EP1600728A1 - Airborne vehicle for ground observation - Google Patents

Airborne vehicle for ground observation Download PDF

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Publication number
EP1600728A1
EP1600728A1 EP05291021A EP05291021A EP1600728A1 EP 1600728 A1 EP1600728 A1 EP 1600728A1 EP 05291021 A EP05291021 A EP 05291021A EP 05291021 A EP05291021 A EP 05291021A EP 1600728 A1 EP1600728 A1 EP 1600728A1
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EP
European Patent Office
Prior art keywords
flying machine
propellant
machine according
flying
displacement
Prior art date
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Granted
Application number
EP05291021A
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German (de)
French (fr)
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EP1600728B1 (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
    • 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
    • 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 present invention relates to a flying machine for observation ground, which can be used for the attack of terrestrial targets, in particular masked by an obstacle.
  • the present invention aims to overcome these disadvantages.
  • the lift and displacement, on the one hand, and attitude, on the other hand are ordered by two separate thrusters dedicated solely to their respective function, which allows a great precision in the follow-up of the trajectory of the flying machine and in the vertical presentation of it in relation to the ground, making it less vulnerable to terrestrial anti-aircraft defenses an enemy and allows him to observe, carefully and slowly, any suspicious of the ground, for example hidden behind an obstacle.
  • said lift and displacement propellant has a larger mass than said attitude propellant 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 elongated body, while said levitation and displacement propellant is disposed just in front of the center of gravity of the said flying machine.
  • the flying machine according to the invention is launched, so known for some attack missiles, by a launching station and control comprising a propulsion or ejection system which is clean and not worn by said flying machine. So, we can remove of said flying machine according to the invention the rear thruster generally charged with launching and having, in place of the said stern thruster, the said means of shooting.
  • said flying machine After its launch, said flying machine can fly autonomously, for example to achieve a pre-established flight plan.
  • the machine steering wheel according to the present invention may comprise means link with said launch and control station. So, he can possibly receive information from said station or have it carried out calculations by the latter, which lighten said flying machine.
  • said connecting means comprise, in known manner, the less an optical fiber, unwindable from said flying machine. Thus, information circulating between the spacecraft and the said post may not be blurred.
  • the flying machine according to the invention may comprise means of additional shots arranged at the front of the elongated body.
  • the flying machine complies the present invention carries a military load and includes propulsion means and guide means enabling it to attack, preferably without turning over, that is to say by its rear part, a target detected by said rear-view means.
  • the attack of said target can be commanded, either from the launch station and command to which the images of the target are transmitted by said means of connection, either automatically by a recognition device target carried by said flying machine.
  • Said propulsion means and said guide means of said gear towards the detected target may be independent of the said thrust propeller and displacement and said attitude thruster.
  • said propulsion means and said guide means said craft towards the target may be constituted by a additional thruster disposed forward of said elongated body.
  • additional propellant may be of the propellant fuel type, possibly provided with a steerable nozzle. It is better that said additional thruster is deposited behind a releasable cap said flying machine.
  • said propulsion means and said means for guiding said machine towards the target detected are respectively formed by said levitation and displacement propellant and by said attitude thrusters, associated respectively with thirds and with fourth nozzles, directed forward of said elongated body and distributed laterally around it.
  • Said first and second nozzles may be orientable and form said third and fourth nozzles when facing forward of said elongate body.
  • said third and fourth nozzles may be stationary and powered in propellant gas by said propellant of levitation and displacement and by said attitude thruster, by means of switching power supply arranged at the respective outputs of said thruster of levitation and displacement and said attitude booster and to feed either said first and second nozzles, or said third and fourth nozzles.
  • FIGS 1 to 4 schematically show four modes of embodiment of the flying machine according to the present invention.
  • FIGS 5 and 6 schematically illustrate two examples of flight of said flying craft.
  • FIGS 1 to 4 schematically show four embodiments I to IV of the flying vehicle 1 according to the present invention.
  • the thrusters 3 and 5 are arranged on either side of the center CG gravity of the flying machine and the thruster 3 is heavier than the thruster 5 and closer to the CG center of gravity than the latter.
  • the combustion of the propellant fuel charges of these propellants is set so that, when the thrusters 3 and 5 are in operation, the position of the center of gravity CG remains at least substantially fixed.
  • the nozzles 4 and 6 are orientable, as illustrated by the arrows, and can take positions 7 and 8 respectively directed forward 2A of the elongated body 2, as shown in dotted lines.
  • the lift propellant and displacement 3 comprises, in addition to the nozzles 4, nozzles fixed 9, equidistributed laterally around said elongated body 2 and directed forward 2A of it.
  • the thruster of levitation and displacement 3 can supply combustion gases, either the nozzles 4 or the nozzles 9.
  • the attitude booster 5 comprises, in addition to the nozzles 6, fixed nozzles 10, equally distributed laterally around the body lying 2 and directed forward 2A thereof. Through means of controllable switching known, the attitude booster 5 can feed in combustion gas, either the nozzles 6 or the fixed nozzles 10.
  • the flying machine 1 comprises an additional thruster 11, for example of the type to load propellant fuel, arranged at the front 2A of the elongated body 2, by example behind a releasable cap 12 of the latter.
  • the additional thruster 11 is provided with an axial nozzle 13, preferably orientable, directed towards the front 2A of the elongate body 2.
  • the flying machine 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.
  • all these examples of embodiments I to IV include, known way for missiles, a military charge, an electronic system flight control device (not shown) and a rewinding reserve (no shown) of an optical fiber 16.
  • the flying machine comprises an additional camera 17 the front 2A of the elongated body 2.
  • the flying machine 1 whatever its embodiment I to IV, is able to be launched by a launch and control post 18, which is provided with a propulsion system of said flying machine 1 remaining in its launch tube 19, after launch.
  • the flying machine 1 is connected auditing launch and control station 18 through the fiber optical 16 of the reelable reserve. With such an optical fiber 16, the flying machine 1 and the post 18 can exchange information, making the possibly unnecessary the presence of a calculator on board the craft flying 1.
  • the flying machine 1 After launching by the post 18, the flying machine 1 lights its thrusters 3 and 5 that propel and fly through their nozzles 4 and 6 and make him take a vertical position, with the rear 2R and so his camera 14 In the upright position, the flying machine 1 can move laterally, being stabilized in attitude and roll, so that his camera 14 observes the ground beneath it.
  • the flying machine 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), or by the nozzles 9 and 10 (embodiment II), or else by the thruster additional 11 and the nozzle 13 (example III).
  • a process of recognition and attack which corresponds more particularly to a shot of bell-destruction of a masked target whose existence was likely, is shown in Figure 5.
  • the flying machine 1 must search in marauding a target 21 to attack, it is advantageous that, above of empty target lands, thrusters 3 and 5 roll over the flying machine 1 in a horizontal position and propel it in this position up to a reverse position in a vertical observation position to examine an area likely to have a target 22. In this phase of horizontal flight, the additional camera 17 is particularly useful.
  • the present invention is particularly useful for successively observing terrain zones masked at the firing point by obstacles 22, 23 and likely to contain targets 21 to be destroyed.

