EP4088079A1 - Guidance head and method - Google Patents

Guidance head and method

Info

Publication number
EP4088079A1
EP4088079A1 EP21700327.6A EP21700327A EP4088079A1 EP 4088079 A1 EP4088079 A1 EP 4088079A1 EP 21700327 A EP21700327 A EP 21700327A EP 4088079 A1 EP4088079 A1 EP 4088079A1
Authority
EP
European Patent Office
Prior art keywords
steering
image
scene
energy
target
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP21700327.6A
Other languages
German (de)
French (fr)
Inventor
Des Wallace
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Thales Holdings UK PLC
Original Assignee
Thales Holdings UK PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Thales Holdings UK PLC filed Critical Thales Holdings UK PLC
Publication of EP4088079A1 publication Critical patent/EP4088079A1/en
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/14—Indirect aiming means
    • F41G3/16—Sighting devices adapted for indirect laying of fire
    • F41G3/165—Sighting devices adapted for indirect laying of fire using a TV-monitor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/24—Beam riding guidance systems
    • F41G7/26—Optical guidance systems
    • F41G7/263—Means for producing guidance beams
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/14—Indirect aiming means
    • F41G3/145—Indirect aiming means using a target illuminator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H13/00—Means of attack or defence not otherwise provided for
    • F41H13/0043—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H13/00—Means of attack or defence not otherwise provided for
    • F41H13/0043—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target
    • F41H13/005—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target the high-energy beam being a laser beam
    • F41H13/0056—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target the high-energy beam being a laser beam for blinding or dazzling, i.e. by overstimulating the opponent's eyes or the enemy's sensor equipment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H13/00—Means of attack or defence not otherwise provided for
    • F41H13/0043—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target
    • F41H13/005—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target the high-energy beam being a laser beam
    • F41H13/0062—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target the high-energy beam being a laser beam causing structural damage to the target
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H13/00—Means of attack or defence not otherwise provided for
    • F41H13/0043—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target
    • F41H13/0068—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target the high-energy beam being of microwave type, e.g. for causing a heating effect in the target
    • G—PHYSICS
    • G02—OPTICS
    • G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
    • G02B26/00—Optical devices or arrangements for the control of light using movable or deformable optical elements
    • G02B26/08—Optical devices or arrangements for the control of light using movable or deformable optical elements for controlling the direction of light
    • G02B26/0816—Optical devices or arrangements for the control of light using movable or deformable optical elements for controlling the direction of light by means of one or more reflecting elements
    • G—PHYSICS
    • G02—OPTICS
    • G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
    • G02B26/00—Optical devices or arrangements for the control of light using movable or deformable optical elements
    • G02B26/08—Optical devices or arrangements for the control of light using movable or deformable optical elements for controlling the direction of light
    • G02B26/10—Scanning systems
    • G02B26/101—Scanning systems with both horizontal and vertical deflecting means, e.g. raster or XY scanners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/226—Semi-active homing systems, i.e. comprising a receiver and involving auxiliary illuminating means, e.g. using auxiliary guiding missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/24—Beam riding guidance systems
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
    • G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
    • G01S7/38—Jamming means, e.g. producing false echoes
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
    • G01S7/48—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S17/00
    • G01S7/495—Counter-measures or counter-counter-measures using electronic or electro-optical means

Definitions

  • the present disclosure relates to a guidance head and method for directing a beam of energy towards a target and, in particular, though not exclusively to a guidance head and method for a weapon system such as a guided missile weapon system, a directed energy weapon system, and a dazzle weapon system, or to a guidance head and method for a target designator.
  • a guidance head and method for directing a beam of energy towards a target and, in particular, though not exclusively to a guidance head and method for a weapon system such as a guided missile weapon system, a directed energy weapon system, and a dazzle weapon system, or to a guidance head and method for a target designator.
  • Laser beam-riding guided missile systems include a missile launcher and a guidance head that is co-located or provided with the missile launcher.
  • the guidance head includes a laser source and a beam-steering arrangement, wherein the laser source emits a laser beam and the beam-steering arrangement directs the laser beam to a target.
  • the missile launcher subsequently launches a missile that is configured to detect the laser beam and fly along a path or trajectory defined by the laser beam to the target.
  • SAL guided-missile systems include a missile launcher and a target designator in the form of a guidance head that is located remotely, or provided separately, from the missile launcher.
  • the guidance head includes a laser source and a beam-steering arrangement, wherein the laser source emits a laser beam and the beam-steering arrangement directs the laser beam to a target that scatters light from the laser beam.
  • the missile launcher subsequently launches a missile towards the target.
  • the missile is configured to detect the light scattered by the target as the missile approaches the target and to follow the path of the scattered light back to the target.
  • the beam-steering arrangement typically includes a set of beam-steering mirrors for steering the laser beam towards the target.
  • An aiming mark is imaged into an operator’s field of view (FOV) in the sights or viewer of the guidance head via a further set of mirrors that are mechanically linked to the mirrors of the beam-steering arrangement.
  • the guidance head is configured so that the aiming mark is aligned with a projected position of the laser beam on an object in the scene as viewed directly through the sights or viewer of the guidance head.
  • a guidance head for use in directing a beam of energy towards a target, the guidance head comprising: one or more beam-steering elements for directing a beam of energy towards a projected position on an object in a scene, each beam-steering element having a corresponding beam-steering configuration which determines a direction of the beam of energy leaving the beam-steering element for a given direction of incidence of the beam of energy on the beam-steering element; one or more beam-steering element sensors, each beam-steering element sensor being configured to generate an electrical signal representative of the beam steering configuration of the corresponding beam-steering element; a display; and a processing resource, wherein the processing resource is configured to: receive image data representative of the scene; and cause the display to display an image of the scene that is based on the received image data and which includes an aiming mark displayed at a position in the image of the scene based at least in part on the one or more electrical signals representative of the beam-steering configuration of
  • the guidance head may comprise one or more user controls, wherein the processing resource is configured to receive one or more electrical signals from the one or more user controls and adjust the beam-steering configuration of each beam steering element, and therefore also the position of the aiming mark in the image of the scene, based at least in part on the one or more electrical signals received from the one or more user controls.
  • the one or more user controls may comprise one or more joysticks.
  • the processing resource may be configured to allow or perform an offset adjustment of the position of the aiming mark in the image of the scene independently of the beam-steering configuration of each beam-steering element.
  • the processing resource may be configured to allow an offset adjustment of the position of the aiming mark in the image of the scene independently of the beam-steering configuration of each beam-steering element based on one or more electrical signals received from the one or more user controls.
  • the processing resource may be configured to allow or perform an offset adjustment of the position of the aiming mark in the image of the scene independently of the beam-steering configuration of each beam-steering element until the position of the aiming mark coincides with the projected position of the beam of energy on an image of an object in the image of the scene.
  • Such a guidance head may allow accurate alignment of the aiming mark with the projected position of the beam of energy on an image of a target in the image of the scene and, therefore, more accurate alignment of the beam of energy with the target in the scene than known guidance heads.
  • such a guidance head may allow more accurate alignment of a beam of energy with the target in the scene than known guidance heads over time and/or in the presence of one or more changes in an environment surrounding the guidance head such as a change in temperature of an environment surrounding the guidance head.
  • Such a guidance head may allow an offset adjustment procedure to be performed as part of a factory calibration procedure before the guidance head is deployed in the field. Additionally or alternatively, when the guidance head is used as part of a beam-riding guided missile system, such an offset adjustment procedure may be performed after the beam-riding guided missile system is deployed in the field, for example as part of an embedded process. Such an offset adjustment procedure may be performed before and/or after the beam-riding guided missile system launches a missile. Such an offset adjustment procedure may be performed during the flight of the missile to the target. Such an offset adjustment procedure may be performed so that, when the aiming mark is coincident with the image of the target in the image of the scene, the direction of the beam of energy is deliberately offset relative to the target.
  • Deliberately offsetting the direction of the beam of energy relative to the target in this way may be useful to control the flight path of the missile.
  • the direction of the beam of energy may be deliberately offset above the target before missile launch and/or early during the flight of the missile and the offset may be reduced to zero as the missile approaches the target. Offsetting the direction of the beam of energy during the flight of the missile in this way may cause the missile to follow a higher flight path to avoid the missile unintentionally colliding with the ground.
  • Deliberately offsetting the direction of the beam of energy relative to the target may also be useful to control the flight path of the missile to compensate for wind.
  • the beam-steering configuration of each beam-steering element may be determined by a position and/or orientation of the beam-steering element.
  • Each beam-steering element sensor may comprise an encoder for measuring the position and/or orientation of the corresponding beam-steering element.
  • the guidance head may comprise one or more beam-steering element drivers, wherein each beam-steering element driver is configured to adjust the beam-steering configuration of a corresponding beam-steering element.
  • Each beam-steering element driver may comprise an actuator, wherein each actuator is configured to move, for example translate and/or rotate, a corresponding beam-steering element.
  • Each actuator may comprise a motor such as a servo motor.
  • Each beam-steering element may comprise a reflective beam-steering element such as a mirror.
  • Each beam-steering element may comprise a refractive beam-steering element.
  • Each beam-steering element may comprise a diffractive beam-steering element.
