EP0679861B1 - Firing installation for wire guided ammunition from a mobile launcher - Google Patents
Firing installation for wire guided ammunition from a mobile launcher Download PDFInfo
- Publication number
- EP0679861B1 EP0679861B1 EP19950400899 EP95400899A EP0679861B1 EP 0679861 B1 EP0679861 B1 EP 0679861B1 EP 19950400899 EP19950400899 EP 19950400899 EP 95400899 A EP95400899 A EP 95400899A EP 0679861 B1 EP0679861 B1 EP 0679861B1
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- EP
- European Patent Office
- Prior art keywords
- launch tube
- reel
- pivoting
- installation according
- axis
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
- F42B15/04—Arrangements thereon for guidance or control using wire, e.g. for guiding ground-to-ground rockets
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
- F41G7/30—Command link guidance systems
- F41G7/32—Command link guidance systems for wire-guided missiles
Definitions
- the invention relates to an installation designed to fire wire-guided ammunition such as a missile, from a mobile launcher such as a ship or an aircraft.
- the filiform connecting member can in particular be made up of several conductors electrical or optical fiber. Because the transmission capacity of optical fiber is very far superior to that of drivers electrical connections over distances of several tens of kilometers can be insured when using an optical fiber, while these connections are limited to approximately 12 km in the case of electrical conductors. The flight time of the ammunition is considerably increased and reached several minutes.
- the use of a coil linked to the launcher mobile is also illustrated in the document EP-A-0 443 623.
- the coil linked to the mobile launcher is either attached directly to the latter so that its axis is oriented vertically, either mounted on the launcher via a gimbal type joint.
- the angle formed between the axis of unwinding of the organ of filiform connection and the axis of the coil limits the maximum permissible unwinding speed.
- the second configuration is incompatible with shooting a ammunition from a launch tube since the loop which forms between the ammunition and the coil linked to the launcher would then pass through the launch tube. In indeed, any significant change in focus of the launch tube resulting from displacement of the launcher mobile would exert significant mechanical stress on the filiform connecting member already unrolled since ammunition.
- the subject of the invention is precisely a wire-fired munition firing installation, from a launch tube on board a mobile launcher, do not not having the disadvantages of the installations existing and in particular allowing the mobile launcher to follow any trajectory after firing the ammunition with a higher speed than in the existing facilities and without any part of the filiform connecting member is exposed and risks to be damaged at any time.
- this result is obtained through an ammunition firing facility guided by a mobile launcher, comprising a tube launch ammunition normally housed in the launch tube, and a threadlike connecting member able to unwind from a first reel linked to the ammunition and a second coil linked to the tube launch, characterized by the fact that the launch has a front door, normally closed, the second coil being normally mounted in the launch tube, between the ammunition and the front door, through a means of tilting this second coil outside the launch tube, able to be activated before firing the ammunition.
- the connecting member threadlike that connects the ammunition to the launch tube is completely placed inside the latter before firing.
- the housing of the linked coil to the mobile launcher at the front of the ammunition and the tilting of this coil outside the tube launch just before firing allow practically cancel the angle formed between the axis of unwinding and axis of the reel when the launcher makes a U-turn and moves away from the ammunition after firing.
- the second coil is fixed on an internal face of the front door, the means of tilting being interposed between the latter and the launch tube.
- a buffer length of the filiform connecting member located between parts of this organ normally wound on the first and the second coil, is normally associated with the second coil.
- means for ejecting this buffer length capable of being actuated after a actuation of the tilting means and before putting ammunition fire, are mounted in the second coil. This feature initiates the unwinding of the coil linked to the launcher, whereas this the latter has not yet completed his turn, without the filiform connecting member is not subjected to mechanical constraints too severe.
- the second coil comprises a core in which the buffer length of the organ is housed of filiform connection and the ejection means.
- the buffer length of the filiform connecting member advantageously supports means for increasing the drag coefficient.
- this section is reinforced by protective sheathing.
- the tilting means controls a about 270 ° pivoting of the second coil between a normal position, internal to the launch tube, in which the axis of the second coil is substantially orthogonal to the axis of the launch tube, and a firing position, external to the tube launch, in which the axis of the second coil is substantially parallel to the axis of the tube launch.
- the second coil has then a cover, advantageously covered with a fairing, surrounding the part of the connecting member filiform normally wound on the second coil.
- This cover has a circular outlet opening from the filiform connecting member, centered on the axis of the second coil and oriented upwards respectively or backwards depending on whether the second coil occupies its normal position or its firing position.
- the launch On its outer surface, the launch then advantageously includes means of locking the second coil in its position Firing.
- the tilting means comprises at minus a tilt control system and a articulation hinge of the second coil on the launch tube.
- the hinge may include, either a single pivot axis orthogonal to the axis of the launch tube, i.e. two pivot axes parallel, orthogonal to the axis of the launch tube.
- at least one piece of link able to pivot relative to the launching tube around a first of the pivot axes and by how the second coil can rotate around the second of the pivot axes.
- the launch tube further includes a rear door, normally closed, as well as means opening of this door, capable of being actuated during the firing of the ammunition.
- the reference 10 designates a helicopter on which several are on board firing installations 12 in accordance with the invention. Each of these shooting installations includes a tube of launch 14 (Fig. 2), a guided missile 16 and a fiber optic 18 permanently connecting missile 16 to launch tube 14. More specifically, Figure 1 depicts helicopter 10 making a U-turn after the firing of one of the missiles 16.
- the invention does not not only applies in case the mobile launcher consists of a helicopter 10, but concerns also the case where this launcher is constituted by an aircraft of a different nature, a surface ship or submarine, or even a land vehicle.
- missile 16 can be replaced by any ammunition wire-guided adapted to the launcher concerned.
- the fiber optics can be replaced by any other threadlike connection such as a set of conductors electric.
- a second section 18b of the optical fiber 18 comes out of missile 16 at the back of it and runs inside the launch tube 14, along missile 16, to connect the first section 18a mounted in the missile to a second coil 22 placed in the launch tube 14, in front of missile 16. More precisely, the second coil 22 is fixed on the inner face of a front door 24 of the launch tube 14, which normally closes the front end of this tube. The second coil 22 is thus interposed between missile 16 and front door 24, inside of the launch tube 14, when the firing installation 12 occupies its normal storage position.
- the section 18b of the optical fiber, which connects coils 20 and 22, is reinforced by cladding of protection which allows it to resist attacks produced by the missile propellant 16, during ejecting the latter from the launch tube 14.
- the second coil 22 includes a core 26, generally cylindrical or frustoconical in shape, eventually ended with flared ends. In the normal storage position illustrated in the figure 2, the axis of this core 26 is oriented substantially vertically, its lower end being connected to the front door 24 by a support 27.
- the core 26 In its part turned upwards when the coil 22 occupies its storage position, the core 26 forms a housing, open upwards, in which a buffer length 18c of the optical fiber is stored 18, for example in the form of a winding.
