EP0685702B1 - Launching installation for a wire-guided rocket - Google Patents

Description

The present invention relates to a packaging and launch facility guided missile equipped with ejection thrusters lateral.

A guided missile is a missile that is launched from a container to which it remains connected after its launch by a flexible organ of transmission of information that can be called "thread".

This thread is used to transmit orders to missile in flight, in order to modify its path.

The launch of a wire-guided missile at from its container is a very delicate for this thread.

So the problem arises of not damage the flexible transmission member information when the missile was launched.

This problem is already solved by the packaging and launch facility described in document EP-A-0 337 880 on which the preamble of claim 1 is based, by means of a deformable protective device which is placed around the flexible transmission member until the moment when the thrusters of the missile arrive outside the container.

This deformable protection device is a tubular device which consists of a flexible sleeve or by rigid ferrules telescopic.

The present invention aims to solve the problem mentioned above in a simpler way than the installation described in the cited document.

• un organe de fermeture qui résiste aux gaz chauds, dont une extrémité est raccordée de façon détachable sur le missile, autour de l'orifice arrière de celui-ci, et qui est fermé en regard du fond du conteneur et traversé par l'organe souple de transmission d'informations,
• un support ajouré, rendu solidaire de cet organe de fermeture et déplaçable en translation dans le conteneur, l'organe de fermeture muni du support étant apte à se détacher automatiquement du missile lors d'un lancement, lorsque les propulseurs arrivent en dehors du conteneur, et
• un organe protecteur souple qui résiste aux gaz chauds et entoure une partie de l'organe souple de transmission d'informations, cette partie allant de l'organe de fermeture jusqu'à l'ensemble d'accrochage.

Specifically, the subject of the present invention is an installation for launching and launching a wire-guided missile equipped with thrusters intended to eject hot gases laterally, this installation comprising a container-launcher for conditioning the missile provided with a supporting base. a fastening assembly for a flexible information transmission member wound in the missile and leaving the latter via a rear orifice, a protection device being placed around the flexible information transmission member, up to moment when the thruster ejection nozzles arrive outside the container, this installation being characterized in that the protection device comprises:

• a closure member which resists hot gases, one end of which is detachably connected to the missile, around the rear orifice thereof, and which is closed opposite the bottom of the container and crossed by the flexible member information transmission,
• an openwork support, made integral with this closure member and movable in translation in the container, the closure member provided with the support being able to detach automatically from the missile during a launch, when the thrusters arrive outside the container, and
• a flexible protective member which resists hot gases and surrounds a part of the flexible information transmission member, this part going from the closure member to the attachment assembly.

Although the invention can be used whatever the nature of the flexible organ of transmission of information, it applies advantageously in case this organ comprises a fiber optical.

• un câble qui résiste aux gaz chauds, qui est apte à transmettre des signaux électriques au missile et qui va du missile à l'ensemble d'accrochage en traversant l'organe de fermeture, et
• un connecteur électrique en deux parties qui permet la continuité électrique de ce câble et qui est monté sur le câble, en dehors de la partie de celui-ci allant de l'organe de fermeture jusqu'à l'ensemble d'accrochage, les deux parties du connecteur étant aptes à se séparer l'une de l'autre en même temps que l'organe de fermeture se détache du missile,

l'organe protecteur souple comprenant le câble et l'organe souple de transmission d'informations étant logé dans ce câble, sensiblement depuis l'organe de fermeture jusqu'à l'ensemble d'accrochage.The installation which is the subject of the present invention can comprise:

• a cable which resists hot gases, which is capable of transmitting electrical signals to the missile and which goes from the missile to the attachment assembly by passing through the closure member, and
• a two-part electrical connector which allows the electrical continuity of this cable and which is mounted on the cable, apart from the part of the latter going from the closure member to the attachment assembly, both parts of the connector being able to separate from one another at the same time as the closure member detaches from the missile,

the flexible protective member comprising the cable and the flexible information transmission member being housed in this cable, substantially from the closure member to the attachment assembly.

According to an embodiment of the installation which is the subject of the invention, preferred for its simplicity, the end of the container through which comes out the missile is provided with a means of stopping the support, allowing the closure member provided with this support detach from the missile when the nozzles thruster ejectors arrive outside the container.

In order to increase the range of the missile, the installation which is the subject of the invention may include in in addition to an auxiliary coil on which is wound the flexible information transmission device, the closure member being tubular and this coil auxiliary being fixed in this closing member.

