EP0089273B1 - Feuerkontrollsystem mit doppelter Bestimmung der Winkelabweichungen - Google Patents

Feuerkontrollsystem mit doppelter Bestimmung der Winkelabweichungen Download PDF

Info

Publication number
EP0089273B1
EP0089273B1 EP19830400464 EP83400464A EP0089273B1 EP 0089273 B1 EP0089273 B1 EP 0089273B1 EP 19830400464 EP19830400464 EP 19830400464 EP 83400464 A EP83400464 A EP 83400464A EP 0089273 B1 EP0089273 B1 EP 0089273B1
Authority
EP
European Patent Office
Prior art keywords
signals
circuit
detector
control system
tracking device
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.)
Expired
Application number
EP19830400464
Other languages
English (en)
French (fr)
Other versions
EP0089273A1 (de
Inventor
Jean Dansac
Robert Pressiat
Bernard Grancoin
Jean-Paul Lepeytre
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 SA
Original Assignee
Thomson CSF SA
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 Thomson CSF SA filed Critical Thomson CSF SA
Publication of EP0089273A1 publication Critical patent/EP0089273A1/de
Application granted granted Critical
Publication of EP0089273B1 publication Critical patent/EP0089273B1/de
Expired legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/22—Aiming or laying means for vehicle-borne armament, e.g. on aircraft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/06—Aiming or laying means with rangefinder