  • Each beam-steering element may comprise a digital micro-mirror array or a spatial light modulator.
  • the guidance head may comprise one or more temperature sensors for sensing a temperature of an environment surrounding the guidance head, wherein the processing resource is configured to adjust the beam-steering configuration of each beam-steering element so as to maintain the position of the aiming mark relative to the image of a stationary object in the image of the scene in the presence of a change in the temperature of the environment surrounding the guidance head as sensed by the one or more temperature sensors.
  • the guidance head may comprise one or more motion and/or orientation sensors such as one or more accelerometers and/or one or more gyroscopes for measuring motion and/or orientation of the guidance head.
  • the one or more motion and/or orientation sensors may be provided in the form of an inertial measurement unit such as a rate sensor unit.
  • the processing resource may be configured to adjust the beam-steering configuration of each beam-steering element so as to maintain the position of the aiming mark relative to the image of a stationary object in the image of the scene in the presence of a change in the motion and/or orientation of the guidance head as sensed by the one or more motion and/or orientation sensors.
  • the processing resource may be configured to: identify an image of a target in the image of the scene based on the image data representative of the scene; and adjust the beam-steering configuration of each beam-steering element so that the position of the aiming mark in the image of the scene coincides with, and/or tracks, the identified image of the target in the image of the scene.
  • the processing resource may be configured to perform auto target tracking (ATT) based on the image data representative of the scene.
  • ATT auto target tracking
  • providing ATT functionality with such a guidance head may avoid any requirement for the complex opto-mechanical arrangements used in known guidance heads.
  • the processing resource may be configured to cause the display to display additional information which is additional to the image of the scene and the aiming mark.
  • the additional information may include command data and/or control data.
  • the additional information may include at least one of: one or more cueing arrows to allow an operator of the guidance head to find the target identified by an external input from a radar, battery status, target range data, operating modes, and target interrogator response.
  • the beam of energy may comprise a beam of electromagnetic energy.
  • the beam of energy may comprise an optical beam such as a coherent optical beam.
  • the beam of energy may comprise a laser beam.
  • the beam of energy may comprise a microwave beam.
  • the guidance head may comprise an energy source for emitting the beam of energy.
  • Such a guidance head may be more readily adapted for use with different kinds of energy sources for emitting different kinds of beams of energy than known guidance heads.
  • the energy source may comprise a source of electromagnetic energy.
  • the energy source may comprise an optical source such as a coherent optical source.
  • the energy source may comprise a laser.
  • the energy source may comprise a source of microwave energy.
  • the energy source may be configured to emit a beam of energy that is configured to damage and/or destroy a target.
  • the energy source may be configured to dazzle, for example wherein the energy source comprises a dazzle laser.
  • the guidance head may comprise an image sensor for generating the image data representative of the scene.
  • Such a guidance head may be more readily adapted for use with different kinds of image sensors than known guidance heads.
  • the image sensor may comprise a video image sensor such as a camera.
  • the image sensor may be sensitive to visible light.
  • the image sensor may be sensitive to infrared light.
  • the image sensor may comprise a thermal image sensor. Such an image sensor may allow the guidance head to be used in low light conditions and/or at night time, thereby providing 24 hour capability.
  • the guidance head may comprise a housing for housing the one or more beam steering elements.
  • the housing may house each of the one or more beam-steering element sensors.
  • the housing may house each of the one or more beam-steering element drivers.
  • the energy source may be fixed relative to the housing.
  • the guidance head may comprise one or more waveguides for coupling the beam of energy from the energy source to the housing.
  • the energy source may comprise an optical source
  • the beam of energy may comprise an optical beam
  • the guidance head may comprise one or more optical fibres for coupling the optical beam from the optical source to the housing.
  • the guidance head may comprise one or more flexible waveguides for coupling the beam of energy from the energy source to the housing so that the energy source may be movable relative to the housing.
  • the image sensor may be fixed relative to the housing.
  • a weapon system comprising a guidance head as described above.
  • the guidance head may be configured to direct the beam of energy to the target.
  • the weapon system may comprise a guided missile system.
  • the weapon system may comprise a missile launcher for launching a missile.
  • the weapon system may be configured so that the beam of energy guides the missile to the target.
  • the weapon system may be a beam-riding guided missile system.
  • the missile may be configured to ride the beam of energy to the target.
  • the missile may be configured to detect a scattered portion of the beam of energy which is scattered from the target as the missile approaches the target and to follow the path of the scattered portion of the beam of energy back to the target.
  • the weapon system may comprise a semi-active laser (SAL) guided missile system.
  • SAL semi-active laser
  • the SAL guided missile system may comprise a manual SAL guided missile system or a self-designated SAL guided missile system.
  • the energy source may be configured to emit a beam of energy that is configured to damage the target.
  • the weapon system may comprise a directed energy weapon system.
  • the weapon system may comprise a dazzle weapon system.
  • a target designator comprising a guidance head as described above.
  • the target designator may be portable.
  • the target designator may be configured to be carried by an operator.
  • the target designator may be configured to be hand-held.
  • a guidance method for use in directing a beam of energy towards a target comprising: directing a beam of energy towards a position of incidence on an object in a scene using one or more beam-steering elements; generating an electrical signal representative of a beam-steering configuration of each of the one or more beam-steering elements, wherein the beam-steering configuration of each beam-steering element determines a direction of the beam of energy leaving the beam-steering element for a given direction of incidence of the beam of energy on the beam-steering element; receiving image data representative of the scene; and causing a display to display an image of the scene that is based on the received image data and which includes an aiming mark displayed at a position in the image of the scene based at least in part on the one or more electrical signals representative of the beam-steering configuration of the one or more beam-steering elements.
  • the method may comprise adjusting the beam-steering configuration of each beam-steering element, and therefore also the position of the aiming mark in the image of the scene, based at least in part on the one or more electrical signals received from one or more user controls.
  • the method may comprise adjusting an offset of the position of the aiming mark in the image of the scene independently of the beam-steering configuration of each beam-steering element.
  • the method may comprise adjusting an offset of the position of the aiming mark in the image of the scene independently of the beam steering configuration of each beam-steering element based on one or more electrical signals received from one or more user controls.
  • the method may comprise adjusting an offset of the position of the aiming mark in the image of the scene independently of the beam-steering configuration of each beam-steering element until the position of the aiming mark coincides with the projected position of the beam of energy on an image of an object in the image of the scene.
  • Such a method may allow accurate alignment of the aiming mark with the projected position of the beam of energy on an image of a target in the image of the scene and, therefore, more accurate alignment of the beam of energy with the target in the scene than known methods.
  • such a method may allow more accurate alignment of a beam of energy with the target in the scene than known methods over time and/or in the presence of changes in an environment surrounding the guidance head such as a change in a temperature of an environment surrounding the guidance head.
  • the method may comprise performing an offset adjustment procedure as part of a factory calibration procedure before the guidance head is deployed in the field. Additionally or alternatively, when the guidance head is used as part of a beam-riding guided missile system, the method may comprise performing an offset adjustment procedure after the beam-riding guided missile system is deployed in the field, for example as part of an embedded process. Such an offset adjustment procedure may be performed before and/or after the beam-riding guided missile system launches a missile. Such an offset adjustment procedure may be performed during the flight of the missile to the target.
  • the method may comprise performing an offset adjustment procedure so that, when the aiming mark is coincident with the image of the target in the image of the scene, the direction of the beam of energy is deliberately offset relative to the target. Deliberately offsetting the direction of the beam of energy relative to the target in this way may be useful to control the flight path of the missile.
  • the method may comprise deliberately offsetting the direction of the beam of energy above the target before missile launch and/or early in the flight of the missile and reducing the offset to zero as the missile approaches the target. Offsetting the direction of the beam of energy during the flight of the missile in this way may cause the missile to follow a higher flight path to avoid the missile unintentionally colliding with the ground. Deliberately offsetting the direction of the beam of energy relative to the target may also be useful to control the flight path of the missile to compensate for wind.
  • FIG. 1A schematically illustrates a laser beam-riding guided missile weapon system for guiding a missile towards a target
  • FIG. 1B schematically illustrates an image of a scene including an image of the target in a FOV of the weapon system of FIG. 1 A;
  • FIG. 2 schematically illustrates the weapon system of FIG. 1A in greater detail
  • FIG. 3A schematically illustrates a first image of a scene at a first instant in time including an image of a stationary object in a FOV of the weapon system of FIG. 1A during vibration of the weapon system relative to the stationary object in a vertical direction;
  • FIG. 3B schematically illustrates a second image of the same scene as FIG. 3A at a second instant in time including an image of the stationary object in the FOV of the weapon system of FIG. 1A during vibration of the weapon system relative to the stationary object in the vertical direction;
  • FIG. 4A schematically shows a first image of a scene at a first instant in time including an image of a moving object at a first position in the FOV of the weapon system of FIG. 1A illustrating auto target tracking (ATT);
  • ATT auto target tracking
  • FIG. 4B schematically shows a second image of a scene at a second instant in time including an image of the moving object at a second position in the FOV of the weapon system of FIG. 1A illustrating auto target tracking (ATT);
  • ATT auto target tracking
  • FIG. 5 schematically illustrates a semi-active laser (SAL) guided missile weapon system for guiding a missile towards a target;
  • SAL semi-active laser
  • FIG. 6 schematically illustrates a dazzle weapon system
  • FIG. 7 schematically illustrates a directed energy weapon system for damaging and/or destroying a target.
