EP0679861A1 - Firing installation for wire guided ammunition from a mobile launcher - Google Patents

Abstract

Equipment for firing a wire-guided munition from a mobile launcher comprises a launching tube (14) for mounting on the launcher, a munition (16) normally located in the tube and a connection wire (18) which unwinds from a first spool (20) joined to the munition and from a second spool (22) joined to the tube. The novelty is that the launching tube (14) has a normally closed front opening (24) and the second spool (22) is normally mounted in the tube, between the munition (16) and the front opening (24), by a mechanism (36,38) which can swing the second spool out of the tube before the munition is fired. <IMAGE>

Description

The invention relates to an installation designed to fire a wire-guided munition such as a missile, from a mobile launcher such as a ship or an aircraft.

Throughout the text, the term "wire-guided munition" designates any projectile connected to its firing station by a filiform connecting member used to transmit information making it possible to remotely control the ammunition from the firing station.

The filiform connecting member can in particular consist of several electrical conductors or an optical fiber. Because the transmission capacity of optical fiber is very much higher than that of electrical conductors, connections over distances of several tens of kilometers can be ensured 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 reaches several minutes.

When a wire-guided munition is implemented from a mobile launcher, it is important for the protection of the latter that it is not constrained to a stationary or collinear trajectory to the ammunition for the entire duration of the flight of the latter. However, compliance with this imperative is difficult, due to the fragility of the filiform connecting member, in particular when it is an optical fiber.

Indeed, as it progresses in air or in water, the ammunition filoguide unrolls the filiform connecting member of a coil associated with this ammunition, so that the unwound part is stationary relative to the ambient environment. The other end of the filiform connecting member being integral with the launcher, any movement of the latter after the departure of the ammunition exerts mechanical stress on the part already unwound from the filiform connecting member. The mechanical strength of this member therefore significantly limits the possible developments of the mobile launcher.

To overcome this difficulty, it is known to equip the mobile launcher with a second coil connected to the ammunition coil and which takes place behind the mobile launcher as it moves. This characteristic makes it possible to make the trajectories of the two mobiles constituted by the ammunition and by the launcher independent.

This solution is illustrated in particular by document EP-A-0 337 254, in which the mobile launcher supports a coil whose axis is oriented substantially vertically. More specifically, the coil mounted on the mobile launcher is carried by a ball-joint type joint which makes it possible to reduce the angle between the axis of unwinding of the filiform connecting member and the axis of the coil. However, this angle can never be canceled when the launcher is moving in a horizontal plane. It therefore constitutes a limitation to the maximum admissible speed of unwinding and, consequently, to the speed of movement of the mobile launcher.

In addition, in the firing installation described in document EP-A-0 337 254, part of the filiform connecting member circulates outside the launching tube, since the reel carried by the launcher is located at the outside of this tube. This part no protected from the filiform connecting member therefore risks being damaged, either during the placing of the ammunition on the launcher, or during the flight preceding the firing. It is the same for the reel carried by the launcher, which is permanently in the open air and risks being damaged particularly during the takeoff and landing phases of the launcher, during which projections of materials can occur. .

The use of a coil linked to the mobile launcher is also illustrated by document EP-A-0 443 623. In this document, the coil linked to the mobile launcher is either fixed directly to the latter so that its axis is oriented vertically, or mounted on the launcher via a cardan joint. In the first case, the angle formed between the unwinding axis of the filiform connecting member and the axis of the coil limits the maximum admissible unwinding speed. The second configuration is incompatible with the firing of an ammunition from a launch tube since the loop which forms between the ammunition and the coil linked to the launcher would then pass into the launch tube. Indeed, any significant change in orientation of the launching tube resulting from the movement of the mobile launcher would exert significant mechanical stress on the threadlike connecting member already unwound from the munition.

On the other hand, in this document EP-A-0 443 623, as in the previous document, there exists between the two coils a portion of unprotected filiform connecting member, which risks being damaged during the setting up. places ammunition on the launcher or during the flight preceding the shooting.

The subject of the invention is precisely a wire-fired munition firing installation, from a launch tube on board a mobile launcher, which does not have the drawbacks of existing installations and in particular allowing the mobile launcher to follow any trajectory after firing the ammunition with a higher speed than in existing installations and without any part of the filiform connecting member being exposed and risk being damaged at any time.

