EP0915314A1 - Apparatus for guiding a flying device, especially a missile - Google Patents

Apparatus for guiding a flying device, especially a missile Download PDF

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Publication number
EP0915314A1
EP0915314A1 EP98402413A EP98402413A EP0915314A1 EP 0915314 A1 EP0915314 A1 EP 0915314A1 EP 98402413 A EP98402413 A EP 98402413A EP 98402413 A EP98402413 A EP 98402413A EP 0915314 A1 EP0915314 A1 EP 0915314A1
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EP
European Patent Office
Prior art keywords
guidance
images
missile
touch screen
flying object
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
EP98402413A
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German (de)
French (fr)
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EP0915314B1 (en
Inventor
Frédéric Naccache
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.)
Aerospatiale Matra
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Airbus Group SAS
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Filing date
Publication date
Application filed by Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0915314A1 publication Critical patent/EP0915314A1/en
Application granted granted Critical
Publication of EP0915314B1 publication Critical patent/EP0915314B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • 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
    • F41G7/30—Command link guidance systems
    • F41G7/32—Command link guidance systems for wire-guided missiles

Definitions

  • the present invention relates to a device for guidance of a flying object, in particular a missile.
  • said guide station includes a desk with a screen for viewing the generated images by said image sensor and a handle for controlling moving a pointing reticle on said screen.
  • the operator brings said aiming reticle to the selected point on said image, i.e. at the point to be reached by the flying object, for example the center of a target.
  • the pointing is accompanied generally of more or less damped oscillations around of the selected position, which of course leads a relatively long aiming time (about one second in the best of cases) and random precision.
  • the object of the present invention is to remedy these disadvantages. It relates to a guiding device a flying object, notably a missile, which allows a operator to carry out the guidance extremely quickly and precise.
  • the device for guidance of the aforementioned type is remarkable in that said guidance station includes a touch screen, on which the images generated by said sensor are viewed of images, the selection of said guide points being made by a specific contact of the touch screen to points considered, preferably either by means of a finger operator, either using an optical pen.
  • the transmission between the flying machine and the guidance station located on the ground is carried out by means of a hertzian connection and / or a fiber optic link.
  • Said guide device 1 is intended to guide a flying object, for example an M missile, on a target, in this case a C tank.
  • said guidance station 3 includes a flat ET touch screen, on which are viewed the I images generated by the image sensor 2, and the selection of a point P is carried out by a contact one-off touch screen AND, either directly by a finger D of the operator, of which a hand Ma is represented partially in broken lines, i.e. using an optical pen, not shown.
  • the calculation means 4 determine, continuously, guidance orders that move the missile M so as to bring a reticle R located in the center of the touch screen AND, at said selected point P and thus to guide missile M on target C.
  • the transmission of data between the missile M and the ground can be achieved either by means a fiber optic link, such as the L2 link, either by radio link, such as link L1.
  • said data transmission can be performed, either by separate means for both directions of transmission either by unique means double direction of transmission, which simplifies said device 1.
  • the image sensor 2 is mounted on the missile M.
  • said sensor of images 2 can also be arranged on the ground, for example at a shooting station not shown including also said guide station.

Abstract

La présente invention concerne un dispositif de guidage d'un engin volant (M), notamment un missile, comportant un capteur d'images (2) monté sur l'engin volant (M), des moyens de transmission de données, un poste de guidage (3) recevant les images (I) et permettant à un opérateur de sélectionner sur chaque image (I) un point de guidage (P) vers lequel il désire guider l'engin volant (M), et des moyens de calcul (4) qui déterminent des ordres de guidage de l'engin volant (M), à partir des points de guidage (P). Selon l'invention, le poste de guidage (3) comprend un écran tactile (ET), sur lequel sont visualisées les images (I), la sélection des points de guidage (P) étant réalisée par un contact ponctuel de l'écran tactile (ET). <IMAGE>The present invention relates to a device for guiding a flying object (M), in particular a missile, comprising an image sensor (2) mounted on the flying object (M), data transmission means, a guidance (3) receiving the images (I) and allowing an operator to select on each image (I) a guidance point (P) towards which he wishes to guide the flying object (M), and calculation means (4 ) which determine guidance orders for the flying object (M), from the guide points (P). According to the invention, the guidance station (3) comprises a touch screen (ET), on which the images (I) are displayed, the selection of the guidance points (P) being carried out by a point contact of the touch screen (AND). <IMAGE>

Description

La présente invention concerne un dispositif de guidage d'un engin volant, notamment un missile.The present invention relates to a device for guidance of a flying object, in particular a missile.