  • a laser beam-riding guided missile weapon system generally designated 2 for guiding a missile (not shown) towards a target 4 in the form of a helicopter in a scene 5.
  • the guided missile weapon system 2 includes a missile launcher 6 for launching a missile (not shown) and a guidance head 8.
  • the guidance head 8 is configured to image light 10 received from the scene 5 including one or more objects such as the target 4, and to display an image in an operator’s FOV 12 which includes an image 11 of the scene 5 containing an image 13 of the target 4.
  • the guidance head 8 is further configured to direct a beam of energy in the form of a laser beam 16 towards a projected position on the target 4.
  • the missile is configured so that, once launched towards the target 4, the missile follows or rides the laser beam 16 to the projected position of the laser beam 16 on the target 4.
  • the guidance head 8 generates a synthetic aiming mark 14 and displays the synthetic aiming mark 14 in the image 11 of the scene 5 in the operator’s FOV 12.
  • the guidance head 8 is further configured to allow an offset adjustment of the position of the aiming mark 14 in the image 11 of the scene 5 until the position of the aiming mark 14 coincides with the projected position of the laser beam 16 on an image of an object in the image 11 of the scene 5 and the projected position of the laser beam 16 coincides with the object in the actual scene 5.
  • the missile launcher 6 subsequently launches a missile, the missile can follow or ride the laser beam 16 to the target 4.
  • the guidance head 8 includes a laser source 20 for emitting the laser beam 16, a beam-steering arrangement generally designated 22, an image sensor in the form of a video camera 24 for imaging visible light 10a and/or for imaging infrared light 10b received from the scene 5, one or more user controls 25, a display or viewer in the form of a monocular digital display 26, a temperature sensor 27 for sensing a temperature of an environment surrounding the guidance head 8, and a processing resource 28.
  • the one or more user controls 25 may, for example, include one or more joysticks.
  • the beam-steering arrangement 22 includes a first beam-steering element in the form of a yaw mirror 30 for controlling the yaw of the laser beam 16 and a second beam-steering element in the form of a pitch mirror 32 for controlling the pitch of the laser beam 16.
  • the beam-steering arrangement 22 further includes a yaw servo motor 34 for controlling a beam-steering configuration of the yaw mirror 30 and a pitch servo motor 36 for controlling a beam-steering configuration of the pitch mirror 32.
  • the yaw servo motor 34 may be configured to control a tilt or orientation of the yaw mirror 30 so as to control a direction of the laser beam 16 leaving the yaw mirror 30 for a given direction of incidence of the laser beam 16 on the yaw mirror 30.
  • the pitch servo motor 36 may be configured to control a tilt or orientation of the pitch mirror 32 so as to control a direction of the laser beam 16 leaving the pitch mirror 32 for a given direction of incidence of the laser beam 16 on the pitch mirror 32.
  • the beam-steering arrangement 22 also includes a first beam-steering element sensor in the form of a yaw mirror encoder 38 for generating an electrical signal representative of the tilt or orientation of the yaw mirror 30.
  • the beam-steering arrangement 22 also includes a second beam-steering element sensor in the form of a pitch mirror encoder 40 for generating an electrical signal representative of the tilt or orientation of the pitch mirror 32.
  • the encoders 38, 40 may, for example, be high-resolution encoders having a resolution of up to 27 bits (0.047 pR).
  • the beam-steering arrangement 22 further includes a Rate Sensor Unit (RSU) 42 which includes one or more motion and/or orientation sensors for measuring acceleration and/or orientation of the guidance head 8.
  • RSU Rate Sensor Unit
  • the RSU 42 may include one or more accelerometers and/or one or more gyroscopes for measuring acceleration and/or orientation of the guidance head 8.
  • the beam-steering arrangement 22 further includes a housing 44 for housing the mirrors 30, 32, the servo motors 34, 36, the encoders 38, 40 and the RSU 42.
  • the housing 44 is fixed relative to the laser source 20 and the video camera 24.
  • the processing resource 28 is configured for communication with the laser source 20, the servo motors 34, 36, the encoders 38, 40, the video camera 24, the one or more user controls 25, the monocular digital display 26, the temperature sensor 27, the RSU 42 and the missile launcher 6.
  • each encoder 38, 40 generates an electrical signal representative of the tilt or orientation of the mirrors 30, 32 respectively.
  • the video camera 24 images the light 10a, 10b received from the scene 5, captures an image of the scene 5, and generates image data representative of the scene 5.
  • the processing resource 28 receives the image data representative of the scene 5 from the video camera 24.
  • the processing resource 28 causes the monocular digital display 26 to display the image 11 of the scene 5 based on the image data received from the video camera 24.
  • the processing resource 28 also causes the monocular digital display 26 to display the aiming mark 14 at a position in the image 11 of the scene 5 based at least in part on the encoder electrical signals which are representative of the tilt or orientation of the mirrors 30, 32.
  • the processing resource 28 receives one or more electrical signals from the one or more user controls 25 and adjusts the tilt or orientation of the mirrors 30, 32, and therefore also the position of the aiming mark 14 relative to the image 11 of the scene 5, based at least in part on the one or more electrical signals received from the one or more user controls 25.
  • the guidance head 8 is temperature stabilised in the sense that the guidance head 8 adjusts the tilt or orientation of the mirrors 30, 32 so as to stabilise the direction of the laser beam 16 against changes in a temperature of the environment surrounding the guidance head 8.
  • the processing resource 28 receives an electrical signal from the temperature sensor 27, which electrical signal is representative of the temperature of the environment surrounding the guidance head 8.
  • the processing resource 28 adjusts the tilt or orientation of the mirrors 30, 32 so as to maintain the position of the aiming mark 14 relative to the image of a stationary object in the image 11 of the scene 5 in the presence of a change in the temperature of the environment surrounding the guidance head 8 as sensed by the temperature sensor 27 to thereby stabilise the direction of the laser beam 16 against changes in the temperature of the environment surrounding the guidance head 8.
  • the guidance head 8 is stabilised against changes in motion and/or orientation of the guidance head 8 in the sense that the guidance head 8 adjusts the tilt or orientation of the mirrors 30, 32 so as to stabilise the direction of the laser beam 16 relative to the scene against changes in motion and/or orientation of the guidance head 8.
  • Such changes in motion and/or orientation of the guidance head 8 may, for example, be caused by vibration, wind buffeting, missile launch shock or the like.
  • the missile system 2 may be subject to vertical vibration resulting in the FOV 12 of the monocular digital display 26 moving vertically up and down relative to an image 50 of a stationary object.
  • the processing resource 28 receives one or more electrical signals from the RSU 42, which one or more electrical signals are representative of the motion and/or orientation of the guidance head 8.
  • the processing resource 28 adjusts the tilt or orientation of the mirrors 30, 32 in response to the one or more electrical signals representative of the change in motion and/or orientation of the guidance head 8 so as to maintain the position of the aiming mark 14 relative to the image 50 of the stationary object in the image 11 of the scene 5 to thereby stabilise the direction of the laser beam 16 relative to the scene 5 against changes in motion and/or orientation of the guidance head 8.
  • the processing resource 28 is configured to allow an offset adjustment of the position of the aiming mark 14 relative to the image 11 of the scene 5 independently of the tilt or orientation of the mirrors 30, 32. Specifically, the processing resource 28 is configured to allow an offset adjustment of the position of the aiming mark 14 in the image 11 of the scene 5 independently of the tilt or orientation of the mirrors 30, 32 until the position of the aiming mark 14 coincides with the projected position of the laser beam 16 on an image of an object in the image 11 of the scene 5, and the projected position of the laser beam 16 coincides with the object in the actual scene 5.
  • Such an offset adjustment procedure may, for example, be performed as part of a factory calibration procedure before the laser beam-riding guided missile system 2 is deployed in the field.
  • such an offset adjustment procedure may be performed after the laser beam-riding guided missile system 2 is deployed in the field, for example as part of an embedded process. Such an offset adjustment procedure may be performed before and/or after the laser beam-riding guided missile system 2 launches a missile. Such an offset adjustment procedure may be performed during the flight of the missile to the target 4. Such an offset adjustment procedure may be performed so that, when the aiming ring 14 is coincident with the image 13 of the target 4 in the image 11 of the scene 5, the direction of the laser beam 16 is deliberately offset relative to the target 4. Deliberately offsetting the direction of the laser beam 16 relative to the target 4 in this way may be useful to control the flight path of the missile.
  • the direction of the laser beam 16 may be deliberately offset above the target 4 before missile launch and/or early in the flight of the missile and the offset may be reduced to zero as the missile approaches the target 4. Offsetting the direction of the laser beam 16 during the flight of the missile in this way may cause the missile to follow a higher flight path to avoid the missile unintentionally colliding with the ground. Deliberately offsetting the direction of the laser beam 16 relative to the target 4 may also be useful to control the flight path of the missile to compensate for wind.
  • the guidance head 8 is ready for use with the missile launcher 6.
