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EP3048410A1 - Tete chercheuse pour un missile guide - Google Patents

Tete chercheuse pour un missile guide Download PDF

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Publication number
EP3048410A1
EP3048410A1 EP16000016.2A EP16000016A EP3048410A1 EP 3048410 A1 EP3048410 A1 EP 3048410A1 EP 16000016 A EP16000016 A EP 16000016A EP 3048410 A1 EP3048410 A1 EP 3048410A1
Authority
EP
European Patent Office
Prior art keywords
roll
rolling
frame
detector
sensor
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
EP16000016.2A
Other languages
German (de)
English (en)
Other versions
EP3048410B1 (fr
Inventor
Joachim Barenz
Nicolai Künzner
Hakan KISAKÜREK
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.)
Diehl Defence GmbH and Co KG
Original Assignee
Diehl BGT Defence GmbH and Co KG
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 Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Publication of EP3048410A1 publication Critical patent/EP3048410A1/fr
Application granted granted Critical
Publication of EP3048410B1 publication Critical patent/EP3048410B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2213—Homing guidance systems maintaining the axis of an orientable seeking head pointed at the target, e.g. target seeking gyro
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2253—Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves

Definitions

  • the invention relates to a seeker head for a missile with an outer housing, a detector unit with a matrix detector, an optical system for imaging an object from an object scene surrounding the missile to the detector comprising an input optic and an optical hinge and a roll pitch system for Aligning at least the entrance optics on the object with a rolling frame and a pitch frame.
  • Target seeking guided missiles are equipped with a seeker head with input optics that can track the movement of a moving target.
  • an input optics is movably mounted to a dome of the missile or its outer casing and driven by a motor so that it is pivotable in a large angular range.
  • Such a viewfinder optics is from the DE 10 2010 055 493 A1 known.
  • a very accurate image with small aberrations on an imaging unit is advantageous in order to reliably detect the target as such, even at a great distance.
  • the detector unit is arranged roll-stable on the rolling frame.
  • the invention is based on the consideration that it requires the optical detection of very distant and small targets of a very sensitive seeker.
  • the sensitivity of a seeker depends especially on the exposure time of the detector system, so for example the integration time of a matrix detector.
  • the maximum possible exposure time for a sharp imaging of the object on the matrix detector in turn depends on the scene dynamics during the integration time, ie on the movement of the image of the object over the detector surface.
  • the search head which is structurally connected to the guided missile, rolls along with it and also a matrix-fixedly arranged matrix detector.
  • the input optics of the seeker head oriented thereon must be unrolled, ie rotated at the same roll rate counter to the direction of roll of the seeker head so that it remains stationary in space. There is thus a relative rotation between input optics and a structure-fixed matrix detector. Accordingly, the object imaged by the optics also rotates on the sensitive surface of the matrix detector.
  • the object scene smeared by this rotation, in particular on the edge of the sensitive area of the matrix detector, so that details such as point targets can no longer be clearly recognized there. This reduces the sensitivity of the seeker and thus its optical range.
  • image enhancement algorithms can reduce image blurring in the edge area of the sensitive area of the matrix detector, it is not complete enough to obtain high sensitivity of the seeker during fast reel.
  • the invention proposes the separation of matrix detector and outer housing according to the invention.
  • the matrix detector is rotated with the input optics, so that the object imaged by it is dot-stable on the matrix detector even with an enrotation rotation of the input optics.
  • the maximum integration time and thus the sensitivity of the seeker for example, be limited only by the refresh rate and no longer from the roles of the missile. It can be realized a highly sensitive seeker for finding even small and distant objects.
  • the seeker head is advantageously arranged at the tip of the guided missile and in particular under a dome.
  • the optical system suitably comprises a catadioptric optic with an input optic and an optical hinge.
  • the input optics in particular comprises Cassegrain optics and is expediently designed in the form of a mirror optic having a concave aspherical main mirror and a convex aspherical aspirating mirror.
  • the primary mirror that is, the mirror on which the rays from the object scene first impinge, as well as the secondary mirror are expediently arranged in the pitch frame and thus about the roll axis coaxial with the missile axis or Suchkopfachse, and a pitch axis two-dimensional pivot.
  • the optical joint is expediently used to track the beam path onto the matrix detector during a movement of the input optics.
  • the optical joint may be a mirror joint with multiple mirror surfaces.
  • the optical joint is a prism joint with a plurality of reflective prisms. It is expedient to have four mirrors or reflecting prism surfaces.
