EP0628780A1 - Zielesystem für Luftfahrzeug - Google Patents

Zielesystem für Luftfahrzeug Download PDF

Info

Publication number
EP0628780A1
EP0628780A1 EP94400904A EP94400904A EP0628780A1 EP 0628780 A1 EP0628780 A1 EP 0628780A1 EP 94400904 A EP94400904 A EP 94400904A EP 94400904 A EP94400904 A EP 94400904A EP 0628780 A1 EP0628780 A1 EP 0628780A1
Authority
EP
European Patent Office
Prior art keywords
aiming system
aircraft
observation device
scanning
observation
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.)
Granted
Application number
EP94400904A
Other languages
English (en)
French (fr)
Other versions
EP0628780B1 (de
Inventor
Jacques Brunand
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.)
Airbus Helicopters SAS
Original Assignee
Eurocopter France 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 Eurocopter France SA filed Critical Eurocopter France SA
Publication of EP0628780A1 publication Critical patent/EP0628780A1/de
Application granted granted Critical
Publication of EP0628780B1 publication Critical patent/EP0628780B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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

Definitions

  • the present invention relates to an aiming system for an aircraft, in particular a rotary wing aircraft, such as a helicopter.
  • EP-0 167 432 discloses an airborne system for detecting, locating and tracking a target, comprising an adjustable optical head placed under a dome outside the fuselage of the aircraft.
  • the mounting of the optical detection and telemetry means is a gimbal type mounting, comprising two frames perpendicular to each other.
  • the optical sighting system for aircraft is mounted in a nacelle comprising a first part fixed to the aircraft, a second part which can be oriented relative to said first part around a first axis, and a third part orientable relative to said second part about an axis orthogonal to the first axis mentioned.
  • patent FR-2,570,195 relates to a target search device, comprising a camera mounted on a tilting stabilization platform, on board an aircraft.
  • the movement of the stabilization platform can be a triangular, sinusoidal, sawtooth, or spiral movement.
  • the present invention aims to avoid these drawbacks, and relates to an aiming system easily integrated into its carrier (aircraft) and which can be easily adapted to different carriers, missions and armaments.
  • the sighting system for an aircraft in particular a rotary wing aircraft, such as a helicopter, is remarkable, according to the invention, in that it comprises the combination of a first individual observation device , integrated laterally to the aircraft, and a second individual axial firing device, integrated at the front of the aircraft, said first and second devices being connected to the on-board computer of the aircraft.
  • the combination of separate observation and aiming devices according to the invention constitutes an original architecture due to the location fixed specific of said devices integrated into the aircraft.
  • the architecture of the sighting system according to the invention makes it possible to satisfy all of the existing and projected operational needs, while meeting the numerous constraints of performing these functions on an aircraft, in particular an aircraft with rotary wing, such as a helicopter.
  • the modular nature of this architecture makes it possible, in particular, to rapidly configure the carrier aircraft for a specific mission and a given weaponry, by installing appropriate detectors and guidance equipment, and to reduce the integration and harmonization constraints of the equipment on the carrier aircraft.
  • the first observation device comprises two sensors integrated directly on the fuselage of the aircraft on either side, respectively, of the longitudinal axis of the latter, and each covering approximately 180 ° in bearing and of 20 ° to 40 ° on site. This allows a 360 ° bearing sweep range to be covered.
  • each sensor having a plurality of elementary detectors, may comprise a first scanning optic comprising a scanning prism in bearing, making it possible to obtain a scanning ply in bearing, and a tilting prism of said ply allowing perform the site sweep.
  • each sensor may include a second optic, allowing the exploration of part of the total field, which includes a scanning mirror in bearing, rotating at reduced speed, and a retractable lens.
  • the second axial firing device can be either integrated into the nose of the aircraft, or integrated into the aircraft above the cockpit thereof.
  • the second axial shooting device comprises a thermal camera with two simultaneous fields, namely a large field for the acquisition of the objectives and a small field for the identification and the long-range engagement of a determined target.
  • the first observation device and the second axial firing device work in the 8 to 12 micrometer band (infrared range).
