EP1432958A1 - Flugkörperlenkungsverfahren - Google Patents

Flugkörperlenkungsverfahren

Info

Publication number
EP1432958A1
EP1432958A1 EP02783193A EP02783193A EP1432958A1 EP 1432958 A1 EP1432958 A1 EP 1432958A1 EP 02783193 A EP02783193 A EP 02783193A EP 02783193 A EP02783193 A EP 02783193A EP 1432958 A1 EP1432958 A1 EP 1432958A1
Authority
EP
European Patent Office
Prior art keywords
rocket
images
imaging device
target
camera
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
EP02783193A
Other languages
English (en)
French (fr)
Other versions
EP1432958B1 (de
Inventor
Michel Broekaert
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.)
Safran Electronics and Defense SAS
Original Assignee
Sagem 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 Sagem SA filed Critical Sagem SA
Publication of EP1432958A1 publication Critical patent/EP1432958A1/de
Application granted granted Critical
Publication of EP1432958B1 publication Critical patent/EP1432958B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22Homing guidance systems
    • F41G7/2273Homing guidance systems characterised by the type of waves
    • F41G7/2293Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/007Preparatory measures taken before the launching of the guided missiles
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22Homing guidance systems
    • F41G7/2206Homing guidance systems using a remote control station
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22Homing guidance systems
    • F41G7/2253Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target