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, pouvant être utilisé pour l'attaque de cibles terrestres, notamment masquées par un obstacle.The present invention relates to a flying machine for observation ground, which can be used for the attack of terrestrial targets, in particular masked by an obstacle.

On connaít 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.We already know flying machines for the observation of the ground itself. usually presenting in the form of a small unmanned aircraft (drone). Such flying machines are relatively vulnerable and are targets for enemy anti-aircraft defenses and more, they must be continuously moving and therefore can not not stop to carefully observe a particular area of a lot. To avoid this last inconvenience, we have already thought to make drones in the form of small helicopters. However, these 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, aircraft or helicopter, they can only be used for reconnaissance and not for the attack of the enemy targets that 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 of action pass through the center of gravity of said flying machine, said forces being able to ensure the lift and the movements of said flying machine in an observation position for which it is at least approximately vertical with the rear end of said machine steering wheel facing down;
    • 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 displacement, on the one hand, and attitude, on the other hand, are ordered by two separate thrusters dedicated solely to their respective function, which allows a great precision in the follow-up of the trajectory of the flying machine and in the vertical presentation of it in relation to the ground, making it less vulnerable to terrestrial anti-aircraft defenses an enemy and allows him to observe, carefully and slowly, any suspicious 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 should be noted that, due to the near-coincidence of the center of gravity, from the steering point of the lift propeller and displacement (driving force) and aerodynamic center, the latter thruster, as well as transverse aerodynamic forces -including gusts of wind- have little influence on the 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 propellant has a larger mass than said attitude propellant 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 elongated body, while said levitation and displacement propellant is disposed just in front of the center of gravity of the 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 means of shooting to generate clear images of the observed soil, it is necessary to control the roll of the flying machine according to the present invention. Since the lift propeller and displacement performs less sensitive functions than the thruster of attitude, it is better that it is this first thruster which 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, so known for some attack missiles, by a launching station and control comprising a propulsion or ejection system which is clean and not worn by said flying machine. So, we can remove of said flying machine according to the invention the rear thruster generally charged with launching and having, in place of the said stern thruster, the said means of 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 machine steering wheel according to the present invention may comprise means link with said launch and control station. So, he can possibly receive information from said station or have it carried out calculations by the latter, which lighten said flying machine. Of preferably, said connecting means comprise, in known manner, the less an optical fiber, unwindable from said flying machine. Thus, information circulating between the spacecraft and the said post may not be blurred.

