EP1375345B1 - Weapon provided with a missile and which is mounted on a stealth aircraft, and a weapon system comprising a stealth aircraft and such a weapon - Google Patents

Weapon provided with a missile and which is mounted on a stealth aircraft, and a weapon system comprising a stealth aircraft and such a weapon Download PDF

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Publication number
EP1375345B1
EP1375345B1 EP03291082A EP03291082A EP1375345B1 EP 1375345 B1 EP1375345 B1 EP 1375345B1 EP 03291082 A EP03291082 A EP 03291082A EP 03291082 A EP03291082 A EP 03291082A EP 1375345 B1 EP1375345 B1 EP 1375345B1
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EP
European Patent Office
Prior art keywords
missile
stealth
tube
aircraft
weapon
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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EP03291082A
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German (de)
French (fr)
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EP1375345A1 (en
Inventor
Jean Thery
Frédéric Naccache
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MBDA France SAS
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MBDA France SAS
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Publication of EP1375345A1 publication Critical patent/EP1375345A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/06—Rocket or torpedo launchers for rockets from aircraft

Definitions

  • the present invention relates to a missile carrying means intended to be mounted on the outer structure of a stealth aircraft.
  • the present invention also relates to a weapon mounted on a stealth aircraft and provided with such a means of transport and at least one missile, and a weapon system comprising a stealth aircraft equipped with such a weapon.
  • a weapon system of this type is generally intended to perform a mission in a hostile environment, the success of such a mission often depends, in large part, on the ability of the weapon system to escape completely or at least as long as possible for any type of detection, and in particular radar detection.
  • such a weapon system comprises means for external carriage of the missiles on the aircraft.
  • Such external means of transport comprises a missile launcher which is fixed under the aircraft and which retains the missile (s).
  • Such a means of transportation has a significant disadvantage with regard to stealth. Indeed, it causes the presence of many strong electromagnetic couplings between the aircraft, the missile launcher and the wings, control surfaces and fuselage of the missile, which makes it very difficult to reduce the radar signature of this assembly forming the said system. 'armed.
  • This weapon reduces the radar signature of the weapon system (consisting of the weapon and the stealth aircraft). However, it makes it necessary, during firing of the missile, the implementation of a difficult operation to control and dangerous, namely the ejection of the missile out of the stealth tube. In addition, this ejection operation requires particular ejection means, which increases, although moderately, the cost and size of said weapon.
  • the present invention relates to a transport means which is intended to at least partially overcome the aforementioned drawbacks.
  • the present invention also relates to a weapon, of reduced cost, provided with at least one missile and intended to be mounted on a stealth aircraft, said weapon being able to be mounted on existing aircraft and being such that the weapon system formed by said weapon and the aircraft carrying it, has a reduced radar signature during the mission phase during which the stealth aircraft carries the weapon, and especially said weapon allowing a safe and controlled missile.
  • the missile is released (or launched) in the usual manner, which reduces the cost and bulk of the weapon.
  • the missile since the missile is housed in a tube which has stealth characteristics, specified below, it is possible to reduce the radar signature of said weapon system.
  • the weapon according to the invention can be easily mounted on any type of existing aircraft. In particular, it is not necessary to design a specific aircraft to implement the present invention.
  • the present invention is applicable to any type of missile (or bomb) fired from an aircraft, be it an air-to-air, air-sea or air-to-ground missile.
  • said first means comprise cutting means, of mechanical and / or pyrotechnic type, for cutting the wall of said stealth tube so as to separate said lower part of said upper part.
  • the carrying means according to the invention further comprises an auxiliary pivot connection system, which is provided between said lower and upper portions of the stealth tube and which allows the complete separation of said lower part, only when, after the control of said first means, the latter has, relative to the longitudinal axis of said stealth tube, a predetermined angle.
  • an auxiliary pivot connection system which is provided between said lower and upper portions of the stealth tube and which allows the complete separation of said lower part, only when, after the control of said first means, the latter has, relative to the longitudinal axis of said stealth tube, a predetermined angle.
  • said stealth tube also surrounds said third means which link the missile to the external structure of the aircraft.
  • said stealth tube has a cylindrical shape and comprises a nose-shaped cap at the front, in the direction of flight of the aircraft, which makes it possible to minimize or even cancel the wave reflections electromagnetic in the directions of observations generally considered as main or priority, namely those corresponding to the sight of the front and side parts of the tube.
  • said stealth tube preferably has a circular, rhombic or lenticular cross section.
  • said stealth tube is provided at least on a portion of its outer face with a coating that absorbs electromagnetic waves.
  • said tube is made of composite material of known type having a high mechanical strength and a reduced mass, such as an epoxy or carbon-based composite material or aramid fibers (of the "Kevlar” type).
  • the present invention further relates to a weapon system which includes a stealth aircraft and a weapon such as the one above, which is mounted on said stealth aircraft.
  • Figures 1 to 3 respectively show three successive phases of the launch of a missile forming part of a weapon system according to the invention.
  • Figures 4 and 5 illustrate schematically in longitudinal section a weapon according to the invention and mounted on an aircraft, respectively in two different situations.
  • Figures 6 and 7 schematically illustrate an auxiliary connection system, respectively corresponding to the situations of Figures 4 and 5.
  • Figures 8 to 10 show, in cross section, a missile arranged in a missile carrying means according respectively to different embodiments of the invention.
  • the weapon system 1 according to the invention and shown in particular in FIG. 1 comprises a stealth type aircraft A, for example a stealth fighter aircraft, and at least one weapon 2 comprising a missile M.
  • FIGS. 1 to 3 represent the weapon system 1 in successive phases during a firing of the missile M.
  • Said weapon 2 is of the type comprising, as represented in particular in FIG. 4, in addition to the missile M, a carrying means 3 comprising a stealth tube 4 specified below, which is arranged under the aircraft A and which is linked by an end portion 5 to the structure (fuselage F) of said aircraft A.
  • the missile M an air-to-air, air-to-ground or air-sea missile, or a bomb (guided or not, propelled or not) , is completely housed in said tube 4 so as not to be visible from the outside and thus not to modify the radar signature of the weapon system 1.
  • said means 6 comprise mechanical and / or pyrotechnic cutting means for cutting along a cutting line 12 the wall 4A of said stealth tube 4 so as to separate said lower part 7A from said upper part 7B.
  • the weapon 2 further comprises an auxiliary connection system 13 (FIGS. 4 to 7) which is provided behind the stealth tube 4 between said lower portions 7A and 7B of the stealth tube 4 and which allows complete separation. of said lower part 7A, only when, after the control of said means 6, the latter has with respect to the longitudinal axis of said stealth tube 4 a predetermined angle ⁇ , as shown in Figures 5 and 7.
  • auxiliary connection system 13 FIGS. 4 to 7
  • This auxiliary connection system 13 is a pivot system 14 which comprises, as shown in Figures 6 and 7, a ball 15 secured to the upper portion 7B of the tube 4.
  • This ball 15 is provided with a cutout 16 and cooperates with an end 17 in an arc, which is connected to the lower part 7A of the tube 4 and which surrounds the ball 15.
  • the cutout 16 one can adjust the separation angle ⁇ and thus adapt, in particular, to the conditions of carriage and firing of the missile M under the aircraft A, so as to ensure a risk-free separation for the aircraft A from said lower part 7A of the stealth tube 4.
  • the means 10 comprise a conventional pylon 18 to which the missile M is bonded.
  • This pylon 18 comprises means for fixing the missile M and means for unlocking this attachment.
  • the stealth tube 4 also surrounds said pylon 18 by its end portion, which minimizes the reflections of electromagnetic waves at this level.
  • the missile M and the pylon 18 are housed in said tube 4 which has stealth characteristics, specified below, it is possible to reduce the radar signature of said weapon system 1.
  • the weapon 2 does not require specific ejection means for ejecting the missile M out of the tube 4, the missile M being released and ejected in the usual way (in particular by falling thanks to its own weight), which allows to reduce the cost and bulk of said weapon 2.
  • the missile M can also be ejected from the front by being drawn on rail in the usual manner, the opening 8 releasing a passage forwards for this purpose.
  • the installation of the tube 4 under the aircraft A is identical to that of an additional fuel tank.
  • the mechanical connections are of the same type and the electrical connections are ensured by a limited number of connectors.
  • the mechanical connections and the electrical connections are implemented by the tower 18.
  • the interface between the tube 4 and the aircraft A is simplified. It is moreover, preferably, standardized, in particular to facilitate manufacture.
  • the tubes 4 are fixed longitudinally to said aircraft A, under the wings B, C and / or the fuselage F of the latter.
  • the number of weapons 2 and therefore tubes 4 is adapted to the dimensions of the aircraft A and mission to achieve.
  • two tubes 4 are fixed under the wings B and C of the aircraft A and a third tube 4 is fixed at the center below the fuselage F.
  • a stealth tube may comprise, in a particular embodiment not shown, more than one missile, for example two, three ... missiles.
  • the missile M comprises bearing surfaces 19 (flanges, control surfaces) may take one of two positions: a folded position ( Figure 4) and an extended position. Said bearing surfaces 19 are in the folded position as long as the missile M is housed in the stealth tube 4 and they are automatically supplied by known means and not shown in the deployed position, for a part of them when the lower part 7A is separated ( Figures 2 and 5) and for the rest when the missile M is ejected out of said upper part 7B of the tube 4 ( Figure 3).
  • tube 4 protects the missile M at least in the aircraft A, but generally during all phases of its operational life.
  • the shooting conditions and security measures to be taken into account are the same. than those taken into account when firing a missile, in external carriage, with a conventional missile launcher.
  • the stealth tube 4 has a shape that makes it possible to minimize or even cancel the reflection of electromagnetic waves at least along predetermined directions of observation.
  • said stealth tube 4 has a cylindrical shape and comprises a nose-shaped cap 25 in the forward direction, in the direction of flight of the aircraft A, which makes it possible to minimize the reflection in the observation directions aimed at the front and lateral parts of the tube 4.
  • the tube 4 has at the rear a flattened shape that makes a compromise between the requirements of stealth and aerodynamics and which is compatible with the constraints of implementation under the aircraft A.
  • the tube 4 has a cross section, for example lozenge as shown in FIG. 8 or lenticular, having a direction XX of greater width, and said missile M is housed in said tube 4 so that said air inlets 27 are arranged in said direction XX of greater width, which allows to adapt the dimensions of the tube 4 to those of the missile M and thus to reduce them to maximum.
  • the missile M has a ventral air inlet 28 or a dorsal air inlet 29, the provisions of the missile are shown respectively in FIGS. 9 and 10.
  • the tube 4 has in this case a looser-shaped rhombic section. only in Figure 8, with a direction LL (orthogonal to the direction XX) more elongated.
  • the ventral air inlet 28 or the dorsal air inlet 29 is arranged in said direction L-L.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Heat Sensitive Colour Forming Recording (AREA)