Definitions

  • the invention relates to rocket guidance.
  • a rocket is a small rocket, without guidance. It is often used in the fight against tanks and it can be launched from a land, sea or air vehicle, for example from an airplane or a helicopter.
  • the invention applies equally well to missiles and when we speak in the text of rockets, it will be necessary to take the term in its general sense and to consider that we also cover missiles.
  • an operator Before launching a rocket, an operator first acquires the target in its sight, it identifies it, it follows it, to know its angular speed, then it ranges it, to know its distance and finally to know the position of the target in its benchmark. With this data and a flight model of the device, the fire calculator develops a future goal materialized by a reticle in the viewfinder.
  • the present application aims to perfect the precision of rockets and, for this purpose, it relates to a method for guiding a rocket on a target in which, the rocket being equipped with self-guiding means with imaging device and trajectory correction means,
  • the target is acquired by an aiming device and its position is determined
  • the rocket is guided according to this law until it acquires the target itself.
  • the harmonization of the two aiming and imaging devices, of the launcher and of the rocket can be carried out in a completely simple manner, first by harmonizing the aiming and taking axes, respectively, then, by calculating the image of the launcher sight in the reference frame of the rocket imaging device.
  • the stabilization of the images of the rocket imaging device makes it possible at least to overcome the disadvantages of the launcher before launching and therefore to stabilize these images in the absolute landscape of the target.
  • an initial guidance law is developed and the rocket is guided until it acquires the target according to this initial law.
  • an initial guidance law is developed and, after launch, a continuously variable guidance and trajectory correction law is developed until the rocket acquires the target.
  • electronic harmonization is carried out according to which, in a terrestrial frame of reference, the images of the scene taken at the same times by the two devices are filtered in a low-pass filter, i:> to retain only the low spatial frequencies, and the equation of the optical flow between these pairs of respective images of the two devices is solved to determine the rotations and the variation of the ratio of the parameters respective zoom to subject these images to harmonize them on each other.
  • the images of the rocket imaging device are stabilized in a terrestrial frame of reference, on the landscape, even if stabilization by inertial unit is still possible.
  • FIG. 1 is a schematic axial sectional view of a rocket equipped with self-guiding means with imaging device and path correction means;
  • FIG. 2 is a block representation of the electrical, electronic and optical functional means of the rocket of Figure 1;
  • - Figure 3 illustrates the geometry of the movement of a camera
  • - Figure 4 is a block diagram of the rocket imaging device allowing the implementation of electronic stabilization of its images and harmonization with the aiming device;
  • - Figure 5 is a representation of the image of the rocket imaging device showing the various fields of view and - Figure 6 is a schematic view illustrating the method of guiding a rocket on a target from a helicopter.
  • the rocket comprises a body 1, of which only the front part has been shown, the rear part comprising the payload and the trajectory correction members, which may be control surfaces or small directional rockets, and a nose 2, covered of a cap 3.
  • the cap 3 carries a first lens which acts as an aerodynamic window and which focuses the image on the detector using the rest of the optics which are discussed below.
  • the cap 3 carries a first lens which acts as an aerodynamic window and which focuses the image on the detector using the rest of the optics which are discussed below.
  • the rocket is a self-directing spinnated rocket, partly in the nose, partly in the body, as will be seen below, but the nose 2 and the body 1 of which are decoupled in rotation, the nose 2 carrying, by means of a hollow shaft 4, a flywheel 5 disposed in the body 1 creating a differential spin between the nose 2 and the body 1, so that the nose 2 is only rotated very slowly if not at all.
  • the hollow shaft 4 therefore extends on either side of the joint plane 6 between the nose 2 and the body 1, in rolling bearings 7 and 8 respectively in one 2 and the other part 1 rocket.
  • the self-steering of the rocket comprises, in the nose 2, behind the cap 3 and a fixed optical system 9, an imaging device 10 and in the body 1, u 'n equipment 11 Trajectory correction controlled by the device 10.
  • the equipment 11 also ensures, after launch, the comparison of the image taken by the imaging device 10 with the stored large and small field images of the scene taken, before launch, with the wearer's aiming device, it will be discussed below.
  • the imaging device 10 comprises a camera 13, with its conventional proximity electronic circuits 14, an analog-digital converter 15 and an image transmission component 16.
  • the device 10 is supplied from the body of the rocket and through the hollow shaft 4, by a rechargeable battery 12.
  • the camera 13 can be a camera or video or infrared device.
