EP2508836A1 - Head for missile homing device and corresponding homing device - Google Patents

Head for missile homing device and corresponding homing device 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
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EP
European Patent Office
Prior art keywords
sight
line
sensor
actuator
axis
Prior art date
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Granted
Application number
EP12162212A
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German (de)
French (fr)
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EP2508836B1 (en
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
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Publication of EP2508836A1 publication Critical patent/EP2508836A1/en
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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.

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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)

Abstract

The head (1) has a first sensor (3) and a second sensor that are mounted on an actuator so as to be turned up in first and second directions on a first line of sight (AA) and a second line of sight opposite to one another, respectively. The actuator is angularly displaced at 180 degrees to assure orientation of the second line of sight with respect to axes (410, 420) and to assure stabilization of the second line of sight, where the axes are perpendicular to each other.

Description

DOMAINE TECHNIQUE GENERALGENERAL TECHNICAL FIELD

La présente invention concerne une tête, notamment mais non limitativement, pour un autodirecteur de missile.The present invention relates to a head, including but not limited to, for a missile seeker.

Elle concerne également avantageusement un autodirecteur correspondant.It also advantageously relates to a corresponding homing device.

ETAT DE L'ARTSTATE OF THE ART

On connaît des têtes pour des autodirecteurs de missiles.Heads are known for missile search engines.

Les têtes connues comportent un capteur sensible dans une bande de rayonnement électromagnétique, par exemple l'infrarouge, et comportent en outre une ligne de visée. Elles comportent en général également un actionneur sur lequel est monté le capteur, l'actionneur comportant un cardan externe adapté pour être monté à rotation autour d'un premier axe, et un cardan interne adapté pour être monté à rotation, par rapport au cardan externe, autour d'un deuxième axe en général perpendiculaire au premier axe, de sorte que l'actionneur assure l'orientation de la ligne de visée par rapport au premier axe et au deuxième axe, et assure en outre la stabilisation de la ligne de visée.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 .

Les têtes précédentes présentent généralement une limitation.Previous heads generally have a limitation.

Elles ne comportent en effet qu'un seul premier capteur, or il peut être souhaitable de disposer d'un deuxième capteur pour compléter le domaine d'observation d'une cible effectuée par le premier capteur.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.

PRESENTATION DE L'INVENTIONPRESENTATION OF THE INVENTION

L'invention propose de pallier cette limitation de manière efficace.The invention proposes to overcome this limitation effectively.

A cet effet, on propose selon l'invention une tête comportant

  • un premier capteur dans une première bande de rayonnement électromagnétique, comportant une première ligne de visée,
  • un actionneur sur lequel est monté le premier capteur pointant dans un premier sens sur la première ligne de visée, l'actionneur comportant
    un cardan externe adapté pour être monté à rotation autour d'un premier axe, et
    un cardan interne adapté pour être monté à rotation, par rapport au cardan externe, autour d'un deuxième axe,
    de sorte que l'actionneur assure l'orientation de la première ligne de visée par rapport au premier axe et au deuxième axe, et assure en outre la stabilisation de la première ligne de visée,
    la tête étant caractérisée en ce qu'elle comporte
  • un deuxième capteur dans une deuxième bande de rayonnement électromagnétique, comportant une deuxième ligne de visée parallèle à la première ligne de visée, le deuxième capteur étant monté sur l'actionneur de sorte que le deuxième capteur pointe dans un deuxième sens sur la deuxième ligne de visée, le deuxième sens sur la deuxième ligne de visée étant opposé au premier sens sur la première ligne de visée,
    l'actionneur étant en outre adapté pour pouvoir effectuer un débattement angulaire de sorte que l'actionneur assure en outre l'orientation de la deuxième ligne de visée par rapport au premier axe et au deuxième axe, et assure aussi la stabilisation de la deuxième ligne de visée.
For this purpose, it is proposed according to the invention a head comprising
  • a first sensor in a first electromagnetic radiation band, having a first line of sight,
  • an actuator on which is mounted the first sensor pointing in a first direction on the first line of sight, 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,
    so that the actuator ensures the orientation of the first line of sight relative to the first axis and the second axis, and further ensures the stabilization of the first line of sight,
    the head being characterized in that it comprises
  • a second sensor in a second electromagnetic radiation band, having a second line of sight parallel to the first line of sight, the second sensor being mounted on the actuator so that the second sensor points in a second direction on the second line of sight; aiming, the second direction on the second line of sight being opposite the first direction on the first line of sight,
    the actuator being further adapted to perform angular deflection so that the actuator further ensures the orientation of the second line of sight relative to the first axis and the second axis, and also ensures the stabilization of the second line of aiming.

