the reflected versions of the uniquely coded signals and identifies a position of a non-cooperative object in the coordinate system. A platform with a platform receiver receives non-reflected versions of the uniquely coded signals. The platform determines a position of the platform in the coordinate system. In an example, the platform uses a self-determined position and a position of the non-cooperative object communicated from the SDA to navigate or guide the platform relative to the non-cooperative object. In another example, the platform uses a self-determined position and information from an alternative signal source in a second coordinate system to guide the platform. Guidance solutions may be generated in either coordinate system. 1. A method , comprising:receiving, with a first receiver connected to a platform, a set of uniquely identifiable signals transmitted from respective spatially-distributed antenna arrays separate from the platform;determining, with a platform processor in communication with the first receiver, one or more of a position, a motion and an orientation of the platform in a first coordinate system, wherein the platform processor identifies at least one of the position, motion and orientation of the platform using one or more characteristics of the uniquely identified signals received by the first receiver;receiving one or more signals containing information about a position of a non-cooperative object, wherein the information about the position of the non-cooperative object is communicated in an established inertial frame or the first coordinate system defined by the spatially-distributed antenna arrays;generating, with the platform processor, a guidance solution responsive ...

Seeker head for a guided missile and method of depicting an object

A seeker head for a guided missile has an outer casing, a detector unit with a matrix detector, and an optical system for depicting an object from an object scene surrounding the guided missile on the matrix detector. The optical system contains entrance optics and an optical link. The seek head further has a rolling-pitching system with a rolling frame and a pitching frame for aligning at least the entrance optics with the object. In order to be able to detect even objects that are far away and radiating weakly when the guided missile is rolling, it is proposed that the detector unit is arranged on the rolling frame for conjoint rolling.

METHOD FOR REDUCING THE LOW-FREQUENCY COMPONENT OF THE MEASUREMENT NOISE OF A PHOTOSENSITIVE IMAGER AND APPLICATIONS OF SAME

A method for reducing the low-frequency component of the measurement noise of a photosensitive imager and applications of same. The invention involves intentionally creating a non-straight scanning movement of the observed scene on the photosensitive matrix of the imager. 111-. (canceled)13. The method according to claim 12 , wherein the amplitude of said scrolling movement is at least equal to 10 pixels.14. The method according to claim 12 , wherein the scrolling movement forms a loop.15. The method according to claim 14 , wherein the loop is approximately circular.16. The method according to claim 12 , wherein said scrolling movement is obtained by controlling an orientation of a line of sight of said imager.17. The method according to claim 16 , wherein said line of sight is fixed relative to said imager claim 16 , and said imager is mounted in a mobile manner.18. The method according to claim 16 , further comprising:observing the scene via the matrix of photosensitive pixels of the photosensitive imager through an optical device implemented with the imager, wherein said imager is fixed and wherein said line of sight is rendered movable by means of said optical device.21. The system according to claim 20 , wherein scrolling movement forms a circular loop.22. The system according to claim 20 , further comprising:a missile comprising the homing device, wherein the missile is configured to use the homing device for a final phase guidance. The present invention relates to a method for reducing the low-frequency component of the measurement noise of an imager with a matrix of photosensitive pixels and its application to the improvement of homing devices for the final phase guidance of missiles towards a target.Photosensitive imagers operating in a time-rated manner and comprising a matrix of photosensitive pixels sensitive to visible light or to infrared radiation are well known. It is also known that the cost of such imagers is higher the greater their resolution, i. ...

PROJECTILE RANGING WITH DIGITAL MAP

A terrain-referenced navigation system for an aircraft comprises: a stored digital terrain map; a position calculation unit arranged to calculate aircraft position relative to the stored digital terrain map to determine a terrain-referenced aircraft position; a fall line calculation unit arranged to calculate a fall line for a projectile starting from the terrain-referenced aircraft position as a launch point; and an impact point calculation unit arranged to directly compare the fall line with the digital terrain map, by incrementally comparing a height of the projectile along the fall line with a height of the terrain according to the stored digital terrain map in order to find an expected impact point on the terrain. 1. A terrain-referenced navigation system for an aircraft , the system comprising:a stored digital terrain map;a position calculation unit arranged to calculate aircraft position relative to the stored digital terrain map to determine a terrain-referenced aircraft position;a fall line calculation unit arranged to calculate a fall line for a projectile starting from the terrain-referenced aircraft position as a launch point; andan impact point calculation unit arranged to directly compare the fall line with the digital terrain map, by incrementally comparing a height of the projectile along the fall line with a height of the terrain according to the stored digital terrain map in order to find an expected impact point on the terrain.2. The system of claim 1 , wherein the impact point calculation unit is arranged to incrementally compare a height of the projectile along the fall line with a height of the terrain by searching map data in the stored digital terrain map.3. The system of claim 2 , wherein the impact point calculation unit is arranged to incrementally compare a height of the projectile along the fall line with a height of the terrain according to a coarse search of the digital terrain map and then according to a fine search of the digital ...

HIT PERFORMANCE WHILE APPROACHING A TARGET

The present invention relates to a computer-implemented method for targeting missiles, to a corresponding computer program, to a corresponding computer-readable medium and to a corresponding data processing device, as well as to a missile. 110. Computer-implemented method () for targeting missiles , comprising the steps of:{'b': '40', 'a) receiving, once and prior to the departure of a missile (), a template T including a target point of aim;'}{'b': 40', '44', '40, 'sub': B', 'neu, 'sup': 'IM', 'b) repeatedly receiving, during the flight of the missile () and at a predefined image cycle rate f, image data I from a camera () of the missile () and inertial range estimations Dfrom an inertial measurement;'}{'sub': 'B', 'c) per image cycle of the predefined image cycle rate f, calculating a pre-scaled starting parameter vector p* for this image cycle using a last calculated range correction ΔD;'}{'sub': B', 'neu', 'p', 'p, 'd) per image cycle of the predefined image cycle rate f, carrying out an iterative Lucas-Kanade method in order to calculate an estimated parameter vector p, including a current scale sbased on the current image data I and on the template T, from the calculated pre-scaled starting parameter vector p* by means of mapping W, wherein the target point of aim is improved by means of the mapping Wusing the estimated parameter vector p;'}{'sub': B', 'neu', 'alt', 'neu', 'alt, 'sup': IM', 'IM, 'f) per image cycle of the predefined image cycle rate f, calculating a range correction ΔD for the next image cycle from a current scale s, a previous scale s, a current inertial range estimation Dand a previous inertial range estimation D; and'}{'b': 40', '40, 'h) per image cycle of the predefined image cycle rate, controlling the missile () in a closed-loop manner in order to target the missile () based on the improved target point of aim.'}210. Method () according to claim 1 , further comprising the step of:{'sub': B', 'p, 'e) per image cycle of the predefined ...

METHOD FOR DETERMINING CHARACTERISTIC-CURVE CORRECTION FACTORS OF A MATRIX DETECTOR THAT IMAGES IN THE INFRARED SPECTRAL RANGE, METHOD FOR CONTROLLING A GUIDED MISSLE AND GUIDED MISSLE

The invention relates to a method for determining characteristic-curve correction factors a matrix detector that images in the infrared spectral range. A good image correction can be obtained by virtue of an area of homogeneous temperature being recorded at two different temperatures by the matrix detector, there being two images with different integration times for each temperature. A signal gradient over the integration time is established for each of the pixels from the four pixel values at the two temperatures in each case and the gain being established from the difference of the signal gradients and characteristic-curve correction factors for the gain being stored. 1. A method for determining characteristic-curve correction factors of a matrix detector that images in an infrared spectral range , which comprises the steps of:recording an area having a homogeneous temperature at two different temperatures by the matrix detector, there being two images with different integration times for each temperature;determining a signal gradient over an integration time for each pixel from four pixel values at the two different temperatures in each case;determining a gain from a difference of signal gradients; andstoring the characteristic-curve correction factors for the gain.2. The method according to claim 1 , which further comprises determining a signal offset for each of the pixels from at least two pixel values that are assigned to one of the temperatures claim 1 , the signal offset is subtracted from the pixel values and the gain is thereupon determined.3. The method according to claim 2 , wherein the characteristic-curve correction factors for the gain are determined while the matrix detector is in a building and the characteristic-curve correction factors for the signal offset are determined during a subsequent use of a guided missile that contains the matrix detector.4. The method according to claim 1 , which further comprises recording the two images with the ...

Multi-function radio frequency (mfrf) module and gun-launched munition with active and semi-active terminal guidance and fuzing sensors

A multi-function radio frequency (MFRF) module integrates command guidance, active and semi-active terminal guidance (and possibly passive) and fuzing sensors for gun-launched munitions into a single assembly. The MFRF module can be incorporated into a variety of different gun-launched munitions to execute missions currently performed by guided missiles. The MFRF module is programmable during munition activation to select the guidance mode, active or semi-active, and a primary fuze mode, proximity or height of burst.

METHOD FOR STEERING A MISSILE TOWARDS A FLYING TARGET

A method steers a missile towards a flying target. In order to permit precise flight to the target even under poor visibility conditions owing to the weather, a radar which is remote from the missile detects the target and transmits data relating to a first location area of the target to the missile. The missile determines, from the data of its own missile radar, a second location area of the target, processes both location areas to form a target area and flies to the target area.