Abstract

The system has first control units for separating the lower longitudinal part (7A) of the low radar signature tube from the top part (7B) which is connected to the external body of the aircraft (A) such that it creates in the tube, by its separation, an opening (8) allowing the complete ejection of the missile, with second control units (9) for controlling the first units, and third control units (10) controllable for movably connecting the missile when it is controlled, and fourth control units (11) for controlling the third control units. The weapon system is carried by a stealth aircraft, and has a low radar signature tube (4) which is radar absorbing, with a missile (M) located inside this tube.

Description

La présente invention concerne un moyen d'emport de missile, destiné à être monté sur la structure externe d'un aéronef furtif. La présente invention concerne également une arme montée sur un aéronef furtif et pourvue d'un tel moyen d'emport et d'au moins un missile, ainsi qu'un système d'arme comprenant un aéronef furtif muni d'une telle arme.The present invention relates to a missile carrying means intended to be mounted on the outer structure of a stealth aircraft. The present invention also relates to a weapon mounted on a stealth aircraft and provided with such a means of transport and at least one missile, and a weapon system comprising a stealth aircraft equipped with such a weapon.

Comme un système d'arme de ce type est généralement destiné à remplir une mission dans un environnement hostile, la réussite d'une telle mission dépend souvent, en grande partie, de la faculté du système d'arme à pouvoir échapper complètement ou au moins le plus longtemps possible à tout type de détection, et en particulier à une détection par radar.Since a weapon system of this type is generally intended to perform a mission in a hostile environment, the success of such a mission often depends, in large part, on the ability of the weapon system to escape completely or at least as long as possible for any type of detection, and in particular radar detection.

Aussi, pour augmenter l'efficacité d'un tel système d'arme, il est intéressant de réduire sa signature radar de manière à rendre plus difficile sa détection. On sait que la signature radar d'un aéronef, notamment d'un avion de combat, comportant un ou plusieurs missiles est modifiée par ce(s) dernier(s), lors de l'emport de ce(s) missile(s).Also, to increase the efficiency of such a weapon system, it is interesting to reduce its radar signature so as to make it more difficult to detect. It is known that the radar signature of an aircraft, in particular a combat aircraft, comprising one or more missiles is modified by this last one (s), during the carriage of this missile (s) .

Généralement, un tel système d'arme comporte un moyen d'emport externe des missiles sur l'aéronef. Un tel moyen d'emport externe comprend un lance-missiles qui est fixé sous l'aéronef et qui retient le(s) missile(s). Un moyen d'emport de ce type présente un inconvénient important en ce qui concerne la furtivité. En effet, il provoque la présence de nombreux et forts couplages électromagnétiques entre l'aéronef, le lance-missiles et les ailes, gouvernes et fuselage du missile, ce qui rend très difficile la réduction de la signature radar de cet ensemble formant ledit système d'arme.Generally, such a weapon system comprises means for external carriage of the missiles on the aircraft. Such external means of transport comprises a missile launcher which is fixed under the aircraft and which retains the missile (s). Such a means of transportation has a significant disadvantage with regard to stealth. Indeed, it causes the presence of many strong electromagnetic couplings between the aircraft, the missile launcher and the wings, control surfaces and fuselage of the missile, which makes it very difficult to reduce the radar signature of this assembly forming the said system. 'armed.