L'invention est avantageusement complétée par les caractéristiques suivantes, prises seules ou en une quelconque de leur combinaison techniquement possible :

  • le deuxième axe est perpendiculaire au premier axe ;
  • l'actionneur est adapté pour pouvoir effectuer un débattement angulaire d'au moins 180° de rotation ;
  • le cardan externe est adapté pour pouvoir effectuer le débattement angulaire d'au moins 180° de rotation ;
  • la première bande se situe dans l'IR, et
  • la deuxième bande se situe dans le visible et/ou le proche infrarouge ;
  • le deuxième capteur est coudé d'un côté de la deuxième ligne de visée et lesté pour que la tête soit équilibrée autour des deux axes ;
  • la tête est adaptée pour un autodirecteur de missile.
The invention is advantageously completed by the following features, taken alone or in any of their technically possible combination:
  • the second axis is perpendicular to the first axis;
  • the actuator is adapted to perform an angular deflection of at least 180 ° of rotation;
  • the external gimbal is adapted to perform angular deflection of at least 180 ° of rotation;
  • the first band is in the IR, and
  • the second band is in the visible and / or near infrared;
  • the second sensor is bent on one side of the second line of sight and weighted so that the head is balanced around the two axes;
  • the head is suitable for a missile seeker.

L'invention concerne également un autodirecteur correspondant. L'invention présente de nombreux avantages.The invention also relates to a corresponding homing device. The invention has many advantages.

L'invention permet de disposer de deux capteurs dans une même tête, par exemple pour un autodirecteur.The invention makes it possible to have two sensors in the same head, for example for a homing device.

Les capteurs montés sur l'actionneur sont indépendants l'un de l'autre, de sorte que chacune des voies de chaque capteur est indépendante de l'autre voie de l'autre capteur, et est optimisée pour le capteur correspondant. Seul le hublot de l'autodirecteur par exemple est commun aux deux capteurs.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.

L'invention est compacte et peut s'adapter à tout calibre d'autodirecteur de missile.The invention is compact and can adapt to any caliber of missile seeker.

L'invention permet un changement de capteur à tout moment, c'est-à-dire avant le vol ou pendant le vol du missile.The invention allows a sensor change at any time, that is to say before the flight or during the flight of the missile.

L'invention n'ajoute pas de coût de réalisation supplémentaire pour le changement de voie, car elle consiste à permettre un débattement angulaire important à un actionneur, l'actionneur permettant toujours l'orientation et la stabilisation de la ligne de visée des capteurs.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.

PRESENTATION DES FIGURESPRESENTATION OF FIGURES

D'autres caractéristiques, buts et avantages de l'invention ressortiront de la description qui suit, qui est purement illustrative et non limitative, et qui doit être lue en regard des dessins annexés sur lesquels :

  • la figure 1 représente schématiquement en perspective une partie avant d'un missile comportant une tête selon l'invention ;
  • la figure 2 représente schématiquement une vue en coupe longitudinale de la figure 1, un premier capteur étant en face d'un hublot ;
  • la figure 3 montre une vue correspondant à la figure 2, dans laquelle l'actionneur a effectué un débattement angulaire de 90° ;
  • la figure 4 représente schématiquement une vue en coupe longitudinale de la figure 1, un deuxième capteur étant en face du hublot, l'actionneur ayant effectué un débattement angulaire de 180° par rapport à la figure 2 ; et
  • la figure 5 présente les deux axes de l'actionneur selon l'invention, vus de face.
Other features, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the appended drawings in which:
  • the figure 1 schematically shows in perspective a front part of a missile comprising a head according to the invention;
  • the figure 2 schematically represents a view in longitudinal section of the figure 1 a first sensor being in front of a porthole;
  • the figure 3 shows a view corresponding to the figure 2 in which the actuator has made an angular deflection of 90 °;
  • the figure 4 schematically represents a view in longitudinal section of the figure 1 , a second sensor being in front of the window, the actuator having effected an angular deflection of 180 ° with respect to the figure 2 ; and
  • the figure 5 presents the two axes of the actuator according to the invention, seen from the front.