  • the transmission component 16 can be a laser diode or an LED (light-emitting diode). This component 16 can be placed in the imaging device 10 and then, the transmission of images through the hollow shaft 4 and the flywheel 5 is effected by optical fiber 17 extending along the roll axis 30 of the machine.
  • the image transmission component 22 can be placed in the inertia flap 5, opposite a diode 24 receiving the transmitted images and then the signal transmission between the imaging device 10 and the component 22 s' made by wires through the hollow shaft 4.
  • the imaging device is cooled by Peltier effect, if necessary.
  • the flywheel 5 symbolized in FIG. 2 by the two vertical dashed lines, carries the secondary 19 of a transformer 18 for coupling the power supply to the nose 2 of the rocket connected to the battery 12, a wheel 20 of an optical encoder 21 and a laser diode 22, or an LED, as the case may be, for transmitting in the body 1 of the rocket images of the device 10.
  • the trajectory correction equipment 11 of the rocket body comprises the transceiver 23 of the optical encoder 21, the diode 24 receiving the transmitted images, the primary 25 of the transformer 18, with its source 26, and circuits 27 for processing the received images and for guiding and controlling the control surfaces 28 of the rocket, connected to the receiving diode 24 and to the transceiver 23 of the encoder 21.
  • the circuits 27 include a computer of edge.
  • the encoder 21 indicates the relative angular position between the imaging device 10 and the body 1 of the rocket.
  • the rocket is guided using the computer of circuits 27, as a function of this angular position and of the comparison between the images received from the imaging device and stabilized in circuits 27 and the stored images previously supplied by example by a viewfinder.
  • the guidance commands are applied in synchronism with the rocket's own rotation, also taking into account the location of the control surface.
  • the operator Before launching the rocket, the operator, using a sighting device, takes a wide field image 52 of the scene, which is memorized, and which will serve, in the case of low spatial frequencies, to be determined the approximate direction of the target ( Figure 5). It also takes a small field image 53 which is also stored.
  • the overall view is a view 50 of the navigation field, with, inside, a view 51 of the rocket's auto-director, then a view 52 of the wide field, then again more inside, a view 53 small field.
  • FIG. 6 shows a sighting device 62 and a firing computer 63 of the helicopter as well as the angle of field ⁇ of the seeker of the rocket from right, corresponding to view 51, and the angle of small field v of the sighting device 62 of the helicopter, corresponding to view 53, angles in which the tank 61 is located.
  • the fire control operator shooter of the helicopter 60
  • the fire control operator begins by acquiring the target 61 using his aiming device 62, that is to say that it proceeds to the determination of the position, the distance and the speed of the target 61 which will enable it subsequently, in combination with a flight model and with the aid of the fire calculator 63, to develop a law of guidance, or command, initial.
  • the pilot of the helicopter brings back at best the axis of the helicopter in the direction aimed by the shooter thanks to a repeater.
  • the on-board computer After acquisition of the target 61 and its designation by the operator, the on-board computer, proceeds to the harmonization of the aiming device 62 and of the imaging device 10 of the rocket then to the stabilization of the images of the device rocket imagery, before developing the optimal rocket guidance law.
  • the camera is in a three-dimensional Cartesian or Polar coordinate system with the origin placed on the front lens of the camera and the z axis directed along the viewing direction.
  • the position of the camera relative to the wearer's center of gravity is defined by three rotations (ab, vc, gc) and three translations (Txc, Tyc, Tzc).
  • the relationship between the 3D coordinates of the camera and those of the wearer is:
  • R is a 3 x 3 rotation matrix
  • T is a 1 x 3 translation matrix
  • x (t) F (t) .x (t) + u (t) + v (t)
  • H (t) is a matrix m x n function of t and w is a white Gaussian noise of dimension m, which one can assimilate to the angular and linear vibrations of the camera compared to the center of gravity of the carrier.
  • x k [k aP, aV k, bP k, k bV, gP k, gV k, k xP, xV k, k yP, yV k, zP k, k zV] ⁇ is the state vector at the instant k of the trajectory, composed of the angles and speeds yaw, pitch, roll and positions and speeds in x, y and z.
  • u k is the known input vector function of k; it is the flight or trajectory model of the wearer's center of gravity.
  • v k is the n-dimensional white Gaussian noise representing the acceleration noises in yaw, pitch, roll, positions x, y, z.
  • angles and translations to which the camera is subjected relative to the center of gravity are not constant during the trajectory, in a viewfinder for example, it suffices to describe their measured or controlled values (ac (t), bc (t ), gc (t), Txc (t), Tyc (t), Tzc (t) as a function of t or k.
  • the trajectory of the camera can be defined by a vector
  • the camera undergoes pure 3D rotations and three translations, the values of which are provided by the vector x ' k + ⁇ .
  • Figure 3 shows the geometry of the camera movement in 3D space in the real world.