Definitions

  • the present invention relates to a fire control system, and more precisely to an automatic target targeting and tracking system, particularly suitable for use on aircraft (combat helicopter in particular).
  • the automatic aiming and tracking device is therefore particularly important since it must take full charge of monitoring the movements of a target from the moment an operator has designated this target, so that the latter is free to devote himself to piloting, issuing the firing order, monitoring and locating other targets, etc.
  • Document FR-A-2 352 271 describes a method and device for locating and shooting, day and night, at a target. This process consists in using, in both cases, a goniometer with infrared rays of a day vision device on which is fixed a night vision device previously set on the main line of a day tracking installation and to bring in superimposition, after the departure of the projectile, the thermal images of the projectile and of the target in the variable line of sight of the night vision device by continuation of the whole installation of the shooting.
  • the present invention provides a fire control system allowing rapid acquisition of the target and making automatic pursuit as much as possible.
  • the system according to the invention is designed to choose the channel used (visual or infrared) in order to avoid as much as possible the loss of the target for reasons which may be poor optical visibility, masking by obstacles, movements of the aircraft carrying the system, its structural deformations, etc.
  • the hot spot deviation allows the position and movement speeds of the target to be identified. target.
  • This location is a rough location, if only because the "hot spots" emitting infrared radiation are diffuse sources that do not allow the shape of a target to be reconstructed.
  • the aiming device is designed so that the two types of radiation follow the same optical axis, which is the aiming axis, the passage from one type of deviation measurement to the other takes place without risk of parallax error .
  • the fire control system is more particularly intended to be carried by an aircraft, and provision is preferably made for the sighting device to be stabilized by a gyroscopic system.
  • This gyroscopic system is sensitive to the movements of the device along the two independent axes around which the latter can rotate, and it includes torque motors and angular sensors through which the orientation control of the aiming device is carried out: the control signals from the control mode selection circuit are applied to the torque motors of the gyroscopic system, and the angular sensors consequently generate displacement signals which are applied after amplification to the orientation motors of the aiming device in a direction such as the rotation of the sighting device, and therefore of the gyroscopic system which it carries, generates precession torques opposing the torques applied by the torque motors.
  • the gyroscopic system to include two gyrometers, or two integrating gyrometers, or even a two-axis gyroscope with tuned suspension.
  • Figure 1 shows all of the fire control organs of the system mounted on a helicopter; we will explain how these organs work.
  • the helicopter pilot and co-pilot may be provided with helmet sights 10 and 12 coupled to an electronic circuit 14 to supply the latter with signals identifying the position of the pilot's (or co-pilot's) head and therefore the direction that he observes.
  • helmet sights 10 and 12 coupled to an electronic circuit 14 to supply the latter with signals identifying the position of the pilot's (or co-pilot's) head and therefore the direction that he observes.
  • These helmet sights can thus be used for a first acquisition of a target 18, for example a helicopter.
  • a magnifying observation telescope 16 optionally makes it possible to take over from observation with the naked eye.
  • This telescope is tele-orientable (for example on site and in bearing) manually by means of a control stick 20 with two axes, or automatically from the signals supplied by the helmet sights.
  • An automatic aiming device 22, used to track the target after its acquisition, is coupled to the helmet sights or to the telescopic sight 16 via the electronic circuit 14, so that the movements of the aiming device and the telescope are coupled to each other, whether it be the telescope 16 which drives the sighting device 22 or the opposite.
  • the sighting device 22 is orientable in elevation and in bearing (for example). It is preferably gyro-stabilized as will be explained below and the motors which drive it are preferably torque motors with electromagnetic drive to avoid the presence of gears in the transmission of movement.
  • head-up viewfinder 24 and “head-down display” 26 are provided to allow observation, for example in the form of a television image, of the field of view of the telescope, as well as of miscellaneous information, shooting or navigation aid symbols, etc. These display devices are coupled to the electronic circuit 14 which supplies them with the images to be represented.
  • a firing weapon 28 for example a cannon mounted on a turret and capable of pivoting in elevation and in bearing with respect to the structure of the helicopter, is also coupled to the electronic circuit 14 to receive information therefrom on the direction aimed by. the sighting device 22 therefore, taking into account any shooting corrections, on the pointing direction to be given to the weapon.