- the part of the core 26 adjacent to the buffer length 18c of optical fiber is used to house ejection means 28 which function, as we will see later, to expel the buffer length 18c from optical fiber outside the housing formed in the core 26, just before firing missile 16.
- ejection means 28 can be constituted either by a spring mechanism, either by a pneumatic system or pyrotechnic.
- buffer length 18c optical fiber supports means (not shown) to artificially increase the coefficient of aerodynamic drag of this part of the fiber when it is outside the tube of launch 14.
- the buffer length 18c of the optical fiber connects the section 18b of this fiber to a section 18d of optical fiber, wound together in several layers on the core 26 of the coil 22.
- the length of the section 18d wound on the coil 22 is generally less than or at most equal to the length of the section 18a wound on the reel 20.
- a suitable adhesive ensures unrolling progressive and regular fiber optic from coils 20 and 22.
- the end of the optical fiber 18 coming out coil 22 opposite the buffer length 18b is connected by a fiber section 18th to a connector optic 30 mounted on the launch tube 14 so as to allow the connection of optical fiber with a control system (not shown) installed on the helicopter 10.
- the end of the optical fiber leaving the coil 22 enters a case (not shown) allowing transform in one direction the light signal into a signal electrical and in reverse the electrical signal in light signal.
- the 18th fiber optic segment is then replaced by an electrical conductor and the optical connector 30 is itself replaced by a electrical connector.
- the second coil 22 further includes a cover 32, which surrounds the optical fiber wound on the core 26.
- This cover 32 is arranged coaxially to the core 26 and its inside diameter is slightly higher the diameter of the outermost fiber layer wound on the core 26, so as to leave a space allowing the fiber to unwind easily, account due to the bloating phenomenon that occurs during of this unfolding.
- the cover 32 extends beyond the end of the core 26 facing upwards in the normal storage position of the coil 22 and its diameter then decreases to present a circular opening 32a, centered on the axis of the core 26 and by which the fiber leaves the reel 22.
- the diameter of this opening 32a is for example close the outside diameter of the core 26.
- the cover 32 is covered with a fairing 34 which extends below the support 27, in the normal storage position of the reel 22 illustrated in solid lines in Figure 2.
- the front door 24 and the coil 22 fixed on this door are linked to the launch tube 14 by tilting means allowing this set of come and stand outside the launch tube, in a firing position that fully clears the front end of the launch tube.
- This position of firing is illustrated in dashed lines on the Figure 2 and in solid lines in Figure 3C.
- tilting means include a hinge 36, through which the front door 24 is articulated on the front end of the launch tube 14, and a tilt control system 38, which normally locks the front door 24 on the tube launch 14.
- the tilt control system 38 may in particular be constituted by a gas generator pyrotechnic mounted in the top of the launch tube 14, at the front of the latter. This system 38 ensures normally keeping the front door 24 in its closed position and propels door 24 forward, around the hinge 36, when actuated.
- the hinge 36 has a single axis 40, substantially horizontal, located at the bottom and in front of the launch tube 14. More precisely, the axis 40 is orthogonal to the axis of the launch tube and slightly offset forward and outward relative to this launch tube, so as to allow a 270 ° pivoting of the assembly formed by the door front 24 and reel 22, clockwise of a watch considering figure 2. This pivoting ends when the outer face of the front door 24 abuts against the underside of the tube launch 14. The axis of the coil 22 is then substantially parallel to the axis of the launch tube 14 and the circular opening 32a through which the fiber optic 18 comes out of the cover 32 is oriented towards the back.
- the launch tube 14 bears on its outer surface of the locking means 42 which cooperate with the front door 24 when it has tilted 270 °.
- the locking means 42 thus immobilize the second coil 22 in its firing position.
- the locking means 42 can consist of a blocking system any mechanical.
- the launching tube 14 In the normal storage position of the firing installation 12, the launching tube 14 also has a rear door 44 which closes the rear end of this tube.
- Means of opening 46 mounted inside the launch tube 14 cooperate with the rear door 44 to maintain it normally closed and order the opening when firing the missile 16.
- These opening means 46 can be any means, for example pyrotechnic, electrical, etc.
- the firing installation 12 occupies its normal storage position illustrated in solid lines in FIG. 2, the front end of the installation does not has no protuberance likely to prohibit stacking or increasing the master-couple.
- the installation forms a set which can be integrated on the launcher without other intervention than that required by fixing and installation connection.
- the entire length of the optical fiber is housed in the launch tube, handling operations are facilitated and the missile is protected against attack by all kinds (mechanical, fluids or atmospheric agents such as hail, sand, etc.) encountered during handling and carrying phases on the launcher mobile.
- the fiber link optic between the launcher and the missile is protected from assaults in the same way as the missile itself.
- this configuration makes any mechanism useless fiber blocking to prevent unwinding spontaneous of one or the other of the coils under the effect of the aerodynamic drive generated by the moving the launcher.
- the fiber output axes from the two coils are oriented towards the rear of the mobiles that constitute missile 16 and helicopter 10, which allows high travel speeds for each of them.
- FIG. 2 The implementation of the shooting facility illustrated in FIG. 2 will now be described in referring successively to FIGS. 3A to 3C.
- the tilt control system 38, the means ejection 28, the opening means 46 and the missile 16 thrusters are activated sequentially, with time intervals predetermined, as follows.
- the system 38 of tilt control is activated, which effect of propelling the front door 24 forwards, around its pivot axis 40, as illustrated in Figure 3A.
- the opening means 46 are actuated ( Figure 3C) so as to release the rear door 44 and missile 16 is fired. From then on, the helicopter can start a U-turn and move away missile speed, since the fiber exit axis unwinding from the reel 22 is oriented towards the rear compared to helicopter 10.
- FIGS. 4A to 4C there is illustrated a alternative embodiment of the hinge 36.
- the hinge has two horizontal and parallel axes 40a and 40b, oriented in a direction orthogonal to the axis of the tube launch 14. These axes 40a and 40b are linked launch tube 14 and door respectively rear 24.
- the hinge further comprises one or more several connecting pieces constituted by levers 48, substantially C-shaped, the ends of which are articulated on axes 40a and 40b. All formed by the axes 40a and 40b and by the levers 48 is normally housed inside the launch tube 14, in the storage position of the firing installation ( Figure 4A).
- the tilting means may include an electric actuator or a spring mechanism, to control the rotation of the front door 24 and levers 48 around the axis 40a, as well as torsion bars to then ensure the rotation of the front door 24 about the axis 40b.
- the coil 22 can be directly supported by the launch tube 14, at instead of being fixed on the inside of the front door 24. Releasing the front door and tilting to the outside of the coil then intervene sequentially.
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- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Description
L'invention concerne une installation conçue pour tirer une munition filoguidée telle qu'un missile, depuis un lanceur mobile tel qu'un navire ou un aéronef.The invention relates to an installation designed to fire wire-guided ammunition such as a missile, from a mobile launcher such as a ship or an aircraft.