Plus précisément, la présente invention concerne un dispositif de guidage nécessitant une intervention humaine, à savoir un dispositif de guidage du type comportant :

  • un capteur d'images monté sur ledit engin volant ou agencé au sol et engendrant des images de l'environnement situé à l'avant dudit engin volant ;
  • des moyens de transmission de données ;
  • un poste de guidage recevant les images engendrées par ledit capteur d'images par l'intermédiaire desdits moyens de transmission de données et permettant à un opérateur de sélectionner sur chaque image un point de guidage vers lequel il désire guider ledit engin volant ; et
  • des moyens de calcul qui déterminent des ordres de guidage de l'engin volant, à partir des points de guidage ainsi sélectionnés, lesdits ordres de guidage étant transmis à des organes de guidage montés sur ledit engin volant.
More specifically, the present invention relates to a guidance device requiring human intervention, namely a guidance device of the type comprising:
  • an image sensor mounted on said flying vehicle or arranged on the ground and generating images of the environment located in front of said flying vehicle;
  • data transmission means;
  • a guidance station receiving the images generated by said image sensor via said data transmission means and allowing an operator to select on each image a guidance point towards which he wishes to guide said flying machine; and
  • calculation means which determine guidance orders for the flying object, from the guide points thus selected, said guidance orders being transmitted to guide members mounted on said flying object.

On sait que pour le guidage d'armes volantes telles que des missiles antichar par exemple, on recherche de plus en plus une intervention humaine, puisque seule une telle intervention permet de gérer efficacement les situations de plus en plus complexes (comme une identification entre des intervenants amis, ennemis et neutres) apparaissant dans les conflits présents et/ou futurs (crise politique, opération de maintien de la paix, ...).We know that for the guidance of flying weapons such that anti-tank missiles for example, we are looking for more and more human intervention, since only one such intervention makes it possible to manage situations effectively more and more complex (as an identification between friendly, enemy and neutral stakeholders) appearing in present and / or future conflicts (crisis political, peacekeeping operation, ...).

Généralement, ledit poste de guidage comprend un pupitre muni d'un écran pour visualiser les images engendrées par ledit capteur d'images et un manche pour commander le déplacement d'un réticule de pointage sur ledit écran. Pour réaliser le guidage de l'engin volant, l'opérateur amène ledit réticule de pointage au point sélectionné sur ladite image, c'est-à-dire au point à atteindre par l'engin volant, par exemple le centre d'une cible.Generally, said guide station includes a desk with a screen for viewing the generated images by said image sensor and a handle for controlling moving a pointing reticle on said screen. To guide the flying machine, the operator brings said aiming reticle to the selected point on said image, i.e. at the point to be reached by the flying object, for example the center of a target.

Toutefois, un tel mode de guidage présente de nombreux inconvénients, et notamment une manipulation délicate et une optimisation difficile et lente.However, such a guidance mode has many disadvantages, including delicate handling and difficult and slow optimization.

En effet, comme l'opérateur trouve souvent difficilement la relation entre l'effort qu'il exerce sur le manche et la vitesse et l'amplitude de déplacement du réticule de pointage sur l'écran, le pointage s'accompagne généralement d'oscillations plus ou moins amorties autour de la position sélectionnée, ce qui entraíne bien entendu un temps de pointage relativement long (d'environ une seconde dans le meilleur des cas) et une précision aléatoire.Indeed, as the operator often finds it difficult the relationship between the effort it exerts on the stick and the speed and range of displacement of the reticle pointing on the screen, the pointing is accompanied generally of more or less damped oscillations around of the selected position, which of course leads a relatively long aiming time (about one second in the best of cases) and random precision.

La présente invention a pour objet de remédier à ces inconvénients. Elle concerne un dispositif de guidage d'un engin volant, notamment un missile, qui permet à un opérateur de réaliser le guidage de façon extrêmement rapide et précise.The object of the present invention is to remedy these disadvantages. It relates to a guiding device a flying object, notably a missile, which allows a operator to carry out the guidance extremely quickly and precise.