  • the shooting corrections are developed from various information, including in particular a measurement of the distance from the target by a rangefinder at laser 30 (whose laser transmitter emits along the axis or parallel to the axis of the sighting device 22), a measurement of the relative speed of the helicopter and of the target (measured by the tracking speed of the sighting device aiming 22), as well as other information (aerodynamic speed, speed relative to the ground, wind speed, etc.) provided by various sensors 32 mounted on the helicopter.
  • various information including in particular a measurement of the distance from the target by a rangefinder at laser 30 (whose laser transmitter emits along the axis or parallel to the axis of the sighting device 22), a measurement of the relative speed of the helicopter and of the target (measured by the tracking speed of the sighting device aiming 22), as well as other information (aerodynamic speed, speed relative to the ground, wind speed, etc.) provided by various sensors 32 mounted on the helicopter.
  • the sighting device 22 may or may not be placed on the turret of the shooting weapon. We will consider below that it is separate from it. After a target has been identified by means of the helmet sights (or of the observation telescope 16), the operator decides to switch to automatic tracking, the electronic circuit 14 then driving the orientation motors of the aiming device 22 to maintain the image of the target in the axis thereof. The shooting weapon 28 follows the movements of the sighting device, with an offset corresponding to the shooting corrections. Then the operator gives the firing order.
  • FIG. 2 shows the overall diagram of the automatic tracking system. However, to simplify the description, only the bearing tracking circuits have been shown, it being understood that the tracking is carried out both in elevation and in bearing, independently therefore with two similar independent circuit paths respectively driving a site orientation engine and a field orientation engine.
  • the sighting device 22 comprises an optical assembly 34 having a sighting axis 36 which it is desired to direct permanently towards a target.
  • the optical assembly 34 is mounted for rotation about two axes, preferably by means of a gimbal system; the universal joint assembly being conventional, it has not been shown to simplify the figure, and only the axis of rotation has been shown in reservoir 38 and a motor 40 for driving around this axis 38.
  • the motor 40 and the motor, not shown, for driving the optical assembly around the axis of rotation in elevation, is preferably a torque motor, acting without friction by electromagnetic action between a rotor and a stator.
  • the optical assembly 34 of the sighting device is preferably stabilized by gyroscopic action, that is to say to drive it in rotation, a control signal will not be directly applied to the drive motors but a signal will be applied control gyros which themselves will provide control signals to the motors.
  • the optical assembly can carry two gyrometers or two integrating gyrometers, or even a gyroscope with two axes with tuned suspension, these devices having as sensitive axes respectively the axis of rotation in bearing 38 and an axis of rotation in elevation 42 perpendicular to the plane of the figure.
  • Figure 2 which describes only one orientation control channel, there is only shown an integrating gyrometer 44 having as its sensitive axis the axis of rotation in bearing.
  • This gyrometer has a rotor rotating in a support frame, a torque motor 46 for controlling the rotation of the frame and an angular sensor 48 identifying the rotation of the frame.
  • the torque motor receives control signals which rotate the support frame, therefore the output shaft of the gyroscope, by an angle identified by the sensor 48.
  • the sensor 48 transmits a signal corresponding to this rotation, after processing and amplification in a circuit 50, to the motor 40 which rotates the optical assembly 34 around the bearing axis, thus generating on the gyroscope rotor a precession torque which balances the torque generated by the torque motor 46.
  • the process is the same for the site rotation control channel which includes an identical servo. This gyroscopic stabilization of the optical assembly 34 along the two axes makes it possible in particular to avoid the transmission of vibrations from the helicopter to the optical assembly.
  • the orientation of the line of sight 36 is identified by angular sensors, for example synchrodetectors; the reference 52 designates such a sensor symbolically represented in FIG. 2.
  • the orientation information is transmitted to the electronic circuit 14 of FIG. 1, with a view in particular to controlling the orientation of the telescopic sight 16 and of the weapon firing 28.
  • the optical assembly 34 comprises various optical means which will be detailed below, for receiving both visible and infrared radiation in the band of approximately 3 to 5 microns, along the same line of sight 36, and for separating these radiations by means of selectively reflecting surfaces, in order to direct and focus these two types of radiation on respective detectors which are an infrared detector 54 and a visible image detector 56.
  • the detector 54 is of the four-quadrant type to make it possible to locate the angular depointing of a hot point with respect to the line of sight 36.
  • the detected signals provide information on the approximate direction of the hot point and make it possible to indicate if it is to the left or to the right of the line of sight (deviation in bearing) or higher or lower (deviation in elevation).
  • a deviation circuit 58 receives the signals from the four quadrants of the detector, processes them and combines them to deliver deviation signals on hot spots enabling the aiming axis of the optical assembly 34 to be controlled in the direction of the point hot spotted.