Dans l'ensemble du texte, on désigne par l'expression "munition filoguidée" tout projectile relié à son poste de tir par un organe de liaison filiforme servant à transmettre des informations permettant de télécommander la munition depuis le poste de tir.Throughout the text, we mean by the expression "wire-guided munition" any projectile linked to its shooting station by a liaison body filiform used to transmit information allowing remote control of the ammunition from the post shooting.
L'organe de liaison filiforme peut notamment être constitué de plusieurs conducteurs électriques ou d'une fibre optique. Du fait que la capacité de transmission de la fibre optique est très largement supérieure à celle des conducteurs électriques, des liaisons sur des distances de plusieurs dizaines de kilomètres peuvent être assurées lorsqu'on utilise une fibre optique, alors que ces liaisons sont limitées à environ 12 km dans le cas des conducteurs électriques. La durée de vol de la munition s'en trouve considérablement accrue et atteint plusieurs minutes.The filiform connecting member can in particular be made up of several conductors electrical or optical fiber. Because the transmission capacity of optical fiber is very far superior to that of drivers electrical connections over distances of several tens of kilometers can be insured when using an optical fiber, while these connections are limited to approximately 12 km in the case of electrical conductors. The flight time of the ammunition is considerably increased and reached several minutes.
Lorsqu'une munition filoguidée est mise en oeuvre depuis un lanceur mobile, il est important pour la protection de ce dernier qu'il ne soit pas contraint à une trajectoire stationnaire ou colinéaire à la munition pendant toute la durée du vol de cette dernière. Cependant, le respect de cet impératif est difficile, du fait de la fragilité de l'organe de liaison filiforme, notamment lorsqu'il s'agit d'une fibre optique.When wire-guided ammunition is placed works from a mobile launcher, it's important for protection of the latter that he is not forced to a stationary or collinear trajectory to the ammunition for the duration of the flight of this last. However, compliance with this imperative is difficult, due to the fragility of the threadlike bond, especially when it is a optical fiber.
En effet, au fur et à mesure qu'elle progresse dans l'air ou dans l'eau, la munition filoguidée déroule l'organe de liaison filiforme d'une bobine associée à cette munition, de façon que la partie dévidée soit immobile par rapport au milieu ambiant. L'autre extrémité de l'organe de liaison filiforme étant solidaire du lanceur, tout mouvement de ce dernier postérieur au départ de la munition exerce une contrainte mécanique sur la partie déjà dévidée de l'organe de liaison filiforme. La résistance mécanique de cet organe délimite donc notablement les évolutions possibles du lanceur mobile.Indeed, as it progresses in air or water, the ammunition wire-guided unrolls the thread-like link member of a coil associated with this ammunition, so that the unwound part is immobile from the middle ambient. The other end of the link filiform being integral with the launcher, any movement of the latter after the departure of the ammunition mechanical stress on the already unwound part of the filiform connecting member. Mechanical resistance of this body therefore demarcates the evolutions notably mobile launcher.
Pour surmonter cette difficulté, il est connu d'équiper le lanceur mobile d'une deuxième bobine reliée à la bobine de la munition et qui se déroule derrière le lanceur mobile au fur et à mesure de son déplacement propre. Cette caractéristique permet de rendre indépendantes les trajectoires des deux mobiles constitués par la munition et par le lanceur.To overcome this difficulty, it is known to equip the mobile launcher with a second coil connected to the coil of the ammunition and which takes place behind the mobile launcher as it goes clean movement. This feature allows make the trajectories of the two mobiles independent constituted by the ammunition and by the launcher.
Cette solution est illustrée notamment par le document EP-A-0 337 254 sur lequel le préambule de la revendication 1 est fondé, dans lequel le lanceur mobile supporte une bobine dont l'axe est orienté sensiblement verticalement. Plus précisément, la bobine montée sur le lanceur mobile est portée par une articulation de type rotule qui permet de réduire l'angle entre l'axe de déroulement de l'organe de liaison filiforme et l'axe de la bobine. Cependant, cet angle ne peut jamais être annulé lorsque le lanceur se déplace dans un plan horizontal. Il constitue donc une limitation à la vitesse maximale de déroulement admissible et, par conséquent, à la vitesse de déplacement du lanceur mobile.This solution is illustrated in particular by EP-A-0 337 254 on which the preamble of claim 1 is based, in which the launcher mobile supports a coil whose axis is oriented substantially vertically. Specifically, the coil mounted on the mobile launcher is carried by a ball joint type which reduces the angle between the axis of unwinding of the organ of threadlike connection and axis of the coil. However, this angle can never be canceled when the launcher moves in a horizontal plane. It therefore constitutes a limitation to the maximum unwinding speed permissible and therefore at the speed of moving the mobile launcher.
De plus, dans l'installation de tir décrite dans le document EP-A-0 337 254, une partie de l'organe de liaison filiforme circule à l'extérieur du tube de lancement, puisque la bobine portée par le lanceur est située à l'extérieur de ce tube. Cette partie non protégée de l'organe de liaison filiforme risque donc d'être endommagée, soit lors de la mise en place des munitions sur le lanceur, soit lors du vol précédant le tir. Il en est de même pour la bobine portée par le lanceur, qui est en permanence à l'air libre et risque d'être endommagée particulièrement lors des phases de décollage et d'atterrissage du lanceur, pendant lesquelles des projections de matériaux peuvent se produire.In addition, in the shooting installation described in document EP-A-0 337 254, part of the organ of filiform connection circulates outside the tube of launch, since the coil carried by the launcher is located outside of this tube. This part no protected from the filiform connecting member therefore risks to be damaged, either during the installation of ammunition on the launcher, either during the flight preceding the shoot. The same is true for the coil carried by the launcher, which is constantly in the open air and is at risk to be damaged especially during the phases of take-off and landing of the launcher, during which material projections can occur produce.
L'utilisation d'une bobine liée au lanceur mobile est également illustrée par le document EP-A-0 443 623. Dans ce document, la bobine liée au lanceur mobile est, soit fixée directement à ce dernier de telle sorte que son axe soit orienté verticalement, soit montée sur le lanceur par l'intermédiaire d'une articulation de type cardan. Dans le premier cas, l'angle formé entre l'axe de déroulement de l'organe de liaison filiforme et l'axe de la bobine limite la vitesse maximale de déroulement admissible. La deuxième configuration est incompatible avec le tir d'une munition depuis un tube de lancement puisque la boucle qui se forme entre la munition et la bobine liée au lanceur passerait alors dans le tube de lancement. En effet, tout changement significatif d'orientation du tube de lancement résultant du déplacement du lanceur mobile exercerait une contrainte mécanique importante sur l'organe de liaison filiforme déjà déroulé depuis la munition.The use of a coil linked to the launcher mobile is also illustrated in the document EP-A-0 443 623. In this document, the coil linked to the mobile launcher is either attached directly to the latter so that its axis is oriented vertically, either mounted on the launcher via a gimbal type joint. In the first case, the angle formed between the axis of unwinding of the organ of filiform connection and the axis of the coil limits the maximum permissible unwinding speed. The second configuration is incompatible with shooting a ammunition from a launch tube since the loop which forms between the ammunition and the coil linked to the launcher would then pass through the launch tube. In indeed, any significant change in focus of the launch tube resulting from displacement of the launcher mobile would exert significant mechanical stress on the filiform connecting member already unrolled since ammunition.