Preferably, the support is returned secured to the other end of the closure, so that this closure member is placed outside the container when the missile has left this container.

This is particularly advantageous in the case where the auxiliary coil mentioned above is used.

The installation which is the subject of the invention can also include at least one Cardan suspension through which the closing member is secured to the support.

Preferably, the closure member is waterproof and tightly connected to the missile.

This protects the flexible member from transmission of information while the missile is stored in the container.

• la figure 1A est une vue schématique d'un mode de réalisation particulier de l'installation de conditionnement et de lancement d'un missile filoguidé objet de la présente invention, ce dernier étant représenté dans son conteneur,
• la figure 1B illustre schématiquement ce missile en cours de lancement, lorsque les propulseurs à éjection latérale qu'il comporte ne sont plus dans le conteneur,
• la figure 1C illustre schématiquement le missile après son lancement, l'organe souple de transmission d'informations qu'il comporte commençant à se dérouler,
• la figure 2A est une vue en coupe schématique et partielle d'une installation conforme à l'invention ne comprenant pas de bobine auxiliaire,
• la figure 2B est une vue en coupe schématique et partielle d'une autre installation conforme à l'invention, comprenant une bobine auxiliaire qui reste solidaire du conteneur après le lancement du missile, et
• la figure 3 est une vue en perspective schématique d'un organe de fermeture faisant partie d'une installation conforme à l'invention et monté sur un support par l'intermédiaire de suspensions à la Cardan.

The present invention will be better understood on reading the description of exemplary embodiments given below, by way of purely indicative and in no way limiting, with reference to the appended drawings in which:

• FIG. 1A is a schematic view of a particular embodiment of the installation and launching installation of a wire-guided missile which is the subject of the present invention, the latter being represented in its container,
• FIG. 1B schematically illustrates this missile in the course of launching, when the lateral ejection thrusters which it comprises are no longer in the container,
• FIG. 1C schematically illustrates the missile after its launch, the flexible information transmission member that it comprises starting to unfold,
• FIG. 2A is a schematic and partial sectional view of an installation according to the invention not comprising an auxiliary coil,
• FIG. 2B is a schematic and partial sectional view of another installation in accordance with the invention, comprising an auxiliary coil which remains integral with the container after the launch of the missile, and
• Figure 3 is a schematic perspective view of a closure member forming part of an installation according to the invention and mounted on a support by means of Cardan suspensions.

Figure 1A is a schematic view of a installation of packaging and storage of a guided missile 2 with ailerons 4.

This missile 2 is equipped with side ejection of which we see the ejection nozzles 6.

Figure 1A shows this installation under the conditions of storage of the missile.

In a known manner, this installation includes a container for packaging and launch 8 in which the missile is fully housed 2.

The end of the container 8, through which is intended to come out of a missile, is closed by a missile protection cover or door 10, lid or door that flips on command before missile launch.

Container 8 has a bottom supporting a hanging assembly 12.

A flexible transmission device information such as an optical fiber 14 (FIG. 1C) is wound in a rear part of missile 2.

The end of this optical fiber leaves the missile 2 through an annular orifice 16 (FIG. 1C) formed at the rear of missile 2, to be fixed on the attachment assembly 12 that the container 8 includes.

It should be noted that this attachment assembly 12 is itself connected to a shooting station not shown.

The installation according to the invention which is schematically represented in FIGS. 1A to 1C also includes a protective device 18 which is placed around the optical fiber 14 until the moment when the thrusters 6 arrive outside the container 8.

This protection device 18 comprises a closure member 20, an openwork support 22 and a flexible protective member 24.

One end of this closure member 20 is detachably connected to missile 2, around the rear hole 16 thereof.

In addition, this closure member 20 is closed opposite the bottom of the container 8 and crossed by optical fiber 14.

Preferably, the closure member 20 is waterproof and tightly connected to the missile 2.

It is thus possible to maintain the fiber optics wound in the missile under an atmosphere suitable gas to preserve the qualities mechanical and optical of the fiber, while leaving a as easy access as possible to other parts of the missile for its maintenance.

In addition, the closing member 20 is made a material that resists hot gases ejected by the thrusters 6 during the launch of the missile, this material being for example an alloyed steel.

The openwork support 22 is made integral with the closing member 20 and it is capable of move in translation in container 8 during launch.

The flexible protective member 24 is also made of a material that resists hot exhaust gases propellants, this material being for example a silicone.

This flexible protective member 24 surrounds the optical fiber 14 from the closure member 20 up to the attachment assembly 12.