  • This type of detector and associated deviation circuit is known and can be found in examples in French patents 2,356,152 or 2,350,010 of the applicant.
  • a modulation of infrared radiation by a mobile grid formed by transparent and opaque sectors alternating regularly or according to a code, with synchronous detection or suitable filtering or correlation, allows an improvement in the contrast between the image of the hot spot and the background (especially in the presence of sun), as well as the elimination of large sources (spatial filtering).
  • the detector 56 receiving only visible radiation, is capable of forming an image of the field of view of the objective. It can be constituted for example by a vidicon tube or by an array of photodetectors (of the charge transfer type) with the associated reading circuits. It delivers signals representing a relatively precise image of the field of view, with the target in this field; this image can be transmitted for example to the head-down display device 26 of FIG. 1.
  • the signals from the detector 56 are in any case transmitted to a second deviation circuit 60 which makes it possible to define the deviation along two independent axes location between the image of the target on the detector 56 and a reference image recorded in memory in the deviation circuit and representing the target centered in the field of view.
  • the second deviation circuit 60 is more complex than the first but much more precise. It can be a deviation measurement circuit operating by contrast: a modification of a contrasting area in a fixed location translates a displacement of the image and generates deviation measurement signals intended to control the sighting device 22 of so as to bring the contrasted area back to its initial position.
  • These offsets constitute another pair of deviation signals, called visible deviation signals, used to control the sighting device 22 so as to bring the image of the sight field as much as possible in superposition with the initial image .
  • French patent 1 504 656 of October 18, 1966 describes such an image correlation device.
  • the orientation motors of the aiming device can be controlled either by the first pair of deviation measurement signals (on hot spots), or by the second (on visible image).
  • these are signals from the control stick 20, or from angular sensors locating the position of the observation telescope 16, or from the helmet sights, etc., which serve to control the orientation of the sighting device.
  • a tracking speed memory 62 provides for Replacement signals for the orientation control of the aiming device. This memory records the tracking speed simply from the currents applied to the torque motors (46 for example) of the gyroscopic stabilization system.
  • the aiming device continues as if the target was continuing its path with the same direction and the same speed as when it was lost.
  • a control mode selection circuit 64 which receives several pairs of control signals and which selects one to transmit it to a circuit 66 for excitation of the torque motors of the gyroscopic stabilization system.
  • the selected control signals exit on an output S of circuit 64.
  • Circuit 64 can comprise either simple switches for switching a selected pair of control signals, with manual control of these switches by an operator, or automatic selection circuits, for example threshold circuits detecting a value too weak of the correlation signals of the deviation measurement circuit on visible image (60) and thus imposing the transmission of deviation measurement signals on hot spots, as well as threshold circuits detecting too low a value of the signals representing the presence of a dot hot and thus imposing the transmission of D speed memory signals.
  • control signals A In order, priority is given to the control signals A in acquisition mode, then, in tracking mode, first the signals C then the signals B if the visible light deviation is of insufficient quality, then the D signals if the infrared deviation is also of insufficient quality.
  • optical assemblies 34 Examples of the constitution of optical assemblies 34 will now be described. These assemblies are represented schematically with only the optical elements themselves, in order to make it clear how from which visible and infrared radiation are received and separated.
  • FIG. 3 shows a first example in which the incoming rays centered around the optical axis 36 are reflected by a first concave mirror 70 which returns them to a second convex mirror 72.
  • These two mirrors form a set of Cassegrain type transmitting the rays visible as the infrared rays towards a dichroic separating mirror which can be constituted by a first prism 74 behind which is attached a second prism 76, the face common to the two prisms being treated to be reflective for the infrared rays in the band from 3 to 5 microns, and transparent for visible light.
  • the photosensitive surface of the detector 56 used to detect the image of the field of view formed by the mirrors 70 and 72, in visible light only.
  • the modulating grid 78 has been placed, which may consist of a certain number of alternating transparent and opaque sectors arranged on a disc in uniform rotation.
  • the infrared radiation, separated at 75 from that in visible light, is focused by the mirrors 70 and 72 on the grid 78; if a "hot" point emitting in the infrared is present in the field of view, the image of this hot point will be alternately discovered and hidden by the alternating sectors of the grid; on the other hand, the ambient radiation sources (in the presence of the sun, such as clouds) do not undergo modulation because of their large extent.