MULTIMODE UNMANNED AERIAL VEHICLE

A system comprising an unmanned aerial vehicle (UAV) configured to transition from a terminal homing mode to a target search mode, responsive to an uplink signal and/or an autonomous determination of scene change. 1. An unmanned aerial vehicle (UAV) comprising:a processing unit which transitions the UAV from a first trajectory to impact a target to a second trajectory to avoid impact of the target by the UAV, wherein the transition is responsive to an indicator generated by onboard processing of the processing unit as an autonomous determination of scene change.2. The UAV of wherein the processing unit maintains a divert trajectory outside of a closed maneuver limit cone while in the first trajectory.3. The UAV of wherein the UAV transfers power from a battery of the UAV to a flight energy of the UAV in the divert trajectory claim 2 , wherein the divert trajectory transitions the UAV from the first trajectory to the second trajectory claim 2 , and wherein the UAV can achieve at least an altitude in the second trajectory as the altitude at a start of the first trajectory.4. The UAV of wherein the processing unit stores at least one of: a pre-terminal commit point and a return waypoint claim 2 , wherein the processing unit transitions the UAV to at least one of: the pre-terminal commit point and the return waypoint in response to an external command to transition the UAV from the first trajectory to the second trajectory.5. The UAV of wherein the external command causes the processing unit to transition from the first trajectory to the second trajectory claim 4 , and wherein the external command is received via an uplink receiver.6. The UAV of further comprising:one or more sensors, wherein the one or more sensors detect at least one of: a UAV position, a UAV linear velocity, a UAV rotational velocity, a UAV linear acceleration, and a UAV attitude.7. The UAV of wherein the processing unit transitions the UAV from the first trajectory to the second trajectory via the ...

OPTICAL RADIATION-COLLECTING ASSEMBLY FOR A HOMING DEVICE FOR GUIDING A ROCKET

An optical radiation-collecting assembly includes a convex mirror, a concave mirror with a central opening and a window, arranged such that light passes through the opening in the concave mirror, is reflected first by the convex mirror and then by the concave mirror, and subsequently passes through the window. The optical assembly is suitable for use in a homing device for guiding a rocket, preventing an optical input component of such a device from being damaged and rendered inoperative from abrasion when exposed to a high-speed air flow containing dense particles. The optical assembly also includes an image-forming function. 1. A radiation-collecting optical assembly designed to form an optical entrance of a seeking device for guiding a self-propelled machine , said collecting optical assembly comprising:a convex mirror, which has a reflecting face and an optical axis;a concave mirror, which is placed in front of the reflecting face of the convex mirror and facing said convex mirror, the concave mirror being provided with an aperture through a central portion of said concave mirror, the concave and convex mirrors having same optical axis, and said optical axis passing through the aperture of the concave mirror at a central point of said aperture; andat least one window that is transparent to the radiation, and that extends behind the convex mirror, on a side opposite the reflecting face of said convex mirror,the assembly being designed so that part of an electromagnetic radiation that passes through the aperture of the concave mirror in direction of the convex mirror is reflected by said convex mirror then by the concave mirror, then passes through the window, and then propagates behind the convex mirror,and being further designed so that a fluid that passes through the aperture of the concave mirror in direction of the convex mirror is deviated in front of said convex mirror, thereby acquiring a radial velocity component that is divergent with respect to the ...

Method for Simulating Live Aircraft Infrared Seeker Obscuration During Live, Virtual, Constructive (LVC) Exercises

The illustrative embodiments provide for a method a training system. The training system includes a physical sensor system connected to a physical vehicle. The physical sensor system is configured to obtain real atmospheric obscuration data of a real atmospheric obscuration. The training system also includes a data processing system comprising a processor and a tangible memory. The data processing system is configured to receive the real atmospheric obscuration data, and determine based on the real atmospheric obscuration data whether a target is visible to the physical vehicle in a simulation training environment generated by the data processing system. The simulation training environment at least including a virtual representation of the physical vehicle and a virtual representation of the real atmospheric obscuration. 1. A training system comprising:a physical sensor system connected to a physical vehicle, the physical sensor system configured to obtain real atmospheric obscuration data of a real atmospheric obscuration; anda data processing system comprising a processor and a tangible memory, the data processing system configured to receive the real atmospheric obscuration data, and determine based on the real atmospheric obscuration data whether a target is visible to the physical vehicle in a simulation training environment generated by the data processing system, the simulation training environment at least including a virtual representation of the physical vehicle and a virtual representation of the real atmospheric obscuration.2. The training system of claim 1 , wherein the vehicle comprises an aircraft claim 1 , and wherein the physical sensor system is installed in an externally mounted pod on the aircraft.3. The training system of claim 1 , wherein the data processing system is further configured to determine whether the real atmospheric obscuration comprises at least one of direct sunlight claim 1 , a cloud claim 1 , smoke claim 1 , or precipitation.4. ...

IMPROVEMENTS IN AND RELATING TO MISSILE TARGETING

A method of targeting a missile. A plurality of images of a target, taken from a plurality of viewpoints, are received. Features in the images characteristic of the target are identified. Data representing the characteristic features are provided to the missile to enable the missile to identify, using the characteristic features, the target in images of the environment of the missile obtained from an imager included in the missile. 1. A method of targeting a missile , the method comprising:receiving a plurality of images of a target taken from a plurality of viewpoints;identifying in the images features characteristic of the target;providing data representing the characteristic features to the missile to enable the missile to identify, using the characteristic features, the target in images of the environment of the missile obtained from an imager included in the missile.2. A method as claimed in claim 1 , wherein the plurality of viewpoints are overlapping viewpoints.3. A method as claimed in claim 1 , wherein the characteristic features are regions of the target which in the image of the target provide a change in contrast greater than a selected threshold value.4. A method as claimed in claim 1 , wherein the characteristic features are identified using a scale-invariant feature transform algorithm.5. A method as claimed in claim 1 , wherein the identification of the characteristic features includes the step of generating resealed versions of at least one of the images of the target.6. A method as claimed in claim 5 , wherein the identification of the characteristic features includes the step of smoothing the resealed image versions.7. A method as claimed in claim 6 , wherein the identification of the characteristic features includes the step of calculating difference images between the smoothed claim 6 , resealed image versions.8. A method as claimed in claim 7 , wherein the identification of the characteristic features includes the step of finding extrema in the ...

METHOD OF STRENGTHENING AN OPTICAL ELEMENT

According to various aspects and embodiments, a system and method for providing an optical element is disclosed. In one example, the optical element includes a substrate formed from a Nanocomposite Optical Ceramic (NCOC) material that includes a first oxide nanograin material dispersed in a second oxide nanograin material, and a compressive layer of the NCOC material formed on a surface of the substrate. 1. An optical element , comprising:a substrate formed of a Nanocomposite Optical Ceramic (NCOC) material including a first oxide nanograin material dispersed in a second oxide nanograin material; anda compressive layer of the NCOC material formed on a surface of the substrate.2. The optical element of claim 1 , wherein the compressive layer of the NCOC material has a microstructure different than a microstructure of the substrate.3. The optical element of claim 2 , wherein the microstructure of the substrate has a grain size that is substantially uniform throughout the substrate and is in a range of about 100 nm to about 200 nm.4. The optical element of claim 2 , wherein the microstructure of the compressive layer has a columnar polycrystalline grain structure with grain boundaries extending approximately perpendicular to the surface of the substrate.5. The optical element of claim 1 , wherein the optical element has a Knoop hardness measured on a surface of the compressive layer of at least 2000 kg/mmfor a 50 g load.6. The optical element of claim 1 , wherein the optical element has a hardness value that is greater than a hardness value of an optical element comprising a substrate of the NCOC material formed without the compressive layer.7. The optical element of claim 1 , wherein the optical element has a flexural strength value of at least 600 MPa at room temperature.8. The optical element of claim 1 , wherein the optical element has a flexural strength value that is greater than a flexural strength value of an optical element comprising a substrate of the NCOC ...

UNMANNED AIRCRAFT TURN AND APPROACH SYSTEM

An aircraft including a wing system, a plurality of control surfaces, a camera mounted on a camera pod, and a control system. The camera pod is configured to vary the orientation of the camera field of view only in yaw, relative to the aircraft, between a directly forward-looking orientation and a side-looking orientation. The control system controls the control surfaces such that they induce a significant aircraft yaw causing an identified target to be within the field of view of the camera with the camera in the directly forward-looking orientation. 1. An unmanned aircraft system including an aircraft , comprising:a wing system configured to carry the majority of the aircraft weight when in flight;a plurality of control surfaces configured to control aircraft pitch, aircraft roll and aircraft yaw in flight;a camera characterized by a field of view, the camera being mounted on a camera pod, wherein the camera pod is configured to vary the orientation of the camera field of view only in yaw, relative to the aircraft, between a directly forward-looking orientation and a directly side-looking orientation; anda control system configured to control the control surfaces, and further configured to control the camera pod to change the camera position in yaw relative to the aircraft;wherein the control system is programmed with a commit function for use when the camera is observing an identified target that is not directly in front of the aircraft; andwherein the commit function controls the camera position in yaw such that the camera continuously maintains the identified target within its lateral field of view.2. An unmanned aircraft system including an aircraft , comprising:a wing system configured to carry the majority of the aircraft weight when in flight;a plurality of control surfaces configured to control aircraft pitch, aircraft roll and aircraft yaw in flight;a camera characterized by a field of view, the camera being mounted on a camera pod, wherein the camera pod ...