  • the first observation device can also work in the band of 3 to 5 micrometers, and / or in the 0.45 to 0.9 micrometer band, as well as being associated with a radar.
  • the aiming system comprises means for memorizing the targets detected by the first observation device and / or alarms associated with the first observation device, active for the purpose of fire control .
  • sensors working in the infrared or visible range allow the piloting of the aircraft in fire control mode.
  • different color symbologies are used depending on the results of the friend / foe identification procedure.
  • the observation device can have a visualization via a visual helmet visor, and the axial shooting device, a visualization at head-up or a visualization at medium head. Only the shooting symbologies are possibly represented on a clear viewfinder head up.
  • Figure 1 is a schematic perspective view of a helicopter, showing the location of the sighting system according to the invention.
  • FIG. 2 shows, in a simplified and schematic manner, the optical chain of a sensor of the observation device.
  • FIG. 3 represents the two simultaneous images provided by the two-field thermal camera of the axial shooting device.
  • the helicopter 1 represented in FIG. 1 essentially comprises, as is usual, a fuselage 2 extending along the longitudinal axis XX of the helicopter, a cockpit 3, a rotary wing 4, and a fin 5 provided with an anti-torque propeller 6. Furthermore, it has two fins 7 (only one is visible in FIG. 1) intended to receive armaments (missiles, rockets), a cannon which can possibly be housed in the nose 8 of the device.
  • the sighting system comprises the combination of a first individual observation device 9, integrated laterally to the aircraft (in this application example, the helicopter 1), and of a second individual observation device axial shot 10, integrated at the front of the aircraft, the first and second devices 9, 10 being connected to the on-board computer 11 of the aircraft.
  • the observation device 9 comprises two optoelectronic sensors 12a, 12b, integrated directly on the fuselage 2 of the helicopter 1 on either side, respectively, of the latter's longitudinal axis XX, that is that is, each on a side 2a, 2b of the helicopter, and each covering approximately 180 ° in bearing and from 20 ° to 40 ° in elevation, as illustrated by the observation volumes 13a, 13b in FIG. 1.
  • An angular 360 ° observation coverage can thus be obtained.
  • each sensor 12a, 12b has an optical window with three plane windows 14a, 14b.
  • the field covered by the axial firing device 10, which can be either integrated into the nose 8 of the helicopter 1, or integrated into the helicopter 1 above the cockpit 3 of the latter, is designated by the reference numeral 15.
  • FIG. 2 illustrates the optical chain of each of the sensors 12a, 12b.
  • Each of the sensors 12a, 12b comprising a matrix 16 of elementary detectors 17, the conjugate of the matrix of detectors is moved in the object space by a first scanning optic comprising a prism 18 of scanning in bearing, capable of carrying out an excursion by 180 °, and thus obtain a sweeping ply 19 in the field, while a ply tilting prism 20 makes it possible to carry out the sweeping in elevation, the assembly producing a superposition of horizontal plies 19, covering 180 ° in deposit and 20 ° to 40 ° on site.
  • a second lens allows the exploration of part of the total field (approximately 1 ° x 1 ° among 180 ° x 40 °).
  • This second optic comprises a scanning mirror in bearing 21 which, rotating at reduced speed, in an alternating motion, in a limited part of the total field, receives more photons, which makes it possible to obtain better contrast (better resolution).
  • the installation of a retractable lens (magnifying glass) 22 also ensures better definition of the image. In addition to sweeping in a field in a reduced field, one could also provide a sweep in site in this same field, for the same purpose.
  • the most suitable spectral band should be the 8 to 12 micrometer band (infrared range). Its complement by the band of 3 to 5 micrometers can be envisaged.
  • the second function can be performed by a sub-scanning mode of the total field of the first function, thanks to the second optic 21,22 described above.
  • the gain in range compared to the first function is obtained by increasing the integration time of the elementary detectors (which can go as far as stopping the scanning completely) and, possibly, by interposing the lens. focusing 22 specific to this mode.
  • the value of the required field is of the order of the degree.
  • the spectral band of 8 to 12 micrometers offers the operator the advantages and disadvantages of thermal imaging.
  • the usefulness of supplementing it with an image with intensification of light in the visible range (0.45 to 0.9 micrometer) can be envisaged.