D'autre part, dans ce document EP-A-0 443 623, comme dans le document précédent, il existe entre les deux bobines une portion d'organe de liaison filiforme non protégée, qui risque d'être endommagée lors de la mise en place des munitions sur le lanceur ou lors du vol précédant le tir. On the other hand, in this document EP-A-0 443 623, as in the previous document, it between the two coils there is a portion of unprotected filiform bond, which may be damaged when placing ammunition on the launcher or during the flight preceding the firing.
L'invention a précisément pour objet une installation de tir de munition filoguidée, depuis un tube de lancement embarqué sur un lanceur mobile, ne présentant pas les inconvénients des installations existantes et permettant notamment au lanceur mobile de suivre une trajectoire quelconque après le tir de la munition avec une vitesse plus élevée que dans les installations existantes et sans qu'aucune partie de l'organe de liaison filiforme ne soit exposée et risque d'être endommagée à un moment quelconque.The subject of the invention is precisely a wire-fired munition firing installation, from a launch tube on board a mobile launcher, do not not having the disadvantages of the installations existing and in particular allowing the mobile launcher to follow any trajectory after firing the ammunition with a higher speed than in the existing facilities and without any part of the filiform connecting member is exposed and risks to be damaged at any time.
Conformément à l'invention, ce résultat est obtenu au moyen d'une installation de tir de munition filoguidée depuis un lanceur mobile, comprenant un tube de lancement, une munition normalement logée dans le tube de lancement, et un organe de liaison filiforme apte à se dérouler d'une première bobine liée à la munition et d'une deuxième bobine liée au tube de lancement, caractérisée par le fait que le tube de lancement comporte une porte avant, normalement fermée, la deuxième bobine étant normalement montée dans le tube de lancement, entre la munition et la porte avant, par l'intermédiaire d'un moyen de basculement de cette deuxième bobine à l'extérieur du tube de lancement, apte à être actionné avant une mise à feu de la munition.According to the invention, this result is obtained through an ammunition firing facility guided by a mobile launcher, comprising a tube launch ammunition normally housed in the launch tube, and a threadlike connecting member able to unwind from a first reel linked to the ammunition and a second coil linked to the tube launch, characterized by the fact that the launch has a front door, normally closed, the second coil being normally mounted in the launch tube, between the ammunition and the front door, through a means of tilting this second coil outside the launch tube, able to be activated before firing the ammunition.
Grâce à cet agencement, l'organe de liaison filiforme qui relie la munition au tube de lancement est totalement placé à l'intérieur de ce dernier avant la mise à feu. De plus, le logement de la bobine liée au lanceur mobile à l'avant de la munition et le basculement de cette bobine à l'extérieur du tube de lancement juste avant la mise à feu permettent pratiquement d'annuler l'angle formé entre l'axe de déroulement et l'axe de la bobine lorsque le lanceur effectue un demi-tour et s'éloigne de la munition après la mise à feu.Thanks to this arrangement, the connecting member threadlike that connects the ammunition to the launch tube is completely placed inside the latter before firing. In addition, the housing of the linked coil to the mobile launcher at the front of the ammunition and the tilting of this coil outside the tube launch just before firing allow practically cancel the angle formed between the axis of unwinding and axis of the reel when the launcher makes a U-turn and moves away from the ammunition after firing.
Dans une forme de réalisation préférentielle de l'invention, la deuxième bobine est fixée sur une face interne de la porte avant, le moyen de basculement étant interposé entre cette dernière et le tube de lancement.In one embodiment preferential of the invention, the second coil is fixed on an internal face of the front door, the means of tilting being interposed between the latter and the launch tube.
De préférence, une longueur tampon de l'organe de liaison filiforme, située entre des parties de cet organe normalement enroulées sur la première et la deuxième bobines, est normalement associée à la deuxième bobine. De plus, des moyens d'éjection de cette longueur tampon, aptes à être actionnés après un actionnement des moyens de basculement et avant la mise à feu de la munition, sont montés dans la deuxième bobine. Cette caractéristique permet d'initier le déroulement de la bobine liée au lanceur, alors que ce dernier n'a pas encore terminé son demi-tour, sans que l'organe de liaison filiforme ne soit soumis à des contraintes mécaniques trop sévères.Preferably, a buffer length of the filiform connecting member, located between parts of this organ normally wound on the first and the second coil, is normally associated with the second coil. In addition, means for ejecting this buffer length, capable of being actuated after a actuation of the tilting means and before putting ammunition fire, are mounted in the second coil. This feature initiates the unwinding of the coil linked to the launcher, whereas this the latter has not yet completed his turn, without the filiform connecting member is not subjected to mechanical constraints too severe.
Dans la forme de réalisation préférentielle de l'invention, la deuxième bobine comprend un noyau dans lequel sont logés la longueur tampon de l'organe de liaison filiforme et les moyens d'éjection.In the preferred embodiment of the invention, the second coil comprises a core in which the buffer length of the organ is housed of filiform connection and the ejection means.
Afin que la partie du câble située entre la bobine liée à la munition et la bobine liée au lanceur reste sensiblement stationnaire, la longueur tampon de l'organe de liaison filiforme supporte avantageusement des moyens d'accroissement du coefficient de traínée.So that the part of the cable between the coil linked to ammunition and coil linked to launcher remains substantially stationary, the buffer length of the filiform connecting member advantageously supports means for increasing the drag coefficient.
Par ailleurs, afin de protéger le tronçon de l'organe de liaison filiforme qui chemine dans le tube de lancement entre la première et la deuxième bobines avant la mise à feu, ce tronçon est renforcé par un gainage de protection. Furthermore, in order to protect the section of the filiform connecting member which runs in the launch tube between first and second coils before firing, this section is reinforced by protective sheathing.
Dans la forme de réalisation préférentielle de l'invention, le moyen de basculement commande un pivotement d'environ 270° de la deuxième bobine entre une position normale, interne au tube de lancement, dans laquelle l'axe de la deuxième bobine est sensiblement orthogonal à l'axe du tube de lancement, et une position de mise à feu, externe au tube de lancement, dans laquelle l'axe de la deuxième bobine est sensiblement parallèle à l'axe du tube de lancement.In the preferred embodiment of the invention, the tilting means controls a about 270 ° pivoting of the second coil between a normal position, internal to the launch tube, in which the axis of the second coil is substantially orthogonal to the axis of the launch tube, and a firing position, external to the tube launch, in which the axis of the second coil is substantially parallel to the axis of the tube launch.