  • the camera is in a three-dimensional Cartesian or Polar coordinate system with the origin placed on the front lens of the camera and the z axis directed along the viewing direction.
  • F1 (X, Y) is the focal length of the camera at time t.
  • aw, bw, gw, xw, yw, zw are the angular vibrations.
  • imagek + 1 (Ai, Aj) imagek (Ai, Aj) + Gradie ⁇ tX (Ai, Aj) .dAi .pasH + GradientY (Ai, Aj). dAj .pasH with Gradie ⁇ tX and Gradie ⁇ tY the derivatives according to X and Y of ima ⁇ ek (X.Y).
  • Low-pass filtering consists, in a conventional manner, of dragging a convolution kernel from pixel to pixel of the digital images of the camera, a kernel on which the origin of the kernel is replaced by the average of the gray levels of the pixels of the kernel .
  • the results obtained with a rectangular core of 7 pixels high (v) and 20 pixels wide (H) are very satisfactory on normally contrasted scenes.
  • v pixels high
  • H pixels wide
  • Wavelet functions can also be used as the averaging kernel.
  • the optical flow equation measures the total displacement of the camera. We saw above that we could distinguish more finely the movements of the camera deduced from those of the wearer and the real movements of the camera by saying that the wearer and the camera have the same trajectory, but that the camera undergoes in addition to the linear and angular vibrations.
  • the displacements due to the trajectory of the camera are contained in the state vector x ' k + ⁇ of the camera, or rather in the estimation that one can make it, by averaging it, or by having a Kalman filter which provides the best estimate.
  • the fourth axis (zoom) is not necessarily necessary but it may prove to be essential in the event of optical zoom but also in the case where the focal length is not known with sufficient precision or when the focal length varies with the temperature ( IR, Germanium optics, etc.) or pressure (air index).
  • image k + 1 (X, Y) image (X - dX k + ⁇ (X, Y), Y - dY k + 1 (X, Y))
  • a (,:, 2) DeriveeX (Ai, Aj). (1 + (Ai.pasH / F1 (X, Y)) ⁇ 2)
  • a (,:, 3) DeriveeY (Ai, Aj) .Ai. pasH / pasV - DeriveeX (Ai, Aj). .Aj .notV / pasH
  • a (:,:, 4) DeriveeX (Ai, Aj). Ai + Derivative Y (Ai, Aj). aj
  • the shooting camera 13 delivers its video signal from images to a filter
  • the filter 10 low-pass 42 as well as to a processing block 43 receiving on a second input the stabilization data and supplying as output the stabilized images. On its second input, the block 43 therefore receives the rotational speeds to be subjected to the images taken by the camera 13.
  • the two buffer memories 44, 45 are connected to two inputs of a computation component 46, which is either an ASIC or an FPGA (field programmable gate array).
  • the calculation component 46 is connected to a working memory 47 and, at the output, to the processing block 43. All the electronic components of the
  • the harmonization implemented in the guiding method of the invention is an extrapolation of the stabilization step, the sighting device and the rocket imaging device being, before launch, mounted on the same carrier.
  • the stabilization of the images of the rocket imaging device is a self-stabilization process, in which the image of time t is stabilized on the image of time t-1.
  • we harmonize each image of the imaging system on the previous one we can say that we harmonize each image of the imaging system on the previous one.
  • the two images of the two devices are taken and they are stabilized one on the other, that is to say that the two devices are harmonized.
  • Harmonizing is tantamount to confusing the optical axes of the two devices as well as matching the pixels of the two images two by two, and preferably also confusing these pixels.
  • the two devices to be harmonized according to this process must be of the same optical nature, that is to say operate in comparable wavelengths.
  • the two devices both taking images of the same scene, in a terrestrial frame of reference, the images of the scene taken at the same times by the two devices are filtered in a low-pass filter, for n ' retain only the low spatial frequencies, and the equation of the optical flow between these pairs of respective images of the two devices is solved, to determine the rotations and the variation of the ratio of the respective zoom parameters to be subjected to these images for the harmonize on each other.
  • the initial guidance law is developed by means of the position, distance and speed of the target, on the one hand, and a flight model on the other.
  • the operator of the firing control proceeds to launch it. Up to a certain distance from the target 61, until the rocket acquires the target, the image taken by the imaging device 10 of the rocket is compared with the stored wide field image 52 of the scene taken at the start with the aiming device 62, that is to say that the rocket guidance is permanently controlled.
  • the guidance of the rocket is continued until the terminal phase, by comparison of the image taken by the imaging device 10 of the rocket with the small field image 53 also stored.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Studio Devices (AREA)
  • Length Measuring Devices By Optical Means (AREA)
  • Telescopes (AREA)
EP02783193A 2001-09-25 2002-09-23 Lenkungsverfahren für flugkörperwaffensystem Expired - Lifetime EP1432958B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0112330A FR2830078B1 (fr) 2001-09-25 2001-09-25 Procede de guidage d'une roquette
FR0112330 2001-09-25
PCT/FR2002/003240 WO2003027599A1 (fr) 2001-09-25 2002-09-23 Procede de guidage d'une roquette