Pour remédier à cet inconvénient, le document FR-2 796 454 de la demanderesse prévoit une arme qui comporte, en plus du missile :

  • un tube furtif fixé sur la structure externe dudit aéronef et présentant une forme qui permet de minimiser la réflexion d'ondes électromagnétiques au moins suivant des directions prioritaires d'observation prédéterminées, ledit missile étant entièrement logé à l'intérieur dudit tube furtif ;
  • des moyens d'éjection commandables, permettant d'éjecter ledit missile hors dudit tube furtif ; et
  • des moyens de déclenchement commandables, destinés à réaliser le déclenchement de moyens de propulsion dudit missile après son éjection dudit tube furtif, lorsque l'aéronef se trouve au moins à une distance prédéterminée (distance de sécurité) dudit missile éjecté.
To remedy this drawback, document FR-2 796 454 of the applicant provides a weapon which comprises, in addition to the missile:
  • a stealth tube attached to the external structure of said aircraft and having a shape that minimizes the reflection of electromagnetic waves at least according to predetermined priority directions of observation, said missile being entirely housed inside said stealth tube;
  • controllable ejection means for ejecting said missile out of said stealth tube; and
  • controllable trigger means for triggering means for propelling said missile after ejecting said stealth tube, when the aircraft is at least at a predetermined distance (safety distance) from said ejected missile.

Cette arme permet de réduire la signature radar du système d'arme (formé de l'arme et de l'aéronef furtif). Toutefois, elle rend nécessaire, lors du tir du missile, la mise en oeuvre d'une opération difficile à maîtriser et dangereuse, à savoir l'éjection du missile hors du tube furtif. De plus, cette opération d'éjection nécessite des moyens d'éjection particuliers, ce qui augmente, bien que modérément, le coût et l'encombrement de ladite arme.This weapon reduces the radar signature of the weapon system (consisting of the weapon and the stealth aircraft). However, it makes it necessary, during firing of the missile, the implementation of a difficult operation to control and dangerous, namely the ejection of the missile out of the stealth tube. In addition, this ejection operation requires particular ejection means, which increases, although moderately, the cost and size of said weapon.

Par ailleurs, par le document US-A-5 717 397, on connaît un moyen d'emport de missile, destiné à être monté sur la structure externe d'un aéronef furtif. Ce moyen d'emport de missile comporte :

  • un tube furtif lié à ladite structure externe et présentant une forme qui permet de minimiser la réflexion d'ondes électromagnétiques au moins suivant des directions d'observation prédéterminées ;
  • des premiers moyens commandables, pour séparer une première partie dudit tube furtif d'une seconde partie de ce dernier ; et
  • des deuxièmes moyens pour commander lesdits premiers moyens.
Furthermore, US-A-5,717,397 discloses a missile carrying means for mounting on the outer structure of a stealth aircraft. This means of carrying missiles comprises:
  • a stealth tube bonded to said external structure and having a shape that minimizes the reflection of electromagnetic waves at least in predetermined directions of observation;
  • first controllable means for separating a first portion of said stealth tube from a second portion thereof; and
  • second means for controlling said first means.

La présente invention concerne un moyen d'emport qui a pour objet de remédier au moins partiellement aux inconvénients précités.The present invention relates to a transport means which is intended to at least partially overcome the aforementioned drawbacks.

A cet effet, selon l'invention, ledit moyen d'emport de missile, destiné à être monté sur la structure externe d'un aéronef furtif et comportant :

  • un tube furtif lié à ladite structure externe et présentant une forme qui permet de minimiser la réflexion d'ondes électromagnétiques au moins suivant des directions d'observation prédéterminées ;
  • des premiers moyens commandables, pour séparer une première partie dudit tube furtif d'une seconde partie de ce dernier ; et
  • des deuxièmes moyens pour commander lesdits premiers moyens,
est remarquable en ce que :
  • ladite première partie est une partie inférieure longitudinale dudit tube furtif ;
  • ladite seconde partie est une partie supérieure dudit tube furtif ;
  • ladite partie supérieure reste liée à ladite structure externe dudit aéronef après séparation de ladite partie inférieure longitudinale ; et
  • lesdites parties inférieure et supérieure sont telles qu'elles créent, lors de la séparation, une ouverture permettant l'éjection complète et usuelle d'un missile qui est logé dans ledit moyen d'emport.
For this purpose, according to the invention, said missile carrying means, intended to be mounted on the outer structure of a stealth aircraft and comprising:
  • a stealth tube bonded to said external structure and having a shape that minimizes the reflection of electromagnetic waves at least in predetermined directions of observation;
  • first controllable means for separating a first portion of said stealth tube from a second portion thereof; and
  • second means for controlling said first means,
is remarkable in that:
  • said first portion is a longitudinal lower portion of said stealth tube;
  • said second portion is an upper portion of said stealth tube;
  • said upper part remains connected to said external structure of said aircraft after separation of said longitudinal lower part; and
  • said lower and upper parts are such that they create, during separation, an opening for the complete and usual ejection of a missile which is housed in said carrier means.

La présente invention concerne également une arme, de coût réduit, pourvue d'au moins un missile et destinée à être montée sur un aéronef furtif, ladite arme pouvant être montée sur des aéronefs existants et étant telle que le système d'arme formé par ladite arme et l'aéronef qui la porte, présente une signature radar réduite pendant la phase de la mission pendant laquelle l'aéronef furtif porte l'arme, et surtout ladite arme permettant un tir sûr et maîtrisé du missile.The present invention also relates to a weapon, of reduced cost, provided with at least one missile and intended to be mounted on a stealth aircraft, said weapon being able to be mounted on existing aircraft and being such that the weapon system formed by said weapon and the aircraft carrying it, has a reduced radar signature during the mission phase during which the stealth aircraft carries the weapon, and especially said weapon allowing a safe and controlled missile.

A cet effet, selon l'invention, ladite arme montée sur un aéronef furtif et comportant :

  • un moyen d'emport de missile destiné à être monté sur la structure externe dudit aéronef ; et
  • au moins un missile qui est entièrement logé à l'intérieur dudit moyen d'emport de missile,
est remarquable en ce que :
  • ledit moyen d'emport de missile est du type de celui précité ; et
  • ladite arme comporte de plus :
    • des troisièmes moyens commandables, pour lier, de façon amovible, ledit missile à ladite structure externe dudit aéronef, lesdits troisièmes moyens libérant ledit missile lorsqu'ils sont commandés ; et
    • des quatrièmes moyens pour commander lesdits troisièmes moyens.
For this purpose, according to the invention, said weapon mounted on a stealth aircraft and comprising:
  • missile carrying means for mounting on the external structure of said aircraft; and
  • at least one missile which is entirely housed inside said missile carrying means,
is remarkable in that:
  • said missile carrying means is of the type mentioned above; and
  • said weapon further comprises:
    • third controllable means for releasably connecting said missile to said outer structure of said aircraft, said third means releasing said missile when commanded; and
    • fourth means for controlling said third means.

Par conséquent, grâce à l'arme conforme à l'invention, le missile est libéré (ou lancé) de façon usuelle, ce qui permet de réduire le coût et l'encombrement de l'arme.Therefore, with the weapon according to the invention, the missile is released (or launched) in the usual manner, which reduces the cost and bulk of the weapon.

De plus, comme le missile est logé dans un tube qui présente des caractéristiques de furtivité, précisées ci-dessous, on est en mesure de réduire la signature radar dudit système d'arme. En outre, l'arme conforme à l'invention peut être facilement montée sur tout type d'aéronef existant. En particulier, il n'est pas nécessaire de concevoir un aéronef spécifique pour mettre en oeuvre la présente invention. De plus, la présente invention est applicable à tout type de missile (ou de bombe) tiré à partir d'un aéronef, que ce soit un missile air-air, air-mer ou air-sol.In addition, since the missile is housed in a tube which has stealth characteristics, specified below, it is possible to reduce the radar signature of said weapon system. In addition, the weapon according to the invention can be easily mounted on any type of existing aircraft. In particular, it is not necessary to design a specific aircraft to implement the present invention. In addition, the present invention is applicable to any type of missile (or bomb) fired from an aircraft, be it an air-to-air, air-sea or air-to-ground missile.