A cet effet, selon l'invention, le dispositif de guidage du type précité est remarquable en ce que ledit poste de guidage comprend un écran tactile, sur lequel sont visualisées les images engendrées par ledit capteur d'images, la sélection desdits points de guidage étant réalisée par un contact ponctuel de l'écran tactile aux points considérés, de préférence soit au moyen d'un doigt de l'opérateur, soit à l'aide d'un stylo optique.To this end, according to the invention, the device for guidance of the aforementioned type is remarkable in that said guidance station includes a touch screen, on which the images generated by said sensor are viewed of images, the selection of said guide points being made by a specific contact of the touch screen to points considered, preferably either by means of a finger operator, either using an optical pen.

Ainsi, grâce à l'invention, on obtient notamment les avantages suivants :

  • une réduction du temps de pointage, puisque le doigt de l'opérateur ou le stylo optique va directement sur le point choisi, ce qui permet de remédier aux problèmes d'oscillations du pointage existant dans la solution usuelle précitée ; et
  • une augmentation de la précision du pointage, notamment lorsqu'on utilise un crayon optique, dont l'extrémité est plus fine que celle d'un doigt.
Thus, thanks to the invention, the following advantages are obtained in particular:
  • a reduction in pointing time, since the operator's finger or the optical pen goes directly to the point chosen, which makes it possible to remedy the problems of pointing oscillations existing in the usual solution mentioned above; and
  • an increase in pointing accuracy, especially when using an optical pencil, the end of which is finer than that of a finger.

De plus, il est possible de laisser glisser le doigt ou le crayon optique sur l'écran pour permettre le suivi d'un objectif mobile, en temps réel, ce qui permet notamment de s'affranchir d'une poursuite automatique de la cible par traitement d'images et donc de simplifier énormément les algorithmes des moyens de calcul et ainsi de réduire le coût du guidage.In addition, it is possible to let the finger or the optical pencil on the screen to allow the tracking a mobile goal, in real time, which allows notably to get rid of an automatic pursuit of the target by image processing and therefore to simplify enormously the algorithms of the computing means and so reduce the cost of guidance.

Par ailleurs, de façon avantageuse, la transmission de données entre l'engin volant et le poste de guidage situé au sol est réalisée au moyen d'une liaison hertzienne et/ou d'une liaison à fibre optique.Furthermore, advantageously, the transmission between the flying machine and the guidance station located on the ground is carried out by means of a hertzian connection and / or a fiber optic link.

L'unique figure du dessin annexé fera bien comprendre comment l'invention peut être réalisée. Elle montre schématiquement un dispositif de guidage conforme à l'invention.The single figure in the attached drawing will make it clear how the invention can be realized. She shows schematically a guide device according to the invention.

Ledit dispositif de guidage 1 est destiné à guider un engin volant, par exemple un missile M, sur une cible, en l'occurrence un char C.Said guide device 1 is intended to guide a flying object, for example an M missile, on a target, in this case a C tank.

A cet effet, ledit dispositif 1 est du type comportant :

  • un capteur d'images 2 monté à l'avant du missile M en étant centré sur son axe longitudinal et engendrant des images I de l'environnement qui est situé vers l'avant du missile M et qui comprend notamment ladite cible C ;
  • des moyens de transmission de données, non représentés, qui sont susceptibles de transmettre des données du missile M vers le sol, comme illustré par une liaison L1, et en sens inverse, comme illustré par une liaison L2 ;
  • un poste de guidage 3 disposé au sol, recevant les images I engendrées par ledit capteur d'images 2 et permettant à un opérateur de sélectionner sur chaque image I, le point P vers lequel il désire guider ledit missile M, par exemple le centre de la cible C ; et
  • des moyens de calcul 4 qui sont reliés par une liaison 5 audit poste de guidage 3 et qui déterminent des ordres de guidage du missile M à partir des points P sélectionnés par l'opérateur, lesdits ordres de guidage étant transmis à des organes de guidage 6A, 6B de type usuel du missile M par l'intermédiaire de la liaison L2.
To this end, said device 1 is of the type comprising:
  • an image sensor 2 mounted at the front of the missile M while being centered on its longitudinal axis and generating images I of the environment which is located towards the front of the missile M and which comprises in particular said target C;
  • data transmission means, not shown, which are capable of transmitting data from the missile M to the ground, as illustrated by a link L1, and in the opposite direction, as illustrated by a link L2;
  • a guidance station 3 arranged on the ground, receiving the images I generated by said image sensor 2 and allowing an operator to select on each image I, the point P towards which he wishes to guide said missile M, for example the center of target C; and
  • calculation means 4 which are connected by a link 5 to said guidance station 3 and which determine guidance orders for the missile M from the points P selected by the operator, said guidance orders being transmitted to guidance members 6A , 6B of the usual type of missile M via the link L2.