  • an operator 60 of the guided missile weapon system 2 manoeuvers and/or orients the guided missile weapon system 2 whilst viewing the image 11 of the scene 5 and the aiming mark 14 in the FOV 12 of the monocular digital display 26 until the target 4 is visible in the FOV 12 of the monocular digital display 26.
  • the operator 60 then uses the one or more user controls 25 to align the aiming mark 14 with the image 13 of the target 4 in the FOV 12 of the monocular digital display 26.
  • the operator 60 uses the one or more user controls 25 to activate the laser source 20 causing the laser source 20 to emit the laser beam 16 towards the target 4 and to cause the missile launcher 6 to launch a missile towards the target 4.
  • the missile follows or ride the laser beam 16 to the projected position of the laser beam 16 on the target 4.
  • the guidance head 8 continues to adjust the tilt or orientation of the mirrors 30, 32 and therefore also the direction of the laser beam 16 so as to stabilise the direction of the laser beam 16 against changes in environmental temperature, and against changes in motion and/or orientation of the guidance head 8 during the flight of the missile.
  • the guidance head 8 may also be configured to perform auto target tracking (ATT).
  • the processing resource 28 may process the image 11 of the scene 5, identify the image 13 of the target 4 in the image 11 of the scene 5, and adjust the tilt or orientation of the mirrors 30, 32 so that the position of the aiming mark 14 in the image 11 of the scene 5 coincides with, and/or tracks, the identified image 13 of the target 4 in the image 11 of the scene 5. It should be understood that the guidance head 8 continues to track the target 4 and adjust the tilt or orientation of the mirrors 30, 32 and therefore also the direction of the laser beam 16 during the flight of the missile.
  • ATT auto target tracking
  • the processing resource 28 is configured to cause the monocular digital display 26 to display additional information in the FOV 12, which additional information is additional to the image 11 of the scene 5 and the aiming mark 14.
  • the processing resource 28 may be configured to cause the monocular digital display 26 to display command data and/or control data.
  • the processing resource 28 may be configured to cause the monocular digital display 26 to display one or more cueing arrows to allow the operator 60 of the guidance head 8 to find the target 4 as identified by an external input to the processing resource 28, for example as identified by an external input to the processing resource 28 from a radar.
  • the processing resource 28 may be configured to cause the monocular digital display 26 to display at least one of battery status, target range data, operating modes, and target interrogator response.
  • a SAL guided missile weapon system which is generally designated 102 and which includes a missile launcher 106 and a separate, remotely located, laser target designator 108.
  • the missile launcher 106 is configured to launch a missile (not shown) towards a target 4.
  • the laser target designator 108 is essentially identical to the guidance head 8 described with reference to FIG. 1A to FIG. 4B and operates in essentially the same way as the guidance head 8 described with reference to FIG. 1A to FIG. 4B.
  • the laser target designator 108 images light 110 received from a scene 5 including a target 4 and directs a laser beam 116 to the target 4 based on an image of the scene 5.
  • the target 4 scatters the laser beam 116 so as to form a cone of scattered light 116a.
  • the missile launcher 106 subsequently launches a missile towards the target 4.
  • the missile is configured to detect the scattered light 116a as the missile approaches the target 4 and to follow the path of the scattered light 116a back to the target 4.
  • the dazzle weapon system 202 is essentially identical to the guidance head 8 described with reference to FIG. 1A to FIG. 4B and operates in essentially the same way as the guidance head 8 described with reference to FIG. 1A to FIG. 4B except that the laser source 20 of the guidance head 8 is replaced with a laser source (not shown) which is specifically selected so as to generate a laser beam 216 which is capable of dazzling a person located in, or with, a target 4 in a scene 5.
  • the dazzle weapon system 202 images light 210 received from the scene 5 including the target 4 and directs the dazzle laser beam 216 to the target 4 based on an image of the scene 5 so as to dazzle a person located in, or with, the target 4.
  • the directed energy weapon system 302 is essentially identical to the guidance head 8 described with reference to FIG. 1A to FIG. 4B and operates in essentially the same way as the guidance head 8 described with reference to FIG. 1A to FIG. 4B except that the laser source 20 of the guidance head 8 is replaced with an energy source (not shown) which is specifically selected so as to generate a beam of energy 316 which is capable of causing damage to, or destroying, a target 4 in a scene 5.
  • the directed energy weapon system 302 images light 310 received from the scene 5 including the target 4 and directs the beam of energy 316 to the target 4 based on an image of the scene 5 so as to cause damage to, or destroy, the target 4.
  • the guidance heads and target designators described above use a laser beam
  • the guidance heads or target designators may use a beam of electromagnetic energy of any kind.
  • the beam of electromagnetic energy may comprise an optical beam of any kind such as a coherent optical beam of any kind.
  • the beam of electromagnetic energy may comprise a microwave beam.
  • the guidance heads and target designators described above include an energy source such as a laser source which is fixed relative to the housing of the beam-steering arrangement, the energy source may be coupled to the housing of any of the guidance heads and target designators using one or more waveguides.
  • the energy source may comprise an optical source
  • the beam of energy may comprise an optical beam
  • the guidance head or target designator may comprise one or more optical fibres for coupling the optical beam from the optical source to the housing.
  • the energy source may be coupled to the housing of any of the guidance heads and target designators using one or more flexible waveguides so that the energy source may be movable relative to the housing of the beam-steering arrangement.
  • Each beam-steering element may comprise a reflective beam-steering element of any kind.
  • Each beam-steering element may comprise a refractive beam-steering element.
  • Each beam-steering element may comprise a diffractive beam-steering element.
  • Each beam-steering element may comprise a digital micro-mirror array or a spatial light modulator.
  • the guidance head may comprise one or more beam-steering element drivers, wherein each beam-steering element driver is configured to adjust the beam-steering configuration of a corresponding beam-steering element.
  • Each beam-steering element driver may comprise an actuator, wherein each actuator is configured to move, for example translate and/or rotate, a corresponding beam-steering element.
  • Each actuator may comprise a motor of any kind.
  • weapon systems, guidance heads, target designators, and methods described above are described in the context of a target in the form of a helicopter, the weapon systems, guidance heads, target designators, and methods may be used on any kind of air-based target or on any kind of land- or sea-based target.

Abstract

A guidance head (8) for use in directing a beam (16) of energy towards a target comprises one or more beam-steering elements (30,32) for directing a beam of energy towards a projected position on an object in a scene, one or more beam-steering element sensors (38,40), a display (26), and a processing resource (24), wherein each beam-steering element has a corresponding beam-steering configuration, each beam-steering element sensor is configured to generate an electrical signal representative of the beam-steering configuration of the corresponding beam-steering element, and the processing resource is configured to receive image data representative of the scene and cause the display to display an image of the scene that is based on the received image data and which includes an aiming mark displayed at a position in the image of the scene based at least in part on the one or more electrical signals representative of the beam-steering configuration of the one or more beam-steering elements. The guidance head may be suitable for a weapon system such as a guided missile weapon system, a directed energy weapon system, a dazzle weapon system, or may be suitable for a target designator.

Description

GUIDANCE HEAD AND METHOD
FIELD
The present disclosure relates to a guidance head and method for directing a beam of energy towards a target and, in particular, though not exclusively to a guidance head and method for a weapon system such as a guided missile weapon system, a directed energy weapon system, and a dazzle weapon system, or to a guidance head and method for a target designator.
BACKGROUND
Laser beam-riding guided missile systems are known that include a missile launcher and a guidance head that is co-located or provided with the missile launcher. The guidance head includes a laser source and a beam-steering arrangement, wherein the laser source emits a laser beam and the beam-steering arrangement directs the laser beam to a target. The missile launcher subsequently launches a missile that is configured to detect the laser beam and fly along a path or trajectory defined by the laser beam to the target.
Semi-active laser (SAL) guided-missile systems are also known that include a missile launcher and a target designator in the form of a guidance head that is located remotely, or provided separately, from the missile launcher. The guidance head includes a laser source and a beam-steering arrangement, wherein the laser source emits a laser beam and the beam-steering arrangement directs the laser beam to a target that scatters light from the laser beam. The missile launcher subsequently launches a missile towards the target. The missile is configured to detect the light scattered by the target as the missile approaches the target and to follow the path of the scattered light back to the target.
In such known guidance heads, the beam-steering arrangement typically includes a set of beam-steering mirrors for steering the laser beam towards the target. An aiming mark is imaged into an operator’s field of view (FOV) in the sights or viewer of the guidance head via a further set of mirrors that are mechanically linked to the mirrors of the beam-steering arrangement. The guidance head is configured so that the aiming mark is aligned with a projected position of the laser beam on an object in the scene as viewed directly through the sights or viewer of the guidance head. However, it may be difficult to accurately align the aiming mark in the sights or viewer with the projected position of the laser beam on the object in the scene when viewed directly through the sights or viewer. Moreover, it may be difficult to maintain alignment between the aiming mark in the sights or viewer with the projected position of the laser beam on the object in the scene viewed through the sights or viewer over time and/or in the presence of changes in temperature. It may also be difficult to adapt such known guidance heads for thermal imaging. Providing auto target tracking (ATT) functionality with such known guidance heads may also require complex opto-mechanical arrangements.