  • a simple embodiment of the optical joint can be achieved if the beam path from the input optics extends at least partially within the optical joint symmetrically to the roll axis and to the pitch axis of the optics. In the transition from a primary part to a secondary part of the optical joint, the beam path expediently runs symmetrically to the pitch axis.
  • the missile is suitably an actively propelled missile with a rocket engine and steering vanes for controlling the flight and directing the orientation of the missile.
  • the guided missile in particular the seeker head, is equipped with a control unit which is prepared for steering the missile in response to the signals of the matrix detector and for this purpose activates the steering vanes of the guided missile.
  • the detector unit is arranged roll-stable on the rolling frame, so attached to the rolling frame in such a way that it rotates with each rolling movement of the rolling frame.
  • the matrix detector is expediently sensitive in the infrared spectral range, so that heat sources can be detected.
  • the seeker head in an advantageous embodiment of the invention comprises a cooler for cooling the matrix detector.
  • the operating temperature of the matrix detector is expediently cooled down to a temperature whose equivalent spectral range in the radiation maximum lies energetically below the sensitive spectral range of the matrix detector.
  • a relatively bulky cooler for example a Joule-Thomson cooler
  • Such a cooler would represent a large moment of inertia on the roll axis if it were to co-roll with the detector unit.
  • the radiator is expediently arranged rigidly to the outer housing. In a rolling movement of the missile and a Entrollterrorism the input optics, the detector unit thus rotates to the radiator, but otherwise remains in the other spatial directions expediently immovable to the radiator.
  • the cooler is expediently a gas cooler with a gas outlet, which is expediently aligned with the detector unit.
  • the gas outlet is advantageously parallel, in particular coaxial, aligned with the roll axis.
  • a gap can be arranged between these two units.
  • the gap is suitably sealed by means of a ceramic seal.
  • PTFE polytetrafluoroethylene
  • the image signals generated by the matrix detector are transmitted to a control unit for evaluation.
  • the control unit is expediently structurally fixed in the seeker head, that is to say fixed rigidly to the outer housing, at least with a part which carries out the image evaluation and / or controls a rolling drive. Due to the unrolling movement, ie the roll relative movement of the matrix detector to the outer housing, it is necessary to transmit the data to the control unit via a communication unit permitting the rolling motion of the matrix detector.
  • the communication unit can be equipped with sliding contacts, which are guided via a slip ring. At a high data rate, it is advantageous to transmit the detector signals without contact.
  • the communication unit expediently comprises a transmitter and a receiver for wireless data transmission between transmitter and receiver, in particular from the matrix detector to the control unit and / or vice versa.
  • the transmitter is, for example, frame-mounted and the receiver is fixed to the housing.
  • One possibility for wireless data transmission may be the inductive coupling, with two conductor loops or antennas forming the transmitter and the receiver. Also a capacitive coupling is possible.
  • an optical data transmission for wireless transmission of the data can be considered.
  • a known data transmission standard with sufficient data rate for example WLAN or WHDI, is used.
  • a power supply of the matrix detector is advantageously carried out via a slip ring.
  • a power supply device is present, which has a power storage, a slip ring and a power line between the power storage and slip ring.
  • the slip ring is suitably connected to a grinding element, which rotates in contact with the rolling ring during an unwinding movement.
  • the grinding element is expediently wired to a current input of the detector unit.
  • the rolling frame is advantageously held stationary relative to the outside space of the seeker head or relative to the object scene with respect to the rolling movement.
  • the absolute roll rate of the rolling frame disappears.
  • the absolute roll rate here can be understood as a geo-related rolling movement per time, which disappears when the input optics are focused on a stationary object relative to the seeker head.
  • the speed of the rolling movement of the outer housing is usually derived from a measured variable of a structure-fixed sensor in order to initiate a control of a rolling drive an equally fast counter-rolling of the rolling frame, so its Entolling, so that the absolute roll rate of the input optics disappears.
  • This can be done using the so-called "strapdown principle" take place, in which is closed from a course of an acceleration to the rolling rate of the outer housing and hereby the rolling drive is controlled.
  • the absolute roll rate of the rolling frame is sensory detected as such, in particular by a rolling frame fixed roll sensor.
  • the thus detected absolute roll rate can then be controlled by means of a sensor signal to zero or a desired roll value.
  • the seeker head in a further advantageous embodiment of the invention comprises a rolling frame fixedly arranged roll sensor for detecting a rolling movement of the rolling frame.