Sur l'ensemble des figures, les éléments similaires portent des références numériques identiques.In all the figures, similar elements bear identical reference numerals.

DESCRIPTION DETAILLEEDETAILED DESCRIPTION

Comme le montrent les figures 1 à 5, un exemple d'un mode de réalisation possible d'une tête 1 comporte principalement

  • un premier capteur 3 dans une première bande λ1 de rayonnement électromagnétique, comportant une première ligne de visée AA, et
  • un deuxième capteur 5 dans une deuxième bande λ2 de rayonnement électromagnétique, comportant une deuxième ligne de visée BB.
As shown by Figures 1 to 5 , an example of a possible embodiment of a head 1 comprises mainly
  • a first sensor 3 in a first band λ1 of electromagnetic radiation, comprising a first line of sight AA, and
  • a second sensor 5 in a second band λ2 of electromagnetic radiation, having a second line of sight BB.

Les bandes λ1 et λ2 sont soit distinctes l'une de l'autre soit peuvent se recouvrir au moins partiellement, et peuvent être de tout type, comme par exemple une bande IR, notamment proche infrarouge, une bande visible, ou une bande radar.The bands λ1 and λ2 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.

Le capteur 3 ou 5 peut ainsi comporter une matrice IR, refroidie ou non, une caméra du type TV (éventuellement sensible également au proche infrarouge), ou un senseur laser, semi-actif ou actif, capable de capter un faisceau LASER réfléchi par une cible. De manière préférentielle, la première bande λ1 se situe dans l'IR, et la deuxième bande λ2 se situe dans le visible et/ou le proche infrarouge en fonction de la sensibilité du capteur 5.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. Preferably, the first band λ1 lies in the IR, and the second band λ2 is located in the visible and / or near infrared according to the sensitivity of the sensor 5.

La tête 1 comporte également un actionneur 4 sur lequel est monté le premier capteur 3 pointant dans un premier sens sur la première ligne de visée AA. Le deuxième capteur 5 est également monté sur l'actionneur 4 de sorte que le deuxième capteur 5 pointe dans un deuxième sens sur la deuxième ligne de visée BB.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.

De manière préférentielle mais aucunement limitative, la deuxième ligne de visée BB est parallèle à la première ligne AA de visée, et le deuxième sens est opposé au premier sens : le capteur 3 pointe donc dans un sens opposé au capteur 5 sur l'actionneur 4.Preferably, but in no way limiting, 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 .

Chaque capteur monté sur l'actionneur 4 est indépendant de l'autre capteur, de sorte que chacune des voies de chaque capteur (matérialisée par les lentilles par exemple et ayant un champ et une focale donnés) est indépendante de l'autre voie de l'autre capteur, et est optimisée pour le capteur correspondant. On peut donc optimiser les formules optiques de chaque voie (notamment le matériau des lentilles, les champs et les distances focales de chaque voie) pour obtenir les meilleures observations, par exemple l'observation d'une cible par un autodirecteur, un drone ou tout autre dispositif d'observation dans lequel la tête 1 est placée.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.

En outre, comme le montre plus précisément la figure 5, l'actionneur 4 comporte un cardan 41 externe adapté pour être monté à rotation autour d'un premier axe 410, et un cardan 42 interne adapté pour être monté à rotation, par rapport au cardan 41 externe, autour d'un deuxième axe 420. De manière classique connue de l'homme du métier, le cardan externe 41 forme un cadre pouvant être monté à l'intérieur d'un système d'observation (un autodirecteur d'un missile par exemple) par une liaison pivot définissant l'axe 410 et étant externe au cardan 41. Le cardan interne 42 forme quant à lui un cadre pouvant être monté à l'intérieur du cardan externe 41 par une liaison pivot situé entre le cardan 41 et le cardan 42, et définissant l'axe 420.In addition, as shown more specifically figure 5 , 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 In a manner conventionally known to those skilled in the art, 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 .