SUMMARY
According to an aspect of the present disclosure there is provided a guidance head for use in directing a beam of energy towards a target, the guidance head comprising: one or more beam-steering elements for directing a beam of energy towards a projected position on an object in a scene, each beam-steering element having a corresponding beam-steering configuration which determines a direction of the beam of energy leaving the beam-steering element for a given direction of incidence of the beam of energy on the beam-steering element; one or more beam-steering element sensors, each beam-steering element sensor being configured to generate an electrical signal representative of the beam steering configuration of the corresponding beam-steering element; a display; and a processing resource, wherein the processing resource is configured to: receive image data representative of the scene; and cause the display to display an image of the scene that is based on the received image data and which includes an aiming mark displayed at a position in the image of the scene based at least in part on the one or more electrical signals representative of the beam-steering configuration of the one or more beam-steering elements.
The guidance head may comprise one or more user controls, wherein the processing resource is configured to receive one or more electrical signals from the one or more user controls and adjust the beam-steering configuration of each beam steering element, and therefore also the position of the aiming mark in the image of the scene, based at least in part on the one or more electrical signals received from the one or more user controls. The one or more user controls may comprise one or more joysticks.
The processing resource may be configured to allow or perform an offset adjustment of the position of the aiming mark in the image of the scene independently of the beam-steering configuration of each beam-steering element. For example, the processing resource may be configured to allow an offset adjustment of the position of the aiming mark in the image of the scene independently of the beam-steering configuration of each beam-steering element based on one or more electrical signals received from the one or more user controls.
The processing resource may be configured to allow or perform an offset adjustment of the position of the aiming mark in the image of the scene independently of the beam-steering configuration of each beam-steering element until the position of the aiming mark coincides with the projected position of the beam of energy on an image of an object in the image of the scene.
Such a guidance head may allow accurate alignment of the aiming mark with the projected position of the beam of energy on an image of a target in the image of the scene and, therefore, more accurate alignment of the beam of energy with the target in the scene than known guidance heads. In particular, such a guidance head may allow more accurate alignment of a beam of energy with the target in the scene than known guidance heads over time and/or in the presence of one or more changes in an environment surrounding the guidance head such as a change in temperature of an environment surrounding the guidance head.
Such a guidance head may allow an offset adjustment procedure to be performed as part of a factory calibration procedure before the guidance head is deployed in the field. Additionally or alternatively, when the guidance head is used as part of a beam-riding guided missile system, such an offset adjustment procedure may be performed after the beam-riding guided missile system is deployed in the field, for example as part of an embedded process. Such an offset adjustment procedure may be performed before and/or after the beam-riding guided missile system launches a missile. Such an offset adjustment procedure may be performed during the flight of the missile to the target. Such an offset adjustment procedure may be performed so that, when the aiming mark is coincident with the image of the target in the image of the scene, the direction of the beam of energy is deliberately offset relative to the target. Deliberately offsetting the direction of the beam of energy relative to the target in this way may be useful to control the flight path of the missile. For example, when the target is low relative to the horizon, the direction of the beam of energy may be deliberately offset above the target before missile launch and/or early during the flight of the missile and the offset may be reduced to zero as the missile approaches the target. Offsetting the direction of the beam of energy during the flight of the missile in this way may cause the missile to follow a higher flight path to avoid the missile unintentionally colliding with the ground. Deliberately offsetting the direction of the beam of energy relative to the target may also be useful to control the flight path of the missile to compensate for wind.
The beam-steering configuration of each beam-steering element may be determined by a position and/or orientation of the beam-steering element.
Each beam-steering element sensor may comprise an encoder for measuring the position and/or orientation of the corresponding beam-steering element.
The guidance head may comprise one or more beam-steering element drivers, wherein each beam-steering element driver is configured to adjust the beam-steering configuration of a corresponding beam-steering element.
Each beam-steering element driver may comprise an actuator, wherein each actuator is configured to move, for example translate and/or rotate, a corresponding beam-steering element.
Each actuator may comprise a motor such as a servo motor.
Each beam-steering element may comprise a reflective beam-steering element such as a mirror.
Each beam-steering element may comprise a refractive beam-steering element.
Each beam-steering element may comprise a diffractive beam-steering element. Each beam-steering element may comprise a digital micro-mirror array or a spatial light modulator.
The guidance head may comprise one or more temperature sensors for sensing a temperature of an environment surrounding the guidance head, wherein the processing resource is configured to adjust the beam-steering configuration of each beam-steering element so as to maintain the position of the aiming mark relative to the image of a stationary object in the image of the scene in the presence of a change in the temperature of the environment surrounding the guidance head as sensed by the one or more temperature sensors.
The guidance head may comprise one or more motion and/or orientation sensors such as one or more accelerometers and/or one or more gyroscopes for measuring motion and/or orientation of the guidance head. The one or more motion and/or orientation sensors may be provided in the form of an inertial measurement unit such as a rate sensor unit.
The processing resource may be configured to adjust the beam-steering configuration of each beam-steering element so as to maintain the position of the aiming mark relative to the image of a stationary object in the image of the scene in the presence of a change in the motion and/or orientation of the guidance head as sensed by the one or more motion and/or orientation sensors.
The processing resource may be configured to: identify an image of a target in the image of the scene based on the image data representative of the scene; and adjust the beam-steering configuration of each beam-steering element so that the position of the aiming mark in the image of the scene coincides with, and/or tracks, the identified image of the target in the image of the scene.
The processing resource may be configured to perform auto target tracking (ATT) based on the image data representative of the scene.
Consequently, providing ATT functionality with such a guidance head may avoid any requirement for the complex opto-mechanical arrangements used in known guidance heads.
The processing resource may be configured to cause the display to display additional information which is additional to the image of the scene and the aiming mark.
The additional information may include command data and/or control data.
The additional information may include at least one of: one or more cueing arrows to allow an operator of the guidance head to find the target identified by an external input from a radar, battery status, target range data, operating modes, and target interrogator response.
The beam of energy may comprise a beam of electromagnetic energy.
The beam of energy may comprise an optical beam such as a coherent optical beam.
The beam of energy may comprise a laser beam.
The beam of energy may comprise a microwave beam.
The guidance head may comprise an energy source for emitting the beam of energy. Such a guidance head may be more readily adapted for use with different kinds of energy sources for emitting different kinds of beams of energy than known guidance heads.
The energy source may comprise a source of electromagnetic energy.
The energy source may comprise an optical source such as a coherent optical source.
The energy source may comprise a laser.
The energy source may comprise a source of microwave energy.
The energy source may be configured to emit a beam of energy that is configured to damage and/or destroy a target.
The energy source may be configured to dazzle, for example wherein the energy source comprises a dazzle laser.
The guidance head may comprise an image sensor for generating the image data representative of the scene.
Such a guidance head may be more readily adapted for use with different kinds of image sensors than known guidance heads.
The image sensor may comprise a video image sensor such as a camera.
The image sensor may be sensitive to visible light.
The image sensor may be sensitive to infrared light.
The image sensor may comprise a thermal image sensor. Such an image sensor may allow the guidance head to be used in low light conditions and/or at night time, thereby providing 24 hour capability.
The guidance head may comprise a housing for housing the one or more beam steering elements. The housing may house each of the one or more beam-steering element sensors. The housing may house each of the one or more beam-steering element drivers.
The energy source may be fixed relative to the housing.
The guidance head may comprise one or more waveguides for coupling the beam of energy from the energy source to the housing.
The energy source may comprise an optical source, the beam of energy may comprise an optical beam, and the guidance head may comprise one or more optical fibres for coupling the optical beam from the optical source to the housing.
The guidance head may comprise one or more flexible waveguides for coupling the beam of energy from the energy source to the housing so that the energy source may be movable relative to the housing. The image sensor may be fixed relative to the housing.
According to an aspect of the present disclosure there is provided a weapon system comprising a guidance head as described above.
The guidance head may be configured to direct the beam of energy to the target.
The weapon system may comprise a guided missile system.
The weapon system may comprise a missile launcher for launching a missile.
The weapon system may be configured so that the beam of energy guides the missile to the target.
The weapon system may be a beam-riding guided missile system.
The missile may be configured to ride the beam of energy to the target.
The missile may be configured to detect a scattered portion of the beam of energy which is scattered from the target as the missile approaches the target and to follow the path of the scattered portion of the beam of energy back to the target.
The weapon system may comprise a semi-active laser (SAL) guided missile system.
The SAL guided missile system may comprise a manual SAL guided missile system or a self-designated SAL guided missile system.
The energy source may be configured to emit a beam of energy that is configured to damage the target.
The weapon system may comprise a directed energy weapon system.
The weapon system may comprise a dazzle weapon system.
According to an aspect of the present disclosure there is provided a target designator comprising a guidance head as described above.
The target designator may be portable. For example, the target designator may be configured to be carried by an operator. The target designator may be configured to be hand-held.
According to an aspect of the present disclosure there is provided a guidance method for use in directing a beam of energy towards a target, the guidance method comprising: directing a beam of energy towards a position of incidence on an object in a scene using one or more beam-steering elements; generating an electrical signal representative of a beam-steering configuration of each of the one or more beam-steering elements, wherein the beam-steering configuration of each beam-steering element determines a direction of the beam of energy leaving the beam-steering element for a given direction of incidence of the beam of energy on the beam-steering element; receiving image data representative of the scene; and causing a display to display an image of the scene that is based on the received image data and which includes an aiming mark displayed at a position in the image of the scene based at least in part on the one or more electrical signals representative of the beam-steering configuration of the one or more beam-steering elements.
