EP2508836A1 - Kopf für Zielsuchgerät einer Rakete, und entsprechendes Zielsuchgerät - Google Patents

Kopf für Zielsuchgerät einer Rakete, und entsprechendes Zielsuchgerät Download PDF

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Publication number
EP2508836A1
EP2508836A1 EP12162212A EP12162212A EP2508836A1 EP 2508836 A1 EP2508836 A1 EP 2508836A1 EP 12162212 A EP12162212 A EP 12162212A EP 12162212 A EP12162212 A EP 12162212A EP 2508836 A1 EP2508836 A1 EP 2508836A1
Authority
EP
European Patent Office
Prior art keywords
sight
line
sensor
actuator
axis
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
EP12162212A
Other languages
English (en)
French (fr)
Other versions
EP2508836B1 (de
Inventor
Pascal Junique
Vincent Fraysse
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 Defense Securite 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 Defense Securite SA filed Critical Sagem Defense Securite SA
Publication of EP2508836A1 publication Critical patent/EP2508836A1/de
Application granted granted Critical
Publication of EP2508836B1 publication Critical patent/EP2508836B1/de
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
    • F41G7/008—Combinations of different guidance systems
    • 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
    • F41G7/226—Semi-active homing systems, i.e. comprising a receiver and involving auxiliary illuminating means, e.g. using auxiliary guiding missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—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 present invention relates to a head, including but not limited to, for a missile seeker.
  • Heads are known for missile search engines.
  • Known heads comprise a sensitive sensor in a band of electromagnetic radiation, for example infrared, and further include a line of sight. They generally also comprise an actuator on which the sensor is mounted, the actuator comprising an external gimbal adapted to be rotatably mounted about a first axis, and an internal gimbal adapted to be rotatably mounted relative to the external gimbal. , about a second axis generally perpendicular to the first axis, so that the actuator ensures the orientation of the line of sight relative to the first axis and the second axis, and further ensures the stabilization of the line of sight .
  • Previous heads generally have a limitation.
  • They comprise only one first sensor, or it may be desirable to have a second sensor to complete the field of observation of a target made by the first sensor.
  • the invention proposes to overcome this limitation effectively.
  • the invention also relates to a corresponding homing device.
  • the invention has many advantages.
  • the invention makes it possible to have two sensors in the same head, for example for a homing device.
  • the sensors mounted on the actuator are independent of each other, so that each of the channels of each sensor is independent of the other channel of the other sensor, and is optimized for the corresponding sensor. Only the porthole of the homing device, for example, is common to both sensors.
  • the invention is compact and can adapt to any caliber of missile seeker.
  • the invention allows a sensor change at any time, that is to say before the flight or during the flight of the missile.
  • the invention does not add additional cost of implementation for the lane change, because it consists in allowing a large angular movement to an actuator, the actuator still allowing the orientation and stabilization of the line of sight of the sensors.
  • the bands ⁇ 1 and ⁇ 2 are either distinct from one another or may overlap at least partially, and may be of any type, such as for example an IR band, especially near-infrared, a visible band, or a radar band.
  • the sensor 3 or 5 may thus comprise an IR matrix, cooled or not, a TV type camera (possibly also sensitive to the near infrared), or a laser sensor, semi-active or active, capable of capturing a LASER beam reflected by a target.
  • a TV type camera possibly also sensitive to the near infrared
  • a laser sensor capable of capturing a LASER beam reflected by a target.
  • the first band ⁇ 1 lies in the IR
  • the second band ⁇ 2 is located in the visible and / or near infrared according to the sensitivity of the sensor 5.
  • the head 1 also comprises an actuator 4 on which is mounted the first sensor 3 pointing in a first direction on the first line of sight AA.
  • the second sensor 5 is also mounted on the actuator 4 so that the second sensor 5 points in a second direction on the second line of sight BB.
  • the second line of sight BB is parallel to the first sight line AA, and the second direction is opposite to the first direction: the sensor 3 thus points in a direction opposite to the sensor 5 on the actuator 4 .
  • Each sensor mounted on the actuator 4 is independent of the other sensor, so that each of the channels of each sensor (materialized by the lenses for example and having a given field and focal length) is independent of the other channel of the sensor. other sensor, and is optimized for the corresponding sensor. It is therefore possible to optimize the optical formulas of each channel (in particular the lens material, the fields and the focal lengths of each channel) to obtain the best observations, for example the observation of a target by a homing device, a drone or any other observation device in which the head 1 is placed.
