EP1600728B1 - Airborne vehicle for ground observation - Google Patents

Airborne vehicle for ground observation Download PDF

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Publication number
EP1600728B1
EP1600728B1 EP05291021A EP05291021A EP1600728B1 EP 1600728 B1 EP1600728 B1 EP 1600728B1 EP 05291021 A EP05291021 A EP 05291021A EP 05291021 A EP05291021 A EP 05291021A EP 1600728 B1 EP1600728 B1 EP 1600728B1
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Prior art keywords
flying object
elongate body
motor
lift
nozzles
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EP05291021A
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German (de)
French (fr)
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EP1600728A1 (en
Inventor
Bernard Teneze
Michel Blin
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MBDA France SAS
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MBDA France SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/365—Projectiles transmitting information to a remote location using optical or electronic means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust

Definitions

  • the flying vehicle 1 can be propelled and directed on this target 21, by the rear 2R of the elongate body 2, or by the nozzles 4 and 6 in positions 7 and 8 (embodiment examples I and IV), either by the fixed nozzles 9 and 10 (embodiment II), or else by the additional propellant 11 and the nozzle 13 (embodiment III) ).
  • a recognition and attack process which more specifically corresponds to a bell-destroying fire of a masked target whose existence was probable, is illustrated in FIG.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical & Material Sciences (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Geophysics And Detection Of Objects (AREA)
  • Earth Drilling (AREA)
  • Jib Cranes (AREA)
  • Investigating, Analyzing Materials By Fluorescence Or Luminescence (AREA)
  • Analysing Materials By The Use Of Radiation (AREA)

Abstract

The machine has a lifting and displacing propulsive unit (3) and an altitude propulsive unit (5) which are placed on both sides of centre of gravity of the machine. The position of the centre of gravity remains fixed, during the combustion of propulsive loads of the propulsive units. The unit (3) has a mass less than that of the unit (5) and close to the centre of gravity of the machine.

Description

La présente invention concerne un engin volant pour l'observation du sol, comportant un corps allongé et pouvant être utilisé pour l'attaque de cibles terrestres, notamment masquées par un obstacle. Un tel engin est décrit par DE-A-3 313 648.The present invention relates to a flying machine for the observation of the ground, comprising an elongate body and can be used for the attack of terrestrial targets, in particular masked by an obstacle. Such a machine is described by DE-A-3,313,648.

On connaît déjà des engins volants pour l'observation du sol se présentant généralement sous la forme d'un petit avion sans pilote (drone). De tels engins volants sont relativement vulnérables et sont des cibles faciles pour les moyens de défense antiaérienne ennemis et, de plus, ils doivent être continuellement en mouvement et ne peuvent donc pas s'arrêter pour observer avec soin une zone particulière d'un terrain. Pour éviter ce dernier inconvénient, on a déjà pensé à réaliser des drones sous forme de petits hélicoptères. Toutefois, ces derniers sont également très vulnérables.Flying machines for ground observation are already known, usually in the form of a small unmanned aircraft (drone). Such flying machines are relatively vulnerable and easy targets for enemy anti-aircraft defenses and, moreover, they must be continuously moving and therefore can not stop to carefully observe a particular area of a terrain. To avoid this last disadvantage, we have already thought to make drones in the form of small helicopters. However, they are also very vulnerable.

Par ailleurs, quelle que soit la forme de ces drones connus, avion ou hélicoptère, ils ne peuvent servir qu'à la reconnaissance et non pas à l'attaque des cibles ennemies qu'ils peuvent découvrir et observer.Moreover, whatever the form of these known drones, plane or helicopter, they can only serve the recognition and not the attack of enemy targets they can discover and observe.

La présente invention a pour objet de remédier à ces inconvénients.The present invention aims to overcome these disadvantages.

A cette fin, selon l'invention, l'engin volant pour l'observation du sol, comportant un corps allongé, est remarquable :