In accordance with the invention, this result is obtained by means of an installation for firing ammunition by wire guided from a mobile launcher, comprising a launching tube, an ammunition normally housed in the launching tube, and a filiform connecting member capable of unwind from a first coil linked to the ammunition and from a second coil linked to the launch tube, characterized in that the launch tube has a front door, normally closed, the second coil being normally mounted in the tube launching, between the munition and the front door, by means of a tilting means of this second coil outside the launching tube, capable of being actuated before a firing of the ammunition.

Thanks to this arrangement, the filiform connecting member which connects the ammunition to the launching tube is completely placed inside the latter before firing. In addition, the housing of the coil linked to the mobile launcher at the front of the ammunition and the tilting of this coil outside the launching tube just before firing practically cancel the angle formed between the unwinding axis and coil axis when the launcher makes a U-turn and moves away from the ammunition after firing.

In a preferred embodiment of the invention, the second coil is fixed to an internal face of the front door, the tilting means being interposed between the latter and the launching tube.

Preferably, a buffer length of the filiform connecting member, located between parts of this member normally wound on the first and second coils, is normally associated with the second coil. In addition, means for ejecting this buffer length, capable of being actuated after actuation of the tilting means and before the ignition of the ammunition, are mounted in the second coil. This characteristic makes it possible to initiate the unwinding of the coil linked to the launcher, when the latter has not yet completed its U-turn, without the threadlike connecting member being subjected to excessively severe mechanical stresses.

In the preferred embodiment of the invention, the second coil comprises a core in which are housed the buffer length of the filiform connecting member and the ejection means.

So that the part of the cable located between the reel linked to the ammunition and the reel linked to the launcher remains substantially stationary, the buffer length of the filiform connecting member advantageously supports means for increasing the coefficient of drag.

Furthermore, in order to protect the section of the filiform connecting member which travels in the launching tube between the first and the second coils before firing, this section is reinforced by a protective sheathing.

In the preferred embodiment of the invention, the tilting means controls a pivoting of approximately 270 ° of the second coil between a normal position, internal to the launching 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 launch tube, in which the axis of the second coil is substantially parallel to the axis of the launch tube.

Preferably, the second coil then comprises a cover, advantageously covered with a fairing, surrounding the part of the filiform connecting member 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 respectively upwards or rearwards depending on whether the second coil occupies its normal position or its positioning position. fire.

On its outer surface, the launch tube then advantageously comprises means for locking the second coil in its firing position.

In the preferred embodiment of the invention, the tilting means comprises at least one tilting control system and a hinge for articulation of the second coil on the launching tube.

Depending on the case, the hinge may comprise either a single pivot axis orthogonal to the axis of the launch tube, or two parallel pivot axes, orthogonal to the axis of the launch tube. In the latter case, there is provided at least one connecting piece capable of pivoting relative to the launching tube around a first of the pivot axes and by ratio with which the second coil can pivot around the second of the pivot axes.

The launching tube further comprises a rear door, normally closed, as well as means for opening this door, capable of being actuated during the firing of the ammunition.

• 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.

A preferred embodiment of the invention will now be described, by way of nonlimiting example, with reference to the appended drawings, in which:

• 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.

In FIG. 1, the reference 10 designates a helicopter on which several shooting installations 12 on board are embarked according to the invention. Each of these firing installations includes a launch tube 14 (Fig. 2), a guided missile 16 and an optical fiber 18 permanently connecting the missile 16 to the launch tube 14. More specifically, FIG. 1 represents the helicopter 10 making a U-turn after the firing of one of the missiles 16.

As already specified, the invention does not only apply to the case where the mobile launcher is constituted by a helicopter 10, but also relates to the case where this launcher is constituted by an aircraft of a different nature, a ship of surface or submarine, or even a land vehicle. Likewise, missile 16 can be replaced by any wire-guided munition adapted to the launcher concerned. Finally, the optical fiber can be replaced by any other filiform connecting member such as a set of electrical conductors.