Dans un mode de réalisation particulier, lesdits premiers moyens comportent des moyens de découpe, de type mécanique et/ou pyrotechnique, pour découper la paroi dudit tube furtif de manière à séparer ladite partie inférieure de ladite partie supérieure.In a particular embodiment, said first means comprise cutting means, of mechanical and / or pyrotechnic type, for cutting the wall of said stealth tube so as to separate said lower part of said upper part.

Par ailleurs, avantageusement, le moyen d'emport conforme à l'invention comporte de plus un système de liaison auxiliaire à pivot, qui est prévu entre lesdites parties inférieure et supérieure du tube furtif et qui permet la séparation complète de ladite partie inférieure, uniquement lorsque, après la commande desdits premiers moyens, cette dernière présente, par rapport à l'axe longitudinal dudit tube furtif, un angle prédéterminé. Ainsi, on peut adapter l'angle de séparation, notamment, aux conditions d'emport et de tir du missile sous l'aéronef de manière à assurer une séparation sans risque pour l'aéronef de ladite partie inférieure du tube furtif.Furthermore, advantageously, the carrying means according to the invention further comprises an auxiliary pivot connection system, which is provided between said lower and upper portions of the stealth tube and which allows the complete separation of said lower part, only when, after the control of said first means, the latter has, relative to the longitudinal axis of said stealth tube, a predetermined angle. Thus, it is possible to adapt the angle of separation, in particular, to the conditions of carriage and firing of the missile under the aircraft so as to ensure safe separation for the aircraft from said lower portion of the stealth tube.

En outre, pour augmenter la furtivité de ladite arme, de façon avantageuse, ledit tube furtif entoure également lesdits troisièmes moyens qui lient le missile à la structure externe de l'aéronef.In addition, to increase the stealth of said weapon, advantageously, said stealth tube also surrounds said third means which link the missile to the external structure of the aircraft.

Par ailleurs, dans un premier mode de réalisation, ledit moyen d'emport comporte de plus :

  • des cinquièmes moyens commandables pour lier, de façon amovible, ladite partie supérieure du tube furtif à ladite structure externe dudit aéronef, lesdits cinquièmes moyens libérant ladite partie supérieure lorsqu'ils sont commandés ; et
  • des sixièmes moyens pour commander lesdits cinquièmes moyens.
Furthermore, in a first embodiment, said carrying means further comprises:
  • fifth controllable means for releasably connecting said upper portion of the stealth tube to said outer structure of said aircraft, said fifth means releasing said upper portion when controlled; and
  • sixth means for controlling said fifth means.

En outre, dans un second mode de réalisation, ledit moyen d'emport comporte de plus :

  • au moins un coussin gonflable qui est agencé dans ladite partie supérieure du tube furtif et qui est destiné à fermer au moins en partie ladite ouverture qui est formée dans le tube furtif par la séparation de ladite partie inférieure ;
  • des septièmes moyens commandables pour gonfler ledit coussin ; et
  • des huitièmes moyens pour commander lesdits septièmes moyens.
In addition, in a second embodiment, said carrying means further comprises:
  • at least one airbag which is arranged in said upper part of the stealth tube and which is intended to close at least in part said opening which is formed in the stealth tube by the separation of said lower part;
  • seventh controllable means for inflating said cushion; and
  • eighth means for controlling said seventh means.

Ces deux derniers modes de réalisation permettent de réduire la traînée de l'aéronef après le tir, ainsi que la signature radar du système d'arme.These last two embodiments make it possible to reduce the drag of the aircraft after firing, as well as the radar signature of the weapon system.

De préférence, ledit tube furtif présente une forme cylindrique et comporte une coiffe en forme d'ogive à l'avant, dans le sens de vol de l'aéronef, ce qui permet de minimiser, voire d'annuler, les réflexions d'ondes électromagnétiques dans les directions d'observations généralement considérées comme principales ou prioritaires, à savoir celles correspondant à la visée des parties avant et latérales du tube.Preferably, said stealth tube has a cylindrical shape and comprises a nose-shaped cap at the front, in the direction of flight of the aircraft, which makes it possible to minimize or even cancel the wave reflections electromagnetic in the directions of observations generally considered as main or priority, namely those corresponding to the sight of the front and side parts of the tube.

De plus, ledit tube furtif présente de préférence une section transversale circulaire, losangique ou lenticulaire.In addition, said stealth tube preferably has a circular, rhombic or lenticular cross section.

Par ailleurs, pour augmenter la furtivité dudit tube et donc du système d'arme formé par l'arme et l'aéronef, avantageusement, ledit tube furtif est muni au moins sur une partie de sa face externe d'un revêtement absorbant des ondes électromagnétiques.Moreover, to increase the stealth of said tube and therefore of the weapon system formed by the weapon and the aircraft, advantageously, said stealth tube is provided at least on a portion of its outer face with a coating that absorbs electromagnetic waves. .

En outre, ledit tube est réalisé en matériau composite de type connu, présentant une haute tenue mécanique et une masse réduite, comme par exemple un matériau composite époxy ou à base de carbone ou de fibres aramides (du type "kevlar").In addition, said tube is made of composite material of known type having a high mechanical strength and a reduced mass, such as an epoxy or carbon-based composite material or aramid fibers (of the "Kevlar" type).

De plus, selon l'invention :

  • lorsque le missile est du type comportant des entrées d'air latérales, de préférence, le tube furtif présente une section transversale présentant une direction de plus grande largeur, et ledit missile est logé dans ledit tube furtif de sorte que lesdites entrées d'air latérales sont agencées selon ladite direction de plus grande largeur ; et
  • lorsque le missile est du type comportant une entrée d'air principale (ventrale ou dorsale), avantageusement le tube furtif présente une section transversale présentant au moins une direction allongée, et ledit missile est logé dans ledit tube furtif de sorte que ladite entrée d'air principale (ventrale ou dorsale) est agencée selon ladite direction allongée.
In addition, according to the invention:
  • when the missile is of the type having lateral air inlets, preferably, the stealth tube has a cross section having a direction of greater width, and said missile is housed in said stealth tube so that said side air inlets are arranged in said direction of greater width; and
  • when the missile is of the type comprising a main air inlet (ventral or dorsal), advantageously the stealth tube has a cross section having at least one elongate direction, and said missile is housed in said stealth tube so that said entry of main air (ventral or dorsal) is arranged in said elongate direction.

La présente invention concerne de plus un système d'arme qui comporte un aéronef furtif et une arme telle que celle précitée, qui est montée sur ledit aéronef furtif.The present invention further relates to a weapon system which includes a stealth aircraft and a weapon such as the one above, which is mounted on said stealth aircraft.

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 3 montrent respectivement trois phases successives du lancement d'un missile faisant partie d'un système d'arme conforme à l'invention.Figures 1 to 3 respectively show three successive phases of the launch of a missile forming part of a weapon system according to the invention.