  • the infrared rays having passed through the grid can be returned by a mirror 80 to a recovery objective 82 which focuses them again on the infrared detector 54 (cf. fig 2) with four quadrants combined with the deviation circuit 58 to provide signals of deviation corresponding to the approximate direction in elevation and in point of the hot spot.
  • Figure 4 recalls, for information only, such an arrangement: the signals from each of the quadrants of the detector 54 each pass individually through a respective synchronous detection circuit 84, working at the frequency of passage of the opaque and transparent sectors of the grid 78. These synchronous detection circuits are followed by amplifiers 85 and summers 87 and 89 which make the differences two by two of the signals coming from opposite quadrants. The outputs of these summers 87 and 89 are applied to two other summers 91 and 93 which sum and differ respectively from the signals which they receive and which supply at their output deviation signals, one at site B and the other in deposit B '.
  • FIG. 5 is another embodiment of the optical assembly 34. Again, only the optical elements and the detectors are shown.
  • the visible and infrared rays are received by the main concave mirror 70 which reflects them towards the convex secondary mirror 72 (Cassegrain type assembly) which returns them according to the initial direction. These returned rays strike a dichroic separator produced by a surface 83 treated to reflect the visible rays and let pass the 3-5 micron infrared rays. Behind the surface 83 there is the rotating modulation grid 78 and, after the recovery objective 82, the four-quadrant infrared detector 54 as in FIG. 3.
  • the surface 83 can moreover be constituted by a deposit on one face of the carrier disk of the modulation grid 78.
  • the visible rays are reflected by the surface 83 towards the center of the secondary mirror 72, and, at this center is placed the visible image detector 56 on which the visible rays are focused.
  • a laser emission means is mounted on the optical assembly 34 to transmit in the direction of the line of sight 36 (along this axis or in parallel to this axis).
  • the laser itself which is too bulky, cannot be mounted on the orientable assembly 34 and therefore a fixed laser and deflection mirrors mounted on the assembly 34 are provided and placed in such a way that the laser beam is always returned in the direction of the line of sight 36, whatever the orientation of the assembly 34.
  • the reception part of the laser rangefinder can be located on the optical assembly 34 or elsewhere.
  • FIG. 6 shows an embodiment in which the optical assembly 34 carries, as laser emission means, several deflection mirrors, the laser illuminator proper, 86, being fixed and being able to be offset.
  • a first mirror M1 secured to a support movable in rotation about the axis of rotation in elevation 42, returns the laser beam to a second mirror M2, then a third mirror M3, secured to the same support.
  • the beam received by M3 is directed towards a fourth mirror M4 mounted on the optical assembly 34 itself which is mobile in rotation around the axis of rotation in bearing 38.
  • the laser beam leaves parallel to the line of sight 36 whatever the orientation of the latter in elevation and in bearing, in particular because the mirrors M1, M3 and M4 are placed so as to return the beam either on the axis of rotation in elevation, or on the axis of rotation in deposit.
  • the laser beam pulses emitted and reflected by the target can be collected by a detection cell separate from the aiming device.
  • the optical assembly 34 can receive, in addition to visible and far infrared radiation, the laser beam (preferably wavelength, 1.06 micron).
  • Figures 7 and 8 show two examples of realization of optical assemblies 34 which incorporate a reception of laser beam at 1.06 micron for telemetry.
  • the laser emission channel which may correspond to the embodiment of FIG. 6, is not shown.
  • FIG. 7 corresponds to a modification of FIG. 3.
  • FIG. 7 The difference with FIG. 3 is located behind the prism 74: in FIG. 7, a second prism 88 is attached to the prism 74.
  • the visible and laser rays pass through this prism, reach a rear face, inclined at 90 ° with respect to the face common to prisms 74 and 88.
  • This rear face is itself a face common to the second prism 88 and to a third prism 90.
  • It is treated dichroic to reflect the laser rays at 1.06 micron, and to let the rays pass visible light.
  • the laser radiation therefore exits through a second prism without passing through the third and it is focused by a recovery objective 92 on a detection cell 94 of the range finder.
  • the visible rays, them pass through the third prism 90, and are focused by a recovery objective 96 on a photosensitive surface 56 as in FIG. 3.
  • the same optical assembly 34 receives and separates three types of radiation useful for the fire control system.
  • FIG. 8 likewise shows a variant which is inspired by FIG. 5 to which a device for separating the laser radiation at 1.06 micron has been added.
  • a device for separating the laser radiation at 1.06 micron we have simply inserted, between the semi-reflecting surface 83 of FIG. 5 and the photosensitive surface 56, two adjoining prisms 98, 100, the common face of which is treated dichroic to be transparent to visible light and reflective for the laser beam. The rays reflected by this common face strike a detection cell 103 of the range finder.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Optical Radar Systems And Details Thereof (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (11)