Le déplacement des cardans 41 et 42 se fait par des moteurs, des recopies et des moyens électroniques connus par l'homme du métier et qui ne sont pas décrits en détail dans la présente description.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.

De manière très avantageuse, le deuxième axe 420 est perpendiculaire au premier axe 410.Very advantageously, the second axis 420 is perpendicular to the first axis 410.

Comme le montre la figure 1, lorsque la tête 1 est montée par exemple dans un autodirecteur 2 comportant un hublot 6 devant lequel est placé le premier capteur 3, l'actionneur 4 assure l'orientation de la première ligne de visée AA par rapport au premier axe 410 et au deuxième axe 420, et assure en outre la stabilisation de la première ligne de visée AA.As shown in figure 1 when the head 1 is mounted for example in a homing device 2 having a window 6 in front of which is placed the first sensor 3, 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.

Cependant, comme le montre plus précisément la figure 4, l'actionneur 4 est en outre adapté pour pouvoir effectuer un débattement angulaire sur un des axes 410 ou 420, pour placer le deuxième capteur 5 devant le hublot 6. Sur la figure 4, les lignes de visée AA et BB étant parallèles, le débattement angulaire supplémentaire de l'actionneur 4 est d'au moins 180° de rotation sur un des axes 410 ou 420, mais on comprend que d'autres valeurs de débattement angulaire sont possibles.However, as shown more specifically figure 4 , 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. On the figure 4 , the lines of sight AA and BB being parallel, 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 .

Ainsi, l'actionneur 4 assure également la sélection du deuxième capteur 5, puis l'orientation de la deuxième ligne de visée BB par rapport au premier axe 410 et au deuxième axe 420, et assure aussi la stabilisation de la deuxième ligne de visée BB, notamment lorsque le deuxième capteur 5 est placé en face du hublot 6.Thus, 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.

Comme le montre la figure 2, c'est préférentiellement le cardan 41 externe qui est adapté pour pouvoir effectuer le débattement angulaire, d'au moins 180° de rotation par exemple sur les figures. De cette manière, la tête 1 peut bénéficier de tout le calibre du missile en pouvant effectuer le débattement angulaire de 180° pour les capteurs 3 et 5. On comprend que le cardan interne 41 pourrait également effectuer le débattement angulaire, mais dans ce cas les capteurs 3 et 5 ne bénéficieraient que de l'espace interne au cardan interne 41.As shown in figure 2 it is preferentially 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. In this way, 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. It is understood that 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.

De manière préférentielle également, une fois la tête 1 montée dans l'autodirecteur 2, le premier axe 410 permet un débattement angulaire en site (par rapport à l'horizontale) et le deuxième axe 420 permet un débattement en gisement (par rapport à la verticale). Il est en effet en général plus avantageux d'avoir un plus grand débattement en site qu'en gisement, et il est donc intéressant de bénéficier à cet égard des possibilités de grand débattement en site de l'actionneur 4.Also preferably, once the head 1 mounted in the homing device 2, 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.

Afin de faciliter la conception de la tête 1, la deuxième ligne de visée BB est confondue avec la première ligne de visée AA, comme le montrent les figures 2 et 3, mais d'autres dispositions des lignes de visée AA et BB sont également possibles.In order to facilitate the design of the head 1, 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.

Avantageusement également, le centre de rotation, correspondant à l'intersection des axes 410 et 420, et le centre de gravité de la tête 1, sont confondus, et correspondent également très préférentiellement au centre du rayon de courbure du hublot 6 des figures 1 à 3. Bien entendu, la tête selon l'invention s'applique également à des autodirecteurs ayant un hublot non sphérique.Advantageously also, 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 . Of course, the head according to the invention also applies to homing devices having a non-spherical porthole.