As illustrated more precisely in FIG. 2, when the missile 16 is stored inside the launching tube 14, a section 18a of the optical fiber 18, corresponding for example to at least half of its total length, is wound up on a first coil 20 housed in the rear part of the missile 16. This arrangement is conventional and will therefore not be described in more detail.

A second section 18b of the optical fiber 18 leaves the missile 16 behind it and travels inside the launch tube 14, along the 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 the missile 16. More specifically, the second coil 22 is fixed on the internal 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 the missile 16 and the front door 24, inside the launch tube 14, when the firing installation 12 occupies its normal storage position.

The section 18b of the optical fiber, which connects the coils 20 and 22, is reinforced by a protective sheathing which allows it to resist the aggressions produced by the propellant of the missile 16, during the ejection of the latter from the tube. launch 14.

The second coil 22 comprises a core 26, of generally cylindrical or frustoconical shape, possibly terminated by flared ends. In the normal storage position illustrated in FIG. 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.

In its part facing upwards when the coil 22 occupies its storage position, the core 26 forms a housing, open upwards, in which is stored a buffer length 18c of the optical fiber 18, for example in the form of a winding. The part of the core 26 adjacent to the buffer length 18c of the optical fiber serves to house ejection means 28 which have the function, as will be seen later, of expelling the buffer length 18c of optical fiber from the housing formed in the core 26, just before the firing of the missile 16. These ejection means 28 can be constituted either by a spring mechanism, or by a pneumatic or pyrotechnic system.

It should be noted that the buffer length 18c of the optical fiber supports means (not shown) making it possible to artificially increase the coefficient of aerodynamic drag of this part of the fiber when it is outside the launching tube 14 .

The buffer length 18c of the optical fiber connects the section 18b of this fiber to a section 18d of the optical fiber, wound together in several layers on the core 26 of the reel 22. The length of the section 18d wound on the reel 22 is generally less than or at most equal to the length of the section 18a wound on the reel 20. In known manner, a suitable adhesive makes it possible to ensure a progressive and regular unwinding of the optical fiber from the coils 20 and 22.

The end of the optical fiber 18 leaving the coil 22 opposite the buffer length 18b is connected by a section of fiber 18e to an optical connector 30 mounted on the launch tube 14 so as to allow the connection of the fiber optic with a control system (not shown) installed on the helicopter 10.

In an alternative embodiment, the end of the optical fiber leaving the coil 22 enters a housing (not shown) making it possible to transform the light signal into an electrical signal in one direction and the electrical signal into a reverse signal in the opposite direction. The section of optical fiber 18e is then replaced by an electrical conductor and the optical connector 30 is itself replaced by an electrical connector.

The second coil 22 further comprises a cover 32, which surrounds the optical fiber wound on the core 26. This cover 32 is arranged coaxially with the core 26 and its internal diameter is slightly greater than the diameter of the outermost fiber layer wound on the core 26, so as to leave a space allowing the fiber to unwind easily, taking into account the phenomenon of bloating which occurs during this unwinding.

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 through which the fiber leaves the coil 22. The diameter of this opening 32a is for example close to the outside diameter of the core 26.

Outside its part adjacent to the rear door 24, the cover 32 is covered with a fairing 34 which extends below the support 27, in the normal position for storing the coil 22 illustrated in solid lines in FIG. 2.

In order to allow the firing of the missile 16, the front door 24 as well as the coil 22 fixed on this door are linked to the launching tube 14 by tilting means allowing this assembly to be placed outside the tube launch, in a firing position that completely clears the front end of the launch tube. This firing position is illustrated in dashed lines in Figure 2 and in solid lines in Figure 3C.

These tilting means comprise a hinge 36, by 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 launch tube 14 .

In the embodiment illustrated in Figure 2, the tilt control system 38 may in particular be constituted by a pyrotechnic gas generator mounted in the top of the launch tube 14, in front of the latter. This system 38 normally maintains the front door 24 in its closed position and propels the door 24 forward, around the hinge 36, when actuated.

In the embodiment illustrated in FIG. 2, the hinge 36 has a single axis 40, substantially horizontal, located at the bottom and in front of the launch tube 14. More specifically, 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 front door 24 and the coil 22, in a clockwise direction considering FIG. 2. This pivoting ends when the face external of the front door 24 abuts against the underside of the launch tube 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 optical fiber 18 out of the cover 32 is oriented towards the rear.