1. Feuerleitsystem mit einer Visiervorrichtung (22), die durch Orientierungsmotoren gemäß zwei unabhängigen Achsen orientierbar ist, und mit einem der Visiervorrichtung zugeordneten elektronischen Kreis (14) zur Steuerung der Motoren derart, daß permanent die Visiervorrichtung auf ein Ziel (18) ausgerichtet ist, dadurch gekennzeichnet, daß die Visiervorrichtung ein erstes optisches Mittel (70, 72) zum gleichzeitigen Empfangen und Aussenden, entlang einer gemeinsamen optischen Visierachse (36), einer Infrarot- strahlung einer Wellenlänge von ungefähr 3 bis 5 JLm und einer vom Ziel ausgehenden sichtbaren Strahlung, sowie ein zweites optisches Mittel (74, 76) aufweist, mit dem diese Strahlungen getrennt werden und auf einen für die Infrarotstrahlung empfindlichen Detektor (54) bzw. auf einen für sichtbares Licht empfindlichen Bilddetektor (56) gelenkt werden, und daß der zugeordnete elektronische Kreis (14) einen ersten Abweichungsmeßkreis (58), der die vom für die Infrarotstrahlung empfindlichen Detektor kommenden Signale empfängt und zwei Abweichungsmeßsignale betreffend sogenannte "heiße Punkte" liefert, einen zweiten Abweichungsmeßkreis (60), der die vom Bilddetektor kommenden Signale empfängt und zwei Abweichungsmeßsignale, sogenannte "Signale für sichtbares Licht" liefert, und einen Steuermodus-Wahlschaltkreis (64) aufweist, der eine Vielzahl von Orientierungssteuersignalpaaren zugeführt erhält, unter denen sich die beiden Abweichunsgmeßsignalpaare befinden, und der an die Orientierungsmotoren ein ausgewähltes Paar von Steuersignalen überträgt.
2. Feuerleitsystem nach Anspruch 1, dadurch gekennzeichnet, daß das erste optische Mittel einen doppelten katadioptischen Spiegel vom Cassegrain-Typ aufweist, daß das zweite optische Mittel einen dichroischen Separator (75) enthält, der für eine der beiden Strahlungen, nämlich die sichtbar oder die Infrarot-Strahlung, durchlässig ist und die andere reflektiert, und daß der Infrarotdetektor und der Bilddetektor je auf einer Seite dieser Oberfläche angeordnet sind.
3. Feuerleitsystem nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, daß ein drehendes Modulationsgitter (78) zwischen das zweite optische Mittel und den Infrarotdetektor eingefügt ist, um die von diesem Detektor empfangene Strahlung mit einer bekannten Frequenz zu modulieren.
4. Feuerleitsystem nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß die Visiervorrichtung ein drittes optisches Mittel (88, 90), das von der sichtbaren Strahlung und der Infrarot- strahlung eine Laserstrahlung abtrennen kann, deren Wellenlänge sich von der der sichtbaren Strahlung und der Infrarotstrahlung von 3 bis 5 ILm unterscheidet, und das in der Lage ist, diese Laserstrahlung auf eine Detektorzelle (94) zu lenken, um eine Lasertelemetrie ausgehend von dieser selben Visiervorrichtung zu erlauben.
5. Feuerleitsystem nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß die Visiervorrichtung außerdem ein Laseremissionsmittel aufweist, das eine Laserstrahlung in Richtung der optischen Visierachse aussendet.
6. Feuerleitsystem nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß das System einen Helmvisierer oder ein von den Orientierungsmotoren gesteuertes Beobachtungsfernrohr aufweist und daß Winkelgeber für die Orientierung des Fernrohrs oder des Helmvisierers vorgesehen und an den Selektionskreis (64) gekoppelt sind, um an ihn ein Paar von Steuersignalen zu liefern, das die Orientierung der Visiervorrichtung ausgehend vom Fernrohr oder dem Helmvisierer erlaubt.
7. Feuerleitsystem nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß die Visiervorrichtung ein gyroskopisches Stabilisationssystem (44) trägt, das auf Verschiebungen in Richtung der beiden Orientierungsachsen der Vorrichtung anspricht und Motorpaare (46) sowie Winkelgeber (48) aufweist, wobei die Motorpaare die Steuersignale des Selektionskreises zugeführt erhalten und die Winkelgeber Betätigungssignale für die Orientierungsmotoren (40) der Visiervorrichtung liefern.
8. Feuerleitsystem nach Anspruch 7, dadurch gekennzeichnet, daß das gyroskopische Stabilisationssystem, das von der Visiervorrichtung getragen wird, zwei Gyrometer (44) aufweist.
9. Feuerleitsystem nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, daß ein Schaltkreis (62) zur Einspeicherung der Winkelverschiebungsgeschwindigkeiten der Visiervorrichtung vorgesehen ist, der hierzu die vom logischen Selektionskreis gelieferten Steuersignale zugeführt erhält und an den letzteren ein Paar von Steuersignalen liefert, wobei der Selektionskreis dieses letztere Signalpaar im Falle des Verschwindens von Abweichungsmeßsignalen zufriedenstellender Qualität überträgt.
10. Feuerleitsystem nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, daß der auf die Infrarotstrahlung ansprechende Detektor (54) ein Vierquadrantendetektor ist.
11. Feuerleitsystem nach einem der Ansprüche 1 bis 10, dadurch gekennzeichnet, daß der Detektor für das sichtbare Bild (56) eine Matrix von Photodetektoren ist und daß der zugeordnete Abweichungsmeßkreis eine Bilderkorrelationskreis enthält.
EP19830400464 1982-03-12 1983-03-07 Feuerkontrollsystem mit doppelter Bestimmung der Winkelabweichungen Expired EP0089273B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8204214A FR2523293A1 (fr) 1982-03-12 1982-03-12 Systeme de conduite de tir a double ecartometrie
FR8204214 1982-03-12