  • the roll sensor may be an acceleration sensor, such as a gyro sensor, a yaw rate sensor, an inertial inertial sensor (IMU), or the like. Due to the rolling-frame-fixed arrangement, ie the rigid connection to the matrix detector, a rolling motion of the matrix detector and also a movement of the input optics rigidly coupled to the matrix detector with respect to the rolling can be measured.
  • the control of the rolling frame is expediently carried out by a control unit for controlling further drives of the seeker head, for example a pitch drive.
  • the control unit may be identical to the control unit for steering the missile during its flight and for controlling the seeker head functions.
  • the seeker head comprises a housing-mounted motion sensor for detecting the movement of the outer housing.
  • the invention is further directed to a method of imaging an object of an object scene onto a missile seeker array detector in which an input optics of an optical system of the seeker head is imaged by means of a roll pitch system having a rolling frame and a pitch frame Object is aligned and the object is imaged by the optical system on the matrix detector.
  • the image of the object rests on the matrix detector with outer housing rolling around the roll axis.
  • the matrix detector also rests in the space in the frame of the rolling frame.
  • Such a rest applies, for example, to a mapped object that is stationary relative to the roll axis.
  • the imaging of the object can also move over the sensitive area of the matrix detector.
  • the input optics is expediently tracked to the moving object, whereby this expediently also the matrix detector is tracked in its rolling motion.
  • the alignment of the input optics on the object is advantageously carried out by a rotation about two axes relative to the missile axis, in particular a roll axis and a pitch axis.
  • the resting of the matrix detector in space, so a disappearance of the absolute rolling motion, can be achieved by driving the rolling frame against the rolling direction of the outer housing.
  • the matrix detector is expediently a detector sensitive in the infrared spectral range.
  • the matrix detector is advantageously cooled.
  • advantageously from a housing-mounted cooler of the seeker head cooling gas is sprayed against a detector having the matrix detector and rotating relative to the radiator about the roll axis detector unit.
  • a roll rate of the rolling frame is detected by a rolling frame fixedly arranged roll sensor.
  • the roll rate is controlled to a desired roll value using the roll sensor data.
  • the controller may include a controller so that the roll value is controlled to the desired roll value.
  • the roll rate may be the absolute roll rate, ie a roll speed relative to the object scene.
  • a further advantageous embodiment of the invention provides that a rolling rate of the outer housing is determined with the aid of an outer housing-fixed motion sensor.
  • the motion sensor is expediently an inertial sensor, in particular an acceleration sensor or a yaw rate sensor.
  • a rolling drive can be controlled so that the rolling frame is rotated relative to the outer housing in opposition to its rolling direction of rotation. The roll rate of the rolling frame is thereby reduced. Also in this way, the rolling rate of the rolling frame can be controlled or regulated to a desired roll value.
  • the rolling frame rolls with a remaining roll rate, so does not rest completely free of space in the room.
  • a remaining absolute roll rate can be detected by means of a roll frame fixed roll sensor.
  • the roll rate is controlled by the data of the roll sensor to a desired roll value, in particular regulated. This control is advantageously done with data from both the motion sensor and the roll sensor.
  • the roll sensor is a sensor that can reliably detect even very fast movements.
  • a measurement error of a rolling frame fixed roll sensor with the help of a housing-fixed motion sensor is at least partially detected and taken into account. If, for example, there is a measurement error of the roll sensor that fluctuates greatly over time, then it can be detected by the stationary motion sensor and / or at least partially compensated.
  • the input optics expediently remains aligned with the object. Accordingly, the rolling frame rolls to allow such tracking of the entrance optics on the object.
  • such roles as rolling motion so that even at a roll rate of zero, a rolling motion is possible, however, by tracking the input optics on a caused by the roll axis moving object is caused.
  • Such a rolling motion can be very fast, especially when the object is moving through or near the roll axis.
  • a rolling movement is detected in addition to the roll rate of the roll frame, which is generated by tracking the object with the input optics.
  • the rolling drive is controlled so that controlled by means of the driven for tracking the object rolling motion and the data of the roll sensor, a roll rate of the rolling frame to the desired roll value, in particular regulated.
  • the movement of the image of the object on the sensitive surface of the matrix detector can be used reliably for evaluating the movement of the object relative to the seeker head or to the roll axis.
  • Another possibility for controlling the absolute roll rate to a desired value is to determine a roll rate of the roll frame by means of data obtained from an image of the object scene on the matrix detector. Accordingly, the roll drive can be controlled and the roll rate controlled to a desired roll value, in particular regulated.
  • FIG. 1 shows the front part of a guided missile 2 in a schematic longitudinal section and there in particular the seeker head 4 at the tip of the missile 2.