  • en ce qu'il comporte :
    • . un propulseur de sustentation et de déplacement, du type à charge propulsive combustible, associé à des premières tuyères d'échappement, dirigées vers l'arrière dudit corps allongé et réparties latéralement autour de celui-ci, engendrant des forces de manoeuvre latérales dont les lignes d'action passent par le centre de gravité dudit engin volant, lesdites forces étant aptes à assurer la sustentation et les déplacements dudit engin volant dans une position d'observation pour laquelle celui-ci est au moins approximativement vertical avec l'extrémité arrière dudit engin volant dirigée vers le bas ;
    • . un propulseur d'attitude, du type à charge propulsive combustible, associé à des deuxièmes tuyères d'échappement, dirigées du côté arrière dudit corps allongé et réparties latéralement autour de celui-ci, engendrant des forces de manoeuvre latérales aptes à maintenir ledit engin volant dans ladite position d'observation au moins approximativement verticale ; et
    • . des moyens de prise de vues, disposés à l'arrière dudit corps allongé et aptes à observer ledit sol lorsque ledit engin volant est dans ladite position d'observation au moins approximativement verticale ; et
  • en ce que ledit propulseur de sustentation et de déplacement et ledit propulseur d'attitude sont disposés de part et d'autre dudit centre de gravité de l'engin volant et en ce que, lors de la combustion des charges propulsives respectives de ces deux derniers propulseurs, la position dudit centre de gravité reste au moins approximativement fixe.
To this end, according to the invention, the flying machine for the observation of the ground, comprising an elongated body, is remarkable:
  • in that it comprises:
    • . a fuel propellant type lift and displacement propellant associated with first exhaust nozzles, directed rearwardly of said elongate body and laterally distributed thereabout, generating lateral maneuvering forces whose lines the center of gravity of said flying machine, said forces being capable of providing lift and displacing said flying machine in an observation position for which it is at least approximately vertical with the rear end of said flying machine directed downwards;
    • . an attitude propellant, of the type with a combustible propellant charge, associated with second exhaust nozzles, directed on the rear side of said elongated body and distributed laterally around it, generating lateral maneuvering forces able to maintain said flying machine in said at least approximately vertical observation position; and
    • . camera means arranged at the rear of said elongate body and adapted to observe said ground when said flying machine is in said at least approximately vertical viewing position; and
  • in that said lift and displacement propellant and said attitude propellant are disposed on either side of said center of gravity of the flying machine and in that, during the combustion of the respective propulsive charges of the latter two thrusters, the position of said center of gravity remains at least approximately fixed.

Ainsi, dans l'engin volant conforme à l'invention, la sustentation et le déplacement, d'une part, et l'attitude, d'autre part, sont commandés par deux propulseurs distincts dédiés uniquement à leur fonction respective, ce qui permet une grande précision dans le suivi de la trajectoire de l'engin volant et dans la présentation verticale de celui-ci par rapport au sol, ce qui le rend moins vulnérable aux défenses antiaériennes terrestres d'un ennemi et lui permet d'observer, avec soin et au ralenti, toute zone suspecte du terrain, par exemple masquée derrière un obstacle.Thus, in the flying machine according to the invention, the lift and the displacement, on the one hand, and the attitude, on the other hand, are controlled by two separate thrusters dedicated solely to their respective function, which allows great precision in tracking the trajectory of the flying machine and in the vertical presentation of it in relation to the ground, which makes it less vulnerable to an enemy's land-based anti-aircraft defenses and enables him to observe, with care and idling, any suspected area of the ground, for example hidden behind an obstacle.

De plus, on remarquera que, du fait de la quasi-coïncidence du centre de gravité, du point de pilotage du propulseur de sustentation et de déplacement (pilotage en force) et du centre aérodynamique, ce dernier propulseur, ainsi que les forces aérodynamiques transversales -y compris les rafales de vent- n'ont que peu d'influence sur l'attitude.In addition, it will be noted that, due to the quasi-coincidence of the center of gravity, the steering point of the lift and displacement propeller (piloting force) and the aerodynamic center, the latter propellant, as well as transverse aerodynamic forces - including wind gusts - have little influence on attitude.

Avantageusement, ledit propulseur de sustentation et de déplacement présente une masse plus importante que ledit propulseur d'attitude et est plus proche du centre de gravité de l'engin volant que ce dernier. Ledit propulseur d'attitude peut être disposé à l'arrière dudit corps allongé, alors que ledit propulseur de sustentation et de déplacement est disposé juste en avant du centre de gravité dudit engin volant.Advantageously, said lift and displacement propeller has a larger mass than said attitude thruster and is closer to the center of gravity of the flying machine than the latter. Said attitude thruster may be disposed at the rear of said elongate body, while said thrust and displacement propellant is disposed just in front of the center of gravity of said flying machine.

Pour permettre auxdits moyens de prise de vues d'engendrer des images nettes du sol observé, il est nécessaire de contrôler le roulis de l'engin volant selon la présente invention. Puisque le propulseur de sustentation et de déplacement exerce des fonctions moins sensibles que le propulseur d'attitude, il est préférable que ce soit ce premier propulseur qui contrôle le roulis dudit engin volant.To enable said imaging means to generate sharp images of the observed ground, it is necessary to control the roll of the flying machine according to the present invention. Since the levitation and displacement propeller exerts less sensitive functions than the attitude propeller, it is preferable that it is this first thruster that controls the roll of said flying machine.