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 his movements over the field observed, the flying machine according to the invention may comprise means of additional shots arranged at the front of the elongated 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 complies the present invention carries a military load and includes propulsion means and guide means enabling it to attack, preferably without turning over, that is to say by its rear part, a target detected by said rear-view means. The attack of said target can be commanded, either from the launch station and command to which the images of the target are transmitted by said means of connection, either automatically by a recognition device target 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 guide means of said gear towards the detected target may be independent of the said thrust propeller and displacement and said attitude thruster. In this case, said propulsion means and said guide means said craft towards the target may be constituted by a additional thruster disposed forward of said elongated body. Such additional propellant may be of the propellant fuel type, possibly provided with a steerable nozzle. It is better that said additional thruster is deposited behind a releasable cap 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.In a variant, said propulsion means and said means for guiding said machine towards the target detected are respectively formed by said levitation and displacement propellant and by said attitude thrusters, associated respectively with thirds and with fourth nozzles, directed forward of said elongated body and distributed laterally around it. Said first and second nozzles may be orientable and form said third and fourth nozzles when facing forward of said elongate body. In a variant, said third and fourth nozzles may be stationary and powered in propellant gas by said propellant of levitation and displacement and by said attitude thruster, by means of switching power supply arranged at the respective outputs of said thruster of levitation and displacement and said attitude booster and to feed 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 annexed drawing will make 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 schematically show four modes of embodiment 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 flight 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.Figures 1 to 4 schematically show four embodiments I to IV of the flying vehicle 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 lift 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 elongated 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 lateral maneuvering forces 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 elongate body 2 and directed back 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 arranged on either side of the center CG gravity of the flying machine and the thruster 3 is heavier than the thruster 5 and closer to the CG center of gravity than the latter. The combustion of the propellant fuel charges of these propellants is set so that, when the thrusters 3 and 5 are in operation, 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 examples of realization I (figure 1) and IV (figure 4) of the flying machine 1, the nozzles 4 and 6 are orientable, as illustrated by the arrows, and can take positions 7 and 8 respectively directed forward 2A of the elongated body 2, as shown in dotted 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 exemplary embodiment II (FIG. 2), the lift propellant and displacement 3 comprises, in addition to the nozzles 4, nozzles fixed 9, equidistributed laterally around said elongated body 2 and directed forward 2A of it. With switching means Known controllables, the thruster of levitation and displacement 3 can supply combustion gases, either the nozzles 4 or the nozzles 9. In the same way, the attitude booster 5 comprises, in addition to the nozzles 6, fixed nozzles 10, equally distributed laterally around the body lying 2 and directed forward 2A thereof. Through means of controllable switching known, the attitude booster 5 can feed in combustion gas, 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 thruster 11, for example of the type to load propellant fuel, arranged at the front 2A of the elongated body 2, by example behind a releasable cap 12 of the latter. The additional thruster 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 machine 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 these examples of embodiments I to IV include, known way for missiles, a military charge, an electronic system flight control device (not shown) and a rewinding reserve (no 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 exemplary embodiment IV (FIG. 4), the flying machine comprises an additional camera 17 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 machine 1, whatever its embodiment I to IV, is able to be launched by a launch and control post 18, which is provided with a propulsion system of said flying machine 1 remaining in its launch tube 19, after launch. In addition, the flying machine 1 is connected auditing launch and control station 18 through the fiber optical 16 of the reelable reserve. With such an optical fiber 16, the flying machine 1 and the post 18 can exchange information, making the possibly unnecessary the presence of a calculator on board the craft flying 1.

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 that propel and fly through their nozzles 4 and 6 and make him take a vertical position, with the rear 2R and so his camera 14 In the upright position, the flying machine 1 can move laterally, being stabilized in attitude and roll, so that his camera 14 observes the ground beneath it. When said camera 14 detects a target 21, for example masked at the shot 18 by an obstacle 22, the flying machine 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), or by the nozzles 9 and 10 (embodiment II), or else by the thruster additional 11 and the nozzle 13 (example III). Such a process of recognition and attack, which corresponds more particularly to a shot of bell-destruction of a masked target whose existence was likely, is shown in Figure 5.