  • the advantage of the latter is to offer the operator a visible type image and to be able to continue working in conditions of disappearance of thermal contrasts, encountered during heavy precipitation and strong wind, as well as in conditions of temperature inversion. However, it is then necessary to install a second sensor and a second optical channel, in the absence of transparent materials at 8-12 microns and 0.45-0.9 microns.
  • the first standby function can be supplemented by an active electromagnetic sensor, presenting the advantages specific to radar detection (range, all-weather capacity, Doppler effect detection).
  • this active device is not effective for the detection of land objectives, apart from the ambush helicopters, and presents the disadvantage of lack of discretion inherent in the principle of radar detection.
  • the third function of this observation device 9 can also be the pointing and the implementation of armaments. It requires angular and distance measurements. The angular measurements are obtained by copying the position of the scanning optics. Distance measurements are obtained by stadimetry, triangulation or telemetry.
  • the axial firing device 10 is made up of a certain number of elements, the choice of which depends on the mission and arming configuration of the helicopter. These elements are mounted directly on the structure of helicopter 1. They are harmonized with each other and with the structure by an integrated system or a ground harmonization bench.
  • the axial firing device 10 has all the functions of an air-to-air and air-to-air optoelectronic firing line.
  • the long-distance identification must be able to be carried out without losing most of the large field.
  • This operation requires the presence of a reduced field offering a high magnification (typically 1 °, x10) and orientable in the main field (typically 40 ° x 30 °).
  • the simultaneous acquisition of these two images can be obtained by known means (as described, for example, in the document "Multiple Function Flir - A Second Generation Pilotage and Targeting System”: Symposium AGARD-CP411, "Advances in Guidance and Control Systems and Technology ", October 7-10, 1986, London), using a single detection module using time-sharing each of two optical channels.
  • the image enlarged in small field could be presented, either in overlay in the large field, on the place of the detection, or in screen “head down” ("Head Down Display”).
  • This principle allows a certain multi-target capacity, by rapid sequential processing of the detected objectives.
  • the essential function of this device being the shooting, the band of 8 to 12 micrometers seems the most appropriate.
  • the use of a 0.45-0.9 micrometer sensor could be envisaged to complete it.
  • armaments The implementation of armaments is carried out from the image of large field or the inlay of small field, after telemetry and attachment of the automatic tracking and thanks to the specific guidance equipment of armaments.
  • the first observation device 9 performs part of the functions traditionally assigned to the captain, in his role of conducting the mission and finding targets. It also allows short reflex engagement range of highly deputy targets, for self-protection or opportunity shooting.
  • the acquisition requires the achievement of angular and distance measurements, for the designation of the targets to the missile seeker and to the firing control in the axis.
  • the acquisition phase must be able to be concluded, under certain conditions, by the firing of certain armaments (gun mounted on turret, air-to-air missiles) in short-range engagement, without necessarily having recourse to the rallying phase of the helicopter and the taking over of objectives by fire control in the axis.
  • This short-range engagement involves the identification of short-range targets, possibly using magnification or a friend / foe identification procedure (BFI).
  • BFI friend / foe identification procedure
  • this function will hardly be used since the engagement will be made at sufficiently short distances to allow visual identification.
  • For the firing control of the cannon it is also necessary to develop the aiming command and control of the turret, while an air-to-air missile latching function is also required.
  • the rallying of the helicopter possibly by a specific mode of automatic piloting, can also be requested for the implementation, at short range, of the axial armaments orientable in site (guns, rocket launchers).
  • the second axial firing device 10 constitutes a multi-armaments firing line, available to the pilot and the captain, capable of implementing, thanks to its high performances of precision and range, all the armaments of the helicopter, in their entire range.
  • this principle makes it possible to mount the various elements of the fire control (infrared detectors, camera, rangefinders, weapons guidance equipment, among others) directly on the structure of the helicopter and not, for example, on a gyro-stabilized platform.