De préférence, la deuxième bobine comporte alors un capot, avantageusement recouvert d'un carénage, entourant la partie de l'organe de liaison filiforme normalement enroulée sur la deuxième bobine. Ce capot comporte une ouverture circulaire de sortie de l'organe de liaison filiforme, centrée sur l'axe de la deuxième bobine et orientée respectivement vers le haut ou vers l'arrière selon que la deuxième bobine occupe sa position normale ou sa position de mise à feu.Preferably, the second coil has then a cover, advantageously covered with a fairing, surrounding the part of the connecting member filiform normally wound on the second coil. This cover has a circular outlet opening from the filiform connecting member, centered on the axis of the second coil and oriented upwards respectively or backwards depending on whether the second coil occupies its normal position or its firing position.
Sur sa surface extérieure, le tube de lancement comporte alors avantageusement des moyens de verrouillage de la deuxième bobine dans sa position de mise à feu.On its outer surface, the launch then advantageously includes means of locking the second coil in its position Firing.
Dans la forme de réalisation préférentielle de l'invention, le moyen de basculement comprend au moins un système de commande de basculement et une charnière d'articulation de la deuxième bobine sur le tube de lancement.In the preferred embodiment of the invention, the tilting means comprises at minus a tilt control system and a articulation hinge of the second coil on the launch tube.
Selon le cas, la charnière peut comporter, soit un seul axe de pivotement orthogonal à l'axe du tube de lancement, soit deux axes de pivotement parallèles, orthogonaux à l'axe du tube de lancement. Dans ce dernier cas, il est prévu au moins une pièce de liaison apte à pivoter par rapport au tube de lancement autour d'un premier des axes de pivotement et par rapport à laquelle la deuxième bobine peut pivoter autour du deuxième des axes de pivotement.Depending on the case, the hinge may include, either a single pivot axis orthogonal to the axis of the launch tube, i.e. two pivot axes parallel, orthogonal to the axis of the launch tube. In the latter case, at least one piece of link able to pivot relative to the launching tube around a first of the pivot axes and by how the second coil can rotate around the second of the pivot axes.
Le tube de lancement comporte en outre une porte arrière, normalement fermée, ainsi que des moyens d'ouverture de cette porte, aptes à être actionnés lors de la mise à feu de la munition.The launch tube further includes a rear door, normally closed, as well as means opening of this door, capable of being actuated during the firing of the ammunition.
On décrira à présent, à titre d'exemple non limitatif, une forme de réalisation préférentielle de l'invention, en se référant aux dessins annexés, dans lesquels :
- la figure 1 est une vue en perspective illustrant le tir d'une munition filoguidée à partir d'un hélicoptère équipé d'une installation de tir conforme à l'invention ;
- la figure 2 est une vue en coupe longitudinale partielle d'une installation de tir conforme à l'invention, représentée en traits pleins à l'état de repos et en traits mixtes dans l'état qu'elle occupe juste avant la mise à feu de la munition ;
- les figures 3A à 3C sont des vues en coupe longitudinale partielle comparables à la figure 2, représentant plus schématiquement l'installation de tir de la figure 2, à différents stades juste avant la mise à feu de la munition ; et
- les figures 4A à 4C sont des vues à plus grande échelle représentant une variante de réalisation de la charnière par laquelle la porte avant est articulée sur le tube de lancement, à différents stades de l'ouverture de cette porte.
- FIG. 1 is a perspective view illustrating the firing of a wire-guided munition from a helicopter equipped with a firing installation in accordance with the invention;
- Figure 2 is a partial longitudinal sectional view of a firing installation according to the invention, shown in solid lines in the rest state and in broken lines in the state it occupies just before firing ammunition;
- FIGS. 3A to 3C are views in partial longitudinal section comparable to FIG. 2, showing more schematically the firing installation of FIG. 2, at different stages just before the firing of the ammunition; and
- FIGS. 4A to 4C are views on a larger scale showing an alternative embodiment of the hinge by which the front door is articulated on the launching tube, at different stages of the opening of this door.
Sur la figure 1, la référence 10 désigne un
hélicoptère sur lequel sont embarquées plusieurs
installations de tir 12 conformes à l'invention.
Chacune de ces installations de tir comprend un tube de
lancement 14 (Fig. 2), un missile filoguidé 16 et une
fibre optique 18 reliant en permanence le missile 16 au
tube de lancement 14. Plus précisément, la figure 1
représente l'hélicoptère 10 en train de faire demi-tour
après la mise à feu de l'un des missiles 16.In FIG. 1, the reference 10 designates a
helicopter on which several are on board
firing
Comme on l'a déjà précisé, l'invention ne
s'applique pas seulement au cas où le lanceur mobile
est constitué par un hélicoptère 10, mais concerne
aussi le cas où ce lanceur est constitué par un aéronef
de nature différente, un navire de surface ou
sous-marin, ou encore un véhicule terrestre. De même,
le missile 16 peut être remplacé par toute munition
filoguidée adaptée au lanceur concerné. Enfin, la fibre
optique peut être remplacée par tout autre organe de
liaison filiforme tel qu'un ensemble de conducteurs
électriques.As already stated, the invention does not
not only applies in case the mobile launcher
consists of a helicopter 10, but concerns
also the case where this launcher is constituted by an aircraft
of a different nature, a surface ship or
submarine, or even a land vehicle. Likewise,
Comme l'illustre plus précisément la figure
2, lorsque le missile 16 est stocké à l'intérieur du
tube de lancement 14, un tronçon 18a de la fibre
optique 18, correspondant par exemple à au moins la
moitié de sa longueur totale, est enroulé sur une
première bobine 20 logée dans la partie arrière du
missile 16. Cet agencement est classique et ne sera
donc pas décrit plus en détail.As the figure illustrates more precisely
2, when
Un deuxième tronçon 18b de la fibre optique
18 sort du missile 16 à l'arrière de celui-ci et
chemine à l'intérieur du tube de lancement 14, le long
du missile 16, pour relier le premier tronçon 18a monté
dans le missile à une deuxième bobine 22 placée dans le
tube de lancement 14, devant le missile 16. Plus
précisément, la deuxième bobine 22 est fixée sur la
face interne d'une porte avant 24 du tube de lancement
14, qui obture normalement l'extrémité avant de ce
tube. La deuxième bobine 22 se trouve ainsi interposée
entre le missile 16 et la porte avant 24, à l'intérieur
du tube de lancement 14, lorsque l'installation de tir
12 occupe sa position normale de stockage. A
Le tronçon 18b de la fibre optique, qui
relie les bobines 20 et 22, est renforcé par un gainage
de protection qui lui permet de résister aux agressions
produites par le propulseur du missile 16, lors de
l'éjection de ce dernier hors du tube de lancement 14.The
La deuxième bobine 22 comprend un noyau 26,
de forme généralement cylindrique ou tronconique,
éventuellement terminé par des extrémités évasées. Dans
la position normale de stockage illustrée sur la figure