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 shown in Figure 6, the flying machine 1 must search in marauding a target 21 to attack, it is advantageous that, above of empty target lands, thrusters 3 and 5 roll over the flying machine 1 in a horizontal position and propel it in this position up to a reverse position in a vertical observation position to examine an area likely to have 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 terrain zones masked at the firing point by obstacles 22, 23 and likely to contain targets 21 to be destroyed.

Claims (15)

Engin volant pour l'observation du sol, comportant un corps allongé (2),
caractérisé : en ce qu'il comporte : un propulseur de sustentation et de déplacement (3), du type à charge propulsive combustible, associé à des premières tuyères d'échappement (4), dirigées vers l'arrière (2R) 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 (CG) 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 (5), du type à charge propulsive combustible, associé à des deuxièmes tuyères d'échappement (6), dirigées vers l'arrière (2R) 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 (14), disposés à l'arrière (2R) 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 (3) et ledit propulseur d'attitude (5) sont disposés de part et d'autre dudit centre de gravité (CG) 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. Flying machine for observation of the ground, comprising an elongate body (2),
characterized in that it comprises: a fuel propellant type lift and displacement propellant (3) associated with first, rearward directed (2R) exhaust nozzles (4) of said elongated body and laterally distributed thereabout, generating lateral maneuvering forces whose lines of action pass through the center of gravity (CG) of said flying machine, said forces being capable of ensuring the lift and the movements of said flying machine in an observation position for which the latter is at least approximately vertical with the rear end of said downwardly directed flying craft; a propellant charge type propellant (5) associated with second exhaust nozzles (6) directed rearwardly (2R) of said elongated body and distributed laterally thereagainst, generating lateral maneuvering forces able to maintain said flying machine in said at least approximately vertical observation position; and rearwardly arranged camera means (14) (2R) of said elongated 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 (3) and said attitude propellant (5) are arranged on either side of said center of gravity (CG) of the flying machine and in that, during the combustion of the respective propulsive charges of these last two thrusters, the position of said center of gravity remains at least approximately fixed. Engin volant selon la revendication 1,
caractérisé en ce que ledit propulseur de sustentation et de déplacement (3) présente une masse plus importante que ledit propulseur d'attitude (5) et est plus proche du centre de gravité (CG) de l'engin volant que ce dernier.Flying machine according to claim 1,
characterized in that said buoyancy and displacement propellant (3) has a larger mass than said attitude propellant (5) and is closer to the center of gravity (CG) of the flying machine than the latter. Engin volant selon l'une des revendications 1 ou 2,
caractérisé en ce que ledit propulseur d'attitude (5) est 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 (CG) dudit engin volant.Flying machine according to one of claims 1 or 2,
characterized in that said attitude propeller (5) is disposed at the rear of said elongate body, while said lift and displacement propellant is disposed just in front of the center of gravity (CG) of said flying craft. Engin volant selon l'une des revendications 1 à 3,
caractérisé en ce que l'orientation en roulis dudit engin volant est contrôlée par le propulseur de sustentation et de déplacement (3).Flying machine according to one of claims 1 to 3,
characterized in that the roll orientation of said flying machine is controlled by the lift and displacement propellant (3). Engin volant selon l'une des revendications 1 à 4,
caractérisé en ce qu'il est lancé par un poste de lancement et de commande (18) comportant un système de propulsion ou d'éjection qui lui est propre et qui n'est pas porté par ledit engin volant.Flying machine according to one of claims 1 to 4,
characterized in that it is launched by a launching and control station (18) having a propulsion system or ejection of its own and not worn by said flying machine. Engin volant selon la revendication 5,
caractérisé en ce qu'il comporte des moyens de liaison (16) avec ledit poste de lancement et de commande (18).Flying machine according to claim 5,
characterized in that it comprises connecting means (16) with said launch and control station (18). Engin volant selon la revendication 6,
caractérisé en ce que lesdits moyens de liaison (16) comportent au moins une fibre optique.Flying machine according to claim 6,
characterized in that said connecting means (16) comprise at least one optical fiber. Engin volant selon l'une des revendications 1 à 7,