SPHERICALLY CONSTRAINED OPTICAL SEEKER ASSEMBLY

A spherically constrained optical seeker assembly includes a spherical lens having an outer surface, an optical sensor assembly associated with the spherical lens, and a gimbal assembly. The optical sensor assembly is coupled to the gimbal assembly. The gimbal assembly is configured to move the optical sensor assembly to at least one desired position on the outer surface of the spherical lens. A method of manipulating the optical sensor assembly includes positioning the optical sensor assembly with respect to the spherical lens and moving the optical sensor assembly to at least one desired position with respect to the outer surface of the spherical lens by the gimbal assembly. 1. A spherically constrained optical seeker assembly comprising:a spherical lens having an outer surface;an optical sensor assembly associated with the spherical lens; anda gimbal assembly, the optical sensor assembly being coupled to the gimbal assembly, the gimbal assembly being configured to move the optical sensor assembly to at least one desired position on the outer surface of the spherical lens.2. The optical seeker assembly of claim 1 , wherein the spherical lens and the gimbal assembly are configured to be mounted in a back shell claim 1 , the back shell including a semi-spherical body having an outer edge that defines a plane of the back shell.3. The optical seeker assembly of claim 2 , wherein the gimbal assembly and the spherical lens are positioned within the back shell with the optical sensor assembly being positioned behind the spherical lens so that the optical sensor assembly has a field of view through the lens.4. The optical seeker assembly of claim 1 , wherein the gimbal assembly includes two arcuate arms configured to move with respect to one another.5. The optical seeker assembly of claim 4 , wherein a first arm of the two arms includes an arcuate body having a first end portion and a second end portion claim 4 , the first arm extending vertically to provided azimuthal ...

DYNAMIC WEAPON TO TARGET ASSIGNMENT USING A CONTROL BASED METHODOLOGY

The system and method of dynamic weapon to target assignment (DWTA) using a control based methodology to dynamically assign each projectile to a target in a multiple target engagement situation. In some cases, closest proximity is used in a real-time, to accomplish the DWTA functional requirement and performance criteria. In some cases, g pulling acceleration and projectile fin deflection motion are also used to assess the best matched pair for each projectile and each target with an end goal of intercepting the target or guiding the projectile to an acceptable error basket for target destruction via detonation. For the closest distance criterion for projectile/target pairing, a cutoff time is used to ensure the pairing is conducted within an acceptable duration while still being able to intercept the target or meet a required miss distance basket (e.g., <3 m). 1. A dynamic projectile to target assignment system , comprising:one or more processors present on an FPGA configured to execute the instructions stored on the FPGA, wherein execution of the instructions causes the one or more processors to perform the following:process a plurality of target measurement data to produce multiple target state estimate vectors;process a plurality of projectile measurement data to produce multiple projectile state vectors to produce one or more potential projectile to target pairs;determine separation distances between each of the one or more projectiles and each of the one or more targets from the potential projectile to target pairs and prioritize based on proximity to produce one or more updated projectile to target pairs;maintain the updated projectile to target pairs as part of a track file management system; andfeed output from the track file management system to a projectile target assignment to calculate a correct acceleration profile to guide the one or more projectiles to intercept the respective one or more targets.2. The system according to claim 1 , further ...

Coordinated Searching Of An Airspace

A method for searching a search area, with a missile and with a missile formation is described Based on the method, in each case at least one radar is arranged in at least two missiles, wherein the method includes: splitting the search area into at least two search subareas, searching the at least two search subareas by the respective radar of the at least two missiles, wherein the at least two missiles carry out the searching cooperatively, wherein the search subareas are chosen such that a total search time is minimal. 1. A method for searching a search area , wherein in each case at least one radar is arranged in at least two missiles , the method comprising:a) splitting the search area into at least two search subareas, 'wherein the search subareas are chosen such that a total search time is minimal.', 'b) searching the at least two search subareas by the respective radar of the at least two missiles, wherein the at least two missiles carry out the searching cooperatively,'}2. The method according to claim 1 , wherein the total search time is the maximum from the search times for the applicable search subareas.3. The method according to claim 1 , wherein the probability of detection of an object in the search area is prescribable or predefined.4. The method according to claim 1 , wherein the search subareas have substantially no overlap.5. The method according to claim 1 , wherein the search area is prescribable or alterable.6. The method according to claim 1 , wherein the splitting of the search area into search subareas changes according to the movement and/or the trajectory of the at least two missiles.7. The method according to claim 1 , wherein the splitting of the search area into search subareas is continually adapted according to the movement and/or the trajectory of the at least two missiles.8. The method according to claim 1 , wherein a minimal probability of detection of an object of prescribed size at a prescribed distance is ensured.9. The method ...

GUIDANCE, NAVIGATION AND CONTROL FOR BALLISTIC PROJECTILES

A system and method to aid in guidance, navigation and control of a guided projectile including a precision guidance munition assembly. The system and method receive position estimates of the guided projectile from a guiding sensor, determine predicted impact points of the guided projectile relative to a target based on the position estimates, determine miss distances of the guided projectile relative to the target, determine smoothed miss distances based, at least in part, on the determined miss distances, and process updated steering commands to steer the guided projectile based on the smoothed miss distances. 1. A precision guidance munition assembly for a guided projectile , comprising:a canard assembly coupled to the precision guidance munition assembly including at least one canard, wherein the at least one canard is moveable;at least one guiding sensor coupled to the precision guidance munition assembly; and receive a first position estimate of the guided projectile;', 'determine a first predicted impact point of the guided projectile relative to a target based on the first position estimate;', 'determine a first miss distance of the guided projectile relative to the target;', 'receive a second position estimate of the guided projectile from the guiding sensor;', 'determine a second predicted impact point of the guided projectile relative to the target based on the second position estimate;', 'determine a second miss distance of the guided projectile relative to the target;', 'determine a smoothed miss distance based, at least in part, on the first determined miss distance and the second determined miss distance; and', 'process an updated steering command to command the at least one canard on the canard assembly to steer the guided projectile based on the smoothed miss distance., 'at least one non-transitory computer-readable storage medium carried by the precision guidance munition assembly having a set of instructions encoded thereon that when executed by ...

Underwater guidance systems, unmanned underwater vehicles and methods

An unmanned underwater vehicle for use in water and with at least one acoustic signal source includes a vehicle body, a steering mechanism to direct the vehicle body through the water, a propulsion device to force the vehicle body through the water, and an adaptive Doppler guidance and control (ADGC) system. The ADGC system is configured to receive acoustic signals from the at least one acoustic signal source and to control the steering mechanism using changes in at least one frequency component of the received acoustic signals caused by Doppler shifts.

METHOD OF STRENGTHENING AN OPTICAL ELEMENT

According to various aspects and embodiments, a system and method for providing an optical element is disclosed. In one example, the optical element includes a substrate formed from a Nanocomposite Optical Ceramic (NCOC) material that includes a first oxide nanograin material dispersed in a second oxide nanograin material, and a compressive layer of the NCOC material formed on a surface of the substrate. 1. A method for treating the surface of an optical substrate ,providing an optical substrate formed of a Nanocomposite Optical Ceramic (NCOC) material including a first oxide nanograin material dispersed in a second oxide nanograin material; anddepositing a compressive layer of the NCOC material on a surface of the optical substrate,wherein the compressive layer of the NCOC material has a microstructure different than a microstructure of the optical substrate, and wherein the microstructure of the compressive layer has a columnar polycrystalline grain structure with grain boundaries extending approximately perpendicular to the surface of the optical substrate.2. The method of claim 1 , wherein depositing includes physical vapor deposition.3. The method of claim 2 , wherein the physical vapor deposition includes sputtering.4. The method of claim 3 , wherein the sputtering includes radio frequency (RF) magnetron sputtering.5. The method of claim 4 , wherein the compressive layer is deposited at a pressure in a range of about 1 mTorr to about 5 mTorr.6. The method of claim 4 , further comprising depositing a protective layer of one of the first and the second oxide nanograin materials onto the compressive layer.7. The method of claim 1 , wherein the microstructure of the optical substrate has a grain size that is substantially uniform throughout the optical substrate and is in a range of about 100 nm to about 200 nm.8. The method of claim 1 , wherein an optical element created by the optical substrate and the compressive layer has a hardness value that is greater than ...

대방사 유도무기용 탐색기

대방사 유도무기용 탐색기를 공개한다. 본 발명은 대방사 유도무기의 관형의 동체 측면 둘레에 배치되는 복수개의 측면 안테나 및 복수개의 측면 안테나에서 감지한 전파신호를 인가받아, 전파신호와 복수개의 측면 안테나 중 전파신호를 수신한 측면 안테나가 배치된 방향을 분석하여 표적의 위치를 판별하는 수신기를 포함한다.

Piezoelectric crystal microbalance purity monitor

순도 모니터가 제공된다. 순도 모니터는 무광택 마감 처리를 가질 수 있는 압전 결정 미량저울 및 극저온 냉각기를 포함한다. 극저온 냉각기는 노즐 및 노즐에 최대 10,000 psig의 작동 압력을 갖는 유체를 공급하도록 배치된 배관 구성 요소를 포함한다. 노즐은 실질적으로 극저온 냉각기의 압력 강하의 전부를 그 출구 근처에 위치시키는 것을 제공한다. 노즐은 압전 결정 미량저울 상으로 유체를 분사하고 압전 결정 미량저울은 분사에 의해 그 위에 남겨진 비 휘발성 잔여물(NVR)의 질량을 측정한다. 유체 및 압전 결정 미량저울 각각의 온도는 NVR의 유형에 기초하여 제어 가능하다. A purity monitor is provided. The purity monitor includes a piezoelectric crystal microbalance and a cryogenic cooler that can have a matte finish. The cryogenic cooler includes a nozzle and piping components arranged to supply a fluid having an operating pressure of up to 10,000 psig to the nozzle. The nozzle provides for locating substantially all of the pressure drop of the cryogenic cooler near its outlet. The nozzle jets the fluid onto the piezoelectric crystal microbalance and the piezoelectric crystal microbalance measures the mass of the nonvolatile residue (NVR) left on it by the jetting. The temperature of each of the fluid and piezoelectric crystal microbalances is controllable based on the type of NVR.