Les figures 4 et 5 illustrent schématiquement en coupe longitudinale une arme conforme à l'invention et montée sur un aéronef, respectivement dans deux situations différentes.Figures 4 and 5 illustrate schematically in longitudinal section a weapon according to the invention and mounted on an aircraft, respectively in two different situations.

Les figures 6 et 7 illustrent schématiquement un système de liaison auxiliaire, correspondant respectivement aux situations des figures 4 et 5.Figures 6 and 7 schematically illustrate an auxiliary connection system, respectively corresponding to the situations of Figures 4 and 5.

Les figures 8 à 10 montrent, en coupe transversale, un missile agencé dans un moyen d'emport de missile conforme respectivement à des modes de réalisation différents de l'invention.Figures 8 to 10 show, in cross section, a missile arranged in a missile carrying means according respectively to different embodiments of the invention.

Le système d'arme 1 conforme à l'invention et représenté notamment sur la figure 1 comporte un aéronef A de type furtif, par exemple un avion de combat furtif, et au moins une arme 2 comprenant un missile M. Les figures 1 à 3 représentent le système d'arme 1 dans des phases successives lors d'un tir du missile M.The weapon system 1 according to the invention and shown in particular in FIG. 1 comprises a stealth type aircraft A, for example a stealth fighter aircraft, and at least one weapon 2 comprising a missile M. FIGS. 1 to 3 represent the weapon system 1 in successive phases during a firing of the missile M.

Ladite arme 2 est du type comportant, comme représenté en particulier sur la figure 4, en plus du missile M, un moyen d'emport 3 comprenant un tube furtif 4 précisé ci-dessous, qui est agencé sous l'aéronef A et qui est lié par une partie d'extrémité 5 à la structure (fuselage F) dudit aéronef A. Le missile M, un missile air-air, air-sol ou air-mer, ou bien une bombe (guidée ou non ; propulsée ou non), est complètement logé dans ledit tube 4 de manière à ne pas être visible de l'extérieur et ainsi à ne pas modifier la signature radar du système d'arme 1.Said weapon 2 is of the type comprising, as represented in particular in FIG. 4, in addition to the missile M, a carrying means 3 comprising a stealth tube 4 specified below, which is arranged under the aircraft A and which is linked by an end portion 5 to the structure (fuselage F) of said aircraft A. The missile M, an air-to-air, air-to-ground or air-sea missile, or a bomb (guided or not, propelled or not) , is completely housed in said tube 4 so as not to be visible from the outside and thus not to modify the radar signature of the weapon system 1.

Selon l'invention, ladite arme 2 comporte de plus :

  • des moyens 6 commandables représentés schématiquement sur la figure 4, pour séparer une partie inférieure 7A longitudinale dudit tube furtif 4 d'une partie restante supérieure 7B qui reste liée à ladite structure externe F dudit aéronef A de manière à créer dans ledit tube 4, par cette séparation, une ouverture 8 (figure 5) permettant l'éjection complète dudit missile M ;
  • des moyens 9 (automatiques ou manuels) représentés schématiquement sur les figures 4 et 5, pour commander lesdits moyens 6 ;
  • des moyens 10 commandables pour lier, de façon amovible, ledit missile M à ladite structure externe F dudit aéronef A, lesdits moyens 10 libérant ledit missile M lorsqu'ils sont commandés ; et
  • des moyens 11 (automatiques ou manuels) représentés schématiquement sur les figures 4 et 5, pour commander lesdits moyens 10.
According to the invention, said weapon 2 further comprises:
  • controllable means 6 shown diagrammatically in FIG. 4, for separating a longitudinal lower portion 7A of said stealth tube 4 from an upper remaining portion 7B which remains connected to said external structure F of said aircraft A so as to create in said tube 4, by this separation, an opening 8 (Figure 5) for the complete ejection of said missile M;
  • means 9 (automatic or manual) diagrammatically shown in FIGS. 4 and 5 for controlling said means 6;
  • controllable means 10 for detachably connecting said missile M to said external structure F of said aircraft A, said means 10 releasing said missile M when they are controlled; and
  • means 11 (automatic or manual) shown diagrammatically in FIGS. 4 and 5, for controlling said means 10.

Dans un mode de réalisation préféré, lesdits moyens 6 comportent des moyens de découpe mécanique et/ou pyrotechnique, pour découper selon une ligne de découpe 12 la paroi 4A dudit tube furtif 4 de manière à séparer ladite partie inférieure 7A de ladite partie supérieure 7B.In a preferred embodiment, said means 6 comprise mechanical and / or pyrotechnic cutting means for cutting along a cutting line 12 the wall 4A of said stealth tube 4 so as to separate said lower part 7A from said upper part 7B.

L'arme 2 comporte, de plus, un système de liaison auxiliaire 13 (figures 4 à 7) qui est prévu à l'arrière du tube furtif 4 entre lesdites parties inférieure 7A et supérieure 7B du tube furtif 4 et qui permet la séparation complète de ladite partie inférieure 7A, uniquement lorsque, après la commande desdits moyens 6, cette dernière présente par rapport à l'axe longitudinal dudit tube furtif 4 un angle α prédéterminé, comme représenté sur les figures 5 et 7.The weapon 2 further comprises an auxiliary connection system 13 (FIGS. 4 to 7) which is provided behind the stealth tube 4 between said lower portions 7A and 7B of the stealth tube 4 and which allows complete separation. of said lower part 7A, only when, after the control of said means 6, the latter has with respect to the longitudinal axis of said stealth tube 4 a predetermined angle α, as shown in Figures 5 and 7.

Ce système de liaison auxiliaire 13 est un système à pivot 14 qui comporte, comme représenté sur les figures 6 et 7, une boule 15 solidaire de la partie supérieure 7B du tube 4. Cette boule 15 est munie d'une découpe 16 et coopère avec une extrémité 17 en arc de cercle, qui est reliée à la partie inférieure 7A du tube 4 et qui entoure cette boule 15. Grâce à la découpe 16, on peut régler l'angle de séparation α et ainsi l'adapter, notamment, aux conditions d'emport et de tir du missile M sous l'aéronef A, de manière à assurer une séparation sans risque pour l'aéronef A de ladite partie inférieure 7A du tube furtif 4.This auxiliary connection system 13 is a pivot system 14 which comprises, as shown in Figures 6 and 7, a ball 15 secured to the upper portion 7B of the tube 4. This ball 15 is provided with a cutout 16 and cooperates with an end 17 in an arc, which is connected to the lower part 7A of the tube 4 and which surrounds the ball 15. With the cutout 16, one can adjust the separation angle α and thus adapt, in particular, to the conditions of carriage and firing of the missile M under the aircraft A, so as to ensure a risk-free separation for the aircraft A from said lower part 7A of the stealth tube 4.

Les moyens 10 comportent un pylône usuel 18 auquel est lié le missile M. Ce pylône 18 comporte des moyens de fixation du missile M et des moyens de déverrouillage de cette fixation.The means 10 comprise a conventional pylon 18 to which the missile M is bonded. This pylon 18 comprises means for fixing the missile M and means for unlocking this attachment.

De plus, le tube furtif 4 entoure également ledit pylône 18 par sa partie d'extrémité, ce qui permet de minimiser les réflexions d'ondes électromagnétiques à ce niveau.In addition, the stealth tube 4 also surrounds said pylon 18 by its end portion, which minimizes the reflections of electromagnetic waves at this level.