caractérisé en ce qu'il comporte des moyens de prise de vues supplémentaires (17) disposés à l'avant dudit corps allongé. Flying machine according to one of claims 1 to 7,
characterized in that it comprises additional recording means (17) arranged in front of said elongated body. Engin volant selon l'une quelconque des revendications 1 à 8,
caractérisé en ce qu'il porte une charge militaire et en ce qu'il comporte des moyens de propulsion et des moyens de guidage lui permettant d'attaquer, par la partie arrière (2R) dudit corps allongé, une cible (21) détectée pour lesdits moyens de prise de vues (14) disposés à l'arrière dudit corps allongé.Flying machine according to one of Claims 1 to 8,
characterized in that it carries a military load and in that it comprises propulsion means and guiding means enabling it to attack, by the rear part (2R) of said elongate body, a target (21) detected for said camera means (14) disposed at the rear of said elongated body. Engin volant selon la revendication 9,
caractérisé en ce que lesdits moyens de propulsion et lesdits moyens de guidage (11, 13) dudit engin en direction de ladite cible (21) sont indépendants dudit propulseur de sustentation et de déplacement (3) et dudit propulseur d'attitude (5).Flying machine according to claim 9,
characterized in that said propulsion means and said guide means (11, 13) of said machine towards said target (21) are independent of said lift and displacement propeller (3) and said attitude propellant (5). Engin volant selon la revendication 10,
caractérisé en ce que lesdits moyens de propulsion et lesdits moyens de guidage dudit engin en direction de ladite cible sont constitués par un propulseur supplémentaire (11, 13) disposé à l'avant (2A) dudit corps allongé.Flying machine according to claim 10,
characterized in that said propulsion means and said means for guiding said machine towards said target are constituted by an additional propellant (11, 13) disposed at the front (2A) of said elongated body. Engin volant selon la revendication 11,
caractérisé en ce que ledit propulseur supplémentaire (11, 13) est disposé derrière une coiffe largable (12).Flying machine according to claim 11,
characterized in that said additional thruster (11, 13) is disposed behind a releasable cap (12). Engin volant selon la revendication 9,
caractérisé en ce que lesdits moyens de propulsion et lesdits moyens de guidage dudit engin en direction de ladite cible (21) sont respectivement formés par ledit propulseur de sustentation et de déplacement (3) et par ledit propulseur d'attitude (5), associés respectivement à des troisièmes et à des quatrièmes tuyères, dirigées vers l'avant (2A) dudit corps allongé et réparties latéralement autour de celui-ci. Flying machine according to claim 9,
characterized in that said propulsion means and said means for guiding said machine towards said target (21) are respectively formed by said lift and displacement propellant (3) and by said attitude propellant (5), respectively associated to third and fourth nozzles directed towards the front (2A) of said elongated body and distributed laterally thereabout. Engin volant selon la revendication 13,
caractérisé en ce que lesdites premières et deuxièmes tuyères (4, 6) sont orientables et forment lesdites troisièmes et quatrièmes tuyères (7, 8) lorsqu'elles sont orientées vers l'avant (2A) dudit corps allongé.Flying machine according to claim 13,
characterized in that said first and second nozzles (4, 6) are orientable and form said third and fourth nozzles (7, 8) when facing forward (2A) of said elongated body. Engin volant selon la revendication 13,
caractérisé en ce que lesdites troisièmes et quatrièmes tuyères (9, 10) sont fixes et sont alimentées en gaz de combustion par ledit propulseur de sustentation et de déplacement (3) et par ledit propulseur d'attitude (5).Flying machine according to claim 13,
characterized in that said third and fourth nozzles (9, 10) are stationary and are supplied with combustion gas by said lift and displacement propellant (3) and by said attitude propellant (5).
EP05291021A 2004-05-27 2005-05-12 Airborne vehicle for ground observation Active EP1600728B1 (en)

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FR0405719A FR2870932B1 (en) 2004-05-27 2004-05-27 FLYING ENGINE FOR SOIL OBSERVATION

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CN100467999C (en) 2009-03-11
US7763834B2 (en) 2010-07-27
JP4823219B2 (en) 2011-11-24
NO333969B1 (en) 2013-11-04
EP1600728B1 (en) 2006-11-02
KR20070015371A (en) 2007-02-02
IL176804A0 (en) 2006-10-31
ATE344434T1 (en) 2006-11-15
ES2274506T3 (en) 2007-05-16
DE602005000222D1 (en) 2006-12-14
DE602005000222T2 (en) 2007-09-06
IL176804A (en) 2011-02-28
KR101287920B1 (en) 2013-07-18
US20080245256A1 (en) 2008-10-09
ZA200607459B (en) 2007-12-27
FR2870932B1 (en) 2006-08-11
WO2006000662A1 (en) 2006-01-05
JP2008500507A (en) 2008-01-10
CN1961194A (en) 2007-05-09
FR2870932A1 (en) 2005-12-02

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