Publications (2)

Publication Number Publication Date
EP1432958A1 true EP1432958A1 (de) 2004-06-30
EP1432958B1 EP1432958B1 (de) 2006-08-30

Family

ID=8867590

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02783193A Expired - Lifetime EP1432958B1 (de) 2001-09-25 2002-09-23 Lenkungsverfahren für flugkörperwaffensystem

Country Status (5)

Country Link
US (1) US7083139B2 (de)
EP (1) EP1432958B1 (de)
DE (1) DE60214407T2 (de)
FR (1) FR2830078B1 (de)
WO (1) WO2003027599A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107966156A (zh) * 2017-11-24 2018-04-27 北京宇航系统工程研究所 一种适用于运载火箭垂直回收段的制导律设计方法

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7643893B2 (en) 2006-07-24 2010-01-05 The Boeing Company Closed-loop feedback control using motion capture systems
US7813888B2 (en) * 2006-07-24 2010-10-12 The Boeing Company Autonomous vehicle rapid development testbed systems and methods
US7885732B2 (en) 2006-10-25 2011-02-08 The Boeing Company Systems and methods for haptics-enabled teleoperation of vehicles and other devices
DE102007054950B4 (de) * 2007-11-17 2013-05-02 Mbda Deutschland Gmbh Verfahren zur Stützung der selbsttätigen Navigation eines niedrig fliegenden Flugkörpers
US8686326B1 (en) * 2008-03-26 2014-04-01 Arete Associates Optical-flow techniques for improved terminal homing and control
US8068983B2 (en) 2008-06-11 2011-11-29 The Boeing Company Virtual environment systems and methods
US20120181376A1 (en) * 2009-01-16 2012-07-19 Flood Jr William M Munition and guidance navigation and control unit
IL214191A (en) 2011-07-19 2017-06-29 Elkayam Ami Ammunition guidance system and method for assembly
IL227982B (en) * 2013-08-15 2018-11-29 Rafael Advanced Defense Systems Ltd A missile system with navigation capability based on image processing
US9464876B2 (en) * 2014-05-30 2016-10-11 General Dynamics Ordnance and Tacital Systems, Inc. Trajectory modification of a spinning projectile by controlling the roll orientation of a decoupled portion of the projectile that has actuated aerodynamic surfaces
DE102015000873A1 (de) * 2015-01-23 2016-07-28 Diehl Bgt Defence Gmbh & Co. Kg Suchkopf für einen Lenkflugkörper
RU2722903C1 (ru) * 2019-10-23 2020-06-04 Акционерное общество "Научно-производственное предприятие "Дельта" Способ идентификации цели с помощью радиовзрывателя ракеты с головкой самонаведения
RU2722904C1 (ru) * 2019-10-23 2020-06-04 Акционерное общество "Научно-производственное предприятие "Дельта" Способ обнаружения цели с помощью радиовзрывателя ракеты

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3459392A (en) * 1959-09-24 1969-08-05 Goodyear Aerospace Corp Passive homing guidance system
US3712563A (en) * 1963-12-04 1973-01-23 Us Navy Automatic path follower guidance system
US3794272A (en) * 1967-02-13 1974-02-26 Us Navy Electro-optical guidance system
US3986682A (en) * 1974-09-17 1976-10-19 The United States Of America As Represented By The Secretary Of The Navy Ibis guidance and control system
DE3334729A1 (de) * 1983-09-26 1985-04-11 Siemens AG, 1000 Berlin und 8000 München Verfahren zur ausrichtung eines zielsuchkopfes eines selbstgesteuerten flugkoerpers
US4881270A (en) * 1983-10-28 1989-11-14 The United States Of America As Represented By The Secretary Of The Navy Automatic classification of images
US6491253B1 (en) * 1985-04-15 2002-12-10 The United States Of America As Represented By The Secretary Of The Army Missile system and method for performing automatic fire control
GB8925196D0 (en) * 1989-11-08 1990-05-30 Smiths Industries Plc Navigation systems
US5785281A (en) * 1994-11-01 1998-07-28 Honeywell Inc. Learning autopilot
DE19546017C1 (de) * 1995-12-09 1997-04-24 Daimler Benz Aerospace Ag Flugkörper-Waffensystem
US5881969A (en) * 1996-12-17 1999-03-16 Raytheon Ti Systems, Inc. Lock-on-after launch missile guidance system using three dimensional scene reconstruction
US6347762B1 (en) * 2001-05-07 2002-02-19 The United States Of America As Represented By The Secretary Of The Army Multispectral-hyperspectral sensing system

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO03027599A1 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107966156A (zh) * 2017-11-24 2018-04-27 北京宇航系统工程研究所 一种适用于运载火箭垂直回收段的制导律设计方法
CN107966156B (zh) * 2017-11-24 2020-09-18 北京宇航系统工程研究所 一种适用于运载火箭垂直回收段的制导律设计方法

Also Published As

Publication number Publication date
FR2830078A1 (fr) 2003-03-28
FR2830078B1 (fr) 2004-01-30
WO2003027599A1 (fr) 2003-04-03
DE60214407T2 (de) 2007-05-10
US7083139B2 (en) 2006-08-01
EP1432958B1 (de) 2006-08-30
US20040245370A1 (en) 2004-12-09
DE60214407D1 (de) 2006-10-12