Apparatus and method for controling strike command using ir sensor and lrf sensor

본 발명은 복합 센서를 이용한 타격 명령 제어 장치 및 그 방법에 관한 것으로, 탄두 발사 후, 제1 센서를 이용하여 지상 또는 공중에 존재하는 목표물을 탐지하고, 탐지된 목표물로부터 발생되는 열원을 감지하는 열원 감지부, 탄두 발사 후, 제2 센서를 이용하여 지상 또는 공중에 존재하는 목표물을 탐지하고, 현재 위치에서 탐지된 목표물과의 현재 거리정보를 수집하는 거리정보 수집부 및 수집된 거리정보를 토대로, 탄두에 대한 타격 명령을 제어하는 타격 명령 제어부를 포함한다.

Method for determining positional data of a target object in a reference system

Dual mode radio frequency-infrared frequency system

A combined RF/IR system in which a common surface is used in the dual modes of radiating and absorbing RF energy and of reflecting and focusing IR energy. The common surface is structured, configured, and used as the slotted array antenna for the RF energy and as the primary mirror of a Cassegrain optical subsystem for the IR energy.

Catadioptric Cassegrain lens

Katadioptrisches Cassegrain-Objektiv (20) zum Abbilden eines Gegenstands (34) in eine Bildebene (9) mit einem konkaven Primarspiegel (24), einem konvexen Sekundärspiegel (26) und einer Anzahl von Korrekturlinsen (28, 30, 32) zur Korrektur eines Abbildungsfehlers der beiden Spiegel (24, 26), wobei a) zumindest eine der Korrekturlinsen (28) in einer Passage des Strahlengangs (40) nach der Reflexion am Primärspiegel (24) und vor der Reflexion am Sekundärspiegel (26) angeordnet ist b) die eine Korrekturlinse (28) eine Trägerlinse ist, die den Sekundärspiegel (26) trägt, und c) die eine Korrekturlinse (28) von einem Streulichttubus (44) getragen ist. A catadioptric cassegrain objective (20) for imaging an object (34) into an image plane (9) having a concave primary mirror (24), a convex secondary mirror (26), and a plurality of correction lenses (28,30,32) for correcting a aberration the two mirrors (24, 26), wherein a) at least one of the correction lenses (28) in a passage of the beam path (40) after reflection on the primary mirror (24) and before reflection on the secondary mirror (26) is arranged b) the one Correction lens (28) is a support lens supporting the secondary mirror (26), and c) the correction lens (28) is carried by a scattered light tube (44).

Moving body detection device of camera

In a moving body detection device of a camera in this invention, in order to correctly detect an area in which a target moving body is present even when the camera moves, an area in which the moving body is present is detected from a plurality of divided areas by comparing respective motion vectors. Further, in the moving body detection device of a camera in this invention, an image of an object derived by use of a video camera is detected by a CPU via a Y/C separation circuit, A/D converter circuit and video RAMs. Motion vectors of image portions are detected from the two image portions which are extracted at two different timings from desired first and second preset areas of the detected image displayed on a display unit by means of the CPU, video RAMs, RAM and ROM. Then, whether an object which is present in the first preset area is a moving body or not is determined by the CPU based on the detected motion vector of the image.

A method and system for locating an unknown emitter

The present invention provides a method and system for locating an unknown emitter. According to an embodiment of the invention, the method for locating an unknown emitter comprises launching from a platform a vehicle equipped with an RF receiver/transmitter; and gathering measurements of electromagnetic signal emitted by the unknown emitter and collected by said platform and said vehicle, thereby enabling Time-of-Arrival processing of said measurements for deriving the location of the unknown emitter.

Multimode unmanned aerial vehicle

시스템은 업링크 신호(451) 및/또는 장면 변화의 자발적인 결정에 응답하여, 터미널 호밍 모드(510)로부터 타겟 서치 모드(530)로 트랜지션되도록 구성된 무인 항공기(UAV)(100)를 포함한다.

View-point guided weapon system and target designation method

A passive guidance system including a viewpoint capture system (VCS) including a first processor in communication with first memory and a first SWIR imager for creating a viewpoint image database having a plurality of images, at least one of the images having a target point. A weapon guidance module is in communication with the VCS and coupled to a weapon. The weapon guidance module includes a second processor in communication with second memory and a second SWIR imager for storing the viewpoint image database and correlating in-flight images from the second SWIR imager to provide guidance commands directing the weapon to the target point.

Microwave radiometric guidance system

A missile guidance system utilizing a single microwave radiometric sensor for both terrain correlation and target homing. Terrain correlation is used to get the missile within the acquisition range of the homing system, and the homing system is used in the terminal phase of operation.

Heat Sensing System with High-Speed Response Calibrator and Application Method of Uniformity Correction

광자 검출기(14)들의 어레이를 포함하고 있는 열 감지 시스템(10)은 조사광에 대한 검출기 의존 응답을 생성한다. 개개의 검출기 특성의 변화는 영상이나 다른 응답을 열화시키는 고정 패턴 노이즈를 생성한다. 전환 가능 미러(M1)가 위치(P cal )에서 발광 다이오드(20)로부터의 적외선 조사광이 검출기 어레이(14)로 향하도록 한다. 상기 다이오드(20)는 양 및 음의 발광 방출기이다. 방출된 플럭스는 주위보다 낮거나 높은 온도의 범위에서 흑체(black body) 조사광과 동일하도록 제어되는 전류이다. 입사 세기를 신호 응답과 관련시키는 전달 함수를 포함하는 교정 관계가 각 검출기에 대해 도출된다. 또한, 미러(M1)는 관측 위치(P obs )에 있을 수 있으며, 원격 장면으로부터의 적외선 조사광이 검출기 어레이(14)에 도달한다. 결과적으로 얻어진 검출기 신호가 이전에 도출된 개개의 교정 관계를 이용하여 보정 플럭스로 변환되며, 감소된 고정 패턴 노이즈를 가진 영상 또는 응답이 얻어진다. A thermal sensing system 10 comprising an array of photon detectors 14 generates a detector dependent response to the irradiated light. A change in the individual detector characteristics produces a fixed pattern noise that degrades the image or other response. The switchable mirror M1 directs the infrared radiation from the light emitting diode 20 to the detector array 14 at the position P cal . The diode 20 is a positive and negative luminescent emitter. The emitted flux is a current controlled to be the same as the black body irradiation light in the range of lower or higher temperature than the ambient. A calibration relationship is derived for each detector that includes a transfer function that relates the incident intensity to the signal response. In addition, the mirror M1 may be at the observer position P obs , and the infrared illuminating light from the remote scene reaches the detector array 14. The resulting detector signal is converted to a correction flux using the previously derived individual calibration relationships and an image or response with reduced fixed pattern noise is obtained.

How to engage a target

본 발명은 최초 발사체 이후에 런칭되어 타겟을 향해 발사되는 적어도 하나의 후속 발사체의 충돌 지점을 개선하는 방법으로서, 타겟을 감지하는 능력을 향상시키기 위하여 후속 발사체는 선행 발사체의 자동 폭발 시간에 대한 정보에 기초하여 궤적을 변경할 수 있다. 본 발명은 또한 발사체 및 신관으로 구성된다.

Multimode unmanned aerial vehicle

시스템은 업링크 신호(451) 및/또는 장면 변화의 자발적인 결정에 응답하여, 터미널 호밍 모드(510)로부터 타겟 서치 모드(530)로 트랜지션되도록 구성된 무인 항공기(UAV)(100)를 포함한다. The system includes an unmanned aerial vehicle (UAV) 100 configured to transition from a terminal homing mode 510 to a target search mode 530 in response to an uplink signal 451 and/or a voluntary determination of a scene change.

Missile and method for detecting a target

Die Erfindung geht aus von einem Verfahren zum Erfassen eines Ziels (8) durch einen von einer Trägerplattform (4) gehaltenen Flugkörper (2) mit einem Suchkopf, bei dem das Ziel (8) anvisiert wird und Zieldaten an ein Suchersystem (12) des Flugkörpers (2) übergeben werden. Es wird vorgeschlagen, dass das Suchersystem (12) des Flugkörpers (2) das Ziel (8 als solches anhand der übergebenen Zieldaten erfasst während dem Suchkopf die Sicht auf das Ziel (8) versperrt ist. Das Ziel kann durch den noch in der Trägerplattform verborgenen Flugkörper erfasst werden, ohne dass auf eine gute Tarnungseigenschaft der Trägerplattform verzichtet werden muss.

Gimbal Composite Sensor Homming System

Disclosed is a gimbal composite sensor homing system which easily embodies alignment for information fusion between sensors. To this end, the present invention comprises: a semi-active laser beam sensing unit which receives a reflective signal reflected by a target corresponding to a laser beam projected towards the target from an external device; an infrared light video sensing unit which traces the target included in an infrared light video acquired with respect to a monitoring area; and a driving unit which is provided to aim the infrared light video sensing unit and the semi-active laser beam sensing unit simultaneously to the direction of the target.