Selon l'invention, notamment pour obtenir un pointage précis et rapide du point P, ledit poste de guidage 3 comprend un écran tactile plat ET, sur lequel sont visualisées les images I engendrées par le capteur d'images 2, et la sélection d'un point P est réalisée par un contact ponctuel dudit écran tactile ET, soit directement par un doigt D de l'opérateur, dont une main Ma est représentée partiellement en traits interrompus, soit à l'aide d'un stylo optique non représenté.According to the invention, in particular for obtaining a score precise and fast from point P, said guidance station 3 includes a flat ET touch screen, on which are viewed the I images generated by the image sensor 2, and the selection of a point P is carried out by a contact one-off touch screen AND, either directly by a finger D of the operator, of which a hand Ma is represented partially in broken lines, i.e. using an optical pen, not shown.

Les moyens de calcul 4 déterminent alors, en continu, des ordres de guidage qui permettent de déplacer le missile M de manière à amener un réticule R situé au centre de l'écran tactile ET, audit point P sélectionné et ainsi à guider le missile M sur la cible C.The calculation means 4 then determine, continuously, guidance orders that move the missile M so as to bring a reticle R located in the center of the touch screen AND, at said selected point P and thus to guide missile M on target C.

Selon l'invention, la transmission de données entre le missile M et le sol peut être réalisée, soit au moyen d'une liaison à fibre optique, telle que la liaison L2, soit au moyen d'une liaison hertzienne, telle que la liaison L1.According to the invention, the transmission of data between the missile M and the ground can be achieved either by means a fiber optic link, such as the L2 link, either by radio link, such as link L1.

De plus, ladite transmission de données peut être effectuée, soit par des moyens séparés pour les deux sens de transmission, soit par des moyens uniques à double sens de transmission, ce qui permet de simplifier ledit dispositif 1.In addition, said data transmission can be performed, either by separate means for both directions of transmission either by unique means double direction of transmission, which simplifies said device 1.

Dans le mode de réalisation précisé ci-dessus, le capteur d'images 2 est monté sur le missile M. Toutefois, dans le cadre de la présente invention, ledit capteur d'images 2 peut également être agencé au sol, par exemple au niveau d'un poste de tir non représenté comprenant également ledit poste de guidage.In the embodiment specified above, the image sensor 2 is mounted on the missile M. However, in the context of the present invention, said sensor of images 2 can also be arranged on the ground, for example at a shooting station not shown including also said guide station.

Claims (6)