This final position of the assembly formed by the front door 24 and the coil 22, called the firing position, allows the missile 16 to exit the launch tube 14 after it has been fired. In its lower part, the launching tube 14 carries on its outer surface locking means 42 which cooperate with the front door 24 when the latter has tilted by 270 °. The locking means 42 thus immobilize the second coil 22 in its firing position. the locking means 42 may be constituted by any mechanical locking system.

In the normal storage position of the firing installation 12, the launch tube 14 also includes a rear door 44 which closes the rear end of this tube. Opening means 46 mounted inside the launch tube 14 cooperate with the rear door 44 to keep it normally closed and to command the opening thereof when the missile 16 is fired. These opening means 46 may be any means, for example of the pyrotechnic, electrical type, etc.

When the firing installation 12 occupies its normal storage position illustrated in solid lines in FIG. 2, the front end of the installation does not have any protuberance capable of preventing its stacking or increasing the master- couple.

In addition, the installation forms an assembly which can be integrated into the launcher without any other intervention than that required by fixing and connecting the installation.

In addition, since the entire length of the optical fiber is housed in the launch tube, handling operations are facilitated and the missile is protected against attacks of all kinds (mechanical, fluids or atmospheric agents such as hail, sand , etc.) encountered during the handling and carrying phases on the mobile launcher. Similarly, the fiber optic link between the launcher and the missile is protected from attack in the same way as the missile itself. In addition, this configuration makes any fiber blocking mechanism intended to prevent spontaneous unwinding of one or other of the coils unnecessary under the effect of the aerodynamic drive generated by the movement of the launcher.

In addition, when the missile has fired, the fiber output axes from the two coils are oriented towards the rear of the mobiles constituted by the missile 16 and the helicopter 10, which allows translational speeds each of them.

The implementation of the shooting installation illustrated in Figure 2 will now be described with reference to Figures 3A to 3C.

When a firing order is given, the tilt control system 38, the ejection means 28, the opening means 46 and the missile thrusters 16 are actuated sequentially, with predetermined time intervals, in the manner next.

Initially, the tilt control system 38 is actuated, which has the effect of propelling the front door 24 forwards, around its pivot axis 40, as illustrated in FIG. 3A.

As shown in FIG. 3B, during the pivoting of the front door 24, the ejection means 28, internal to the core 26 of the coil 22, are activated and the buffer length 18c of optical fiber is ejected downwards, so gradually form a loop, flowing in the air. The length of this loop (FIG. 3C) is determined so as to initiate the unwinding of the secondary coil 22 under the effect of the aerodynamic traction exerted on the fiber by the movement of the helicopter 10.

When the 270 ° pivoting of the assembly formed by the front door 24 and the coil 22 is finished, this assembly is blocked in the firing position by the locking means 42. The opening 32a of the cover 32 by which unwinds the optical fiber, is then oriented towards the rear relative to the helicopter, which allows the latter to move away at high speed after the launch of the missile.

As soon as the coil 22 has reached its firing position, the opening means 46 are actuated (FIG. 3C) so as to release the rear door 44 and the missile 16 is fired. From then on, the helicopter can start its U-turn and move far away speed of the missile, since the exit axis of the fiber unwinding from the reel 22 is oriented towards the rear relative to the helicopter 10.

In FIGS. 4A to 4C, an alternative embodiment of the hinge 36 has been illustrated. In this alternative embodiment, the hinge comprises two horizontal and parallel axes 40a and 40b, oriented in a direction orthogonal to the axis of the launch tube 14. These axes 40a and 40b are respectively linked to the launching tube 14 and to the rear door 24. The hinge further comprises one or more connecting parts constituted by levers 48, substantially C-shaped, the ends of which are articulated on axes 40a and 40b. The assembly formed by the axes 40a and 40b and by the levers 48 is normally housed inside the launching tube 14, in the storage position of the shooting installation (FIG. 4A).