Real-time Small Target Detection Method using Local Contrast Difference Measure

The present invention relates to a real-time small target detection method using local contrast difference measure comprises the following steps: detecting a small target candidate region; selecting label regions and obtaining a size (k) and a center coordinate of each label region; obtaining a local contrast map; classifying the region into a region having a high possibility of a small target and a region having a small possibility of a small target; and detecting a small target by performing adaptive binarization according to a pixel brightness value of the target. The real-time small target detection method using local contrast difference measure of the present invention can overcome the scale-dependent problem of a structure element-based target detection method by dynamically calculating the scale of the target by predicting target candidate pixel regions through the morphological difference operation and labeling predicted candidate pixels.

Individual-use guided anti-aircraft missile

FIELD: rocketry, in particular, guided missiles allotted to portable anti-aircraft complexes intended for interception of aerial targets. SUBSTANCE: missile has infrared homing head 1 with target bearing pick-off 2, solid-propellant engine installation with two-regime cruise engine 10 and booster rocket 11 trapped in the launching tube, control department 3 with control actuator 4, on-board power source 5 and on-board connector 6 switching the missile circuits to the launcher before the launch, and high-explosive warhead 7, including the fuse actuating unit, main eddy-current target sensor and duplicating impact target sensor. To enhance the probability of target destruction, the body of warhead 7 accommodates a laser contactless target sensor and shaper of controlled delay of warhead blasting pulse. Control of delay of blasting pulse of warhead 7 is accomplished by anti-aircraft gunner by means of switches on the launching tube and launcher, as well as by automatic selector of the "pursuit-toward" interception regimes owing to the coupling of the delay shaper control circuit to infrared homing head bearing pick-off 2. Thus, due to selection of the delay value the moment of warhead blasting is determined, which takes into account the target flight speed and direction, target dimensions and conditions of its interception ("pursuit" or "toward"). EFFECT: enhanced efficiency. 2 dwg па ЧУ ЕС ГЭ РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (19) (51) МПК ВИ” 2111 445‘ 13) Сл Е 42 В 15/00 12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ (21), (22) Заявка: 96120588/02, 11.10.1996 (46) Дата публикации: 20.05.1998 (56) Ссылки: Переносной ЗРК 9КЗ8. ТО и инструкция по эксплуатации. -М.: Воениздат, 1987. (71) Заявитель: Конструкторское бюро машиностроения (72) Изобретатель: Гущин Н.И.., Кашин В.М., Фокин Р.В., Деев Л.Г., Батищев К.А., Судариков В.И., Смирнов А.Г., Огнев В.Н. , Вуколов А.С., Яблонский А.С., Кувшинов А.М., Воробьев В.Е., Жуков ...

Device for detecting an object scene

Vorrichtung (1, 1') zur Erfassung einer Objektszene mit einem abbildenden optischen System (2) umfassend eine Eintrittsoptik (3), eine Umlenkoptik (4), und eine strukturfeste Verzweigungsoptik (5), mit einer Anzahl von Detektoreinheiten (27, 38, 39) und mit zumindest einer Emittereinheit (28) zur Emission elektromagnetischer Strahlung, wobei – die Eintrittsoptik (3), die Umlenkoptik (4) und die strukturfeste Verzweigungsoptik (5) bezüglich einer Längsachse (6) hintereinander angeordnet sind, – die Umlenkoptik (4) relativ zur strukturfesten Verzweigungsoptik (5) um die Längsachse (6) drehbar gelagert ist, – die Eintrittsoptik (3) relativ zur Umlenkoptik (4) um eine zur Längsachse (6) im wesentlichen orthogonal angeordnete Nickachse (10) schwenkbar gelagert ist, – die Eintrittsoptik (3) zur Sammlung und Ausrichtung einer einfallenden elektromagnetischen Strahlung auf einen Eingangsstrahlengang (8) und zur fokussierten Aussendung von über einen Ausgangsstrahlengang (9) auslaufender elektromagnetischer Strahlung ausgebildet ist, – die Umlenkoptik (4) zur optischen Verbindung der Eintrittsoptik (3) mit der Verzweigungsoptik (5) durch Führung des Eingangs-(8) und des Ausgangsstrahlenganges (9) ausgebildet ist, – die strukturfeste Verzweigungsoptik (5) zur frequenz- und/oder polarisationsabhängigen Zerlegung von über den Eingangsstrahlengang (8) einlaufender elektromagnetischer Strahlung und zur Führung von der Emittereinheit (28) emittierter elektromagnetischer Strahlung auf den Ausgangsstrahlengang (9) ausgebildet ist, – zur Separation von einfallender und emittierter elektromagnetischer Strahlung in der Eintrittsoptik (3) eine Aperturtrennung (18) ausgebildet ist, die Aperturtrennung (18) in der Eintrittsoptik (3) eine Mittenausnehmung (19) umfasst, – im Bereich der Mittenausnehmung (19) eine Kollimationsoptik (20) zur Fokussierung emittierter Strahlung ausgebildet ist. Device (1, 1 ') for detecting an object scene with an imaging optical system (2) comprising ...

Device for detecting an object scene

Vorrichtung (1) zur Erfassung einer Objektszene mit einem abbildenden optischen System, umfassend – eine Eintrittsoptik (2) mit einer Mittenausnehmung (3), – eine Anzahl von Detektoreinheiten (6, 7), – zumindest eine Emittereinheit (5) zur Strahlemission sowie – eine in der Mittenausnehmung (3) der Eintrittsoptik (2) angeordnete Separationsoptik (4), wobei die Separationsoptik (4) a) mit jeweils einer Faserzuführung (19a, 19b) mit der Emittereinheit (5) und mit einer auf die Zielstrahlung der Emittereinheit (5) ansprechenden Detektoreinheit (6) optisch verbunden ist und b) eine beidseitig reflektierende Schicht (18) umfasst, wobei über eine erste Seite der Schicht (18) ein über die Faserzuführung (19a) von der Emittereinheit (5) zugeleiteter Strahl in Richtung der Objektszene lenkbar ist und über die zweite Seite der Schicht (18) ein über die Eintrittsoptik (2) eintretender Strahl zur Einkopplung in die mit der Detektoreinheit (6) optisch verbundene Faserzuführung (19b) lenkbar ist. Device (1) for detecting an object scene with an imaging optical system, comprising - An entrance optics (2) with a central recess (3), A number of detector units (6, 7), - At least one emitter unit (5) for beam emission and A separation optics (4) arranged in the center recess (3) of the entrance optics (2), the separation optics (4) a) each having a fiber feed (19 a, 19 b) is optically connected to the emitter unit (5) and with a on the target radiation of the emitter unit (5) responsive detector unit (6) and b) comprises a layer (18) reflecting on both sides, wherein a beam directed via the fiber feed (19a) from the emitter unit (5) can be directed in the direction of the object scene via a first side of the layer (18) and over the second side of the layer (18). 18), a beam entering via the entry optics (2) for coupling into the fiber feed (19b) optically connected to the detector unit (6) can be guided.

Piezoelectric Quartz Microbalance Purity Monitor

SEARCHING HEAD FOR MISSILES OR PROJECTILES

Pour une tête chercheuse pour des missiles ou des projectiles de poursuite, un système optique reproducteur (18) muni d'un axe optique (76) est disposé sur un rotor (16) qui est logé dans le missile (10) de façon susceptible à pivoter de tous les côtés et qui tourne autour d'un axe de figure. Le rotor (16) est stabilisé par ce moyen en tant que gyroscope dans l'espace inertiel et découplé des déplacements du missile (10). Le système optique reproducteur (18) reproduit une scène-objet sur une couronne circulaire d'éléments détecteurs (50). Le rotor (16) est susceptible d'être stimulé, en vue de déplacements contrôlés de nutation et de précession, par des circuits de réglage avec des moyens de capteur de position et des moyens générateurs de moments (70). L'axe optique (76) du système optique (18) exécute en mode de recherche et de détection un déplacement périodique en spirale balayant un champ de vision élargi, et exécute en mode de poursuite, après détection de la cible, un déplacement rotatoire dans un domaine du champ de vision limité comprenant la cible. En mode de poursuite, l'image de la cible tourne sur la couronne d'éléments détecteurs (50). For a homing head for missiles or tracking projectiles, a reproducing optical system (18) provided with an optical axis (76) is disposed on a rotor (16) which is housed in the missile (10) in a manner susceptible to swivel from all sides and which rotates around a figure axis. The rotor (16) is stabilized by this means as a gyroscope in inertial space and decoupled from the movements of the missile (10). The reproducing optical system (18) reproduces an object scene on a circular ring of detector elements (50). The rotor (16) is capable of being stimulated, with a view to controlled nutation and precession displacements, by adjustment circuits with position sensor means and moment generator means (70). The optical axis (76) of the optical system (18) performs in search and detection mode a ...