De préférence, l'engin volant selon l'invention est lancé, de façon connue pour certains missiles d'attaque, par un poste de lancement et de commande comportant un système de propulsion ou d'éjection qui lui est propre et qui n'est pas porté par ledit engin volant. Ainsi, on peut supprimer dudit engin volant selon l'invention le propulseur arrière généralement chargé du lancement et disposer, à la place dudit propulseur arrière, lesdits moyens de prise de vues.Preferably, the flying machine according to the invention is launched, in a manner known for certain attack missiles, by a launching and control station comprising a propulsion or ejection system of its own and which is not not worn by said flying machine. Thus, one can remove said flying machine according to the invention the rear thruster generally loaded launch and have, in place of said rear thruster, said means for shooting.

Après son lancement, ledit engin volant peut voler de façon autonome, par exemple pour réaliser un plan de vol préétabli. En variante, l'engin volant conforme à la présente invention peut comporter des moyens de liaison avec ledit poste de lancement et de commande. Ainsi, il peut éventuellement recevoir des informations dudit poste ou faire effectuer des calculs par ce dernier, ce qui permet d'alléger ledit engin volant. De préférence, lesdits moyens de liaison comportent, de façon connue, au moins une fibre optique, dévidable à partir dudit engin volant. Ainsi, les informations circulant entre l'engin volant et ledit poste ne peuvent être brouillées.After its launch, said flying machine can fly autonomously, for example to achieve a pre-established flight plan. Alternatively, the flying machine according to the present invention may comprise connecting means with said launching and control station. Thus, it may possibly receive information from said station or have it perform calculations by the latter, which allows to lighten said flying machine. Preferably, said connecting means comprise, in known manner, at least one optical fiber, unwindable from said flying machine. Thus, information circulating between the flying machine and the said station can not be scrambled.

Notamment, pour faciliter ses déplacements au-dessus du terrain observé, l'engin volant selon l'invention peut comporter des moyens de prise de vues supplémentaires disposés à l'avant du corps allongé.In particular, to facilitate its movements over the observed terrain, the flying vehicle according to the invention may include additional shooting means arranged in front of the elongate body.

Dans un mode de réalisation avantageux, l'engin volant conforme à la présente invention porte une charge militaire et il comporte des moyens de propulsion et des moyens de guidage lui permettant d'attaquer, de préférence sans retournement, c'est-à-dire par sa partie arrière, une cible détectée par lesdits moyens de prise de vues arrière. L'attaque de ladite cible peut être commandée, soit à partir du poste de lancement et de commande auquel les images de la cible sont transmises par lesdits moyens de liaison, soit automatiquement par un dispositif de reconnaissance de cible porté par ledit engin volant.In an advantageous embodiment, the flying machine according to the present invention carries a military load and it comprises propulsion means and guide means allowing it to attack, preferably without reversal, that is to say by its rear part, a target detected by said rear-view means. The attack of said target can be controlled either from the launching and control station to which the images of the target are transmitted by said connecting means, or automatically by a target recognition device carried by said flying machine.

Lesdits moyens de propulsion et lesdits moyens de guidage dudit engin en direction de la cible détectée peuvent être indépendants dudit propulseur de sustentation et de déplacement et dudit propulseur d'attitude. Dans ce cas, lesdits moyens de propulsion et lesdits moyens de guidage dudit engin en direction de la cible peuvent être constitués par un propulseur supplémentaire disposé à l'avant dudit corps allongé. Un tel propulseur supplémentaire peut être du type à charge propulsive combustible, éventuellement pourvu d'une tuyère orientable. Il est préférable que ledit propulseur supplémentaire soit déposé derrière une coiffe largable dudit engin volant.Said propulsion means and said means for guiding said machine towards the detected target may be independent of said lift and displacement propellant and said attitude thruster. In this case, said propulsion means and said means for guiding said machine towards the target may be constituted by an additional thruster disposed in front of said elongated body. Such an additional thruster may be of the type with a combustible propellant charge, possibly provided with a steerable nozzle. It is preferable that said additional thruster is deposited behind a releasable cap of said flying machine.

En variante, lesdits moyens de propulsion et lesdits moyens de guidage dudit engin en direction de la cible détectée sont respectivement formés par ledit propulseur de sustentation et de déplacement et par ledit propulseur d'attitude, associés respectivement à des troisièmes et à des quatrièmes tuyères, dirigées vers l'avant dudit corps allongé et réparties latéralement autour de celui-ci. Lesdites premières et deuxièmes tuyères peuvent être orientables et former lesdites troisièmes et quatrièmes tuyères lorsqu'elles sont orientées vers l'avant dudit corps allongé. En variante, lesdites troisièmes et quatrièmes tuyères peuvent être fixes et alimentées en gaz de propulsion par ledit propulseur de sustentation et de déplacement et par ledit propulseur d'attitude, grâce à des systèmes de commutation d'alimentation disposés aux sorties respectives dudit propulseur de sustentation et de déplacement et dudit propulseur d'attitude et permettant d'alimenter soit lesdites premières et deuxièmes tuyères, soit lesdites troisièmes et quatrièmes tuyères.As a variant, said propulsion means and said means for guiding said machine towards the detected target are respectively formed by said lift and displacement propellant and by said attitude propeller, respectively associated with third and fourth nozzles, directed forward of said elongate body and distributed laterally around it. Said first and second nozzles may be orientable and form said third and fourth nozzles as they face towards the front of said elongated body. Alternatively, said third and fourth nozzles can be fixed and supplied with propellant gas by said lift and displacement propellant and by said attitude thruster, through power switching systems arranged at the respective outputs of said lift propellant. and displacement and said attitude thruster and for feeding either said first and second nozzles, or said third and fourth nozzles.