2, l'axe de ce noyau 26 est orienté sensiblement
verticalement, son extrémité basse étant reliée à la
porte avant 24 par un support 27.The
Dans sa partie tournée vers le haut lorsque
la bobine 22 occupe sa position de stockage, le noyau
26 forme un logement, ouvert vers le haut, dans lequel
est stockée une longueur tampon 18c de la fibre optique
18, par exemple sous la forme d'un enroulement. La
partie du noyau 26 adjacente à la longueur tampon 18c
de la fibre optique sert à loger des moyens d'éjection
28 qui ont pour fonction, comme on le verra
ultérieurement, d'expulser la longueur tampon 18c de
fibre optique hors du logement formé dans le noyau 26,
juste avant la mise à feu du missile 16. Ces moyens
d'éjection 28 peuvent être constitués soit par un
mécanisme à ressort, soit par un système pneumatique ou
pyrotechnique.In its part turned upwards when
the
Il est à noter que la longueur tampon 18c
de la fibre optique supporte des moyens (non
représentés) permettant d'accroítre artificiellement le
coefficient de traínée aérodynamique de cette partie de
la fibre lorsqu'elle se trouve à l'extérieur du tube de
lancement 14.It should be noted that the
La longueur tampon 18c de la fibre optique
relie le tronçon 18b de cette fibre à un tronçon 18d de
la fibre optique, bobiné jointivement en plusieurs
couches sur le noyau 26 de la bobine 22. La longueur du
tronçon 18d enroulé sur la bobine 22 est généralement
inférieure ou au plus égale à la longueur du tronçon
18a enroulé sur la bobine 20. De façon connue, un
adhésif approprié permet d'assurer un déroulement
progressif et régulier de la fibre optique à partir des
bobines 20 et 22.The
L'extrémité de la fibre optique 18 sortant
de la bobine 22 à l'opposé de la longueur tampon 18b
est reliée par un tronçon de fibre 18e à un connecteur
optique 30 monté sur le tube de lancement 14 de façon à
permettre la connexion de la fibre optique avec un
système de commande (non représenté) implanté sur
l'hélicoptère 10.The end of the
Dans une variante de réalisation,
l'extrémité de la fibre optique sortant de la bobine 22
pénètre dans un boítier (non représenté) permettant de
transformer dans un sens le signal lumineux en signal
électrique et en sens inverse le signal électrique en
signal lumineux. Le tronçon de fibre optique 18e est
alors remplacé par un conducteur électrique et le
connecteur optique 30 est lui-même remplacé par un
connecteur électrique.In an alternative embodiment,
the end of the optical fiber leaving the
La deuxième bobine 22 comporte de plus un
capot 32, qui entoure la fibre optique bobinée sur le
noyau 26. Ce capot 32 est disposé coaxialement au noyau
26 et son diamètre intérieur est légèrement supérieur
au diamètre de la couche de fibre la plus externe
bobinée sur le noyau 26, de façon à laisser un espace
permettant à la fibre de se dérouler aisément, compte
tenu du phénomène de ballonnement qui se produit lors
de ce déroulement.The
Le capot 32 se prolonge au-delà de
l'extrémité du noyau 26 tournée vers le haut dans la
position normale de stockage de la bobine 22 et son
diamètre va alors en diminuant pour présenter une
ouverture circulaire 32a, centrée sur l'axe du noyau 26
et par laquelle la fibre sort de la bobine 22. Le
diamètre de cette ouverture 32a est par exemple voisin
du diamètre extérieur du noyau 26.The
En dehors de sa partie adjacente à la porte
arrière 24, le capot 32 est recouvert d'un carénage 34
qui se prolonge en dessous du support 27, dans la
position normale de stockage de la bobine 22 illustrée
en trait plein sur la figure 2.Outside its part adjacent to the door
rear 24, the
Afin de permettre la mise à feu du missile
16, la porte avant 24 ainsi que la bobine 22 fixée sur
cette porte sont liées au tube de lancement 14 par des
moyens de basculement permettant à cet ensemble de
venir se placer à l'extérieur du tube de lancement,
dans une position de mise à feu qui dégage complètement
l'extrémité avant du tube de lancement. Cette position
de mise à feu est illustrée en traits mixtes sur la
figure 2 et en traits pleins sur la figure 3C.To allow the missile to fire
16, the
Ces moyens de basculement comprennent une
charnière 36, par laquelle la porte avant 24 est
articulée sur l'extrémité avant du tube de lancement
14, et un système 38 de commande de basculement, qui
verrouille normalement la porte avant 24 sur le tube de
lancement 14.These tilting means include a
Dans la forme de réalisation illustrée sur
la figure 2, le système 38 de commande de basculement
peut notamment être constitué par un générateur de gaz
pyrotechnique monté dans le haut du tube de lancement
14, à l'avant de ce dernier. Ce système 38 assure
normalement le maintien de la porte avant 24 dans sa
position fermée et propulse la porte 24 vers l'avant,
autour de la charnière 36, lorsqu'il est actionné.In the embodiment illustrated on
Figure 2, the
Dans la forme de réalisation illustrée sur
la figure 2, la charnière 36 comporte un axe unique 40,
sensiblement horizontal, situé en bas et à l'avant du
tube de lancement 14. Plus précisément, l'axe 40 est
orthogonal à l'axe du tube de lancement et légèrement
déporté vers l'avant et vers l'extérieur par rapport à
ce tube de lancement, de façon à permettre un
pivotement de 270° de l'ensemble formé par la porte
avant 24 et la bobine 22, dans le sens des aiguilles
d'une montre en considérant la figure 2. Ce pivotement
se termine lorsque la face externe de la porte avant 24
vient buter contre la face inférieure du tube de
lancement 14. L'axe de la bobine 22 est alors
sensiblement parallèle à l'axe du tube de lancement 14
et l'ouverture circulaire 32a par laquelle la fibre
optique 18 sort du capot 32 est orientée vers
l'arrière.In the embodiment illustrated on
FIG. 2, the
Cette position finale de l'ensemble formé
par la porte avant 24 et la bobine 22, appelée position
de mise à feu, autorise la sortie du missile 16 hors du
tube de lancement 14 après sa mise à feu. Dans sa
partie basse, le tube de lancement 14 porte sur sa
surface extérieure des moyens de verrouillage 42 qui
coopèrent avec la porte avant 24 lorsque celle-ci a
basculé de 270°. Les moyens de verrouillage 42
immobilisent ainsi la deuxième bobine 22 dans sa
position de mise à feu. les moyens de verrouillage 42
peuvent être constitués par un système de blocage
mécanique quelconque.This final position of the whole formed
by the
Dans la position normale de stockage de
l'installation de tir 12, le tube de lancement 14
comporte également une porte arrière 44 qui ferme
l'extrémité arrière de ce tube. Des moyens d'ouverture
46 montés à l'intérieur du tube de lancement 14
coopèrent avec la porte arrière 44 pour la maintenir
normalement fermée et en commander l'ouverture lors de
la mise à feu du missile 16. Ces moyens d'ouverture 46
peuvent être des moyens quelconques, par exemple de
type pyrotechnique, électrique, etc.In the normal storage position of
the firing
Lorsque l'installation de tir 12 occupe sa
position normale de stockage illustrée en traits pleins
sur la figure 2, l'extrémité avant de l'installation ne
présente pas de protubérance susceptible d'en interdire
l'empilement ou d'augmenter le maítre-couple.When the firing
De plus, l'installation forme un ensemble qui peut être intégré sur le lanceur sans autre intervention que celle nécessitée par la fixation et le raccordement de l'installation.In addition, the installation forms a set which can be integrated on the launcher without other intervention than that required by fixing and installation connection.