Dispositif de guidage d'un engin volant (M), notamment un missile, du type comportant : un capteur d'images (2) engendrant des images (I) de l'environnement situé à l'avant dudit engin volant (M) ; des moyens de transmission de données ; un poste de guidage (3) recevant les images (I) engendrées par ledit capteur d'images (2) par l'intermédiaire desdits moyens de transmission de données et comportant un écran tactile (ET) ; et des moyens de calcul (4) qui sont reliés audit poste de guidage (3) et qui déterminent des ordres de guidage de l'engin volant (M), lesdits ordres de guidage étant transmis à des organes de guidage (6A, 6B) montés sur ledit engin volant (M), caractérisé en ce que ledit écran tactile (ET) est formé de manière à visualiser les images (I) engendrées par ledit capteur d'images (2) et à permettre à un opérateur de sélectionner, par un contact ponctuel dudit écran tactile (ET), un point de guidage (P) vers lequel il désire guider ledit engin volant (M).Device for guiding a flying object (M), in particular a missile, of the type comprising: an image sensor (2) generating images (I) of the environment located at the front of said flying vehicle (M); data transmission means; a guidance station (3) receiving the images (I) generated by said image sensor (2) via said data transmission means and comprising a touch screen (ET); and calculation means (4) which are connected to said guidance station (3) and which determine guidance orders for the flying object (M), said guidance orders being transmitted to mounted guide members (6A, 6B) on said flying object (M), characterized in that said touch screen (ET) is formed so as to display the images (I) generated by said image sensor (2) and to allow an operator to select, by one-off contact of said touch screen (ET) , a guide point (P) to which it wishes to guide said flying machine (M). Dispositif selon la revendication 1,
caractérisé en ce que ledit écran tactile (ET) est un écran plat.Device according to claim 1,
characterized in that said touch screen (ET) is a flat screen. Dispositif selon l'une des revendications 1 ou 2,
caractérisé en ce que ledit contact ponctuel est réalisé directement par un doigt (D) de l'opérateur.Device according to one of claims 1 or 2,
characterized in that said point contact is made directly by a finger (D) of the operator. Dispositif selon l'une des revendications 1 ou 2,
caractérisé en ce que ledit contact ponctuel est réalisé par l'intermédiaire d'un crayon optique.Device according to one of claims 1 or 2,
characterized in that said point contact is made by means of an optical pencil. Dispositif selon l'une quelconque des revendications 1 à 4,
caractérisé en ce que la transmission de données entre l'engin volant (M) et le poste de guidage (3) situé au sol est réalisée au moins au moyen d'une liaison hertzienne (L1). Device according to any one of Claims 1 to 4,
characterized in that the data transmission between the flying machine (M) and the guidance station (3) located on the ground is carried out at least by means of a radio link (L1). Dispositif selon l'une quelconque des revendications 1 à 5,
caractérisé en ce que la transmission de données entre l'engin volant (M) et le poste de guidage (3) situé au sol est réalisée au moins au moyen d'une liaison à fibre optique (L2).Device according to any one of Claims 1 to 5,
characterized in that the data transmission between the flying machine (M) and the guidance station (3) located on the ground is carried out at least by means of a fiber optic link (L2).
EP98402413A 1997-10-10 1998-10-01 Apparatus for guiding a flying device, especially a missile Expired - Lifetime EP0915314B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9712667 1997-10-10
FR9712667A FR2769699B1 (en) 1997-10-10 1997-10-10 GUIDING DEVICE FOR A FLYING MACHINE, ESPECIALLY A MISSILE

Publications (2)

Publication Number Publication Date
EP0915314A1 true EP0915314A1 (en) 1999-05-12
EP0915314B1 EP0915314B1 (en) 2003-03-26

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EP98402413A Expired - Lifetime EP0915314B1 (en) 1997-10-10 1998-10-01 Apparatus for guiding a flying device, especially a missile

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US (1) US6142410A (en)
EP (1) EP0915314B1 (en)
DE (1) DE69812537T2 (en)
FR (1) FR2769699B1 (en)
IL (1) IL126396A (en)

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EP1391681A1 (en) * 2002-08-20 2004-02-25 Diehl Munitionssysteme GmbH & Co. KG Method and device for real time ground reconnaissance

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US6978717B1 (en) * 2004-08-16 2005-12-27 The United States Of America As Represented By The Secretary Of The Army Infrared camera deployed by grenade launcher
FR2875613B1 (en) * 2004-09-23 2007-03-16 Giat Ind Sa HUMAN MACHINE INTERFACE OF A THREAT TREATMENT SYSTEM
US7968831B2 (en) * 2007-06-12 2011-06-28 The Boeing Company Systems and methods for optimizing the aimpoint for a missile
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DE102014019199A1 (en) 2014-12-19 2016-06-23 Diehl Bgt Defence Gmbh & Co. Kg automatic weapon
JP2022511815A (en) * 2018-12-05 2022-02-01 テレフオンアクチーボラゲット エルエム エリクソン（パブル） Object targeting

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EP1391681A1 (en) * 2002-08-20 2004-02-25 Diehl Munitionssysteme GmbH & Co. KG Method and device for real time ground reconnaissance

Also Published As

Publication number Publication date
US6142410A (en) 2000-11-07
DE69812537D1 (en) 2003-04-30
EP0915314B1 (en) 2003-03-26
FR2769699B1 (en) 1999-12-10
IL126396A0 (en) 1999-05-09
DE69812537T2 (en) 2004-02-12
FR2769699A1 (en) 1999-04-16
IL126396A (en) 2001-10-31

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