Similar Documents

Publication Publication Date Title
EP1432958B1 (de) Lenkungsverfahren für flugkörperwaffensystem
EP0432014B1 (de) Optoelektronisches Hilfssystem für die Flugnavigation und Luftangriffsaufträge
EP3273318B1 (de) Autonomes aufnahmesystem von animierten bildern durch eine drohne mit zielverfolgung und verbesserter lokalisierung des ziels
EP1298592B1 (de) Stabilisierung von Bildern einer Szene, Korrigierung der Grauwertverschiebung, Erfassung bewegender Objekte und auf Bildstabilisierung basierter Abgleich von zwei Bildaufnahmevorrichtungen
EP2048475B1 (de) Verfahren zur Bestimmung der Lage, Position und Geschwindigkeit eines beweglichen Geräts
EP3268691B1 (de) Luftgestützte vorrichtung zur detektion von schüssen und zur nachweis und zur steuerungsassistenz
EP1623567A1 (de) Verfahren zum übertragen von die räumliche position einer videokamera repräsentierenden daten und das verfahren implementierendes system
EP0484202A1 (de) Anordnung für die Ausrichtung des Inertialsystems eines getragenen Fahrzeugs auf das eines Trägerfahrzeuges
JP6529411B2 (ja) 移動体識別装置及び移動体識別方法
WO2005066024A1 (fr) Systeme optronique modulaire embarquable sur un porteur
Pajusalu et al. Characterization of asteroids using nanospacecraft flybys and simultaneous localization and mapping
EP1676444B1 (de) Verfahren und einrichtung zur erfassung eines weitwinkelbildes und einer interessierenden region davon
FR2788845A1 (fr) Conduite de tir pour projectiles non guides
EP0985900A1 (de) Verfahren und Vorrichtung zum Lenken eines Flugkörpers, insbesondere einer Kampfrakete, auf ein Ziel
EP3929692B1 (de) Sucher mit codierter blende für die navigation
EP0013195B1 (de) Luft-Boden-Entfernungsradar für ein Bordfeuerleitsystem und Verwendung eines solchen Radars bei einem Feuerleitsystem
FR2828314A1 (fr) Procede de stabilisation electronique des images d'une scene d'un appareil de prise de vues d'un systeme d'imagerie et procede d'harmonisation electronique de deux appareils de prise de vues de deux systemes d'imagerie
JP7394724B2 (ja) 宇宙状況監視事業装置、宇宙状況監視システム、監視装置、および、地上設備
EP0176121B1 (de) Verfahren zur Detektion und Beseitigung der von einer pyramidenförmigen Infrarotkuppel erzeugten Störbilder
EP1785688B1 (de) Verfahren und Vorrichtung um die Rotationsgeschwindigkeit der Geschoßziellinie zu bestimmen und Lenkvorrichtung eines Geschoßes, insbesondere von Munition
WO2020144418A1 (fr) Titre de l'invention : fusil permettant une simulation précise d'une séquence de tir avec calcul du point d'impact du ou des projectiles
FR3082012A1 (fr) Dispositif electronique, et procede, de commande d'un drone, programme d'ordinateur associe
FR2731785A1 (fr) Tete chercheuse notamment pour missile
EP0285463A1 (de) Vorrichtung zur Führung eines aerodynamischen Luftfahrzeuges mit Hilfe eines Merkmales der äusseren Umgebung, das der Pilot bestimmt
FR2735584A1 (fr) Systeme aeroporte d'acquisition automatique d'objectif, notamment pour autodirecteur a imagerie

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

17P Request for examination filed

Effective date: 20040416

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SK TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

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 SE

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: SAGEM DEFENSE SECURITE

REF Corresponds to:

Ref document number: 60214407

Country of ref document: DE

Date of ref document: 20061012

Kind code of ref document: P

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

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

Effective date: 20061220

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

Effective date: 20070531

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

Ref country code: SE

Payment date: 20120824

Year of fee payment: 11

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

Ref country code: IT

Payment date: 20120829

Year of fee payment: 11

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

Ref country code: DE

Payment date: 20130820

Year of fee payment: 12

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

Ref country code: GB

Payment date: 20130823

Year of fee payment: 12

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

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

Ref country code: SE

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

Effective date: 20130924

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: 20130923

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 60214407

Country of ref document: DE

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

Effective date: 20140923

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 60214407

Country of ref document: DE

Effective date: 20150401

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: 20150401

Ref country code: GB

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

Effective date: 20140923