  • This architecture gives the system a modular character allowing rapid configuration of the helicopter for a specific mission and a given weaponry, by installing appropriate detectors and guidance equipment, and reducing the constraints of integration and harmonization of equipment on the helicopter.
  • the direct acquisition of targets is possible by the fire control in the axis. It can be performed by the pilot, as is the case with the "Head Up Display” or clear sight, for short-range self-protection shots with air-to-air missile or cannon. However, the handling and engagement of long-range targets (air-to-air and air-to-ground) are carried out, as usual, by the skipper (shooter).
  • the assumption, by the firing line in the axis, of the targets detected by the first observation device 9 requires a target designation function between the observation device 9 and the axial shooting device 10, by via the on-board computer 11.
  • the acquisition is then made in the same way as for a direct detection, after rallying of the helicopter in the direction of the detected target.
  • the performance of the observation device 9 may not always be sufficient for identification. Under these conditions, the rallying of the helicopter and the handling by the axial firing device 10 (firing line in the axis) will remove the ambiguity up to the maximum range of identification of the system as a whole.
  • the telemetry function intervenes just before the implementation of the arming. It can be obtained in several ways: stadimetry, triangulation, telemetry.
  • the fire control function relates to the implementation of armaments. It must be compatible with the greatest possible number of armaments and offer all the possibilities of modes and commands linked to their use (automatic tracking, manual remote control). In particular, he must be possible to integrate the specific guidance equipment of these armaments (distance meters, laser illuminator, alignment laser beam generator). The performance required for the implementation of long-range armaments makes it necessary to have a harmonization function.
  • the functions of the observation device allow it to be controlled and displayed by a visual helmet visor ("head-up" display), which is fast and requires little range and pointing accuracy.
  • the processing of detections in automatic mode could, in this configuration, generate a symbology of the order director type (up / down, right / left, site / deposit) for manual acquisition and observation on such a viewfinder, by rallying of the operator's head or by rallying of the helicopter, for support by the firing line in the axis.
  • the functions of the axial firing device can be fully performed in the 8 to 12 micrometer band by a camera with two simultaneous fields.
  • the display adapted to this function can be considered head up.
  • the use of a clear viewfinder is not possible in the current state of technology, since the intensity of the infrared image delivered by the monitor may not be sufficient to be superimposed, in good conditions, in all cases of light environments encountered.
  • Detection of targets coming from the observation device or the axial shooting device, generates symbologies superimposed on the optoelectronic image of the outside world (markers, results of the friend / enemy identification interrogator, telemetry) allowing the operator to engage them in sequence and in order of priority. For this, he moves a cursor on his "medium head” screen, selects if necessary the opening of the magnification window, inside which the automatic pursuit can be engaged and the firing carried out, by hooking the missile seeker air-to-air or air-to-ground, support for guidance by passive distance meters, directing laser beams or illuminators, implementation of fire control (cannon or rockets).
  • a simplified version of the axis firing device can also be envisaged, which does not present an optoelectronic image in the axis. Only the shooting symbologies are then presented on a clear "head-up" viewfinder. In in this case, the infrared image of the outside world exists, but it is not displayed. It is only used by automatic detection and tracking computers which generate the associated symbologies, directly superimposed on the transmitted image of the outside world. In particular, the embedded zoom function cannot be performed. On the other hand, the image with a small orientable field can be presented and used on a "head down" screen in infrared or visible, depending on the sensors used.
  • the targets detected by the first observation device can be stored, for later analysis, for example in the on-board computer 11 of the aircraft.
  • alarms can be associated with the first observation device, active for fire control, while different color symbologies can be used depending on the results of the friend / enemy identification procedure (IFF) .
  • IFF friend / enemy identification procedure