It can be seen in FIG. 1A that this organ flexible protector 24 is coiled at the bottom of the container 8 when missile 2 is stored in this container.

The end 25 of the container 8, through which fires missile 2, is provided with means 26 for stopping the support 22, this stop means being for example a stop as seen in Figures 1A to 1C.

So when missile 2 was launched, this missile moves in the container towards the end 25 thereof, the closing member 20 does the same and the support 22, which is made integral with this member closure, slides in container 8.

When this support 22 reaches the end 25 of the container, the closure member 20 as well as support 22 which is integral therewith are stopped by the stop 26.

Then missile 2 detaches from the organ closure 20 and moves away from container 8 while the optical fiber 14 begins to unwind.

The closing member 20 constitutes a sort of cap that protects the amount of fiber optics wound in the missile during launch of the last.

The length of optical fiber required to the connection between the closing member 20 and the assembly attachment 12 is also protected, during this launch, thanks to the flexible protective member 24.

In the examples shown on the Figures 1A to 2B, we see that the support 22 is made secured to the end of the closure member 20, end opposite to that attached to missile 2.

Thus, the closing member 20 is located at outside of container 8 after launch missile 2.

FIG. 2A shows a coil 28 which is fixed in missile 2, at the rear of it, and which has the same X axis as this missile.

The optical fiber 14 is wound on this reel 28 and passes from it into the body of closing 20 then leave the latter to meet at the interior of the flexible protective member 24.

In the example shown in this figure 2A, this flexible protective member 24 is a cable intended to transmit electrical signals to the missile for the launch of it.

This cable 24 goes from missile 2 to the attachment assembly 12 (FIG. 1A) crossing the closing member 20.

A two-part electrical connector 30 allows electrical continuity of cable 24.

As seen in Figure 2A, this connector 30 is mounted on cable 24, outside of the part of this cable going from the closure member 20 to the hanging assembly 12.

The two parts 32 and 34 of the connector 30 are able to separate from each other at the same time that the closing member 20 detaches from the missile 2.

In the example shown in Figure 2A, the closure member 20 follows the shape of a tube having the same X axis as missile 2 and the end of this tube, which is located opposite the bottom of the container, is closed and constitutes the bottom 36 of the closure 20.

In the example of FIG. 2A, the support 22 consists of a frame perpendicular to the X axis and rigidly secured to the closure member 20 to which it is fixed by means of bars maintenance such as the bar 38.

It is specified that the optical fiber 14 wound on the coil 28 can be connected to the section of fiber optic contained in cable 24 by through a splice or connector optics (not shown).

FIG. 2A shows a support 39 which is attached to frame 22 and to which the fiber is hung optics 14.

In addition, between the closing member 20 and the place where the fiber 14 is connected to the section of optical fiber contained in cable 24, this fiber is housed in a protective sheath 15 made of a material such as a silicone, which resists gases hot out of the thrusters.

Note that the part of the cable 24 containing the optical fiber constitutes an electro-optical cable (up to the hanging assembly 12).

The tip of the rear part of the missile is bent outward.

In the groove thus formed is placed a O-ring 39a.

In addition, this end is housed in the tube 20.

The seal 39a allows, by friction, to fix detachably the rear of the missile 2 to the organ closing.

This joint 39a also makes it possible to connect tightly the missile to the closing member.

In the event that the range of the missile requires, an auxiliary coil 40 (Figure 2B) is fixed inside the shaped closure of tube 20, at the bottom 36 thereof.

In the case of FIG. 2A, this tube, which contains no reels, maybe a lot more shorter than the tube in Figure 2B.

Returning to Figure 2B, the coil auxiliary 40, on which is also wound the optical fiber 14, has the same X axis as this tube.

In this case, the optical fiber wound on coil 28 goes from it to coil 40 on which it is wound up then passes from this coil 40 this to the cable 24 to be housed inside of it, as seen in Figure 2.

• une partie optique 42 allant vers une connexion à la fibre enroulée sur la bobine 40, et
• une partie électrique allant vers le connecteur électrique 30.

Thus the cable 24 separates into two parts:

• an optical part 42 going towards a connection to the fiber wound on the reel 40, and
• an electrical part going towards the electrical connector 30.

Note that the fiber optic coil 40 is itself protected inside the organ of closure 20 until the launch of missile 2 and ideally located outside the container 8, once the missile has launched.

In the example shown in Figure 2B, the part 32 of the connector 30 is fixed at the end of the coil 28 which is located opposite the coil 40 while the other part 34 of the connector 30 is fixed at the end of the coil 40 which is opposite coil 28.