Ainsi, comme grâce à l'invention, le missile M et le pylône 18 sont logés dans ledit tube 4 qui présente des caractéristiques de furtivité, précisées ci-dessous, on est en mesure de réduire la signature radar dudit système d'arme 1.Thus, as thanks to the invention, the missile M and the pylon 18 are housed in said tube 4 which has stealth characteristics, specified below, it is possible to reduce the radar signature of said weapon system 1.

De plus, l'arme 2 ne nécessite pas de moyens d'éjection spécifiques pour éjecter le missile M hors du tube 4, le missile M étant libéré et éjecté de façon usuelle (notamment en chutant grâce à son propre poids), ce qui permet de réduire le coût et l'encombrement de ladite arme 2. Le missile M peut également être éjecté par l'avant en étant tiré sur rail de façon usuelle, l'ouverture 8 libérant un passage vers l'avant à cet effet.In addition, the weapon 2 does not require specific ejection means for ejecting the missile M out of the tube 4, the missile M being released and ejected in the usual way (in particular by falling thanks to its own weight), which allows to reduce the cost and bulk of said weapon 2. The missile M can also be ejected from the front by being drawn on rail in the usual manner, the opening 8 releasing a passage forwards for this purpose.

En outre, grâce à l'éjection conforme à l'invention, on est en mesure de réaliser un tir sûr et non dangereux pour l'aéronef A.In addition, thanks to the ejection according to the invention, it is able to achieve a safe and non-dangerous shooting for the aircraft A.

On notera que, dans le cadre de la présente invention, l'installation du tube 4 sous l'aéronef A est identique à celle d'un réservoir supplémentaire de carburant. Les liaisons mécaniques sont de même type et les connexions électriques sont assurées par un nombre restreint de connecteurs. Les liaisons mécaniques et les connexions électriques sont mises en oeuvre par le pylône 18. L'interface entre le tube 4 et l'aéronef A est donc simplifiée. Elle est de plus, de préférence, standardisée, notamment pour faciliter la fabrication.It will be noted that, in the context of the present invention, the installation of the tube 4 under the aircraft A is identical to that of an additional fuel tank. The mechanical connections are of the same type and the electrical connections are ensured by a limited number of connectors. The mechanical connections and the electrical connections are implemented by the tower 18. The interface between the tube 4 and the aircraft A is simplified. It is moreover, preferably, standardized, in particular to facilitate manufacture.

Les tubes 4 sont fixés longitudinalement audit aéronef A, sous les ailes B, C et/ou le fuselage F de ce dernier. Le nombre d'armes 2 et donc de tubes 4 est adapté aux dimensions de l'aéronef A et à la mission à réaliser. Dans l'exemple de réalisation représenté sur la figure 1, deux tubes 4 sont fixés sous les ailes B et C de l'aéronef A et un troisième tube 4 est fixé au centre sous le fuselage F.The tubes 4 are fixed longitudinally to said aircraft A, under the wings B, C and / or the fuselage F of the latter. The number of weapons 2 and therefore tubes 4 is adapted to the dimensions of the aircraft A and mission to achieve. In the exemplary embodiment shown in FIG. 1, two tubes 4 are fixed under the wings B and C of the aircraft A and a third tube 4 is fixed at the center below the fuselage F.

On notera toutefois que, dans le cadre de la présente invention, un tube furtif peut comporter, dans un mode de réalisation particulier non représenté, plus d'un missile, par exemple deux, trois ... missiles.It will be noted, however, that in the context of the present invention, a stealth tube may comprise, in a particular embodiment not shown, more than one missile, for example two, three ... missiles.

Par ailleurs, pour réduire les dimensions du tube 4, le missile M comporte des surfaces portantes 19 (ailes, gouvernes) susceptibles de prendre l'une de deux positions : une position repliée (figure 4) et une position déployée. Lesdites surfaces portantes 19 se trouvent dans la position repliée tant que le missile M est logé dans le tube furtif 4 et elles sont amenées automatiquement par des moyens connus et non représentés dans la position déployée, pour une partie d'entre elles lorsque la partie inférieure 7A est séparée (figures 2 et 5) et pour le reste lorsque le missile M est éjecté hors de ladite partie supérieure 7B du tube 4 (figure 3).Moreover, to reduce the dimensions of the tube 4, the missile M comprises bearing surfaces 19 (flanges, control surfaces) may take one of two positions: a folded position (Figure 4) and an extended position. Said bearing surfaces 19 are in the folded position as long as the missile M is housed in the stealth tube 4 and they are automatically supplied by known means and not shown in the deployed position, for a part of them when the lower part 7A is separated (Figures 2 and 5) and for the rest when the missile M is ejected out of said upper part 7B of the tube 4 (Figure 3).

Toutes les opérations d'intégration et de contrôle de l'arme 2 sont effectuées en usine, en utilisant des moyens appropriés à ce type de matériel, ce qui permet d'augmenter la fiabilité et la sécurité de l'arme 2. Ainsi, le tube 4 protège le missile M au moins en emport sur l'aéronef A, mais généralement pendant toutes les phases de sa vie opérationnelle.All integration and control operations of the weapon 2 are performed at the factory, using means appropriate to this type of equipment, which increases the reliability and safety of the weapon 2. tube 4 protects the missile M at least in the aircraft A, but generally during all phases of its operational life.

On précise à présent les différentes étapes conformes à l'invention du tir ou lancement d'un missile M, en référence aux figures 1 à 3. Lorsque, à partir de la situation de vol de la figure 1, un ordre de tir du missile M est donné :

  • les moyens 9 (par exemple un bouton qui est actionné par un pilote de l'aéronef A) commandent les moyens 6 qui déclenchent alors la séparation de la partie inférieure 7A du tube 4 de sa partie supérieure 7B, comme représenté sur la figure 2. Ainsi séparée, cette partie inférieure 7A chute et s'écarte de l'aéronef A. Le missile M reste lié à l'aéronef grâce aux moyens 10 comprenant le pylône 18. Les surfaces portantes 19 situées sous le missile M, qui sont libérées par cette séparation, sont quant à elles automatiquement déployées ;
  • les moyens 11 (par exemple un bouton qui est actionné par un pilote de l'aéronef A) commandent les moyens 10 qui libèrent le missile M, ce dernier chute alors grâce à son seul poids (ou est éjecté vers l'avant) et s'écarte de l'aéronef A, comme représenté sur la figure 3. Toutes les surfaces portantes 19 sont alors déployées ; et
  • lorsque l'aéronef A se trouve à une distance de sécurité du missile M, des moyens de propulsion non représentés de ce dernier sont déclenchés. Le missile M est ensuite guidé de façon usuelle pour réaliser sa mission, par exemple l'interception d'un mobile (avion ou véhicule terrestre ou maritime) ou la destruction d'un bâtiment.
We now specify the various steps according to the invention of the firing or launching of an M missile, with reference to FIGS. 1 to 3. When, from the flight situation of FIG. 1, a firing order of the missile M is given:
  • the means 9 (for example a button which is actuated by a pilot of the aircraft A) control the means 6 which then trigger the separation of the lower part 7A of the tube 4 from its upper part 7B, as shown in FIG. Thus separated, this lower part 7A falls and deviates from the aircraft A. The missile M remains linked to the aircraft by the means 10 comprising the pylon 18. The bearing surfaces 19 located under the missile M, which are released by this separation, they are automatically deployed;
  • the means 11 (for example a button which is actuated by a pilot of the aircraft A) control the means 10 which release the missile M, the latter then falls thanks to its weight alone (or is ejected forwards) and away from the aircraft A, as shown in Figure 3. All the bearing surfaces 19 are then deployed; and
  • when the aircraft A is at a safety distance from the missile M, unrepresented propulsion means of the latter are triggered. The missile M is then routinely guided to achieve its mission, for example the interception of a mobile (aircraft or land or sea vehicle) or the destruction of a building.