  • the seeker 4 is equipped with an optical system 6, which is located immediately behind a dome 8 in a foremost tip of the seeker 4 ,
  • the optical system 6 comprises a Cassegrain optics with an input optics 10 and an optical joint 12.
  • the input optics 10 includes a concave primary mirror 14 and a convex catching mirror 16.
  • the input optics 10 are optically via a detector optics 18 with a detector unit 20, which has a matrix detector 22 on a carrier 24 in a detector housing 26.
  • An object 28 of an object scene 30 is imaged onto the matrix detector 22 via the input optics 10, the optical joint 12 and the detector optics 18.
  • the optical joint 12 is formed of two prism blocks 32, 34, which are designed to be movable relative to each other.
  • the first prism block 32 is pivotable relative to the second prism block 34 about a pitch axis 36 and both prism blocks 32, 34 are rotatable about a roll axis 38, which extends in the axial direction or the longitudinal axis of the guided missile 2.
  • the first prism block 32 is fixedly connected to the input optics 10 so that it is rotatable about the pitch axis 36 and the roll axis 38.
  • the second prism block 34 is firmly connected to the detector optics 18 and the detector unit 20, so that these units are rotatable in the operation of the seeker head 4 only about the roll axis 38.
  • the entire optical system 6 is therefore stored in a roll pitch system 40, the rolling frame 42 and pitch frame 44 in FIG. 1 are shown only schematically.
  • the rolling frame 42 carries all rolling elements of the optical system 6, including the nickbaren elements, and is rigidly attached to a rotor block 46.
  • the pitch frame 44 carries all nickbaren elements, such as the input optics 10 and the prism block 32nd
  • the detector unit 20 is also fixed to the rotor block 46 which is rotatable about the roll axis 38 via bearings 48 by means of a rolling drive 50 having a rotor 52 and a stator 54.
  • a rolling drive 50 having a rotor 52 and a stator 54.
  • the rotor block 46 is held in a stator block 56 which is rigidly secured to the outer housing 58 of the seeker head 4 and the outer housing 60 lying behind it of the other missile 2.
  • Attached to the rear of the stator block 56 is a radiator 62 having a forwardly directed gas outlet 64 which is aligned with the detector unit 20 and opens immediately thereafter.
  • the cooler 62 is supplied with gas via two gas containers 66 during the operation of the seeker head 4.
  • a nickel electronics 68 Also rigidly connected to the rotor block 46 and thus rotatable about the roll axis 38 is a nickel electronics 68, a roll sensor 70, a detector electronics 72 and a communication unit 74 with a transmitter 76 and a receiver 78.
  • the transmitter 76 can also be used as a receiver and the receiver 78th act as a transmitter, so that bidirectional communication is possible.
  • Transmitter 76 and receiver 78 are designed as annular discs, and the transmitter 76 is rigidly connected to the rotor block 46 and the receiver 78 is rigidly connected to the stator block 56.
  • the rotor block 46 carries a power transmission unit 80 with a slip ring 82 and a brush 84 for transmitting electrical energy from a housing-fixed energy storage, not shown, to the detector unit 20.
  • the slip ring 82 is wired to the detector unit 20 and the brush 84 to the energy storage.
  • Connected to the rotor block 46 is also an optical grating 86 by means of which an optical tap 88 of a housing-fixed control unit 90, the rotational speed of the rotor block 46 relative to the stator block 56 can be determined.
  • the rolling rate of the stator block 56 or of the outer housing 58 can be detected by the control unit 90 via a motion sensor 92, which is likewise fixed to the housing, and which is designed as an initial sensor or IMU (inertial measurement unit).
  • the motion sensor 92 detects acceleration values, for example a centrifugal force acceleration and / or accelerations in other spatial directions, and thereby determines from an initial state a later instantaneous state, for example a roll rate, an airspeed and optionally other further variables.
  • the guided missile 2 is a self-propelled and not shown rudder steerable missile, which is launched for example from a canister. About his rocket engine, the guided missile 2 flies toward a predetermined destination, which is stored for example in the control unit 90 or another control unit, for example by means of coordinates. Also possible is the specification of an optical target, for example, the object 28, which is optically detected and passed before or after the start of the missile 2 to the corresponding control unit 90. As it approaches the object 28, it is imaged on the matrix detector 22 via the optical system 6. A movement of the image of the object 28 on the sensitive surface of the matrix detector 22 firstly leads to a movement of the input optics 10 so that it remains aligned as centered as possible on the object 28. Secondly, the movement leads to a steering command for aligning the longitudinal axis of the guided missile 2 in the direction of the object 28, so that the guided missile 2 follows the object 28 in this manner.
  • a predetermined destination which is stored for example in the control unit 90 or another control unit, for example by means of