In the example shown in Figure 2B, the end 2a of the rear part of missile 2 is curved outwards, the front end 20a of the tube 20 is also bent outwards and surrounds this end 2a.

Additionally, as seen in Figure 2B, a flange 2b of axis X is welded to the rear of the missile 2, another flange 20b of axis X is welded at the front part of the tube 20 and surrounds the flange 2b.

In the overlap area of these an O-ring 43 is placed.

This seal 43 allows, by friction, to fix detachably the rear of the missile 2 to the organ closing.

This joint 43 also makes it possible to connect tightly the missile to the closing member.

Once missile 2 is launched, the wind or relative speed between the fiber deposited in the mass air and the firing point is likely to induce drag force which becomes significant when the length of unrolled optical fiber exceeds approximately 10 km.

The unfolding of optical fiber from of the reel 40 also makes it possible to offload the fiber optics of the tension that results from this force of trail.

In addition, the unwinding of the fiber does not not necessarily following an axis parallel to the axis of the container, the closing member 20 can be mounted on its support 22 via one or two Cardan suspensions which leave this organ of closure 20 free to pivot in deposit and / or in site.

Such a possibility is schematically illustrated by Figure 3 where we see the closure 20 pivotally mounted on a support intermediate 44 also in the form of a frame, the organ closure 20 being able to pivot about an axis Y parallel to two opposite uprights of this frame.

The intermediate support 44 is itself pivotally mounted on the support 22 in the form of a frame, the support 44 being movable in rotation about an axis Z which is parallel to two opposite uprights of frame 22 and perpendicular to the Y axis.

Claims (8)

1. Installation for packaging and launching a wire-guided missile (2) equipped with motors which are intended to eject hot gases laterally, this installation comprising a missile packaging container/launcher (8) provided with a bottom supporting an assembly (12) for fastening a flexible information-transmission member (14) reeled up in the missile and exiting the latter through a rear orifice (16), a protection device (18) being placed around the flexible information-transmission member, up to the moment at which the ejection nozzles (6) of the motors clear the container, this installation being characterized in that the protection device (18) comprises:

   a closure member (20) which withstands the hot gases, one end of which is joined in a detachable manner to the missile, around the rear orifice of the latter, and which is closed facing the bottom of the container and through which the flexible information-transmission member passes,

   a perforated support (22), secured to this closure member and translationally moveable in the container, the closure member fitted with the support being able to detach itself automatically from the missile during a launch, when the motors clear the container, and

   a flexible protector member (24, 15) which withstands the hot gases and surrounds a part of the flexible information-transmission member, this part going from the closure member to the fastening assembly.
2. Installation according to Claim 1, characterized in that the flexible information-transmission member comprises an optical fibre (14).
3. Installation according to either one of Claims 1 and 2, characterized in that it comprises:

   a cable (24) which withstands the hot gases, which is able to transmit electrical signals to the missile (2) and which goes from the missile to the fastening assembly (12), passing through the closure member (20), and

   a two-part electrical connector (30) which allows the electrical continuity of this cable and which is mounted on the cable, outside the part of the latter going from the closure member (20) to the fastening assembly (12), the two parts (32, 34) of the connector being able to separate from one another at the same time as the closure member detaches itself from the missile (2),

   and in that the flexible protector member comprises the cable (24), the flexible information-transmission member (14) being housed in this cable (24), substantially from the closure member (20) to the fastening assembly (12).
4. Installation according to any one of Claims 1 to 3, characterized in that the end (25) of the container (8) through which the missile (2) exits is fitted with a means (26) of stopping the support (22), allowing the closure member (20) fitted with this support (22) to detach itself from the missile at the moment at which the ejection nozzles (6) of the motors clear the container.
5. Installation according to any one of Claims 1 to 4, characterized in that it furthermore comprises an auxiliary reel (40) on which is wound the flexible information-transmission member (14), in that the closure member (20) is tubular and in that this auxiliary reel is fixed in this closure member.
6. Installation according to any one of Claims 1 to 5, characterized in that the support (22) is secured to the other end of the closure member (20), in such a way that this closure member is placed outside the container (8) when the missile (2) has left this container.
7. Installation according to any one of Claims 1 to 6, characterized in that it furthermore comprises at least one gimbal suspension by way of which the closure member (20) is secured to the support (22).
8. Installation according to any one of Claims 1 to 7, characterized in that the closure member (20) is leaktight and joined in a leaktight manner to the missile (2).

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