GUIDING METHOD TERMINAL AND MISSILE GUIDE OPERATING ACCORDING TO THIS METHOD

METHODE DE GUIDAGE DE LA PORTION TERMINALE DE LA TRAJECTOIRE D'UN MISSILE GUIDE 10 MUNI D'UN SENSEUR 23 ET COMPRENANT DEUX SECTIONS 20 ET 30 ACCOUPLEES PAR UN ARBRE CENTRAL 21 ET LIBRES DE TOURNER L'UNE PAR RAPPORT A L'AUTRE AUTOUR DE L'AXE LONGITUDINAL X; LA SECTION 20 COMPORTANT UN ORGANE MOTEUR 24 POUR CONTROLER L'ATTITUDE DE ROULIS DE CETTE SECTION ET UN GENERATEUR DE GAZ 26 QUI ALIMENTE UNE TUYERE 27 POUR FOURNIR UNE FORCE DE POUSSEE TRANSVERSE P ET LA SECTION 30 EST MUNIE D'UN EMPENNAGE STABILISATEUR 31 FORME PAR UN JEU D'AILETTES DEPLOYABLES 32. L'INVENTION TROUVE SON APPLICATION, NOTAMMENT, DANS L'INTERCEPTION DE CIBLES ANIMEES D'UNE VITESSE MODEREE, TELLES QUE CELLES CONSTITUEES PAR DES VEHICULES TERRESTRES. GUIDING METHOD OF THE TERMINAL PORTION OF THE TRAJECTORY OF A GUIDE MISSILE 10 EQUIPPED WITH A SENSOR 23 AND INCLUDING TWO SECTIONS 20 AND 30 COUPLED BY A CENTRAL SHAFT 21 AND FREE TO TURN THE ONE IN RELATION TO THE OTHER AROUND THE OTHER. THE LONGITUDINAL AXIS X; SECTION 20 INCLUDING A DRIVE 24 TO CONTROL THE ROLL ATTITUDE OF THIS SECTION AND A GAS GENERATOR 26 WHICH SUPPLIES A TUBE 27 TO PROVIDE A TRANSVERSE THRUST FORCE P AND SECTION 30 IS EQUIPPED WITH A STABILIZER STABILIZER 31 SHAPE BY A SET OF DEPLOYABLE FINS 32. THE INVENTION FINDS ITS APPLICATION, IN PARTICULAR, IN THE INTERCEPTION OF ANIMATED TARGETS AT A MODERATE SPEED, SUCH AS THOSE CONSTITUTED BY LAND VEHICLES.

Self-steering mechanism with optical detection, in particular for mobile devices such as special vehicles

Patent FR2531232B1

GUIDING PROCESS OF A ROCKET

OPTICAL SELF-DIAGRAM SYSTEM WITH IMAGING

SYSTEME OPTIQUE D'AUTODIRECTEUR A IMAGERIE COMPORTANT UN DISPOSITIF OPTIQUE DE BALAYAGE DU CHAMP 4, 5 MONTE SUR UNE MONTURE A CARDAN SOLIDAIRE DU GYROSCOPE DU MISSILE ET UN SYSTEME DE DETECTION CONSTITUE PAR UNE BARRETTE DE DETECTEURS 6 DISPOSEE A L'EXTERIEUR DU GYROSCOPE, FIXE PAR RAPPORT A LA STRUCTURE DU MISSILE ET COUPLEE A UNE EXTREMITE 12 D'UN FAISCEAU SOUPLE 11 DE FIBRES OPTIQUES DONT L'AUTRE EXTREMITE 13 DISPOSEE DANS LE PLAN FOCAL DU DISPOSITIF OPTIQUE DE BALAYAGE EST SOLIDAIRE DUDIT DISPOSITIF. LE COUPLAGE ENTRE LES DETECTEURS ET LES FIBRES OPTIQUES EST EFFECTUE SOIT DIRECTEMENT, SOIT PAR L'INTERMEDIAIRE D'UN DISPOSITIF DE TRANSPORT D'IMAGE 10. APPLICATION: DETECTION ET LOCALISATION DE CIBLES. IMAGING AUTO-DIRECTOR OPTICAL SYSTEM INCLUDING AN OPTICAL SCAN DEVICE FOR FIELD 4, 5 MOUNTED ON A CARDAN MOUNT SOLID WITH THE MISSILE GYROSCOPE AND A DETECTION SYSTEM CONSISTING OF A DETECTOR BAR 6 ARRANGED OUTSIDE THE GYROSCOPE OF THE GYROSCOPE IN RELATION TO THE STRUCTURE OF THE MISSILE AND COUPLED TO ONE END 12 OF A FLEXIBLE BEAM 11 OF OPTICAL FIBERS, THE OTHER END 13 OF WHICH ARRANGED IN THE FOCAL PLANE OF THE OPTICAL SCAN DEVICE IS SOLID WITH THE SAID DEVICE. THE COUPLING BETWEEN THE DETECTORS AND THE OPTICAL FIBERS IS CARRIED OUT EITHER DIRECTLY OR THROUGH AN IMAGE TRANSPORT DEVICE 10. APPLICATION: DETECTION AND LOCATION OF TARGETS.

SEARCHING HEAD FOR MISSILE

Cette tête chercheuse pour missile de poursuite, avec chercheur optique (18) découplé des mouvements du missile, comprend une plate-forme non rotative (16) qui est montée dans le missile de façon à être mobile autour d'un point de pivotement (30), autour d'axes de tangage et de lacet, et qui porte le chercheur optique (18). Un dispositif générateur de couple (32), solidaire du missile, pour la production de couples autour d'axes (48, 52) perpendiculaires l'un à l'autre, agit directement sur la plate-forme (16). Sur celle-ci est disposé un bloc détecteur inertiel (26) dont les signaux sont appliqués au dispositif générateur de couple (32) de sorte que la plate-forme (16) soit découplée des mouvements du missile.par. This tracking missile homing head, with optical finder (18) decoupled from missile movements, comprises a non-rotating platform (16) which is mounted in the missile so as to be movable around a pivot point (30 ), around the pitch and yaw axes, and which carries the optical finder scope (18). A torque generator device (32), integral with the missile, for the production of torques around axes (48, 52) perpendicular to one another, acts directly on the platform (16). Thereon is disposed an inertial detector unit (26), the signals of which are applied to the torque generating device (32) so that the platform (16) is decoupled from the movements of the missile.

Dual color/dual function focal plane

A single focal plane integrated circuit hybrid replaces multiple focal plane circuits and associated off-focal plane signal processing electronics. A dual function, dual color focal plane PSD sensor chip assembly includes a PSD array, a traditional pixelized camera array, a signal processing chip, and flip-chip interconnects and wirebond pads to support electronics on the signal processing chip. The camera array is made of a material sensitive to wavelengths longer than the PSD array material is sensitive to. The PSD array is disposed in the same substrate as the camera array. The PSD array tracks object locations and directs the camera array to window and zoom while capturing images. Inherent registration of PSD cells to the pixelized camera array makes responsivity map testing and spatial calibration unnecessary. Reduction in power dissipation is achieved by powering on the camera array only when the PSD detects a change in scene.

VIDEO IMAGING DEVICE, PARTICULARLY FOR SELF-DIRECTING

OPTOELECTRIC DETECTION AND ANGULAR LOCATION SYSTEM OF A LUMINOUS OBJECT

Système permettant de séparer les fonctions filtrage spatial et modulation dues à des grilles mobiles 2, de celle d'ecartométrie. Il comporte une optique intermédiaire 15 entre les grilles 2 et le détecteur 4 du type à quatre quadrants. Les grilles produisent une modulation à une fréquence déterminée. L'optique intermédiaire est avantageusement du type lentille demi-boule dont le centre de courbure coïncide avec le centre O du détecteur pour permettre un déplacement relatif des grilles par rapport au détecteur, tel que une rotation 0 autour de ce centre commandée par un dispositif d'entraînement 16 annexe. L'invention s'applique notamment à réaliser un système autodirecteur infrarouge passif.

Patent FR2675249B1

DEVICE FOR LOCATING AN OBJECT AND APPLICATION

METHOD AND DEVICE FOR GUIDING A FLYING MACHINE, ESPECIALLY A MISSILE, ON A TARGET

DEVICE FOR ANALYZING A SPATIAL FIELD FOR THE ANGULAR LOCATION OF A RADIANT OBJECT

DETECTION SYSTEM FOR ROLLING STABILIZED AIRCRAFT.

Very short range anti-aircraft defense system, surface-to-air missile type.

FLUID CONDUIT CONNECTION

METHOD FOR SELF-GUIDING A MACHINE TO A TARGET BY MEASURING DISTANCE.

L'engin (E) comprend une unité de reconnaissance et poursuite (13) qui reçoit une image infrarouge afin d'en extraire des objets ayant des caractéristiques identiques à des cibles (CB) prédéterminées. Lorsqu'une identification est établie, l'unité de reconnaissance et poursuite (13) commande alors l'unité de commande d'antenne (14) afin que l'objet identifié soit en permanence au centre de l'image reçue. L'unité de repérage (2) établit la position (S, G) de l'antenne (11) par rapport à l'engin (E) et la centrale de référence inertielle (3) établit la position de l'engin (E) par rapport à un repère inertiel afin de calculer (4) la direction (alphaG) de la cible présumée dans le repère inertiel et en déduire la distance (D) séparant l'engin (E) de la cible présumée (CB). Cette information de distance (D) permet une autentification plus précise de la cible. Des moyens supplémentaires (5, 6) permettent d'orienter l'engin (E) en vue d'atteindre la cible (CB) suivant des critères prédéterminée. The machine (E) comprises a recognition and tracking unit (13) which receives an infrared image in order to extract therefrom objects having characteristics identical to predetermined targets (CB). When an identification is established, the recognition and tracking unit (13) then controls the antenna control unit (14) so that the identified object is permanently at the center of the received image. The tracking unit (2) establishes the position (S, G) of the antenna (11) relative to the machine (E) and the inertial reference unit (3) establishes the position of the machine (E) ) relative to an inertial frame in order to calculate (4) the direction (alphaG) of the presumed target in the inertial frame and to deduce therefrom the distance (D) separating the machine (E) from the presumed target (CB). This distance information (D) allows a more precise autentification of the target. Additional means (5, 6) make it possible ...