The method may comprise adjusting the beam-steering configuration of each beam-steering element, and therefore also the position of the aiming mark in the image of the scene, based at least in part on the one or more electrical signals received from one or more user controls.
The method may comprise adjusting an offset of the position of the aiming mark in the image of the scene independently of the beam-steering configuration of each beam-steering element. For example, the method may comprise adjusting an offset of the position of the aiming mark in the image of the scene independently of the beam steering configuration of each beam-steering element based on one or more electrical signals received from one or more user controls.
The method may comprise adjusting an offset of the position of the aiming mark in the image of the scene independently of the beam-steering configuration of each beam-steering element until the position of the aiming mark coincides with the projected position of the beam of energy on an image of an object in the image of the scene.
Such a method may allow accurate alignment of the aiming mark with the projected position of the beam of energy on an image of a target in the image of the scene and, therefore, more accurate alignment of the beam of energy with the target in the scene than known methods. In particular, such a method may allow more accurate alignment of a beam of energy with the target in the scene than known methods over time and/or in the presence of changes in an environment surrounding the guidance head such as a change in a temperature of an environment surrounding the guidance head.
The method may comprise performing an offset adjustment procedure as part of a factory calibration procedure before the guidance head is deployed in the field. Additionally or alternatively, when the guidance head is used as part of a beam-riding guided missile system, the method may comprise performing an offset adjustment procedure after the beam-riding guided missile system is deployed in the field, for example as part of an embedded process. Such an offset adjustment procedure may be performed before and/or after the beam-riding guided missile system launches a missile. Such an offset adjustment procedure may be performed during the flight of the missile to the target.
The method may comprise performing an offset adjustment procedure so that, when the aiming mark is coincident with the image of the target in the image of the scene, the direction of the beam of energy is deliberately offset relative to the target. Deliberately offsetting the direction of the beam of energy relative to the target in this way may be useful to control the flight path of the missile. For example, when the target is low relative to the horizon, the method may comprise deliberately offsetting the direction of the beam of energy above the target before missile launch and/or early in the flight of the missile and reducing the offset to zero as the missile approaches the target. Offsetting the direction of the beam of energy during the flight of the missile in this way may cause the missile to follow a higher flight path to avoid the missile unintentionally colliding with the ground. Deliberately offsetting the direction of the beam of energy relative to the target may also be useful to control the flight path of the missile to compensate for wind.
It should be understood that any one or more of the features of any one of the foregoing aspects of the present disclosure may be combined with any one or more of the features of any of the other foregoing aspects of the present disclosure.
BRIEF DESCRIPTION OF THE DRAWINGS
A guidance head and method for directing a beam of energy towards a target will now be described by way of non-limiting example only with reference to the accompanying drawings of which:
FIG. 1A schematically illustrates a laser beam-riding guided missile weapon system for guiding a missile towards a target;
FIG. 1B schematically illustrates an image of a scene including an image of the target in a FOV of the weapon system of FIG. 1 A;
FIG. 2 schematically illustrates the weapon system of FIG. 1A in greater detail; FIG. 3A schematically illustrates a first image of a scene at a first instant in time including an image of a stationary object in a FOV of the weapon system of FIG. 1A during vibration of the weapon system relative to the stationary object in a vertical direction;
FIG. 3B schematically illustrates a second image of the same scene as FIG. 3A at a second instant in time including an image of the stationary object in the FOV of the weapon system of FIG. 1A during vibration of the weapon system relative to the stationary object in the vertical direction;
FIG. 4A schematically shows a first image of a scene at a first instant in time including an image of a moving object at a first position in the FOV of the weapon system of FIG. 1A illustrating auto target tracking (ATT);
FIG. 4B schematically shows a second image of a scene at a second instant in time including an image of the moving object at a second position in the FOV of the weapon system of FIG. 1A illustrating auto target tracking (ATT);
FIG. 5 schematically illustrates a semi-active laser (SAL) guided missile weapon system for guiding a missile towards a target;
FIG. 6 schematically illustrates a dazzle weapon system; and
FIG. 7 schematically illustrates a directed energy weapon system for damaging and/or destroying a target.
DETAILED DESCRIPTION OF THE DRAWINGS
Referring to FIGS. 1A and 1B, there is shown a laser beam-riding guided missile weapon system generally designated 2 for guiding a missile (not shown) towards a target 4 in the form of a helicopter in a scene 5. The guided missile weapon system 2 includes a missile launcher 6 for launching a missile (not shown) and a guidance head 8. The guidance head 8 is configured to image light 10 received from the scene 5 including one or more objects such as the target 4, and to display an image in an operator’s FOV 12 which includes an image 11 of the scene 5 containing an image 13 of the target 4. The guidance head 8 is further configured to direct a beam of energy in the form of a laser beam 16 towards a projected position on the target 4. The missile is configured so that, once launched towards the target 4, the missile follows or rides the laser beam 16 to the projected position of the laser beam 16 on the target 4. As will be described in more detail below, the guidance head 8 generates a synthetic aiming mark 14 and displays the synthetic aiming mark 14 in the image 11 of the scene 5 in the operator’s FOV 12. The guidance head 8 is further configured to allow an offset adjustment of the position of the aiming mark 14 in the image 11 of the scene 5 until the position of the aiming mark 14 coincides with the projected position of the laser beam 16 on an image of an object in the image 11 of the scene 5 and the projected position of the laser beam 16 coincides with the object in the actual scene 5. Consequently, when the aiming mark 14 is aligned with the image 13 of the target 4 in the image 11 of the scene 5, the projected position of the laser beam 16 is known to coincide with the target 4 in the actual scene 5. Consequently, if the missile launcher 6 subsequently launches a missile, the missile can follow or ride the laser beam 16 to the target 4.
Referring now to FIG. 2, the guidance head 8 includes a laser source 20 for emitting the laser beam 16, a beam-steering arrangement generally designated 22, an image sensor in the form of a video camera 24 for imaging visible light 10a and/or for imaging infrared light 10b received from the scene 5, one or more user controls 25, a display or viewer in the form of a monocular digital display 26, a temperature sensor 27 for sensing a temperature of an environment surrounding the guidance head 8, and a processing resource 28. The one or more user controls 25 may, for example, include one or more joysticks.
The beam-steering arrangement 22 includes a first beam-steering element in the form of a yaw mirror 30 for controlling the yaw of the laser beam 16 and a second beam-steering element in the form of a pitch mirror 32 for controlling the pitch of the laser beam 16. The beam-steering arrangement 22 further includes a yaw servo motor 34 for controlling a beam-steering configuration of the yaw mirror 30 and a pitch servo motor 36 for controlling a beam-steering configuration of the pitch mirror 32. Specifically, the yaw servo motor 34 may be configured to control a tilt or orientation of the yaw mirror 30 so as to control a direction of the laser beam 16 leaving the yaw mirror 30 for a given direction of incidence of the laser beam 16 on the yaw mirror 30. Similarly, the pitch servo motor 36 may be configured to control a tilt or orientation of the pitch mirror 32 so as to control a direction of the laser beam 16 leaving the pitch mirror 32 for a given direction of incidence of the laser beam 16 on the pitch mirror 32. The beam-steering arrangement 22 also includes a first beam-steering element sensor in the form of a yaw mirror encoder 38 for generating an electrical signal representative of the tilt or orientation of the yaw mirror 30. The beam-steering arrangement 22 also includes a second beam-steering element sensor in the form of a pitch mirror encoder 40 for generating an electrical signal representative of the tilt or orientation of the pitch mirror 32. The encoders 38, 40 may, for example, be high-resolution encoders having a resolution of up to 27 bits (0.047 pR).
The beam-steering arrangement 22 further includes a Rate Sensor Unit (RSU) 42 which includes one or more motion and/or orientation sensors for measuring acceleration and/or orientation of the guidance head 8. For example, the RSU 42 may include one or more accelerometers and/or one or more gyroscopes for measuring acceleration and/or orientation of the guidance head 8. The beam-steering arrangement 22 further includes a housing 44 for housing the mirrors 30, 32, the servo motors 34, 36, the encoders 38, 40 and the RSU 42. The housing 44 is fixed relative to the laser source 20 and the video camera 24.
As shown by the dashed lines in FIG. 2, the processing resource 28 is configured for communication with the laser source 20, the servo motors 34, 36, the encoders 38, 40, the video camera 24, the one or more user controls 25, the monocular digital display 26, the temperature sensor 27, the RSU 42 and the missile launcher 6.
In use, each encoder 38, 40 generates an electrical signal representative of the tilt or orientation of the mirrors 30, 32 respectively. The video camera 24 images the light 10a, 10b received from the scene 5, captures an image of the scene 5, and generates image data representative of the scene 5. The processing resource 28 receives the image data representative of the scene 5 from the video camera 24. The processing resource 28 causes the monocular digital display 26 to display the image 11 of the scene 5 based on the image data received from the video camera 24. The processing resource 28 also causes the monocular digital display 26 to display the aiming mark 14 at a position in the image 11 of the scene 5 based at least in part on the encoder electrical signals which are representative of the tilt or orientation of the mirrors 30, 32.