Publications (2)

Publication Number Publication Date
EP0089273A1 EP0089273A1 (de) 1983-09-21
EP0089273B1 true EP0089273B1 (de) 1987-01-07

Family

ID=9271931

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19830400464 Expired EP0089273B1 (de) 1982-03-12 1983-03-07 Feuerkontrollsystem mit doppelter Bestimmung der Winkelabweichungen

Country Status (3)

Country Link
EP (1) EP0089273B1 (de)
DE (1) DE3368978D1 (de)
FR (1) FR2523293A1 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4777861A (en) * 1987-01-16 1988-10-18 Recon/Optical, Inc. Missile aiming sight
FR2711806B1 (fr) * 1990-07-23 1995-12-29 Aerospatiale Système de détection et de riposte vis-à-vis d'une menace aérienne.
US5331881A (en) * 1992-05-19 1994-07-26 United Technologies Corporation Helicopter integrated fire and flight control having azimuth and pitch control
DE19720903B4 (de) * 1997-05-17 2005-07-14 LFK Lenkflugkörpersysteme GmbH Einrichtung zur Achsparallelisierung eines Wärmebildgerätes
CN102927416B (zh) * 2011-08-08 2015-04-08 天津市亚安科技股份有限公司 安装于监控设备防护罩内部的微动调节台以及监控装置

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4038547A (en) * 1966-05-31 1977-07-26 Philco Corporation Tracking and sighting instrument
US3989947A (en) * 1971-03-01 1976-11-02 Hughes Aircraft Company Telescope cluster
FR2334079A1 (fr) * 1975-12-01 1977-07-01 Telecommunications Sa Dispositif de guidage nocturne d'engins autopropulses
FR2352271A1 (fr) * 1976-05-21 1977-12-16 Eltro Gmbh Procede et dispositif de reperage et de tir sur cible
GB1505314A (en) * 1977-01-25 1978-03-30 Barr & Stroud Ltd Gunnery fire control system sight
FR2419497A1 (fr) * 1978-03-06 1979-10-05 Barbier Benard & Turenne Dispositif optique de pointage pour artillerie antiaerienne de petit calibre automotrice
DE2841622C2 (de) * 1978-09-25 1982-10-21 Siemens AG, 1000 Berlin und 8000 München Laserentfernungsmeßsystem
FR2465188A1 (fr) * 1980-11-03 1981-03-20 Trt Telecom Radio Electr Dispositif pour detecter un point chaud dans un paysage percu selon un rayonnement infrarouge et systeme de guidage d'un missile sur une cible, comportant un tel dispositif