Chacun des capteurs peut être droit ou coudé pour des gains de compacité. Ainsi, sur la figure 2, le capteur 3 IR est droit, tandis que le capteur 5 visible (et/ou proche infrarouge) est coudé. Dans ce cas, le deuxième capteur 5 est préférentiellement coudé d'un côté de la deuxième ligne de visée BB et lesté par un lest 51, pour que la tête 1 soit équilibrée autour des deux axes 410 et 420. On évite ainsi la présence d'un balourd.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.

Le fonctionnement de l'invention est le suivant.The operation of the invention is as follows.

On choisit, en début de mission du missile, un capteur 3 ou 5 à placer devant le hublot 6 grâce à l'actionneur 4, ici par exemple le capteur 3 (le capteur 5 est inactif).One chooses, at the beginning of the mission of the missile, 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).

La mission commence, le missile est lancé et commence un vol vers une cible. Pendant la mission, l'actionneur 4 assure l'orientation de la première ligne de visée AA par rapport au premier axe 410 et au deuxième axe 420, et assure en outre la stabilisation de la première ligne de visée AA. La mission peut se terminer avec le détecteur 3, mais également il peut être souhaitable de placer le capteur 5 devant le hublot 6, en cours de mission. En d'autres termes, le débattement angulaire peut être effectué à n'importe quel moment, c'est-à-dire avant le vol ou pendant le vol du missile.The mission begins, the missile is launched and starts a flight towards a target. During the mission, 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.

Dans ce cas, comme le montre la figure 3, l'actionneur 4 effectue un débattement angulaire (90° sur la figure 3), jusqu'à atteindre par exemple un débattement de 180° de rotation (voir la figure 4), de sorte que le capteur 5 soit placé devant le hublot 6 (le capteur 3 est alors inactif), et puisse continuer la mission du missile. L'actionneur 4 assure en outre l'orientation de la deuxième ligne de visée BB par rapport au premier axe 410 et au deuxième axe 420, et assure aussi la stabilisation de la deuxième ligne de visée BB pendant la mission du missile.In this case, as shown in figure 3 , 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.

Avantageusement, à la position repos, l'actionneur 4 peut orienter les capteurs pour les protéger d'un rayonnement spécifique qui pourrait en altérer le fonctionnement, comme par exemple protéger un capteur IR du rayonnement solaire.Advantageously, in the rest position, 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.

Claims (8)