Les figures du dessin annexé feront bien comprendre comment l'invention peut être réalisée. Sur ces figures, des références identiques désignent des éléments semblables.The figures of the appended drawing will make it clear how the invention can be realized. In these figures, identical references designate similar elements.

Les figures 1 à 4 montrent schématiquement quatre modes de réalisation de l'engin volant conforme à la présente invention.Figures 1 to 4 show schematically four embodiments of the flying machine according to the present invention.

Les figures 5 et 6 illustrent schématiquement deux exemples de vol dudit engin volant.Figures 5 and 6 schematically illustrate two examples of theft of said flying craft.

Sur les figures 1 à 4, on a représenté schématiquement quatre exemples de réalisation I à IV de l'engin volant 1 conforme à la présente invention.FIGS. 1 to 4 schematically show four embodiments I to IV of the flying machine 1 according to the present invention.

Chacun de ces exemples de réalisation comporte un corps allongé 2, par exemple cylindrique, d'axe longitudinal L-L, présentant un avant 2A et un arrière 2R et enfermant :

  • ― un propulseur de sustentation et de déplacement 3, du type à charge propulsive combustible, comportant des tuyères d'échappement 4 pour les gaz de combustion, par exemple au nombre de 4, équiréparties latéralement autour dudit corps allongé 2 et dirigées vers l'arrière 2R de celui-ci. Les axes des tuyères 4 passent par le centre de gravité CG dudit engin volant 1, de sorte que le propulseur 3 engendre des forces de manoeuvre latérales dont les lignes d'action passent également par ledit centre de gravité. Ces forces de manoeuvre sont commandables, de façon connue, par exemple par des déviateurs de jet mobiles, pouvant prendre au moins deux positions, de préférence trois, aptes à obturer au moins partiellement ou à dégager complètement lesdites tuyères 4. Ainsi, comme cela est connu pour certains missiles, ledit engin volant 1 est pilotable "en force" par le propulseur 3 ; et
  • ― un propulseur d'attitude 5, également du type à charge propulsive combustible, comportant des tuyères d'échappement 6 pour les gaz de combustion, distantes du centre de gravité CG et étant par exemple également au nombre de 4, équiréparties latéralement autour dudit corps allongé 2 et dirigées vers l'arrière 2R de celui-ci. Le propulseur d'attitude 5 engendre donc des forces de manoeuvre latérales commandables, de façon connue, par exemple par des déviateurs de jets mobiles, également à au moins deux positions, de préférence trois, aptes à obturer au moins partiellement ou à dégager complètement lesdites tuyères 6. Les tuyères 6 étant distantes du centre de gravité CG, le propulseur d'attitutde 5 exerce un pilotage "en couple" sur l'engin volant 1.
Each of these exemplary embodiments comprises an elongate body 2, for example cylindrical, of longitudinal axis LL, having a front 2A and a rear 2R and enclosing:
  • A thrust and displacement thruster 3, of the type with a combustible propellant charge, comprising exhaust nozzles 4 for the combustion gases, for example four in number, equidistributed laterally around said elongate body 2 and directed towards the rear 2R of it. The axes of the nozzles 4 pass through the center of gravity CG of said flying vehicle 1, so that the thruster 3 generates forces of lateral maneuvers whose lines of action also pass through said center of gravity. These actuating forces are controllable, in known manner, for example by mobile jet deflectors, which can take at least two positions, preferably three, able to at least partially close or to completely clear said nozzles 4. Thus, as is known for some missiles, said flying machine 1 is controllable "in force" by the thruster 3; and
  • An attitude propellant 5, also of the type with a combustible propellant charge, comprising exhaust nozzles 6 for the combustion gases, distant from the center of gravity CG and being for example also 4 in number, equidistributed laterally around said body lying 2 and directed backwards 2R of it. The attitude thruster 5 therefore generates controllable lateral actuating forces, in known manner, for example by moving jet deflectors, also at at least two positions, preferably three, able to close at least partially or to completely clear said Nozzles 6. As the nozzles 6 are spaced from the center of gravity CG, the drive propulsion unit 5 exerts "torque" steering on the flying machine 1.