  • the actuator 4 comprises an external cardan shaft 41 adapted to be rotatably mounted about a first axis 410, and an internal cardan 42 adapted to be rotatably mounted, relative to the external cardan shaft 41, about a second axis 420
  • the external gimbal 41 forms a frame that can be mounted inside an observation system (a homing device of a missile for example) by a pivot link defining the axis 410 and being external to the cardan 41.
  • the internal cardan 42 forms a frame that can be mounted inside the outer gimbal 41 by a pivot link located between the gimbal 41 and the gimbal 42, and defining the axis 420 .
  • the movement of the gimbals 41 and 42 is by motors, recopies and electronic means known to those skilled in the art and which are not described in detail in the present description.
  • the second axis 420 is perpendicular to the first axis 410.
  • the actuator 4 ensures the orientation of the first line of sight AA with respect to the first axis 410 and the second axis 420, and further ensures the stabilization of the first line of sight AA.
  • the actuator 4 is further adapted to be able to perform an angular displacement on one of the axes 410 or 420, to place the second sensor 5 in front of the window 6.
  • the additional angular displacement of the actuator 4 is at least 180 ° of rotation on one of the axes 410 or 420, but it is understood that other angular deflection values are possible .
  • the actuator 4 also ensures the selection of the second sensor 5, then the orientation of the second line of sight BB relative to the first axis 410 and the second axis 420, and also ensures the stabilization of the second line of sight BB, especially when the second sensor 5 is placed in front of the window 6.
  • the external cardan shaft 41 which is adapted to be able to effect the angular deflection, of at least 180 ° of rotation for example in the figures.
  • the head 1 can benefit from all the caliber of the missile by being able to perform the angular deflection of 180 ° for the sensors 3 and 5.
  • the internal cardan 41 could also perform the angular deflection, but in this case the sensors 3 and 5 would only benefit from the internal space of the internal cardan 41.
  • the first axis 410 allows an angular displacement in elevation (relative to the horizontal) and the second axis 420 allows a displacement in the bearing (relative to the vertical). It is in fact generally more advantageous to have a greater clearance in the site than in the reservoir, and it is therefore advantageous to benefit in this respect from the large deflection capabilities of the actuator 4.
  • the second line of sight BB is confused with the first line of sight AA, as shown by the figures 2 and 3 , but other provisions of the lines of sight AA and BB are also possible.
  • the center of rotation corresponding to the intersection of the axes 410 and 420, and the center of gravity of the head 1, are merged, and also very preferably correspond to the center of the radius of curvature of the window 6 of the Figures 1 to 3 .
  • the head according to the invention also applies to homing devices having a non-spherical porthole.
  • Each of the sensors can be straight or angled for compactness gains. So, on the figure 2 , the IR sensor 3 is straight, while the visible sensor 5 (and / or near infrared) is bent. In this case, the second sensor 5 is preferably bent on one side of the second line of sight BB and weighted by a ballast 51 so that the head 1 is balanced around the two axes 410 and 420. This avoids the presence of an imbalance.
  • a sensor 3 or 5 to be placed in front of the window 6 thanks to the actuator 4, here for example the sensor 3 (the sensor 5 is inactive).
  • the mission begins, the missile is launched and starts a flight towards a target.
  • the actuator 4 ensures the orientation of the first line of sight AA with respect to the first axis 410 and the second axis 420, and further ensures the stabilization of the first line of sight AA.
  • the mission may end with the detector 3, but also it may be desirable to place the sensor 5 in front of the window 6 during the mission. In other words, the angular deflection can be performed at any time, that is to say before the flight or during the flight of the missile.
  • the actuator 4 performs an angular deflection (90 ° on the figure 3 ), for example to reach a 180 ° rotation (see figure 4 ), so that the sensor 5 is placed in front of the window 6 (the sensor 3 is then inactive), and can continue the mission of the missile.
  • the actuator 4 furthermore ensures the orientation of the second line of sight BB with respect to the first axis 410 and the second axis 420, and also ensures the stabilization of the second line of sight BB during the mission of the missile.
  • the actuator 4 can orient the sensors to protect them from specific radiation that could alter its operation, such as for example to protect an IR sensor from solar radiation.