The processing resource 28 receives one or more electrical signals from the one or more user controls 25 and adjusts the tilt or orientation of the mirrors 30, 32, and therefore also the position of the aiming mark 14 relative to the image 11 of the scene 5, based at least in part on the one or more electrical signals received from the one or more user controls 25.
The guidance head 8 is temperature stabilised in the sense that the guidance head 8 adjusts the tilt or orientation of the mirrors 30, 32 so as to stabilise the direction of the laser beam 16 against changes in a temperature of the environment surrounding the guidance head 8. Specifically, the processing resource 28 receives an electrical signal from the temperature sensor 27, which electrical signal is representative of the temperature of the environment surrounding the guidance head 8. The processing resource 28 adjusts the tilt or orientation of the mirrors 30, 32 so as to maintain the position of the aiming mark 14 relative to the image of a stationary object in the image 11 of the scene 5 in the presence of a change in the temperature of the environment surrounding the guidance head 8 as sensed by the temperature sensor 27 to thereby stabilise the direction of the laser beam 16 against changes in the temperature of the environment surrounding the guidance head 8.
Similarly, the guidance head 8 is stabilised against changes in motion and/or orientation of the guidance head 8 in the sense that the guidance head 8 adjusts the tilt or orientation of the mirrors 30, 32 so as to stabilise the direction of the laser beam 16 relative to the scene against changes in motion and/or orientation of the guidance head 8. Such changes in motion and/or orientation of the guidance head 8 may, for example, be caused by vibration, wind buffeting, missile launch shock or the like. For example, with reference to FIGS 3A and 3B, the missile system 2 may be subject to vertical vibration resulting in the FOV 12 of the monocular digital display 26 moving vertically up and down relative to an image 50 of a stationary object. The processing resource 28 receives one or more electrical signals from the RSU 42, which one or more electrical signals are representative of the motion and/or orientation of the guidance head 8. The processing resource 28 adjusts the tilt or orientation of the mirrors 30, 32 in response to the one or more electrical signals representative of the change in motion and/or orientation of the guidance head 8 so as to maintain the position of the aiming mark 14 relative to the image 50 of the stationary object in the image 11 of the scene 5 to thereby stabilise the direction of the laser beam 16 relative to the scene 5 against changes in motion and/or orientation of the guidance head 8.
It should be understood that the processing resource 28 is configured to allow an offset adjustment of the position of the aiming mark 14 relative to the image 11 of the scene 5 independently of the tilt or orientation of the mirrors 30, 32. Specifically, the processing resource 28 is configured to allow an offset adjustment of the position of the aiming mark 14 in the image 11 of the scene 5 independently of the tilt or orientation of the mirrors 30, 32 until the position of the aiming mark 14 coincides with the projected position of the laser beam 16 on an image of an object in the image 11 of the scene 5, and the projected position of the laser beam 16 coincides with the object in the actual scene 5. Such an offset adjustment procedure may, for example, be performed as part of a factory calibration procedure before the laser beam-riding guided missile system 2 is deployed in the field. Additionally or alternatively, such an offset adjustment procedure may be performed after the laser beam-riding guided missile system 2 is deployed in the field, for example as part of an embedded process. Such an offset adjustment procedure may be performed before and/or after the laser beam-riding guided missile system 2 launches a missile. Such an offset adjustment procedure may be performed during the flight of the missile to the target 4. Such an offset adjustment procedure may be performed so that, when the aiming ring 14 is coincident with the image 13 of the target 4 in the image 11 of the scene 5, the direction of the laser beam 16 is deliberately offset relative to the target 4. Deliberately offsetting the direction of the laser beam 16 relative to the target 4 in this way may be useful to control the flight path of the missile. For example, when the target 4 is low relative to the horizon, the direction of the laser beam 16 may be deliberately offset above the target 4 before missile launch and/or early in the flight of the missile and the offset may be reduced to zero as the missile approaches the target 4. Offsetting the direction of the laser beam 16 during the flight of the missile in this way may cause the missile to follow a higher flight path to avoid the missile unintentionally colliding with the ground. Deliberately offsetting the direction of the laser beam 16 relative to the target 4 may also be useful to control the flight path of the missile to compensate for wind.
Once the offset adjustment has been performed, the guidance head 8 is ready for use with the missile launcher 6. Specifically, an operator 60 of the guided missile weapon system 2 manoeuvers and/or orients the guided missile weapon system 2 whilst viewing the image 11 of the scene 5 and the aiming mark 14 in the FOV 12 of the monocular digital display 26 until the target 4 is visible in the FOV 12 of the monocular digital display 26. The operator 60 then uses the one or more user controls 25 to align the aiming mark 14 with the image 13 of the target 4 in the FOV 12 of the monocular digital display 26. Once the aiming mark 14 is aligned with the image 13 of the target 4 in the FOV 12 of the monocular digital display 26, the operator 60 uses the one or more user controls 25 to activate the laser source 20 causing the laser source 20 to emit the laser beam 16 towards the target 4 and to cause the missile launcher 6 to launch a missile towards the target 4. Once launched towards the target 4, the missile follows or ride the laser beam 16 to the projected position of the laser beam 16 on the target 4. It should be understood that the guidance head 8 continues to adjust the tilt or orientation of the mirrors 30, 32 and therefore also the direction of the laser beam 16 so as to stabilise the direction of the laser beam 16 against changes in environmental temperature, and against changes in motion and/or orientation of the guidance head 8 during the flight of the missile.
As shown in FIGS. 4A and 4B, the guidance head 8 may also be configured to perform auto target tracking (ATT). Specifically, the processing resource 28 may process the image 11 of the scene 5, identify the image 13 of the target 4 in the image 11 of the scene 5, and adjust the tilt or orientation of the mirrors 30, 32 so that the position of the aiming mark 14 in the image 11 of the scene 5 coincides with, and/or tracks, the identified image 13 of the target 4 in the image 11 of the scene 5. It should be understood that the guidance head 8 continues to track the target 4 and adjust the tilt or orientation of the mirrors 30, 32 and therefore also the direction of the laser beam 16 during the flight of the missile.
The processing resource 28 is configured to cause the monocular digital display 26 to display additional information in the FOV 12, which additional information is additional to the image 11 of the scene 5 and the aiming mark 14. For example, the processing resource 28 may be configured to cause the monocular digital display 26 to display command data and/or control data. The processing resource 28 may be configured to cause the monocular digital display 26 to display one or more cueing arrows to allow the operator 60 of the guidance head 8 to find the target 4 as identified by an external input to the processing resource 28, for example as identified by an external input to the processing resource 28 from a radar. The processing resource 28 may be configured to cause the monocular digital display 26 to display at least one of battery status, target range data, operating modes, and target interrogator response.
Referring to FIG. 5, there is shown a SAL guided missile weapon system which is generally designated 102 and which includes a missile launcher 106 and a separate, remotely located, laser target designator 108. The missile launcher 106 is configured to launch a missile (not shown) towards a target 4. The laser target designator 108 is essentially identical to the guidance head 8 described with reference to FIG. 1A to FIG. 4B and operates in essentially the same way as the guidance head 8 described with reference to FIG. 1A to FIG. 4B. In use, the laser target designator 108 images light 110 received from a scene 5 including a target 4 and directs a laser beam 116 to the target 4 based on an image of the scene 5. The target 4 scatters the laser beam 116 so as to form a cone of scattered light 116a. The missile launcher 106 subsequently launches a missile towards the target 4. The missile is configured to detect the scattered light 116a as the missile approaches the target 4 and to follow the path of the scattered light 116a back to the target 4.
Referring to FIG. 6, there is shown a dazzle weapon system which is generally designated 202. The dazzle weapon system 202 is essentially identical to the guidance head 8 described with reference to FIG. 1A to FIG. 4B and operates in essentially the same way as the guidance head 8 described with reference to FIG. 1A to FIG. 4B except that the laser source 20 of the guidance head 8 is replaced with a laser source (not shown) which is specifically selected so as to generate a laser beam 216 which is capable of dazzling a person located in, or with, a target 4 in a scene 5. In use, the dazzle weapon system 202 images light 210 received from the scene 5 including the target 4 and directs the dazzle laser beam 216 to the target 4 based on an image of the scene 5 so as to dazzle a person located in, or with, the target 4.
Referring to FIG. 7, there is shown a directed energy weapon system which is generally designated 302. The directed energy weapon system 302 is essentially identical to the guidance head 8 described with reference to FIG. 1A to FIG. 4B and operates in essentially the same way as the guidance head 8 described with reference to FIG. 1A to FIG. 4B except that the laser source 20 of the guidance head 8 is replaced with an energy source (not shown) which is specifically selected so as to generate a beam of energy 316 which is capable of causing damage to, or destroying, a target 4 in a scene 5. In use, the directed energy weapon system 302 images light 310 received from the scene 5 including the target 4 and directs the beam of energy 316 to the target 4 based on an image of the scene 5 so as to cause damage to, or destroy, the target 4.