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Optical Radar Systems And Details Thereof (AREA)
EP94400904A 1993-06-09 1994-04-27 Zielesystem für Luftfahrzeug Expired - Lifetime EP0628780B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9306919A FR2706599B1 (fr) 1993-06-09 1993-06-09 Système de visée pour aéronef.
FR9306919 1993-06-09

Publications (2)

Publication Number Publication Date
EP0628780A1 true EP0628780A1 (de) 1994-12-14
EP0628780B1 EP0628780B1 (de) 1998-01-28

Family

ID=9447926

Family Applications (1)

Application Number Title Priority Date Filing Date
EP94400904A Expired - Lifetime EP0628780B1 (de) 1993-06-09 1994-04-27 Zielesystem für Luftfahrzeug

Country Status (6)

Country Link
US (1) US5483865A (de)
EP (1) EP0628780B1 (de)
JP (1) JP3606601B2 (de)
DE (1) DE69408210T2 (de)
FR (1) FR2706599B1 (de)
IL (1) IL109546A (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19647756C1 (de) * 1996-11-19 1998-06-04 Eurocopter Deutschland Elektrooptisches Verfahren zur statischen Harmonisierung von Waffensystemen und Luftfahrzeugen
GB2307233B (en) * 1995-11-17 1999-04-28 Carbone Ind A method and a furnace for activating a woven or non-woven textile sheet based on continuous carbonized filaments or spun carbonized yarn
DE19829710A1 (de) * 1998-07-03 2000-01-13 Lfk Gmbh Verfahren und Vorrichtung zur Vorbereitung der vollautomatischen Harmonisierung der Sichtlinien von Visier und Suchkopf bei einer auf einem Fluggerät eingerichteten Waffenanlage

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4413916A1 (de) * 1994-04-21 1995-11-02 Bodenseewerk Geraetetech Einrichtung zur passiven Freund/Feind-Unterscheidung
FR2751761B1 (fr) * 1996-07-24 1998-10-23 Sfim Ind Systeme d'observation ou de visee
US6166679A (en) 1999-01-13 2000-12-26 Lemelson Jerome H. Friend or foe detection system and method and expert system military action advisory system and method
FR2800035B1 (fr) * 1999-10-25 2001-12-28 Aerospatiale Matra Missiles Dispositif de suspension pour relier un equipement embarque a la structure d'un vehicule, notamment un aeronef a voilure tournante
DE10151597C1 (de) * 2001-10-18 2003-05-15 Howaldtswerke Deutsche Werft System und Verfahren zur Erkennung und Abwehr von Laserbedrohungen und Unterwasserobjekten für Unterwasserfahrzeuge
TW593978B (en) * 2002-02-25 2004-06-21 Mitsubishi Electric Corp Video picture processing method
DE10229273B4 (de) * 2002-06-28 2007-01-25 Diehl Bgt Defence Gmbh & Co. Kg Objekt-Selbstschutzvorrichtung
US6718862B1 (en) * 2002-10-01 2004-04-13 Paul H. Sanderson Sponson tow plate-mounted helicopter armament apparatus and associated methods
CA2526105C (en) * 2003-06-20 2010-08-10 Mitsubishi Denki Kabushiki Kaisha Image display method and image display apparatus
FR2875613B1 (fr) * 2004-09-23 2007-03-16 Giat Ind Sa Interface homme machine d'un systeme de traitement de menaces
DE112006001864T5 (de) * 2005-07-14 2008-06-05 GM Global Technology Operations, Inc., Detroit System zur Beobachtung der Fahrzeugumgebung aus einer entfernten Perspektive
US7870816B1 (en) 2006-02-15 2011-01-18 Lockheed Martin Corporation Continuous alignment system for fire control
DE102009010362A1 (de) * 2009-02-25 2011-01-13 Rheinmetall Waffe Munition Gmbh Feuerleitung einer richtbaren Waffenanlage
US20110181722A1 (en) * 2010-01-26 2011-07-28 Gnesda William G Target identification method for a weapon system
SE535097C2 (sv) * 2010-03-17 2012-04-17 Bae Systems Haegglunds Ab System och förfarande för att bedöma ett potentiellt mål
US8408115B2 (en) 2010-09-20 2013-04-02 Raytheon Bbn Technologies Corp. Systems and methods for an indicator for a weapon sight
US8759735B2 (en) * 2011-05-19 2014-06-24 Raytheon Company Multi-function airborne sensor system
US10782097B2 (en) 2012-04-11 2020-09-22 Christopher J. Hall Automated fire control device
US8434397B1 (en) 2012-06-08 2013-05-07 The United States Of America As Represented By The Secretary Of The Navy Helicopter weapon mounting system
CN111694374B (zh) * 2016-03-01 2024-02-20 深圳市大疆创新科技有限公司 飞行控制方法、装置、控制终端、飞行系统及处理器
US10627503B2 (en) * 2017-03-30 2020-04-21 Honeywell International Inc. Combined degraded visual environment vision system with wide field of regard hazardous fire detection system
US10800526B2 (en) * 2017-05-10 2020-10-13 Textron Innovations Inc. Aircraft adapter
KR101877214B1 (ko) * 2017-10-31 2018-07-12 엘아이지넥스원 주식회사 비행체 탑재용 탐색 장치
KR102483646B1 (ko) * 2017-12-22 2023-01-02 삼성전자주식회사 객체 검출 장치 및 방법
RU2712707C1 (ru) * 2019-08-13 2020-01-30 Илья Сергеевич Пастухов Способ управления темпом стрельбы авиационных автоматических пушек с электрозапальным стреляющим механизмом
FR3134470A1 (fr) * 2022-04-06 2023-10-13 Safran Electronics & Defense Système de surveillance infrarouge pour aéronef militaire et aéronef militire, notamment un missile, équipé d'un tel système