  • the cooler 62 Prior to the activation of the matrix detector 22, it is cooled down by the cooler 62 to a temperature at which a thermally induced excitation of charge carriers in the matrix detector 22 and thus a noise of the matrix detector 22 in the infrared spectral region is greatly reduced compared to room temperature, so that weakly radiating in the infrared Objects of the object scene 30 and in particular the targeted object 28 are detected.
  • the cooler 62 relaxed and thus greatly cooled cooling gas is blown through the gas outlet 64 to the rear side of the carrier 24, so that this and strongly cool the matrix detector 22 with him. The gas is distributed in the gap between the rotor block 46 and the radiator 62 to the rear and is discharged there.
  • the control unit 90 controls the rolling drive 50, so that the rolling frame 42 rotates counter to the rolling direction of the outer housing 58 and with the rolling rate determined by the motion sensor 92.
  • An alternative method of unrolling may be performed using the roll sensor 70.
  • This can also detect a roll rate of the rolling frame 42, so that the control unit 90, which is connected to the roll sensor 70 via the communication unit 74, can control an unrolling of the rolling frame 42 by the corresponding control of the rolling drive 50.
  • the roll rate of the rolling frame 42 it is also possible to control the roll rate of the rolling frame 42.
  • the controlled variable here is, for example, a measured centrifugal force acceleration, which acts on the roll sensor 70.
  • the feed of the rolling drive 50 is controlled by the control unit 90 so that the centrifugal force and thus the absolute roll rate are regulated to zero, for example.
  • Another method is the interaction of the motion sensor 92 with the roll sensor 70 to control the absolute roll rate of the roll frame 42 to a desired roll value, such as zero.
  • the absolute roll rate is controlled by means of the control unit 90 and the motion sensor 92 as described in the first method.
  • the roll sensor 70 would have to confirm the desired absolute roll rate. If this is not the case, the signal of the roll sensor 70 can be used as an additional signal from the control unit 90 to set the desired absolute roll rate of the rolling frame 42.
  • the unrolling thus consists of two components: a component resulting from the signal of the motion sensor 92 and a component resulting from the signal of the roll sensor 70 and added to the first component.
  • the tracking of the Object 28 with the input optics 10 lead to a very sudden and very fast rolling movement of the rolling frame 42.
  • This rolling motion is a movement that is detected by the roll sensor 70 in addition to the rotation of the rolling frame 42.
  • the roll sensor 70 is prepared for this purpose and thus a very fast detecting sensor, which is able to accurately detect fast movements and rapid movement changes. Since the rolling motion of the rolling frame 42 for tracking the input optics 10 is controlled by the control unit 90 and controlled by means of the optical grating 86, the control unit 90 can also separate this rolling motion from the unrolling movement of the rolling frame 42 from the signal from the roll sensor 70. A control of the Entrollrotation remains possible.
  • the measurements of the roll sensor 70 are subject to a measurement inaccuracy. For example, a drift that can result in a roll measurement error is added from a plurality of fluctuating accelerations.
  • a measurement error can be detected by the control unit 90 using the data of the motion sensor 92.
  • the motion sensor 92 rotates relatively constantly with the roll rate of the outer housing 58, and its possible measurement error can be detected and compensated by the signal of the roll sensor 70 from the control unit 90.
  • FIG. 2 A corresponding procedure is in FIG. 2 exemplified.
  • the motion sensor 92 detects a first roll rate RR 1 and supplies the corresponding data to the control unit 90. This controls the roll drive 50 to unroll the roll frame 42.
  • a roll roll RR 2 is detected by the roll sensor 70, which feeds its data to the control unit 90. With the aid of this correction data, the roller drive 50 is likewise activated, so that a more accurate unrolling takes place. This is detected in a control loop by the roll sensor 70 and used by the control unit 90 for control.
  • a movement of the image of the object 28 on the sensitive surface of the matrix detector 22 is detected by the detector electronics 72 and corresponding data is supplied to the control unit 90.
  • the rolling motion RB is detected by the roll sensor 70 and the corresponding signal is passed on to the control unit 90. This separates from the signal the two movements, namely the residual rolling rate RR 2 of the rolling motion RB, and further controls the rolling drive 50 so that the residual rolling rate RR 2 disappears or assumes a desired value.
  • its image on the sensitive surface of the matrix detector 22 can also be used to set the absolute roll rate. If, for example, a horizon is depicted, the sun and or another known and stable object, its image rests on the sensitive surface of the matrix detector 22 as the roll frame 42 disappears and the flight of the guided missile 2 disappears of the rolling frame 42 can be detected by a circular scan of the image on the matrix detector 22, for example by image acquisition. This circle can be used to control the absolute roll rate.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP16000016.2A 2015-01-23 2016-01-08 Tête chercheuse pour un missile guidé Active EP3048410B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102015000873.0A DE102015000873A1 (de) 2015-01-23 2015-01-23 Suchkopf für einen Lenkflugkörper