When the tilting control system ensuring the pivoting of the front door 24 around the hinge 36 is actuated, the assembly formed by the lever (s) 48 and the front door 24 first pivots around the axis 40a in clockwise, as shown in Figure 4B.

When the levers 48 abut against the front end of the launch tube 14, the front door 24 in turn pivots about the axis 40b, in the clockwise direction, as illustrated in FIG. 4C . At the end of this pivoting, there has been a 270 ° rotation of the assembly formed by the front door 24 and the coil 22, in a clockwise direction when considering FIGS. 4A to 4C. The coil 22 then occupies the same positioning position as in the embodiment described above.

In the embodiment which has just been described, the tilting means may comprise an electric actuator or a spring mechanism, making it possible to control the rotation of the front door 24 and of the levers 48 around the axis 40a, as well as torsion bars allowing then to ensure the rotation of the front door 24 about the axis 40b.

It should be noted that the reel 22 can be supported directly by the launch tube 14, instead of being fixed on the internal face of the front door 24. The release of the front door and the tilting towards the outside of the coil then intervene sequentially.

Claims (14)

Installation for firing ammunition guided by a mobile launcher, comprising a launching tube (14) capable of being mounted on the launcher (10), an ammunition (16) normally housed in the launching tube, and a filiform connecting member ( 18) capable of unwinding a first reel (20) linked to the ammunition and a second reel (22) linked to the launch tube, characterized in that the launch tube (14) has a front door ( 24), normally closed, the second coil (22) being normally mounted in the launching tube (14), between the ammunition (16) and the front door (24), by means of a tilting means (36 , 38) of this second coil outside the launching tube, capable of being actuated before firing the munition. Installation according to claim 1, characterized in that the second coil (12) is fixed to an internal face of the front door (24), the tilting means (36, 38) being interposed between the latter and the launching tube (14). Installation according to any one of claims 1 and 2, characterized in that a buffer length (18c) of the filiform connecting member, located between parts of this member normally wound on the first (20) and the second (22) coils, is normally associated with the second coil, ejection means (28) of this buffer length, capable of being actuated after actuation of the tilting means (36, 38) and before the ignition of the ammunition (16), being mounted in the second coil (22). Installation according to claim 3, characterized in that the second coil (22) comprises a core (26) in which are housed said buffer length (18c) and the ejection means (28). Installation according to any one of claims 3 and 4, characterized in that said buffer length (18c) of the filiform connecting member supports means for increasing the drag coefficient. Installation according to any one of the preceding claims, characterized in that a section (18b) of the filiform connecting member, normally traveling in the launching tube (14) between the first (20) and the second (22 ) coils, is reinforced by protective sheathing. Installation according to any one of the preceding claims, characterized in that the tilting means (36, 38) controls a pivoting of about 270 ° of the second coil (22) between a normal position, internal to the launching tube ( 14), 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 launch tube (14), in which the axis of the second coil is substantially parallel to the axis of the launch tube. Installation according to claim 7, characterized in that the second coil has a cover (32) surrounding the part of the filiform connecting member normally wound on the second coil, this cover having a circular opening (32a) for exit from the 'filiform connecting member, centered on the axis of the second coil and oriented respectively upwards and rearwards, when the second coil occupies its normal position and its firing position. Installation according to claim 8, characterized in that the cover (32) is covered with a fairing (34). Installation according to any one of claims 7 to 9, characterized in that the launching tube (14) carries locking means (42) of the second coil (22) in its fired position. Installation according to any one of Claims 7 to 10, characterized in that the tilting means comprises at least one tilting control system (38) and a hinge (36) for articulation of the second coil (22) on the launch tube (14). Installation according to claim 11, characterized in that the hinge (36) has a single pivot axis (40) orthogonal to the axis of the launch tube (14). Installation according to claim 11, characterized in that the hinge (36) has two parallel pivot axes (40a, 40b), orthogonal to the axis of the launch tube (14), and at least one connecting piece (48 ) able to pivot relative to the launch tube around a first of the pivot axes, and relative to which the second coil can pivot around the second of the pivot axes. Installation according to any one of the preceding claims, characterized in that the launching tube (14) comprises a rear door (44), normally closed, as well as opening means (46) of this door, capable of being actuated during the firing of the ammunition.

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