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3641261A (en) * 1969-06-04 1972-02-08 Hughes Aircraft Co Night vision system
US4202246A (en) * 1973-10-05 1980-05-13 General Dynamics Pomona Division Multiple co-axial optical sight and closed loop gun control system
EP0031781A1 (de) * 1979-12-26 1981-07-08 Societe D'applications Generales D'electricite Et De Mecanique S A G E M Vorrichtungen mit stabilisierter Visierlinie für Fahrzeuge
FR2525761A1 (fr) * 1982-04-23 1983-10-28 Sagem Dispositif de visee stabilisee multivoies
EP0127914A1 (de) * 1983-05-11 1984-12-12 Telecommunications Radioelectriques Et Telephoniques T.R.T. Bilddrehungsfreies Panoramasichtgerät mit mehreren Gesichtsfeldern
EP0167432A1 (de) * 1984-06-06 1986-01-08 Thomson-Csf Luftfahrzeuggerät für optoelektrische Entdeckung, Ortung und allseitige Vervolgung eines Zieles
DE3630701A1 (de) * 1985-09-09 1987-03-19 Israel Aircraft Ind Ltd Optisches visiergeraet fuer helikopter
EP0424238A1 (de) * 1989-10-20 1991-04-24 Thomson-Csf Zieleinrichtung

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2420334A (en) * 1943-01-25 1947-05-13 Sperry Gyroscope Co Inc Automatic tracking system
US5223839A (en) * 1966-06-23 1993-06-29 The United States Of America As Represented By The Secretary Of The Army Radar identification
US3457827A (en) * 1968-05-03 1969-07-29 Howell M Sumrall Turret gun directing system (aideye)
US3711638A (en) * 1971-02-02 1973-01-16 J Davies Remote monitoring and weapon control system
US3924232A (en) * 1974-08-26 1975-12-02 Itek Corp Optical warning system
US4779095A (en) * 1986-10-28 1988-10-18 H & G Systems, Inc. Image change detection system
US5359920A (en) * 1992-12-15 1994-11-01 Hughes Aircraft Company Munition impact point indicator and automatic gun aimpoint correction system

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3641261A (en) * 1969-06-04 1972-02-08 Hughes Aircraft Co Night vision system
US4202246A (en) * 1973-10-05 1980-05-13 General Dynamics Pomona Division Multiple co-axial optical sight and closed loop gun control system
EP0031781A1 (de) * 1979-12-26 1981-07-08 Societe D'applications Generales D'electricite Et De Mecanique S A G E M Vorrichtungen mit stabilisierter Visierlinie für Fahrzeuge
FR2525761A1 (fr) * 1982-04-23 1983-10-28 Sagem Dispositif de visee stabilisee multivoies
EP0127914A1 (de) * 1983-05-11 1984-12-12 Telecommunications Radioelectriques Et Telephoniques T.R.T. Bilddrehungsfreies Panoramasichtgerät mit mehreren Gesichtsfeldern
EP0167432A1 (de) * 1984-06-06 1986-01-08 Thomson-Csf Luftfahrzeuggerät für optoelektrische Entdeckung, Ortung und allseitige Vervolgung eines Zieles
DE3630701A1 (de) * 1985-09-09 1987-03-19 Israel Aircraft Ind Ltd Optisches visiergeraet fuer helikopter
EP0424238A1 (de) * 1989-10-20 1991-04-24 Thomson-Csf Zieleinrichtung