Dans un mode de réalisation particulier représenté schématiquement sur les figures 4 et 5, le moyen d'emport 3 comporte de plus :

  • des moyens 20 commandables pour lier, de façon amovible, la partie d'extrémité 5 (extrémité supérieure de la partie supérieure 7B) du tube furtif 4 à ladite structure externe F dudit aéronef A, lesdits moyens 20 libérant ladite partie supérieure 7B lorsqu'ils sont commandés ; et
  • des moyens 21 (automatiques ou manuels) pour commander lesdits moyens 20.
In a particular embodiment shown diagrammatically in FIGS. 4 and 5, the carrying means 3 further comprises:
  • controllable means 20 for releasably connecting the end portion 5 (upper end of the upper part 7B) of the stealth tube 4 to said outer structure F of said aircraft A, said means 20 releasing said upper part 7B when are ordered; and
  • means 21 (automatic or manual) for controlling said means 20.

Par ailleurs, dans un autre mode de réalisation représenté schématiquement sur la figure 8, ledit moyen d'emport 3 comporte de plus :

  • au moins un coussin gonflable 22 usuel, qui est agencé dans ladite partie supérieure 7B du tube furtif 4 et qui est destiné à fermer (après son gonflement) au moins en partie ladite ouverture 8 qui est formée dans ledit tube furtif 4 par la séparation de ladite partie inférieure 7A ;
  • des moyens 23 usuels commandables, pour gonfler ledit coussin 22 ; et
  • des moyens 24 (automatiques ou manuels) pour commander lesdits moyens 23.
Moreover, in another embodiment diagrammatically shown in FIG. 8, said carrying means 3 further comprises:
  • at least one usual airbag 22, which is arranged in said upper part 7B of the stealth tube 4 and which is intended to close (after swelling) at least in part said opening 8 which is formed in said stealth tube 4 by the separation of said lower portion 7A;
  • conventional means 23 controllable for inflating said cushion 22; and
  • means 24 (automatic or manual) for controlling said means 23.

Ces deux derniers modes de réalisation permettent de réduire la traînée et la signature radar de l'aéronef A après le tir du missile M.These last two embodiments make it possible to reduce the drag and the radar signature of the aircraft A after firing the missile M.

On notera que, pour l'arme 2 conforme à l'invention, les conditions de tir et les mesures de sécurité à prendre en compte sont les mêmes que celles prises en compte lors du tir d'un missile, en emport externe, avec un lance-missiles usuel.Note that for the weapon 2 according to the invention, the shooting conditions and security measures to be taken into account are the same. than those taken into account when firing a missile, in external carriage, with a conventional missile launcher.

Selon l'invention, le tube furtif 4 présente une forme qui permet de minimiser, voire d'annuler, la réflexion d'ondes électromagnétiques au moins suivant des directions d'observation prédéterminées.According to the invention, the stealth tube 4 has a shape that makes it possible to minimize or even cancel the reflection of electromagnetic waves at least along predetermined directions of observation.

Dans le mode de réalisation préféré représenté sur les figures, ledit tube furtif 4 présente une forme cylindrique et comporte une coiffe 25 en forme d'ogive à l'avant, dans le sens de vol de l'aéronef A, ce qui permet de minimiser la réflexion dans les directions d'observation visant les parties avant et latérales du tube 4.In the preferred embodiment shown in the figures, said stealth tube 4 has a cylindrical shape and comprises a nose-shaped cap 25 in the forward direction, in the direction of flight of the aircraft A, which makes it possible to minimize the reflection in the observation directions aimed at the front and lateral parts of the tube 4.

Le tube 4 présente à l'arrière une forme aplatie qui réalise un compromis entre les exigences de furtivité et d'aérodynamique et qui est compatible avec les contraintes d'implantation sous l'aéronef A.The tube 4 has at the rear a flattened shape that makes a compromise between the requirements of stealth and aerodynamics and which is compatible with the constraints of implementation under the aircraft A.

De plus, selon l'invention, ledit tube 4 :

  • présente de préférence une section transversale circulaire (figures 1 à 5), losangique (figures 8 à 10) ou lenticulaire ;
  • est réalisé en un matériau composite présentant simultanément une tenue mécanique élevée et une masse réduite ; et
  • est muni au moins sur une partie de sa face externe 26 (notamment sur les faces avant et latérales) d'un revêtement non représenté et absorbant des ondes électromagnétiques, ce qui permet de réduire davantage la signature radar.
In addition, according to the invention, said tube 4:
  • preferably has a circular (FIGS. 1 to 5), rhombic (FIGS. 8 to 10) or lenticular cross-section;
  • is made of a composite material simultaneously having a high mechanical strength and a reduced mass; and
  • is provided at least on a portion of its outer face 26 (especially on the front and side faces) of a coating not shown and absorbing electromagnetic waves, which further reduces the radar signature.

Par ailleurs, dans le cas où le missile M comporte des entrées d'air 27 latérales, le tube 4 présente une section transversale, par exemple losangique comme représenté sur la figure 8 ou lenticulaire, présentant une direction X-X de plus grande largeur, et ledit missile M est logé dans ledit tube 4 de sorte que lesdites entrées d'air 27 sont agencées selon ladite direction X-X de plus grande largeur, ce qui permet d'adapter les dimensions du tube 4 à celles du missile M et donc de les réduire au maximum.Moreover, in the case where the missile M has lateral air inlets 27, the tube 4 has a cross section, for example lozenge as shown in FIG. 8 or lenticular, having a direction XX of greater width, and said missile M is housed in said tube 4 so that said air inlets 27 are arranged in said direction XX of greater width, which allows to adapt the dimensions of the tube 4 to those of the missile M and thus to reduce them to maximum.

Dans le cas où le missile M comporte une entrée d'air ventrale 28 ou une entrée d'air dorsale 29, les dispositions du missile sont représentées respectivement sur les figures 9 et 10. Le tube 4 présente dans ce cas une section losangique moins aplatie que sur la figure 8, avec une direction L-L (orthogonale à la direction X-X) plus allongée. L'entrée d'air ventrale 28 ou l'entrée d'air dorsale 29 est agencée selon ladite direction L-L.In the case where the missile M has a ventral air inlet 28 or a dorsal air inlet 29, the provisions of the missile are shown respectively in FIGS. 9 and 10. The tube 4 has in this case a looser-shaped rhombic section. only in Figure 8, with a direction LL (orthogonal to the direction XX) more elongated. The ventral air inlet 28 or the dorsal air inlet 29 is arranged in said direction L-L.