Les propulseurs 3 et 5 sont disposés de part et d'autre du centre de gravité CG de l'engin volant et le propulseur 3 est plus lourd que le propulseur 5 et plus proche du centre de gravité CG que ce dernier. La combustion des charges propulsives combustibles de ces propulseurs est réglée pour que, lorsque les propulseurs 3 et 5 fonctionnent, la position du centre de gravité CG reste au moins sensiblement fixe.The thrusters 3 and 5 are disposed on either side of the center of gravity CG of the flying machine and the thruster 3 is heavier than the thruster 5 and closer to the center of gravity CG than the latter. The combustion of the propellant fuel charges of these thrusters is adjusted so that, when the thrusters 3 and 5 operate, the position of the center of gravity CG remains at least substantially fixed.

Dans les exemples de réalisation I (figure 1) et IV (figure 4) de l'engin volant 1, les tuyères 4 et 6 sont orientables, comme cela est illustré par les flèches, et peuvent prendre respectivement des positions 7 et 8 dirigées vers l'avant 2A du corps allongé 2, comme indiqué en pointillés.In the exemplary embodiments I (FIG. 1) and IV (FIG. 4) of the flying vehicle 1, the nozzles 4 and 6 are orientable, as illustrated by the arrows, and can respectively take positions 7 and 8 directed towards the front 2A of the elongate body 2, as shown in dashed lines.

Dans l'exemple de réalisation II (figure 2), le propulseur de sustentation et de déplacement 3 comporte, en plus des tuyères 4, des tuyères fixes 9, équiréparties latéralement autour dudit corps allongé 2 et dirigées vers l'avant 2A de celui-ci. Grâce à des moyens de commutation commandables connus, le propulseur de sustentation et de déplacement 3 peut alimenter en gaz de combustion, soit les tuyères 4, soit les tuyères fixes 9. De même, le propulseur d'attitude 5 comporte, en plus des tuyères 6, des tuyères fixes 10, équiréparties latéralement autour du corps allongé 2 et dirigées vers l'avant 2A de celui-ci. Grâce à des moyens de commutation commandables connus, le propulseur d'attitude 5 peut alimenter en gaz de combustion, soit les tuyères 6, soit les tuyères fixes 10.In the embodiment example II (FIG. 2), the lift and displacement propellant 3 comprises, in addition to the nozzles 4, fixed nozzles 9 equidistributed laterally around said elongate body 2 and directed towards the front 2A of the latter. this. Thanks to known controllable switching means, the lift and displacement thruster 3 can supply combustion gases, either the nozzles 4 or the fixed nozzles 9. Similarly, the attitude booster 5 comprises, in addition to the nozzles 6, fixed nozzles 10, equidistributed laterally around the elongate body 2 and directed forward 2A thereof. Thanks to known controllable switching means, the attitude booster 5 can supply combustion gases, either the nozzles 6 or the fixed nozzles 10.

Dans l'exemple de réalisation III (figure 3), l'engin volant 1 comporte un propulseur supplémentaire 11, par exemple du type à charge propulsive combustible, disposé à l'avant 2A du corps allongé 2, par exemple derrière une coiffe largable 12 de ce dernier. Le propulseur supplémentaire 11 est pourvu d'une tuyère axiale 13, de préférence orientable, dirigée du côté de l'avant 2A du corps allongé 2.In the exemplary embodiment III (FIG. 3), the flying machine 1 comprises an additional propellant 11, for example of the type with a combustible propellant charge, disposed at the front 2A of the elongate body 2, for example behind a releasable cap 12 of the last. The additional propellant 11 is provided with an axial nozzle 13, preferably orientable, directed towards the front 2A of the elongate body 2.

Dans tous les exemples de réalisation I à IV, l'engin volant 1 comporte, à l'arrière 2R du corps allongé 2, une caméra 14 protégée par une coiffe 15, transparente aux rayonnements auxquels la caméra 14 est sensible. De plus, tous ces exemples de réalisation I à IV comportent, de façon connue pour les missiles, une charge militaire, un système électronique de commande de vol (non représenté) et une réserve dévidable (non représentée) d'une fibre optique 16.In all embodiments I to IV, the flying vehicle 1 comprises, at the rear 2R of the elongated body 2, a camera 14 protected by a cap 15, transparent to the radiation to which the camera 14 is sensitive. In addition, all of these exemplary embodiments I to IV comprise, in a known manner for the missiles, a military load, an electronic flight control system (not shown) and a reelable reserve (not shown) of an optical fiber 16.

Dans l'exemple de réalisation IV (figure 4), l'engin volant comporte une caméra supplémentaire 17 l'avant 2A du corps allongé 2.In the embodiment IV (FIG. 4), the flying machine comprises an additional camera 17 at the front 2A of the elongated body 2.