SEARCHING HEAD FOR MISSILES OR PROJECTILES

OPTICAL DEVICE FOR A SEARCHING HEAD

L'invention concerne un dispositif optique (2) pour une tête chercheuse (16) pour reproduire une zone-objet sur une unité de détection (4), comprenant une unité de commande (24), une première unité optique (10) avec deux prismes, une deuxième unité optique (14) et une unité de déflexion des rayons (18), la première unité optique (10) étant conçue pour diriger sur l'unité de déflexion des rayons (18), de façon superposée, le rayonnement provenant d'au moins deux parties de la zone-objet, et l'unité de déflexion des rayons (18) étant conçue pour sélectionner l'une des deux parties et, en combinaison avec la deuxième unité optique (14), pour reproduire la partie sélectionnée sur l'unité de détection (4). The invention relates to an optical device (2) for a seeker head (16) for reproducing an object area on a detection unit (4), comprising a control unit (24), a first optical unit (10) with two prisms, a second optical unit (14) and a ray deflecting unit (18), the first optical unit (10) being designed to direct onto the ray deflecting unit (18), in a superimposed manner, the radiation coming from of at least two parts of the object area, and the ray deflection unit (18) being adapted to select one of the two parts and, in combination with the second optical unit (14), to reproduce the part selected on the detection unit (4).

METHOD AND DEVICE FOR GUIDING A FLYING MACHINE, ESPECIALLY A MISSILE, ON A TARGET

- La présente invention concerne un procédé et un dispositif de guidage d'un engin volant sur une cible, le dispositif (1) comportant un détecteur (D) pointé sur la cible de sorte qu'une projection de cette dernière est située sur un champ de mesure du détecteur (D), une unité de calcul (UC) pour déterminer des ordres de guidage, et des organes (6) réalisant le guidage. - Selon l'invention, ledit dispositif (1) comporte de plus des moyens de calcul (C3, C4) pour déterminer des ordres de variation d'attitudes dudit engin volant permettant de centrer ladite projection par rapport à une première direction du champ de mesure, et la ligne de visée du détecteur (D) est mobile et est commandée de manière à centrer ladite projection par rapport à une seconde direction du champ de mesure, différente de ladite première direction. - The present invention relates to a method and a device for guiding a flying object over a target, the device (1) comprising a detector (D) pointed at the target so that a projection of the latter is located on a field of the detector (D), a calculation unit (UC) for determining guidance orders, and bodies (6) carrying out the guidance. - According to the invention, said device (1) further comprises calculation means (C3, C4) for determining orders of variation of attitudes of said flying machine making it possible to center said projection with respect to a first direction of the measurement field , and the line of sight of the detector (D) is movable and is controlled so as to center said projection with respect to a second direction of the measurement field, different from said first direction.

SYSTEM FOR OPTOELECTRIC DETECTION AND ANGULAR LOCATION OF A LIGHT OBJECT

Système du type à fonctionnement passif et dans lequel les fonctions de filtrage spatial et de modulation produites par des grilles sont séparées de celle d'écartométrie résultant d'une détection à quatre quadrants, aménagé en vue d'autoriser un fonctionnement bimode, passif ou semi-actif. Pour permettre le fonctionnement semi-actif, les zones opaques des grilles sont en un matériau formant un filtre interférentiel pour le rayonnement émis par un illuminateur laser annexe modulé selon une modulation distincte de celle des grilles, et les circuits de traitement et d'écartométrie comportent des circuits additionnels de démodulation 60-1 à 3, des signaux laser et des circuits de commutation 62-1 à 3 et de sélection 63 prioritaire ou automatique de mode. L'invention s'applique notamment aux systèmes autodirecteurs. System of the passive operation type and in which the spatial filtering and modulation functions produced by grids are separated from that of deviationometry resulting from a four-quadrant detection, designed to allow dual-mode, passive or semi-operation. -active. To allow semi-active operation, the opaque areas of the grids are made of a material forming an interference filter for the radiation emitted by an auxiliary laser illuminator modulated according to a modulation distinct from that of the grids, and the processing and deviation measurement circuits comprise additional demodulation circuits 60-1 to 3, laser signals and switching circuits 62-1 to 3 and 63 priority or automatic mode selection. The invention applies in particular to seeker systems.

Photosensor video camera device for e.g. missile

In front of the two dimensional semiconductor photosensor arrays (1) is mounted an electronic image intensifier (2) with a controllable amplification factor, which is driven by pulses in such a fashion that the image sensors are only lit for a short instant with an amplified intensity during each image period. Pref. displacement sensors (9) give constant data on the craft movement transmitted along with the picture data, to an interpretation circuit (10). A comparator compares the instructed position data with the actual data and a computer acts to compensate for the divergence between them.

TARGET ACQUISITION DEVICE FOR MISSILES

FLUID DRIVE CONNECTION

UN RACCORD DE CONDUITE DE FLUIDE EST SURTOUT CARACTERISE PAR LE FAIT QU'UN AGENT REFROIDISSEUR PEUT ETRE GUIDE PAR LUI SOUS HAUTE PRESSION A TRAVERS DES FOURCHETTES DE CARDAN VERS UN AUTODIRECTEUR A INFRAROUGES MONTE PAR CARDAN DANS DES MISSILES AUTOGUIDES. LE RACCORD DE CONDUITE DE FLUIDE 18 EST ASSEMBLE AVEC UN BALAI POUR LA TENSION DE SIGNAL ET D'ALIMENTATION. L'ETANCHEITE AVEC UNE FRICTION PEU IMPORTANTE ET UN FAIBLE TAUX DE FUITE EST REALISEE JUSQU'A DES HAUTES PRESSIONS PAR UN ELEMENT D'ETANCHEITE SPECIAL 34 QUI EST TENU, PAR LA PRESSION DE FLUIDE, EN CONTACT ETANCHE. UN ALESAGE DE PRECISION 42 ASSURE UN PARFAIT CENTRAGE DES DIFFERENTS ELEMENTS. UN MANCHON 54 RACCORDE L'AXE DE BALAI 12 ET L'ARBRE DE RACCORD 26 ET SOULAGE DE CETTE FACON LE TUBE CAPILLAIRE 32, QUI SERT DE CONDUITE DE FLUIDE, ET QUI EST GUIDE A TRAVERS L'AXE DE BALAI 12 ET BRASE A L'ARBRE DE RACCORD 26. A FLUID LINE CONNECTION IS ESPECIALLY CHARACTERIZED BY THE FACT THAT A COOLING AGENT CAN BE GUIDED BY IT UNDER HIGH PRESSURE THROUGH CARDAN FORKS TOWARDS A CARDAN-MOUNTED SELF-DIRECTOR IN SELF-GUIDING MISSILS. FLUID LINE COUPLING 18 IS ASSEMBLED WITH BROOM FOR SIGNAL AND SUPPLY VOLTAGE. SEALING WITH LITTLE FRICTION AND LOW LEAKAGE RATE IS ACHIEVED UP TO HIGH PRESSURES BY A SPECIAL SEALING ELEMENT 34 WHICH IS HELD BY THE FLUID PRESSURE IN SEALED CONTACT. PRECISION 42 BORING ENSURES PERFECT CENTERING OF THE DIFFERENT ELEMENTS. A SLEEVE 54 CONNECTS THE BROOM SHAFT 12 AND THE COUPLING SHAFT 26 AND IN THIS WAY RELIEVES THE HAIR TUBE 32, WHICH SERVES AS A FLUID DUCT, AND WHICH IS GUIDED THROUGH THE BRUSH SHAFT 12 AND BRACE TO L '' COUPLING SHAFT 26.