En outre, du fait que toute la longueur de la fibre optique est logée dans le tube de lancement, les opérations de manutention sont facilitées et le missile est protégé contre les agressions de toutes sortes (mécaniques, fluides ou agents atmosphériques tels que grêle, sable, etc.) rencontrées lors des phases de manipulation et d'emport sur le lanceur mobile. De la même manière, la liaison par fibre optique entre le lanceur et le missile est protégée des agressions au même titre que le missile lui-même. De plus, cette configuration rend inutile tout mécanisme de blocage de la fibre destiné à éviter un déroulement spontané de l'une ou l'autre des bobines sous l'effet de l'entraínement aérodynamique engendré par le déplacement du lanceur.Furthermore, because the entire length of the optical fiber is housed in the launch tube, handling operations are facilitated and the missile is protected against attack by all kinds (mechanical, fluids or atmospheric agents such as hail, sand, etc.) encountered during handling and carrying phases on the launcher mobile. Similarly, the fiber link optic between the launcher and the missile is protected from assaults in the same way as the missile itself. Of more, this configuration makes any mechanism useless fiber blocking to prevent unwinding spontaneous of one or the other of the coils under the effect of the aerodynamic drive generated by the moving the launcher.
En outre, lorsque le tir du missile a eu
lieu, les axes de sortie de la fibre à partir des deux
bobines sont orientés vers l'arrière des mobiles que
constituent le missile 16 et l'hélicoptère 10, ce qui
autorise des vitesses de translation élevées de chacun
d'entre eux.Furthermore, when the missile was fired
location, the fiber output axes from the two
coils are oriented towards the rear of the mobiles that
constitute
La mise en oeuvre de l'installation de tir illustrée sur la figure 2 va à présent être décrite en se référant successivement aux figures 3A à 3C. The implementation of the shooting facility illustrated in FIG. 2 will now be described in referring successively to FIGS. 3A to 3C.
Lorsqu'un ordre de tir est donné, le
système 38 de commande de basculement, les moyens
d'éjection 28, les moyens d'ouverture 46 et les
propulseurs du missile 16 sont actionnés
séquentiellement, avec des intervalles de temps
prédéterminés, de la manière suivante.When a firing order is given, the
Dans un premier temps, le système 38 de
commande de basculement est actionné, ce qui a pour
effet de propulser la porte avant 24 vers l'avant,
autour de son axe de pivotement 40, comme illustré sur
la figure 3A.First, the
Comme le montre la figure 3B, pendant le
pivotement de la porte avant 24, les moyens d'éjection
28, internes au noyau 26 de la bobine 22, sont activés
et la longueur tampon 18c de fibre optique est éjectée
vers le bas, de façon à former progressivement une
boucle, en se délovant dans l'air. La longueur de cette
boucle (fig. 3C) est déterminée de façon à initier le
déroulement de la bobine secondaire 22 sous l'effet de
la traction aérodynamique exercée sur la fibre par le
mouvement de l'hélicoptère 10.As shown in Figure 3B, during the
pivoting of the
Lorsque le pivotement de 270° de l'ensemble
formé par la porte avant 24 et la bobine 22 est
terminé, cet ensemble est bloqué dans la position de
mise à feu par les moyens de verrouillage 42.
L'ouverture 32a du capot 32 par laquelle se dévide la
fibre optique, est alors orientée vers l'arrière par
rapport à l'hélicoptère, ce qui permet à ce dernier de
s'éloigner à grande vitesse après le lancement du
missile.When the 270 ° swivel of the assembly
formed by the
Dès que la bobine 22 a atteint sa position
de mise à feu, les moyens d'ouverture 46 sont actionnés
(figure 3C) de façon à larguer la porte arrière 44 et
le missile 16 est mis à feu. Dès lors, l'hélicoptère
peut entamer son demi-tour et s'éloigner à grande
vitesse du missile, puisque l'axe de sortie de la fibre
se dévidant de la bobine 22 est orienté vers l'arrière
par rapport à l'hélicoptère 10.As soon as the
Sur les figures 4A à 4C, on a illustré une
variante de réalisation de la charnière 36. Dans cette
variante de réalisation, la charnière comporte deux
axes horizontaux et parallèles 40a et 40b, orientés
selon une direction orthogonale à l'axe du tube de
lancement 14. Ces axes 40a et 40b sont liés
respectivement au tube de lancement 14 et à la porte
arrière 24. La charnière comporte en outre une ou
plusieurs pièces de liaison constituées par des leviers
48, sensiblement en forme de C, dont les extrémités
sont articulées sur les axes 40a et 40b. L'ensemble
formé par les axes 40a et 40b et par les leviers 48 est
normalement logé à l'intérieur du tube de lancement 14,
dans la position de stockage de l'installation de tir
(figure 4A).In FIGS. 4A to 4C, there is illustrated a
alternative embodiment of the
Lorsque le système de commande de
basculement assurant le pivotement de la porte avant 24
autour de la charnière 36 est actionné, l'ensemble
formé par le ou les leviers 48 et la porte avant 24
pivote tout d'abord autour de l'axe 40a dans le sens
des aiguilles d'une montre, comme l'illustre la figure
4B.When the control system
tilting ensuring the pivoting of the
Lorsque les leviers 48 arrivent en butée
contre l'extrémité avant du tube de lancement 14, la
porte avant 24 pivote à son tour autour de l'axe 40b,
dans le sens des aiguilles d'une montre, comme
l'illustre la figure 4C. A la fin de ce pivotement, il
s'est produit une rotation de 270° de l'ensemble formé
par la porte avant 24 et la bobine 22, dans le sens des
aiguilles d'une montre en considérant les figures 4A à
4C. La bobine 22 occupe alors la même position de mise
à feu que dans le mode de réalisation décrit
précédemment.When the
Dans la variante de réalisation qui vient
d'être décrite, le moyen de basculement peut comprendre
un vérin électrique ou un mécanisme à ressort,
permettant de commander la rotation de la porte avant
24 et des leviers 48 autour de l'axe 40a, ainsi que des
barres de torsion permettant d'assurer ensuite la
rotation de la porte avant 24 autour de l'axe 40b.In the variant which comes
to be described, the tilting means may include
an electric actuator or a spring mechanism,
to control the rotation of the
Il est à noter que la bobine 22 peut être
supportée directement par le tube de lancement 14, au
lieu d'être fixée sur la face interne de la porte avant
24. Le largage de la porte avant et le basculement vers
l'extérieur de la bobine interviennent alors
séquentiellement.It should be noted that the
Claims (14)
- Installation (12) for firing a munition that is wire-guided from a mobile launcher, comprising a launch tube (14) which can be mounted on the launcher (10), a munition (16) normally housed in the launch tube, and a wire-like connecting member (18) which can be paid out from a first reel (20) connected to the munition and from a second reel (22) connected to the launch tube, characterized in that the launch tube (14) comprises a front flap (24) which is normally closed, the second reel (22) normally being mounted in the launch tube (14) between the munition (16) and the front flap (24) via a means (36, 38) of pivoting this second reel to outside the launch tube, which means can be actuated prior to the firing of the munition.