L'engin volant 1, quel que soit son mode de réalisation I à IV, est apte à être lancé par un poste de lancement et de commande 18, qui est pourvu d'un système de propulsion dudit engin volant 1 restant dans son tube de lancement 19, après lancement. De plus, l'engin volant 1 est relié audit poste de lancement et de commande 18 par l'intermédiaire de la fibre optique 16 de la réserve dévidable. Grâce à une telle fibre optique 16, l'engin volant 1 et le poste 18 peuvent échanger des informations, rendant éventuellement inutile la présence d'un calculateur à bord de l'engin volant 1.The flying vehicle 1, whatever its embodiment I to IV, is adapted to be launched by a launching and control station 18, which is provided with a propulsion system of said flying machine 1 remaining in its position. launch tube 19, after launch. In addition, the flying machine 1 is connected to said launching and control station 18 via the optical fiber 16 of the reelable reserve. Thanks to such an optical fiber 16, the flying machine 1 and the station 18 can exchange information, possibly making the presence of a computer on board the flying machine 1 unnecessary.

Après lancement par le poste 18, l'engin volant 1 allume ses propulseurs 3 et 5 qui le propulsent et le pilotent grâce à leurs tuyères 4 et 6 et lui font prendre une position verticale, avec l'arrière 2R et donc sa caméra 14 dirigés vers le sol 20. Dans cette position verticale, l'engin volant 1 peut se déplacer latéralement, en étant stabilisé en attitude et en roulis, de façon que sa caméra 14 observe le sol qui se trouve sous elle. Lorsque ladite caméra 14 détecte une cible 21, par exemple masquée au poste de tir 18 par un obstacle 22, l'engin volant 1 peut être propulsé et dirigé sur cette cible 21, par l'arrière 2R du corps allongé 2, soit par les tuyères 4 et 6 en positions 7 et 8 (exemples de réalisation I et IV), soit par les tuyères fixes 9 et 10 (exemple de réalisation II), ou bien encore par le propulseur supplémentaire 11 et la tuyère 13 (exemple de réalisation III). Un tel processus de reconnaissance et d'attaque, qui correspond plus particulièrement à un tir de destruction en cloche d'une cible masquée dont l'existence était probable, est illustré par la figure 5.After launching by the post 18, the flying machine 1 lights its thrusters 3 and 5 which propel and fly through their nozzles 4 and 6 and make him take a vertical position, with the rear 2R and thus his camera 14 directed towards the ground 20. In this vertical position, the flying machine 1 can move laterally, being stabilized in attitude and roll, so that its camera 14 observes the ground beneath it. When said camera 14 detects a target 21, for example masked at the firing station 18 by an obstacle 22, the flying vehicle 1 can be propelled and directed on this target 21, by the rear 2R of the elongate body 2, or by the nozzles 4 and 6 in positions 7 and 8 (embodiment examples I and IV), either by the fixed nozzles 9 and 10 (embodiment II), or else by the additional propellant 11 and the nozzle 13 (embodiment III) ). Such a recognition and attack process, which more specifically corresponds to a bell-destroying fire of a masked target whose existence was probable, is illustrated in FIG.

Si, comme cela est illustré par la figure 6, l'engin volant 1 doit rechercher en maraude une cible 21 à attaquer, il est avantageux que, au-dessus de terrains vides de cible, les propulseurs 3 et 5 fassent basculer l'engin volant 1 en position horizontale et le propulsent dans cette position jusqu'à un rebasculement en position d'observation verticale pour examiner une zone susceptible de comporter une cible 22. Dans cette phase de vol horizontal, la caméra supplémentaire 17 est particulièrement utile.If, as illustrated in FIG. 6, the flying vehicle 1 must search marauding a target 21 to be attacked, it is advantageous for the thrusters 3 and 5 to rock the craft over empty target lands. steering wheel 1 in the horizontal position and propel it in this position until a reversal in the vertical observation position to examine an area likely to include a target 22. In this phase of horizontal flight, the additional camera 17 is particularly useful.

Comme on le comprendra aisément, la présente invention est particulièrement utile pour observer successivement des zones de terrains masquées au poste de tir par des obstacles 22, 23 et susceptibles de contenir des cibles 21 devant être détruites.As will be readily understood, the present invention is particularly useful for successively observing areas of ground hidden at the firing station by obstacles 22, 23 and likely to contain targets 21 to be destroyed.