One of ordinary skill in the art will understand that various modifications are possible to the weapon systems, guidance heads, target designators, and methods described above. For example, although some of the guidance heads and target designators described above use a laser beam, the guidance heads or target designators may use a beam of electromagnetic energy of any kind. The beam of electromagnetic energy may comprise an optical beam of any kind such as a coherent optical beam of any kind. The beam of electromagnetic energy may comprise a microwave beam. Although the guidance heads and target designators described above include an energy source such as a laser source which is fixed relative to the housing of the beam-steering arrangement, the energy source may be coupled to the housing of any of the guidance heads and target designators using one or more waveguides. For example, the energy source may comprise an optical source, the beam of energy may comprise an optical beam, and the guidance head or target designator may comprise one or more optical fibres for coupling the optical beam from the optical source to the housing. The energy source may be coupled to the housing of any of the guidance heads and target designators using one or more flexible waveguides so that the energy source may be movable relative to the housing of the beam-steering arrangement.
Each beam-steering element may comprise a reflective beam-steering element of any kind.
Each beam-steering element may comprise a refractive beam-steering element.
Each beam-steering element may comprise a diffractive beam-steering element. Each beam-steering element may comprise a digital micro-mirror array or a spatial light modulator.
The guidance head may comprise one or more beam-steering element drivers, wherein each beam-steering element driver is configured to adjust the beam-steering configuration of a corresponding beam-steering element.
Each beam-steering element driver may comprise an actuator, wherein each actuator is configured to move, for example translate and/or rotate, a corresponding beam-steering element.
Each actuator may comprise a motor of any kind.
Although the weapon systems, guidance heads, target designators, and methods described above are described in the context of a target in the form of a helicopter, the weapon systems, guidance heads, target designators, and methods may be used on any kind of air-based target or on any kind of land- or sea-based target.
One of ordinary skill in the art will understand that one or more of the features of the embodiments of the present disclosure described above with reference to the drawings may produce effects or provide advantages when used in isolation from one or more of the other features of the embodiments of the present disclosure and that different combinations of the features are possible other than the specific combinations of the features of the embodiments of the present disclosure described above.

Claims

1. A guidance head for use in directing a beam of energy towards a target, the guidance head comprising: one or more beam-steering elements for directing a beam of energy towards a projected position on an object in a scene, each beam-steering element having a corresponding beam-steering configuration which determines a direction of the beam of energy leaving the beam-steering element for a given direction of incidence of the beam of energy on the beam-steering element; one or more beam-steering element sensors, each beam-steering element sensor being configured to generate an electrical signal representative of the beam steering configuration of the corresponding beam-steering element; a display; and a processing resource, wherein the processing resource is configured to: receive image data representative of the scene; and cause the display to display an image of the scene that is based on the received image data and which includes an aiming mark displayed at a position in the image of the scene based at least in part on the one or more electrical signals representative of the beam-steering configuration of the one or more beam-steering elements.
2. A guidance head according to claim 1, wherein the processing resource is configured to allow or perform an offset adjustment of the position of the aiming mark in the image of the scene independently of the beam-steering configuration of each beam-steering element.
3. A guidance head according to claim 1 or 2, wherein the processing resource is configured to allow or perform an offset adjustment of the position of the aiming mark in the image of the scene independently of the beam-steering configuration of each beam-steering element until the position of the aiming mark coincides with the projected position of the beam of energy on an image of an object in the image of the scene.
4. A guidance head according to any preceding claim, comprising one or more user controls such as one or more joysticks, wherein the processing resource is configured to receive one or more electrical signals from the one or more user controls and adjust the beam-steering configuration of each beam-steering element, and therefore also the position of the aiming mark in the image of the scene, based at least in part on the one or more electrical signals received from the one or more user controls.
5. A guidance head according to any preceding claim, wherein the beam-steering configuration of each beam-steering element is determined by a position and/or orientation of the beam-steering element.
6. A guidance head according to claim 5, wherein each beam-steering element sensor comprises an encoder for measuring the position and/or orientation of the corresponding beam-steering element.
7. A guidance head according to any preceding claim, comprising one or more beam-steering element drivers, wherein each beam-steering element driver is configured to adjust the beam-steering configuration of a corresponding beam-steering element.
8. A guidance head according to claim 7, wherein each beam-steering element driver comprises an actuator, and wherein each actuator is configured to move, for example translate and/or rotate, a corresponding beam-steering element, for example wherein each actuator comprises a motor such as a servo motor.
9. A guidance head according to any preceding claim, wherein each beam steering element comprises a reflective beam-steering element such as a mirror, a refractive beam-steering element and/or a diffractive beam-steering element.
10. A guidance head according to any preceding claim, comprising one or more temperature sensors for sensing a temperature of an environment surrounding the guidance head, wherein the processing resource is configured to adjust the beam steering configuration of each beam-steering element so as to maintain the position of the aiming mark relative to the image of a stationary object in the image of the scene in the presence of a change in the temperature of the environment surrounding the guidance head as sensed by the one or more temperature sensors.
11. A guidance head according to any preceding claim, comprising one or more motion and/or orientation sensors such as one or more accelerometers and/or one or more gyroscopes for measuring motion and/or orientation of the guidance head, wherein the processing resource is configured to adjust the beam-steering configuration of each beam-steering element so as to maintain the position of the aiming mark relative to the image of a stationary object in the image of the scene in the presence of a change in the motion and/or orientation of the guidance head as sensed by the one or more motion and/or orientation sensors.
12. A guidance head according to any preceding claim, wherein the processing resource is configured to: identify an image of a target in the image of the scene based on the image data representative of the scene; and adjust the beam-steering configuration of each beam-steering element so that the position of the aiming mark in the image of the scene coincides with, and/or tracks, the identified image of the target in the image of the scene.
13. A guidance head according to any preceding claim, wherein the processing resource is configured to perform auto target tracking (ATT) based on the image data representative of the scene.
14. A guidance head according to any preceding claim, wherein the beam of energy comprises at least one of: a beam of electromagnetic energy; an optical beam such as a coherent optical beam; a laser beam; and a microwave beam.
15. A guidance head according to any preceding claim, comprising an energy source for emitting the beam of energy, wherein the energy source comprises at least one of: a source of electromagnetic energy; an optical source such as a coherent optical source; a laser; and a source of microwave energy.
16. A guidance head according to claim 15, wherein the energy source is configured to emit a beam of energy that is configured to damage and/or destroy a target.
17. A guidance head according to claim 15, wherein the energy source is configured to dazzle, for example wherein the energy source comprises a dazzle laser.
18. A guidance head according to any preceding claim, comprising an image sensor for generating the image data representative of the scene, wherein at least one of: the image sensor comprises a video image sensor such as a camera; the image sensor is sensitive to visible light; the image sensor is sensitive to IR, for example wherein the image sensor comprises a thermal image sensor.
19. A guided missile weapon system, comprising the guidance head as claimed in any preceding claim and a missile launcher for launching a missile, wherein the weapon system is configured so that the beam of energy guides the missile to the target.
20. A guided missile weapon system as claimed in claim 19, wherein the missile is configured to ride the beam of energy to the target.
21. A guided missile weapon system as claimed in claim 19, wherein the missile is configured to detect a scattered portion of the beam of energy which is scattered from the target as the missile approaches the target and to follow the path of the scattered portion of the beam of energy back to the target.
22. A guided missile weapon system as claimed in claim 21, wherein the weapon system comprises a semi-active laser (SAL) guided missile system such as a manual SAL guided missile system or a self-designated SAL guided missile system.
23. A directed energy weapon system or a dazzle weapon system, comprising the guidance head as claimed in any one of claims 1 to 18.
24. A target designator, comprising a guidance head as claimed in any one of claims 1 to 18, optionally wherein the target designator is portable, configured to be carried by an operator and/or hand-held.
25. A guidance method for use in directing a beam of energy towards a target, the guidance method comprising: directing a beam of energy towards a position of incidence on an object in a scene using one or more beam-steering elements; generating an electrical signal representative of a beam-steering configuration of each of the one or more beam-steering elements, wherein the beam-steering configuration of each beam-steering element determines a direction of the beam of energy leaving the beam-steering element for a given direction of incidence of the beam of energy on the beam-steering element; receiving image data representative of the scene; and causing a display to display an image of the scene that is based on the received image data and which includes an aiming mark displayed at a position in the image of the scene based at least in part on the one or more electrical signals representative of the beam-steering configuration of the one or more beam-steering elements.
EP21700327.6A 2020-01-09 2021-01-06 Guidance head and method Pending EP4088079A1 (en)

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SE416232B (en) * 1976-11-05 1980-12-08 Bofors Ab DEVICE FOR A VIOLATION DETERMINATION FROM THE VIEW LINE
US4386848A (en) * 1980-08-11 1983-06-07 Martin Marietta Corporation Optical target tracking and designating system
FR2816118B1 (en) * 2000-10-27 2003-01-31 Thomson Csf DEVICE FOR THE HARMONIZATION BETWEEN A LASER TRANSMISSION CHANNEL AND A PASSIVE OBSERVATION CHANNEL
US6961171B2 (en) * 2002-10-17 2005-11-01 Raytheon Company Phase conjugate relay mirror apparatus for high energy laser system and method
RU2401410C1 (en) * 2009-11-13 2010-10-10 Александр Алексеевич Бурба Multichannel guidance system using reference image
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