Publications (2)

Publication Number Publication Date
EP3048410A1 true EP3048410A1 (fr) 2016-07-27
EP3048410B1 EP3048410B1 (fr) 2020-03-18

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ID=55310612

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16000016.2A Active EP3048410B1 (fr) 2015-01-23 2016-01-08 Tête chercheuse pour un missile guidé

Country Status (3)

Country Link
US (1) US9709361B2 (fr)
EP (1) EP3048410B1 (fr)
DE (1) DE102015000873A1 (fr)

Cited By (2)

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DE102020000482A1 (de) 2020-01-28 2021-07-29 Diehl Defence Gmbh & Co. Kg Suchoptik, Suchkopf und Lenkflugkörper
CN115038929A (zh) * 2019-12-18 2022-09-09 Bae系统信息和电子系统集成有限公司 使用跟随前方策略的群体导航

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DE19824899C1 (de) * 1998-06-04 1999-08-26 Lfk Gmbh Zielsuchkopf und Verfahren zur Zielerkennung- und Verfolgung mittels des Zielsuchkopfes
FR2830078A1 (fr) * 2001-09-25 2003-03-28 Sagem Procede de guidage d'une roquette
DE10313136A1 (de) * 2003-03-29 2004-10-07 BODENSEEWERK GERäTETECHNIK GMBH Suchkopf mit Nick-Gier-Innenkardansystem
DE102007030880A1 (de) * 2007-07-03 2009-01-08 Diehl Bgt Defence Gmbh & Co. Kg Vorrichtung zur Erfassung einer Objektszene
DE102007044766A1 (de) * 2007-09-19 2009-04-09 Diehl Bgt Defence Gmbh & Co. Kg Vorrichtung zur Erfassung einer Objektszene
DE102010055493A1 (de) 2010-12-15 2012-06-21 Diehl Bgt Defence Gmbh & Co. Kg Verfahren zum Steuern eines Lenkflugkörpers und Suchkopf für einen Lenkflugkörper

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115038929A (zh) * 2019-12-18 2022-09-09 Bae系统信息和电子系统集成有限公司 使用跟随前方策略的群体导航
EP4078074A4 (fr) * 2019-12-18 2024-01-17 BAE SYSTEMS Information and Electronic Systems Integration, Inc. Navigation en essaim au moyen du suivi de l'approche vers l'avant
DE102020000482A1 (de) 2020-01-28 2021-07-29 Diehl Defence Gmbh & Co. Kg Suchoptik, Suchkopf und Lenkflugkörper
EP3859422A1 (fr) 2020-01-28 2021-08-04 Diehl Defence GmbH & Co. KG Optique de recherche, tête de recherche et missile

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US9709361B2 (en) 2017-07-18
US20160216074A1 (en) 2016-07-28
DE102015000873A1 (de) 2016-07-28
EP3048410B1 (fr) 2020-03-18

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