Patent FR2469345B1

DEVICE FOR ANALYZING A SPATIAL FIELD FOR THE ANGULAR LOCATION OF A RADIANT OBJECT

DISPOSITIF PERMETTANT DE REALISER DE MANIERE SIMPLE UNE DETECTION D'IMAGE VIDEO PAR BALAYAGE CIRCULAIRE DU CHAMP ET PARTICULIEREMENT ADAPTE A UNE INTEGRATION GYRO-STABILISEE. LE DISPOSITIF COMPORTE UNE OPTIQUE RECEPTRICE CONSTITUE PAR UN MONTAGE CASSEGRAIN AVEC UN MIROIR PRINCIPAL 1 ET UN MIROIR SECONDAIRE 2 MONTES SUR UN MEME AXE OPTIQUE Z, LE MIROIR SECONDAIRE ETANT CONSTITUE PAR UN DIEDRE DROIT TOURNANT ENTRAINE EN ROTATION AUTOUR DE L'AXE Z ET DONT L'ARETE EST PERPENDICULAIRE A CET AXE. DANS UNE VERSION GYROSCOPEE, LE DIEDRE EST ENTRAINE PAR LA TOUPIE DU GYROSCOPE. LE RAYONNEMENT EST FOCALISE SUR UNE BARRETTE DETECTRICE 3 DISPOSEE RADIALEMENT PAR RAPPORT A L'IMAGE POUR POSITIONNER LE DETECTEUR EN AVAL. LE MONTAGE SUR GYROSCOPE PEUT ETRE PREVU POUR REALISER UNE VERSION A CAPTEUR FIXE OU PORTE PAR LA TETE STABILISEE. L'INVENTION S'APPLIQUE NOTAMMENT AUX AUTODIRECTEURS A IMAGERIE INFRAROUGE. DEVICE ALLOWING SIMPLY CARRYING OUT OF A VIDEO IMAGE DETECTION BY CIRCULAR FIELD SCANNING AND PARTICULARLY SUITABLE FOR GYRO-STABILIZED INTEGRATION. THE DEVICE INCLUDES A RECEIVING OPTIC CONSTITUTED BY A CASSEGRAIN MOUNTING WITH A MAIN MIRROR 1 AND A SECONDARY MIRROR 2 MOUNTED ON THE SAME Z OPTICAL AXIS, THE SECONDARY MIRROR CONSTITUTING BY A RIGHT DIEDER ROTATING DRIVED IN Z ROTATION AROUND THE AXIS THE ARETE IS PERPENDICULAR TO THIS AXIS. IN A GYROSCOPE VERSION, THE DIEDRA IS DRAWN BY THE GYROSCOPE ROUTER. THE RADIATION IS FOCUSED ON A DETECTOR BAR 3 ARRANGED RADIALLY IN RELATION TO THE IMAGE TO POSITION THE DETECTOR DOWNSTREAM. MOUNTING ON A GYROSCOPE MAY BE PROVIDED FOR A VERSION WITH A FIXED SENSOR OR CARRIED BY THE STABILIZED HEAD. THE INVENTION APPLIES IN PARTICULAR TO SELF-DIRECTORS WITH INFRARED IMAGING.

DETECTION SYSTEM FOR AIRCRAFT STABILIZED IN ROLL.

- Système de détection pour aéronef (1) stabilisé en roulis. - Selon l'invention, ce système est caractérisé en ce qu'il comporte: . une couronne rotative creuse (3) susceptible de tourner autour de l'axe de roulis (L-L) dudit aéronef; des moyens pour entraîner ladite couronne (3) en rotation autour dudit axe de roulis; . des moyens photosensibles disposés à l'intérieur de ladite couronne rotative creuse (3) et susceptibles d'observer l'environnement dudit aéronef à travers au moins une fenêtre d'observation (5) ménagée dans la paroi périphérique externe (4) de ladite couronne; . des moyens de mesure indiquant à chaque instant la position angulaire de ladite couronne (3) autour dudit axe de roulis (L-L); et . des moyens de traitement recevant les informations délivrées par lesdits moyens photosensibles et par lesdits moyens de mesure.

METHOD FOR DRIVING AND GUIDING TERMINAL PROJECTILES AND PROJECTILES INCLUDING MEANS FOR CARRYING OUT SAID METHOD

L'INVENTION CONCERNE UN PROCEDE DE PILOTAGE ET DE GUIDAGE D'UN PROJECTILE EN PHASE TERMINALE. LA CORRECTION EST OBTENUE GRACE A UN BARILLET DE (N) IMPULSEURS A TUYERES LATERALES. LA COMBUSTION DU PREMIER EST DECLENCHEE LORSQUE LA VITESSE DE ROTATION DE LA LIGNE DE VISEE ATTEINT UN SEUIL DE DECLENCHEMENT. LA POUSSEE MOYENNE DE CHACUN DES IMPULSEURS QUI SE DECHARGE SUCCESSIVEMENT ET COMPLETEMENT DURANT UN SEUL TOUR DU PROJECTILE EST ORIENTEE SELON UNE MEME DIRECTION REPEREE PAR RAPPORT A UN SYSTEME D'AXES DE REFERENCES ABSOLU LIE A LA CIBLE. UNE DETECTION DE LA CIBLE PAR DES MOYENS OPTRONIQUE PERMET DE DETERMINER LORSQUE CE SEUIL DE DECLENCHEMENT EST ATTEINT. L'INVENTION S'APPLIQUE AUX PROJECTILES EMPENNEE DONT LA TRAJECTOIRE EST SUFFISAMMENT TENDUE POUR ETRE ASSIMILEE A UNE LIGNE DROITE, TELS NOTAMMENT QUE LES OBUS D'ARTILLERIE ANTIAERIENNE, ANTIBLINDES AINSI QU'AUX SOUS PROJECTILES UTILISES EN ARTILLERIE SOL-SOL. THE INVENTION RELATES TO A PROCESS FOR CONTROL AND GUIDANCE OF A PROJECTILE IN THE TERMINAL PHASE. THE CORRECTION IS OBTAINED THANKS TO A BARREL OF (N) IMPELLERS WITH SIDE TUBES. THE FIRST COMBUSTION IS TRIGGERED WHEN THE ROTATION SPEED OF THE LINE OF SIGHT REACHES A TRIGGER THRESHOLD. THE AVERAGE THRUST OF EACH OF THE IMPELLERS WHICH DISCHARGES SUCCESSIVELY AND COMPLETELY DURING A SINGLE ROUND OF THE PROJECTILE IS ORIENTED ACCORDING TO A SAME DIRECTION REFERRED TO WITH A SYSTEM OF ABSOLUTE REFERENCE AXES LINKED TO THE TARGET. DETECTION OF THE TARGET BY OPTRONIC MEANS ALLOWS TO DETERMINE WHEN THIS TRIGGER THRESHOLD IS REACHED. THE INVENTION APPLIES TO IMPENSE PROJECTILES WHOSE TRAJECTORY IS SUFFICIENTLY STRETCHED TO BE ASSIMILED TO A STRAIGHT LINE, SUCH AS ANTI-AIR ARTILLERY SHELLS, ANTI-BLIND AS WELL AS SUB-PROJECTILES USED IN SOL-SOL-SOLARTILLERY.

METHOD FOR AUTOMATICALLY MANAGING AN AUTODIRECTEUR MOUNTED ON A FLYING MACHINE, ESPECIALLY ON A MISSILE

OPTICAL GYROSCOPE SEARCHER FOR MISSILE OR THE LIKE

Ce chercheur optique monté en gyroscope libre comprend un groupe 16 comprenant des moyens de focalisation et un réticule, que l'on peut faire basculer autour d'un point fixe d'un axe 27 tandis que des détecteurs optiques 34 sont montés dans une monture 30 mobile en translation parallèlement à cet axe 27 de manière à maintenir le centre des éléments de détection sur le plan image des moyens de focalisation et du réticule. This optical seeker mounted as a free gyroscope comprises a group 16 comprising focusing means and a reticle, which can be tilted around a fixed point of an axis 27 while optical detectors 34 are mounted in a mount 30 movable in translation parallel to this axis 27 so as to maintain the center of the detection elements on the image plane of the focusing means and of the reticle.

METHOD FOR REDUCING THE LOW FREQUENCY COMPONENT OF THE MEASUREMENT NOISE OF A PHOTOSENSITIVE IMAGER AND ITS APPLICATIONS

Missile control system

Guidance for a shell stabilised by rotation, neither finned nor winged with stabilisation of the trajectory by tractive nozzle with differential effect

Device for guiding a projectile 1, by propulsive ogive 2, driven in rotation by a single fin 7, which, when 1 and 2 are engaged "in skating mode", makes the assembly nod along a divergent spiral, until the target lies in the dead angle 9, close to the axis of the trajectory of the projectile 1. An ogive thruster with "annular outlet" serves as an active empennage.

SIMPLIFIED SELF-GUIDING SYSTEM FOR OBUS OR ROQUETTE TYPE

SYSTEME D'AUTO-GUIDAGE SIMPLIFIE POUR ENGIN. LE DISPOSITIF COMPREND UN DISPOSITIF ACCELEROMETRIQUE 5 MONTE DIRECTEMENT SUR LA STRUCTURE DE L'ENGIN 1 POUR DETECTER L'ACCELERATION LATERALE DE L'ENGIN DUE AUX FORCES EXTERIEURES ET L'ACCELERATION CENTRIFUGE DUE AU ROULIS; UN DETECTEUR DE CIBLE 4 MONTE DIRECTEMENT SUR LA STRUCTURE DE L'ENGIN, DES MOYENS D'ENTRETIEN DU MOUVEMENT DE ROULIS DE L'ENGIN ET DES MOYENS D'ELABORATION, A PARTIR DES SIGNAUX DETECTES, DE GRANDEURS SIMPLIFIED SELF-GUIDANCE SYSTEM FOR MACHINERY. THE DEVICE INCLUDES AN ACCELEROMETRIC DEVICE 5 MOUNTED DIRECTLY ON THE STRUCTURE OF THE MACHINE 1 TO DETECT LATERAL ACCELERATION OF THE MACHINE DUE TO EXTERNAL FORCES AND CENTRIFUGAL ACCELERATION DUE TO ROLLING; A TARGET 4 DETECTOR MOUNTED DIRECTLY ON THE STRUCTURE OF THE MACHINE, MEANS OF MAINTENANCE OF THE ROLL MOVEMENT OF THE MACHINE AND MEANS OF ELABORATION, FROM THE SIGNALS DETECTED, OF QUANTITIES

VARIABLE OPTICAL DEVICE DEVICE, APPLICATION TO SELF-DIRECTING OPTICS

TELEVISION MISSILE GUIDANCE SYSTEM

PASSIVE SELF-GUIDING SYSTEM FOR MACHINE