Tête (1) comportant - un premier capteur (3) dans une première bande (λ1) de rayonnement électromagnétique, comportant une première ligne de visée (AA), - un actionneur (4) sur lequel est monté le premier capteur (3) pointant dans un premier sens sur la première ligne de visée (AA), l'actionneur (4) comportant
un cardan (41) externe adapté pour être monté à rotation autour d'un premier axe (410), et
un cardan (42) interne adapté pour être monté à rotation, par rapport au cardan (41) externe, autour d'un deuxième axe (420),
de sorte que l'actionneur (4) assure l'orientation de la première ligne de visée (AA) par rapport au premier axe (410) et au deuxième axe (420), et assure en outre la stabilisation de la première ligne de visée (AA),
la tête (1) étant caractérisée en ce qu'elle comporte - un deuxième capteur (5) dans une deuxième bande (λ2) de rayonnement électromagnétique, comportant une deuxième ligne de visée (BB), parallèle à la première ligne de visée (AA), le deuxième capteur (5) étant monté sur l'actionneur (4) de sorte que le deuxième capteur (5) pointe dans un deuxième sens sur la deuxième ligne de visée (BB), le deuxième sens sur la deuxième ligne (BB) de visée étant opposé au premier sens sur la première ligne (AA) de visée,
l'actionneur (4) étant en outre adapté pour pouvoir effectuer un débattement angulaire de sorte que l'actionneur (4) assure en outre l'orientation de la deuxième ligne de visée (BB) par rapport au premier axe (410) et au deuxième axe (420), et assure aussi la stabilisation de la deuxième ligne de visée (BB). Head (1) comprising a first sensor (3) in a first band (λ1) of electromagnetic radiation, comprising a first line of sight (AA), an actuator (4) on which is mounted the first sensor (3) pointing in a first direction on the first line of sight (AA), the actuator (4) comprising
an outer gimbal (41) adapted to be rotatably mounted about a first axis (410), and
an internal gimbal (42) adapted to be rotatably mounted relative to the external gimbal (41) about a second axis (420),
so that the actuator (4) provides the orientation of the first line of sight (AA) relative to the first axis (410) and the second axis (420), and further ensures the stabilization of the first line of sight (AA),
the head (1) being characterized in that it comprises a second sensor (5) in a second band (λ2) of electromagnetic radiation, comprising a second line of sight (BB), parallel to the first line of sight (AA), the second sensor (5) being 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 direction on the second line of sight (BB) being opposite the first direction on the first line ( AA) of sight,
the actuator (4) being further adapted to be able to perform angular deflection so that the actuator (4) further ensures the orientation of the second line of sight (BB) relative to the first axis (410) and to the second axis (420), and also ensures the stabilization of the second line of sight (BB). Tête selon la revendication 1, dans laquelle le deuxième axe (420) est perpendiculaire au premier axe (410).The head of claim 1, wherein the second axis (420) is perpendicular to the first axis (410). Tête selon l'une des revendications 1 ou 2, dans laquelle l'actionneur (4) est adapté pour pouvoir effectuer un débattement angulaire d'au moins 180° de rotation.Head according to one of claims 1 or 2, wherein the actuator (4) is adapted to perform an angular deflection of at least 180 ° of rotation. Tête selon la revendication 3, dans laquelle le cardan (41) externe est adapté pour pouvoir effectuer le débattement angulaire d'au moins 180° de rotation.Head according to claim 3, wherein the outer gimbal (41) is adapted to perform the angular deflection of at least 180 ° of rotation. Tête selon l'une des revendications 1 à 4, dans laquelle - la première bande (λ1) se situe dans l'IR, et - la deuxième bande (λ2) se situe dans le visible et/ou le proche infrarouge. Head according to one of claims 1 to 4, wherein the first band (λ1) is in the IR, and - The second band (λ2) is in the visible and / or near infrared. Tête selon la revendication 5, dans laquelle le deuxième capteur (5) est coudé d'un côté de la deuxième ligne de visée (BB) et lesté pour que la tête (1) soit équilibrée autour des deux axes (410) et (420).Head according to claim 5, wherein the second sensor (5) is bent on one side of the second line of sight (BB) and weighted so that the head (1) is balanced around the two axes (410) and (420). ). Tête selon l'une des revendications 1 à 6, adaptée pour un autodirecteur (2) de missile.Head according to one of claims 1 to 6, adapted for a homing missile (2). Autodirecteur (2) caractérisé en ce qu'il comporte une tête selon l'une des revendications 1 à 7.Self-steering device (2) characterized in that it comprises a head according to one of claims 1 to 7.
EP12162212.0A 2011-04-05 2012-03-29 Head for missile homing device and corresponding homing device Active EP2508836B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1101014A FR2973867B1 (en) 2011-04-05 2011-04-05 HEAD FOR SELF-DIRECTING MISSILE, AND SELF-DIRECTING CORRESPONDING

Publications (2)

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EP2508836A1 true EP2508836A1 (en) 2012-10-10
EP2508836B1 EP2508836B1 (en) 2013-11-20

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EP (1) EP2508836B1 (en)
FR (1) FR2973867B1 (en)
IL (1) IL219033A (en)

Cited By (2)

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Publication number Priority date Publication date Assignee Title
FR3059765A1 (en) * 2016-12-07 2018-06-08 Safran Electronics & Defense HEAD FOR SELF-DIRECTING
DE102012017452B4 (en) * 2012-09-04 2018-11-08 Mbda Deutschland Gmbh Seeker head with multi-mode features

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2846123B1 (en) * 2013-09-05 2019-08-07 MBDA Deutschland GmbH Seeker head with multi-mode properties

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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

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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 (en) * 2012-09-04 2018-11-08 Mbda Deutschland Gmbh Seeker head with multi-mode features
FR3059765A1 (en) * 2016-12-07 2018-06-08 Safran Electronics & Defense HEAD FOR SELF-DIRECTING

Also Published As

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

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