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2307233B (en) * 1995-11-17 1999-04-28 Carbone Ind A method and a furnace for activating a woven or non-woven textile sheet based on continuous carbonized filaments or spun carbonized yarn
DE19647756C1 (de) * 1996-11-19 1998-06-04 Eurocopter Deutschland Elektrooptisches Verfahren zur statischen Harmonisierung von Waffensystemen und Luftfahrzeugen
US6040854A (en) * 1996-11-19 2000-03-21 Eurocopter Deutschland Gmbh Electro-optical process for the static harmonization of weapon systems and aircraft
DE19829710A1 (de) * 1998-07-03 2000-01-13 Lfk Gmbh Verfahren und Vorrichtung zur Vorbereitung der vollautomatischen Harmonisierung der Sichtlinien von Visier und Suchkopf bei einer auf einem Fluggerät eingerichteten Waffenanlage

Also Published As

Publication number Publication date
DE69408210D1 (de) 1998-03-05
JP3606601B2 (ja) 2005-01-05
FR2706599A1 (fr) 1994-12-23
IL109546A (en) 1997-09-30
DE69408210T2 (de) 1998-05-28
JPH0710091A (ja) 1995-01-13
FR2706599B1 (fr) 1995-08-18
US5483865A (en) 1996-01-16
EP0628780B1 (de) 1998-01-28

Similar Documents

Publication Publication Date Title
EP0628780B1 (de) Zielesystem für Luftfahrzeug
EP0432014B1 (de) Optoelektronisches Hilfssystem für die Flugnavigation und Luftangriffsaufträge
US5001348A (en) Method and apparatus for recognizing the start and motion of objects
US6741341B2 (en) Reentry vehicle interceptor with IR and variable FOV laser radar
EP0441079B1 (de) Teilbares und rekonfigurierbares Episkophauptzielfernrohr
US7336345B2 (en) LADAR system with SAL follower
EP0033679B1 (de) System zur Andeutung eines Objektes mittels eines Lasers
US7742151B2 (en) Laser-based system with LADAR and SAL capabilities
US20090260511A1 (en) Target acquisition and tracking system
EP0167432B1 (de) Luftfahrzeuggerät für optoelektrische Entdeckung, Ortung und allseitige Vervolgung eines Zieles
FR2639127A1 (fr) Appareil de traitement electronique d'images pour determiner la distance ou la taille d'un objet
GB2272963A (en) Boresighting
US6484619B1 (en) Observation or sighting system
EP2711733A2 (de) Luftraumüberwachungssystem zur Erfassung von innerhalb eines zu überwachenden Gebiets startenden Raketen sowie Verfahren zur Luftraumüberwachung
EP3155358B1 (de) System zum lenken von raketen für fahrzeuge und bewegliche ziele
RU2573709C2 (ru) Активная лазерная головка самонаведения
FR2788845A1 (fr) Conduite de tir pour projectiles non guides
EP1866597B1 (de) System zur zielbestimmung und/oder -beleuchtung und für die luftaufklärung
EP0090713B1 (de) Feuerleitsystem mit einem durch ein automatisches Verfolgungsgerät gesteuerten Fernrohr
EP0089273B1 (de) Feuerkontrollsystem mit doppelter Bestimmung der Winkelabweichungen
FR2525761A1 (fr) Dispositif de visee stabilisee multivoies
Thomson Advances in electro-optic systems for targeting
FR3005359A1 (fr) Procede et dispositif de protection des aeronefs basse altitude vis-a-vis des missiles sol/air
Sillitto Military optoelectronics
FR2741721A1 (fr) Systeme optronique aeroporte pour la recherche, l'acquisition, la poursuite et l'identification de cibles, utilisable notamment pour la conduite de tir

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

Kind code of ref document: A1

Designated state(s): DE GB IT

17P Request for examination filed

Effective date: 19941229

17Q First examination report despatched

Effective date: 19961016

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: EUROCOPTER

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE GB IT

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19980129

REF Corresponds to:

Ref document number: 69408210

Country of ref document: DE

Date of ref document: 19980305

ITF It: translation for a ep patent filed

Owner name: MODIANO & ASSOCIATI S.R.L.

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

26N No opposition filed
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20040329

Year of fee payment: 11

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20051101

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20070328

Year of fee payment: 14

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20080427

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20080427

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20090401

Year of fee payment: 16

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20100427