Claims (15)

  1. A flying object for observing the ground, comprising an elongate body (2), characterized:
    - in that it comprises:
    • a lift and displacement motor (3), of the type with combustible propelling charge, associated with first exhaust nozzles (4) directed towards the rear (2R) of said elongate body and distributed laterally about the latter, producing lateral maneuvering forces whose lines of action pass through the center of gravity (CG) of said flying object, said forces being able to ensure the lift and the displacements of said flying object in an observation position for which said object is at least approximately vertical with the rear end of said flying object directed downwards;
    • an attitude motor (5), of the type with combustible propelling charge, associated with second exhaust nozzles (6), directed towards the rear (2R) of said elongate body and distributed laterally around the latter, producing lateral maneuvering forces able to maintain said flying object in said at least approximately vertical observation position; and
    • picture taking means (14), disposed at the rear (2R) of said elongate body and able to observe said ground when said flying object is in said at least approximately vertical observation position; and
    - in that said lift and displacement motor (3) and said attitude motor (5) are disposed on either side of said center of gravity (CG) of the flying object and in that, during the combustion of the respective propelling charges of these latter two motors, the position of said center of gravity remains at least approximately fixed.
  2. The flying object as claimed in claim 1,
    characterized in that said lift and displacement motor (3) exhibits a larger mass than said attitude motor (5) and is closer to the center of gravity (CG) of the flying object than the latter.
  3. The flying object as claimed in one of claims L or 2,
    characterized in that said attitude motor (5) is disposed at the rear of said elongate body, while said lift and displacement motor is disposed just in front of the center of gravity (CG) of said flying object.
  4. The flying object as claimed in one of claims 1 to 3,
    characterized in that the roll orientation of said flying object is controlled by the lift and displacement motor (3).
  5. The flying object as claimed in one of claims 1 to 4,
    characterized in that it is launched by a launch and control post (18) comprising a propulsion or ejection system which is specific thereto and which is not carried by said flying object.
  6. The flying object as claimed in claim 5,
    characterized in that it comprises means of linking (16) with said launch and control post (18).
  7. The flying object as claimed in claim 6,
    characterized in that said means- of linking (16) comprise at least one optical fiber (8).
  8. The flying object as claimed in one of claims 1 to 7,
    characterized in that it comprises an additional picture taking means (17) disposed at the front of said elongate body.
  9. The flying object as claimed in one of claims 1 to 8,
    characterized in that it carries a warhead charge and-in that it comprises means of propulsion and means of guidance allowing it to attack, via the rear part (2R) of said elongate body, a target (21) detected for said picture taking means (14) disposed at the rear of said elongate body.
  10. The flying object as claimed in claim 9,
    characterized in that said means of propulsion and said means of guidance (11, 13) of said object in the direction of said target (21) are independent of said lift and displacement motor (3) and of said attitude motor (5).
  11. The flying object as claimed in claim 10,
    characterized in that said means of propulsion and said means of guidance of said object in the direction of said target consist of an additional motor (11, 13) disposed at the front (2A) of said elongate body (12).
  12. The flying object as claimed in claim 11,
    characterized in that said additional motor (11, 13) is disposed behind a droppable hood (12).
  13. The flying object as claimed in claim 9,
    characterized in that said means of propulsion and said means of guidance of said object in the direction of said target (21) are respectively formed by said lift and displacement motor (3) and by said attitude motor (5), associated respectively with third and fourth nozzles, directed towards the front (2A) of said elongate body and distributed laterally around the latter.
  14. The flying object as claimed in claim 13,
    characterized in that said first and second nozzles (4, 6) are orientable and form said third and fourth nozzles (7, 8) when they are oriented towards the front (2A) of said elongate body.
  15. The flying object as claimed in claim 13,
    characterized in that said third and fourth nozzles (9, 10) are fixed and are supplied with combustion gas by said lift and displacement motor (3) and by said attitude motor (5).
EP05291021A 2004-05-27 2005-05-12 Airborne vehicle for ground observation Active EP1600728B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0405719A FR2870932B1 (en) 2004-05-27 2004-05-27 FLYING ENGINE FOR SOIL OBSERVATION
FR0405719 2004-05-27

Publications (2)

Publication Number Publication Date
EP1600728A1 EP1600728A1 (en) 2005-11-30
EP1600728B1 true EP1600728B1 (en) 2006-11-02

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Application Number Title Priority Date Filing Date
EP05291021A Active EP1600728B1 (en) 2004-05-27 2005-05-12 Airborne vehicle for ground observation

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US (1) US7763834B2 (en)
EP (1) EP1600728B1 (en)
JP (1) JP4823219B2 (en)
KR (1) KR101287920B1 (en)
CN (1) CN100467999C (en)
AT (1) ATE344434T1 (en)
DE (1) DE602005000222T2 (en)
ES (1) ES2274506T3 (en)
FR (1) FR2870932B1 (en)
IL (1) IL176804A (en)
NO (1) NO333969B1 (en)
WO (1) WO2006000662A1 (en)
ZA (1) ZA200607459B (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007021112B3 (en) * 2007-05-05 2008-07-31 Lfk-Lenkflugkörpersysteme Gmbh Reconnaissance radius enlarging method for combat helicopter, involves carrying unmanned reconnaissance drones in combat helicopters, and launching reconnaissance drones into operational area from flying combat helicopters
JP5279523B2 (en) * 2009-01-22 2013-09-04 三菱電機株式会社 Posture calculation device, guidance device, posture calculation method of posture calculation device, and posture calculation program of posture calculation device
US8878110B2 (en) * 2010-12-14 2014-11-04 Raytheon Company Projectile that includes propulsion system and launch motor on opposing sides of payload and method
FR2970702B1 (en) * 2011-01-26 2013-05-10 Astrium Sas METHOD AND SYSTEM FOR DRIVING A REAR PROPULSE FLYWHEEL
KR101917785B1 (en) 2016-10-26 2019-01-29 한국항공우주연구원 Non-motorized type flying unit for observation
CN109141144B (en) * 2018-09-29 2024-02-09 中国空空导弹研究院 Infrared guided missile crushing type throwing separation cover
CN113776386B (en) * 2020-06-10 2023-05-09 北京机械设备研究所 Close range throwing method for carrier-based vertical emission load