Claims (12)

  1. Means of missile carriage, intended to be mounted on the external structure (F) of a stealth aircraft (A) and comprising:
    - a stealth tube (4) tied to the said external structure (F) and exhibiting a shape which makes it possible to minimize the reflection of electromagnetic waves at least along predetermined directions of observation;
    - first controllable means (6), for separating a first part (7A) of the said stealth tube (4) from a second part (7B) of the latter; and
    - second means (9) for controlling the said first means (6),
    characterized in that:
    - the said first part is a longitudinal lower part (7A) of the said stealth tube (4);
    - the said second part is an upper part (7B) of the said stealth tube (4);
    - the said upper part (7B) remains tied to the said external structure (F) of the said aircraft (A) after separation of the said longitudinal lower part (7A); and
    - the said lower and upper parts (7A, 7B) are such that they create, during separation, an opening (8) allowing the complete and standard ejection of a missile (M) which is lodged in the said means of carriage (3).
  2. Means of carriage according to Claim 1,
    characterized in that the said first means (6) comprise cutting means, for cutting the wall (4A) of the said stealth tube (4), in such a way as to separate the said lower part (7A) from the said upper part (7B).
  3. Means of carriage according to one of Claims 1 and 2,
    characterized in that it furthermore comprises an auxiliary linking system (13) with pivot (14) which is provided between the said lower (7A) and upper (7B) parts of the said stealth tube (4) and which allows the complete separation of the said lower part (7A), when, after the commanding of the said first means (6), this part exhibits, with respect to the longitudinal axis of the said stealth tube (4), a predetermined angle (α).
  4. Means of carriage according to any one of Claims 1 to 3,
    characterized in that it furthermore comprises:
    - fifth controllable means (20) for tying, in a removable manner, the said upper part of the stealth tube (4) to the external structure of the said aircraft (A), the said fifth means (20) freeing the said upper part (7B) when they are commanded; and
    - sixth means (21) for controlling the said fifth means (20).
  5. Means of carriage according to any one of Claims 1 to 3,
    characterized in that it furthermore comprises:
    - at least one inflatable cushion (22) which is arranged in the said upper part (7B) of the stealth tube (4) and which is intended to close at least in part the said opening (8) which is formed in the said stealth tube (4) by the separation of the said lower part (7A);
    - seventh means (23) for inflating the said cushion (22); and
    - eighth means (24) for controlling the said seventh means (23).
  6. Means of carriage according to any one of Claims 1 to 5,
    characterized in that the said stealth tube (4) exhibits a cylindrical shape and comprises a cowl (25) in the shape of an ogive at the front, in the sense of flight of the aircraft (A).
  7. Means of carriage according to any one of Claims 1 to 6,
    characterized in that the said stealth tube (4) is furnished at least on a part of its external face (26) with a coating that absorbs electromagnetic waves.
  8. Weapon mounted on a stealth aircraft (A) and comprising:
    - a means of missile carriage (3) intended to be mounted on the external structure (F) of the said aircraft (A); and
    - at least one missile (M) which is lodged entirely inside the said means of missile carriage (3),
    characterized in that:
    - the said means of missile carriage (3) is of the type of that specified under any one of Claims 1 to 7; and
    - the said weapon (2) furthermore comprises:
    • third controllable means (10) for tying, in a removable manner, the said missile (M) to the said external structure of the said aircraft (A), the said third means (10) freeing the said missile (M) when they are commanded; and
    • fourth means (11) for controlling the said third means (10).
  9. Weapon according to Claim 8,
    characterized in that the said stealth tube (4) surrounds the said third means (10).
  10. Weapon according to any one of Claims 8 and 9,
    characterized in that the said missile (M) is provided with lateral air inlets (27), and in that the said stealth tube (4) exhibits a transverse section exhibiting a direction (X-X) of greater width, and in that the said missile (M) is lodged in the said stealth tube (4) so that the said lateral air inlets (27) are arranged along the said direction (X-X) of greater width.
  11. Weapon according to any one of Claims 8 and 9,
    characterized in that the said missile (M) is provided with a main air inlet (28, 29), in that the said stealth tube (4) exhibits a transverse section exhibiting at least one elongate direction (L-L), and in that the said missile (M) is lodged in the said stealth tube (4) so that the said main air inlet (28, 29) is arranged along the said elongate direction (L-L).
  12. Weapon system,
    characterized in that it comprises a stealth aircraft (A) and at least one weapon (2) such as that specified under any one of Claims 8 to 11, which is mounted on the said stealth aircraft (A).
EP03291082A 2002-06-20 2003-05-06 Weapon provided with a missile and which is mounted on a stealth aircraft, and a weapon system comprising a stealth aircraft and such a weapon Expired - Lifetime EP1375345B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0207632 2002-06-20
FR0207632A FR2841333B1 (en) 2002-06-20 2002-06-20 WEAPON ARRANGED ON A FURTHER AIRCRAFT AND PROVIDED WITH A MISSILE, AND AN ARM SYSTEM COMPRISING A FURTHER AIRCRAFT AND A SUCH ARMY

Publications (2)

Publication Number Publication Date
EP1375345A1 EP1375345A1 (en) 2004-01-02
EP1375345B1 true EP1375345B1 (en) 2006-06-14

Family

ID=29717061

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Application Number Title Priority Date Filing Date
EP03291082A Expired - Lifetime EP1375345B1 (en) 2002-06-20 2003-05-06 Weapon provided with a missile and which is mounted on a stealth aircraft, and a weapon system comprising a stealth aircraft and such a weapon

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Country Link
EP (1) EP1375345B1 (en)
AT (1) ATE329826T1 (en)
DE (1) DE60306038D1 (en)
FR (1) FR2841333B1 (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITRM20110626A1 (en) * 2011-11-25 2013-05-26 Aeronautical Service S R L METHOD FOR THE REALIZATION OF SUPPORT SUPPORTS FOR AVIONICS.
DE102014004838A1 (en) 2014-04-02 2015-10-08 Airbus Defence and Space GmbH Effector with discardable Tarnschale
WO2016207623A1 (en) 2015-06-22 2016-12-29 Bae Systems Plc Aircraft payload launch system
EP3109157A1 (en) * 2015-06-22 2016-12-28 BAE Systems PLC Aircraft stores transport system
JP6480024B2 (en) * 2015-06-22 2019-03-06 ビ−エイイ− システムズ パブリック リミテッド カンパニ−ＢＡＥ ＳＹＳＴＥＭＳ ｐｌｃ Aircraft equipment transportation system
CN110530204B (en) * 2019-07-17 2021-10-01 北京玻钢院复合材料有限公司 Directional separating piece and directional separating structure of integrally-broken type launching box sealing cover

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5279199A (en) * 1992-08-14 1994-01-18 Hughes Aircraft Company Technique and apparatus for rearward launch of a missile
US5717397A (en) * 1996-05-17 1998-02-10 Lockheed Martin Corporation Low observable shape conversion for aircraft weaponry
FR2796454B1 (en) 1999-07-16 2002-08-09 Aerospatiale Matra Missiles WEAPON MOUNTED ON A FURTIVE AIRCRAFT PROVIDED WITH A MISSILE, AS WELL AS A WEAPON SYSTEM COMPRISING A FURTIVE AIRCRAFT AND SUCH A WEAPON

Also Published As

Publication number Publication date
FR2841333A1 (en) 2003-12-26
DE60306038D1 (en) 2006-07-27
FR2841333B1 (en) 2006-05-26
EP1375345A1 (en) 2004-01-02
ATE329826T1 (en) 2006-07-15

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