- Installation according to Claim 1, characterized in that the second reel (22) is fixed to an internal face of the front flap (24), the means (36, 38) of pivoting being inserted between this flap and the launch tube (14).
- Installation according to either one of Claims 1 and 2, characterized in that a buffer length (18c) of the wire-like connecting member, which length lies between parts of this member which are normally wound onto the first (20) and the second (22) reels, is normally associated with the second reel, means (28) of ejecting this buffer length, which means can be actuated after the means (36, 38) of pivoting have been actuated and before the munition (16) is fired, being mounted in the second reel (22).
- Installation according to Claim 3, characterized in that the second reel (22) comprises a core (26) in which the said buffer length (18c) and the ejection means (28) are housed.
- Installation according to either one of Claims 3 and 4, characterized in that the said buffer length (18c) of the wire-like connecting member supports means of increasing the drag coefficient.
- Installation according to any one of the preceding claims, characterized in that a portion (18b) of the wire-like connecting member which is normally routed through the launch tube (14) between the first (20) and second (22) reels, is reinforced with a protective sheath.
- Installation according to any one of the preceding claims, characterized in that the means (36, 38) of pivoting causes a pivoting of the second reel (22) through about 270° between a normal position, inside the launch tube (14), in which position the axis of the second reel is approximately at right angles to the axis of the launch tube, and a firing position, outside the launch tube (14), in which position the axis of the second reel is approximately parallel to the axis of the launch tube.
- Installation according to Claim 7, characterized in that the second reel has a cap (32) surrounding that part of the wire-like connecting member which is normally wound onto the second reel, this cap having a circular outlet opening (32a) for the wire-like connecting member, this opening being centred on the axis of the second reel and facing respectively upwards and backwards when the second reel occupies its normal position and its firing position.
- Installation according to Claim 8, characterized in that the cap (32) is covered by a fairing (34).
- Installation according to any one of Claims 7 to 9, characterized in that the launch tube (14) bears means (42) of locking the second reel (22) in its firing position.
- Installation according to any one of Claims 7 to 10, characterized in that the means of pivoting comprises at least one system (38) for bringing about the pivoting and a hinge (36) for articulating the second reel (22) to the launch tube (14).
- Installation according to Claim 11, characterized in that the hinge (36) has just one axis of pivoting (40) at right angles to the axis of the launch tube (14).
- Installation according to Claim 11, characterized in that the hinge (36) has two parallel axes of pivoting (40a, 40b) which are at right angles to the axis of the launch tube (14), and at least one connecting piece (48) capable of pivoting with respect to the launch tube about a first one of the axes of pivoting, and with respect to which the second reel can pivot about the second of the axes of pivoting.
- Installation according to any one of the preceding claims, characterized in that the launch tube (14) has a rear flap (44), which is normally closed, as well as means (46) of opening this flap, which means can be actuated when the munition is fired.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9404947A FR2719111B1 (en) | 1994-04-25 | 1994-04-25 | Installation of fired ammunition firing from a mobile launcher. |
FR9404947 | 1994-04-25 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0679861A1 EP0679861A1 (en) | 1995-11-02 |
EP0679861B1 true EP0679861B1 (en) | 1998-12-30 |
Family
ID=9462472
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19950400899 Expired - Lifetime EP0679861B1 (en) | 1994-04-25 | 1995-04-21 | Firing installation for wire guided ammunition from a mobile launcher |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP0679861B1 (en) |
DE (1) | DE69506940T2 (en) |
ES (1) | ES2128005T3 (en) |
FR (1) | FR2719111B1 (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102007005254B4 (en) | 2007-02-02 | 2009-01-29 | Lfk-Lenkflugkörpersysteme Gmbh | Dropping device and dropping method for a missile |
DE102009011447B9 (en) * | 2009-03-03 | 2012-08-16 | Diehl Bgt Defence Gmbh & Co. Kg | Method for igniting a warhead of a grenade and vehicle |
FR3022881B1 (en) * | 2014-06-30 | 2016-11-04 | Dcns | SUBMARINE ENGINE HAVING MEANS FOR LAUNCHING A SUBMARINE VEHICLE |
DE102018207712A1 (en) * | 2018-05-17 | 2019-11-21 | Thyssenkrupp Ag | Weapon tube module for ejecting two guided weapons arranged one behind the other |
DE102022001553B4 (en) | 2022-05-04 | 2024-07-18 | Bundesrepublik Deutschland, vertr. durch das Bundesministerium der Verteidigung, vertr. durch das Bundesamt für Ausrüstung, Informationstechnik und Nutzung der Bundeswehr | Measuring method and device for controlling the safe use of missiles on helicopters |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4860968A (en) * | 1988-04-15 | 1989-08-29 | The Boeing Company | Communication link between moving bodies |
US5005930A (en) * | 1990-02-23 | 1991-04-09 | Hughes Aircraft Company | Multi-directional payout fiber optic canister |
DE4112016C1 (en) * | 1991-04-12 | 1992-08-06 | Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De | Flight path and/or actual speed detector - uses sensor at circular gap between fixed parts of missile to register speed of unwinding of guiding optical fibre |
-
1994
- 1994-04-25 FR FR9404947A patent/FR2719111B1/en not_active Expired - Fee Related
-
1995
- 1995-04-21 EP EP19950400899 patent/EP0679861B1/en not_active Expired - Lifetime
- 1995-04-21 ES ES95400899T patent/ES2128005T3/en not_active Expired - Lifetime
- 1995-04-21 DE DE1995606940 patent/DE69506940T2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
EP0679861A1 (en) | 1995-11-02 |
DE69506940D1 (en) | 1999-02-11 |
DE69506940T2 (en) | 1999-07-01 |
FR2719111A1 (en) | 1995-10-27 |
ES2128005T3 (en) | 1999-05-01 |
FR2719111B1 (en) | 1996-07-12 |
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