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB751840A (en) * 1951-07-06 1956-07-04 Armstrong Whitworth Co Eng Improvements relating to self-projected missiles
US3185096A (en) * 1959-08-31 1965-05-25 Roland G Dandelin Thrust reversal unit for rocket motor
FR1288750A (en) * 1960-12-14 1962-03-30 Snecma Platform supported by reaction, with calibrated thrust, used in particular for demining
US3233548A (en) * 1963-11-12 1966-02-08 Canrad Prec Ind Inc Dirigible aerial torpedo
US3806064A (en) * 1968-10-03 1974-04-23 A Parilla Missile configurations, controls and utilization techniques
GB1284487A (en) * 1970-02-24 1972-08-09 Mullard Ltd Improvements in or relating to scanning and imaging systems
US3979086A (en) * 1974-11-08 1976-09-07 The United States Of America As Represented By The Secretary Of The Army Rocketed data communication system
NZ198917A (en) * 1980-11-14 1985-01-31 Commw Of Australia Rocket controlled by spoiler tabs in exhaust
DE3313648A1 (en) * 1983-04-15 1984-10-18 Diehl GmbH & Co, 8500 Nürnberg Process for real-time terrain reconnaissance by means of a sensor and device for carrying out the process
FR2558585B1 (en) * 1984-01-19 1987-10-23 Stauff Emile WIDE SUBMUNITIONS FOR PROJECTILE, ESPECIALLY ANTICHAR
USH236H (en) * 1986-07-14 1987-03-03 The United States Of America As Represented By The Secretary Of The Army Asymmetric side-exhausting nozzles
US4913379A (en) * 1988-02-23 1990-04-03 Japan as represented by Director General, Technical Research and Development Institute, Japan Defence Agency Rocket flight direction control system
JP2588739B2 (en) * 1988-02-23 1997-03-12 防衛庁技術研究本部長 Rocket flight direction control device
JPH0331698A (en) * 1989-06-28 1991-02-12 Boeing Co:The Optical fiber guided shell equipment
DE4132233C2 (en) * 1990-11-22 2003-03-06 Rheinmetall W & M Gmbh Antitank missile system
FR2699610B1 (en) * 1992-12-22 1995-02-10 Aerospatiale Device for actuating a mechanical member, in particular for the force piloting of a missile, and missile equipped with said device.
US5456425A (en) * 1993-11-04 1995-10-10 Aerojet General Corporation Multiple pintle nozzle propulsion control system
GB9501594D0 (en) * 1995-01-27 1995-11-08 British Aerospace Tethered missile system
JP3075343B2 (en) * 1997-06-24 2000-08-14 防衛庁技術研究本部長 Flying object
JP3291542B2 (en) * 1999-07-08 2002-06-10 防衛庁技術研究本部長 Translation and attitude control device
US6705573B2 (en) * 1999-12-30 2004-03-16 Advanced Aerospace Technologies, Inc. Survivability and mission flexibility enhancements for reconnaissance aircraft

Also Published As

Publication number Publication date
WO2006000662A1 (en) 2006-01-05
NO333969B1 (en) 2013-11-04
US7763834B2 (en) 2010-07-27
DE602005000222T2 (en) 2007-09-06
NO20065758L (en) 2006-12-13
IL176804A (en) 2011-02-28
CN1961194A (en) 2007-05-09
KR101287920B1 (en) 2013-07-18
DE602005000222D1 (en) 2006-12-14
JP2008500507A (en) 2008-01-10
IL176804A0 (en) 2006-10-31
ZA200607459B (en) 2007-12-27
ES2274506T3 (en) 2007-05-16
ATE344434T1 (en) 2006-11-15
CN100467999C (en) 2009-03-11
US20080245256A1 (en) 2008-10-09
JP4823219B2 (en) 2011-11-24
FR2870932A1 (en) 2005-12-02
FR2870932B1 (en) 2006-08-11
EP1600728A1 (en) 2005-11-30
KR20070015371A (en) 2007-02-02

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