Landscapes

  • 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)
EP12162212.0A 2011-04-05 2012-03-29 Kopf für Zielsuchgerät einer Rakete, und entsprechendes Zielsuchgerät Active EP2508836B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1101014A FR2973867B1 (fr) 2011-04-05 2011-04-05 Tete pour autodirecteur de missile, et autodirecteur correspondant

Publications (2)

Publication Number Publication Date
EP2508836A1 true EP2508836A1 (de) 2012-10-10
EP2508836B1 EP2508836B1 (de) 2013-11-20

Family

ID=45878015

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12162212.0A Active EP2508836B1 (de) 2011-04-05 2012-03-29 Kopf für Zielsuchgerät einer Rakete, und entsprechendes Zielsuchgerät

Country Status (3)

Country Link
EP (1) EP2508836B1 (de)
FR (1) FR2973867B1 (de)
IL (1) IL219033A (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3059765A1 (fr) * 2016-12-07 2018-06-08 Safran Electronics & Defense Tete pour autodirecteur
DE102012017452B4 (de) * 2012-09-04 2018-11-08 Mbda Deutschland Gmbh Suchkopf mit Multi-Mode-Eigenschaften

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2751249T3 (es) * 2013-09-05 2020-03-30 Mbda Deutschland Gmbh Cabeza de búsqueda con propiedades multimodo

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4085910A (en) * 1972-04-12 1978-04-25 Northrop Corporation Dual mode optical seeker for guided missile control
US6396235B1 (en) * 2001-01-05 2002-05-28 Engineered Support Systems, Inc. Stabilized common gimbal
US6422508B1 (en) * 2000-04-05 2002-07-23 Galileo Group, Inc. System for robotic control of imaging data having a steerable gimbal mounted spectral sensor and methods
US20050093757A1 (en) * 2003-10-30 2005-05-05 Kiernan Sherwood C.Jr. Tri-mode co-boresighted seeker

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4085910A (en) * 1972-04-12 1978-04-25 Northrop Corporation Dual mode optical seeker for guided missile control
US6422508B1 (en) * 2000-04-05 2002-07-23 Galileo Group, Inc. System for robotic control of imaging data having a steerable gimbal mounted spectral sensor and methods
US6396235B1 (en) * 2001-01-05 2002-05-28 Engineered Support Systems, Inc. Stabilized common gimbal
US20050093757A1 (en) * 2003-10-30 2005-05-05 Kiernan Sherwood C.Jr. Tri-mode co-boresighted seeker

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012017452B4 (de) * 2012-09-04 2018-11-08 Mbda Deutschland Gmbh Suchkopf mit Multi-Mode-Eigenschaften
FR3059765A1 (fr) * 2016-12-07 2018-06-08 Safran Electronics & Defense Tete pour autodirecteur

Also Published As

Publication number Publication date
FR2973867B1 (fr) 2014-03-21
IL219033A (en) 2015-11-30
FR2973867A1 (fr) 2012-10-12
EP2508836B1 (de) 2013-11-20
IL219033A0 (en) 2012-07-31

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