Also Published As

Publication number Publication date
FR2523293B1 (de) 1984-04-20
EP0089273A1 (de) 1983-09-21
DE3368978D1 (en) 1987-02-12
FR2523293A1 (fr) 1983-09-16

Similar Documents

Publication Publication Date Title
EP0033679B1 (de) System zur Andeutung eines Objektes mittels eines Lasers
EP0628780B1 (de) Zielesystem für Luftfahrzeug
EP0432014B1 (de) Optoelektronisches Hilfssystem für die Flugnavigation und Luftangriffsaufträge
EP0441079B1 (de) Teilbares und rekonfigurierbares Episkophauptzielfernrohr
EP0004227B1 (de) Einrichtung zur optoelektrischen Detektion und zur Bestimmung der Winkelablage eines leuchtenden Objekts, sowie deren Verwendung
US5796474A (en) Projectile tracking system
US10057509B2 (en) Multiple-sensor imaging system
EP0167432B1 (de) Luftfahrzeuggerät für optoelektrische Entdeckung, Ortung und allseitige Vervolgung eines Zieles
EP0084060B1 (de) Wärmebildgesteuerte zielsucheinrichtung
EP3488540B1 (de) Kombiniertes bildgebungs- und laserkommunikationssystem
US8502128B1 (en) Dual-mode electro-optic sensor and method of using target designation as a guide star for wavefront error estimation
FR2914055A1 (fr) Tete chercheuse pour engin volant guide servant a saisir et poursuivre une cible et procede d'application.
EP0089273B1 (de) Feuerkontrollsystem mit doppelter Bestimmung der Winkelabweichungen
WO1998031985A1 (fr) Dispositif apte a determiner la direction d'une cible dans un repere predefini
FR2480424A1 (fr) Systeme de conduite automatique de tir air-air ou air-sol
FR2642529A1 (fr) Procede et dispositif de mesure de la position d'un vehicule
EP0090713B1 (de) Feuerleitsystem mit einem durch ein automatisches Verfolgungsgerät gesteuerten Fernrohr
FR2687791A1 (fr) Systeme optronique de poursuite tridimensionnelle avec alignement automatique d'un telemetre optique sur la cible.
FR2657154A1 (fr) Appareil de pointage monte sur casque.
EP0169128B1 (de) Optoelektrische Vorrichtung zur Richtungsentdeckung und -ortung von Lichtquellen mit hohem Schutz gegenüber Gegenmassnahmen
EP0197710A2 (de) Flugsteuerungsvorrichtung
EP4174435B1 (de) Ziel- und verteidigungssystem mit einem revolverkopf und einem lasersystem sowie kraftfahrzeug mit einem solchen ziel- und verteidigungssystem
FR2665251A1 (fr) Systeme de guidage pour missiles.
FR3005359A1 (fr) Procede et dispositif de protection des aeronefs basse altitude vis-a-vis des missiles sol/air
WO2023274842A1 (fr) Dispositif d' observation a voies optronique et optique independantes et vehicule equipe d' un tel dispositif

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Designated state(s): DE GB IT NL

17P Request for examination filed

Effective date: 19831207

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE GB

REF Corresponds to:

Ref document number: 3368978

Country of ref document: DE

Date of ref document: 19870212

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

GBPC Gb: european patent ceased through non-payment of renewal fee
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19871201

26N No opposition filed
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19881122