WO2006122984A1

WO2006122984A1 - Radiation-emitting device for protecting aircraft

Info

Publication number: WO2006122984A1
Application number: PCT/EP2006/062497
Authority: WO
Inventors: Philippe Mourry; Henri Glimois; Philippe Cassagne
Original assignee: Etienne Lacroix Tous Artifices S.A.
Priority date: 2005-05-20
Filing date: 2006-05-22
Publication date: 2006-11-23
Also published as: FR2886004B1; FR2886004A1

Abstract

The invention relates to a device comprising at least one launch tube (100), an ejectable projectile (200) comprising at least one charge (210) comprised, at least in part, of an energetic material placed inside the launch tube (100) and a propulsion means assigned to said launch tube (100) for propelling the projectile (200). The invention is characterized in that it comprises, on the one hand, a portion of the means (158, 300) that prevent an initiation transmission to the charge (210) before the projectile (200) exits the launch tube (100) and, on the other, a flap (20) which, at rest, closes the exit of the launch tube (100) and which is to be displaced on command toward a neutral position, in which it frees the exit of the launch tube (100) for allowing the projectile (200) to exit.

Description

RADIATION TRANSMITTING DEVICE, IN PARTICULAR FOR AIRCRAFT PROTECTION

The present invention relates primarily to the field of radiation emitting devices, including devices emitting infrared radiation.

The invention is however not limited to this particular application. The invention is generally applicable to the implementation of charges ejected from a charger or a cartridge socket or equivalent. Many radiation emitting devices, especially in the infrared range, have already been proposed.

However known devices are not always satisfactory, either because they do not include security means avoiding inadvertent operation of the cartridges, either because they incorporate such means but in this case to the detriment of their reliability. The main object of the present invention is to propose a new device making it possible to improve the situation.

This object is achieved in the context of the present invention by means of a device comprising at least one launcher tube, an ejectable projectile placed in the launcher tube and comprising at least one load at least partly made of an energetic material and a propellant associated with the launcher tube and adapted to propel said projectile, characterized in that it comprises in combination on the one hand means that prohibit initiation transmission to the load before the projectile is out of the launcher tube and other a shutter that mechanically closes, at rest, the exit of the launcher tube and which can be moved on command to a neutral position in which it releases the exit of the launcher tube to then allow the output of the projectile. Those skilled in the art will understand that, thanks to the structure proposed in the context of the present invention, as long as the flap has not been moved to a neutral position, the projectile is confined inside the tube launcher. His initiation is then forbidden by the means that forbid the transmission of initiation.

These means designed to prohibit the initiation transmission to the load, as long as the projectile has not left the launcher tube, may be subject to different embodiments.

It may be means forming a mechanical screen facing an initiator associated with the load, for example a mechanical screen interposed between this initiator and the propulsion means, which mechanical screen is retracted automatically when the projectile leaves the launcher tube. Such a mechanical screen prohibits an initiation transmission to the load as it is not retracted and allows this transmission once the screen retracted.

It may also be means designed to delay the initiation of the load and allow this initiation after the projectile out of the launcher tube. According to a particular and nonlimiting example, such means may be formed of initiation means comprising on the one hand a primary load associated with the payload and on the other hand a wire or equivalent placed between the primary load and a ground, such as a piston retained in the launcher tube, adapted to be flared at the exit of the projectile to initiate frictional initiation of the primary charge.

Other features, objects and advantages of the present invention will appear on reading the detailed description which follows, and with reference to the appended drawings, given by way of non-limiting examples and in which:

FIG. 1 represents a schematic view in longitudinal section of a device according to the present invention, in the initial state, in the form of a charger placed in a housing closed by a shutter,

FIG. 2 represents a similar view of the same device after retraction of the shutter,

- Figures 3 and 4 show similar views in longitudinal section of a subset of the same two-stage device successive operations thereof, respectively at the time of the exit of a projectile and after exit of the projectile, and - Figures 5 and 6 show an alternative embodiment according to the present invention, also in two successive stages of its operation.

In the following description we will describe chargers or cartridges according to the present invention having charges capable of generating infrared radiation. The present invention is however not limited to this particular application. It generally extends to the implementation of suitable charges to generate any type of radiation and more generally to any type of charges comprising energetic materials, such as smoke materials or detonating or explosive charges.

There is shown in Figure 1 a charger 10 which comprises a plurality of launching tubes 100 each housing a projectile 200. There is thus seen in Figure 1 three tubes 100. This number is however in no way limiting. The loader 10 comprises a yoke 12 which houses the initiation control means, that is to say the means adapted to initiate the ejection and the implementation of the projectiles 200. These initiation control means integrated in the cylinder head will not be described in more detail later.

As previously indicated in the context of the present invention, there are provided security means that prohibit implementation of the payload of the projectiles 200 as they are placed inside a tube launcher 100.

According to the variant illustrated in FIGS. 1 to 4, the means prohibiting the initiation transmission to the payload are formed by means forming a mechanical screen facing an initiator associated with the load, which mechanical screen is automatically retracted when the projectile leaves the launcher tube.

More specifically, these safety means comprise in combination a shutter 20 which mechanically closes at rest, the output of the charger, and means, preferably integrated respectively into each projectile, which prohibit an initiation transmission to the charge of each projectile 200 before the projectile is released from the associated launcher tube 100.

The flap 20 can be moved on command to a neutral position, as seen in Figure 2, in which it releases the output of the charger to allow the output of the projectiles.

The flap 20 may be formed of any suitable material to resist the solicitation of a projectile, including in case of untimely implementation of the propulsion means thereof. The geometry of the flap 20 can likewise be the subject of many embodiments and will therefore not be described in more detail later. The flap 20 may be integrated with the charger 10 or the structure that receives the latter, for example the structure of an aircraft, when the charger is intended to be implanted in a housing of the latter. It is also the same with regard to the structure and the kinematics of the means adapted to move the flap from its rest position illustrated in FIG. 1 to the neutral position illustrated in FIG. 2. According to the preferred embodiment 1 and 2, the flap 20 is adapted to be moved parallel to its mean plane, between the rest position of FIG. 1 and the neutral position of FIG. 2. This prevents the flap 20 from protruding in front of the mouth of the magazine.

3, 4 and 5, 6, various exemplary embodiments according to the present invention, of means integrated into each projectile 200 to prohibit an initiation transmission towards the load of each projectile will be described in more detail below with reference to FIGS. before the projectile is released from the launcher tube 100.

The present invention can be applied in particular to the protection of aircraft by generating infrared radiation. In this context, it should be noted that the presence of the flap 20, in addition to the aforementioned security function, offers numerous advantages. It guarantees the aerodynamics of the aircraft, in the rest position, and prohibits fraudulent or accidental access to the charger 10. In addition, the shutter 20 brings an undeniable positive psychological effect in that it conceals the charger 10 and thus avoids stress likely to result from the visual observation of the charger 10 by the passengers of the aircraft.

The movement of the shutter 20 from the rest position to the neutral position can be controlled manually or automatically when the implementation of the charger is desired.

By way of nonlimiting example, in the case of the protection of an aircraft, the movement of the flap 20 can be controlled when the following events are detected individually or in combination: Powering the charger through the cockpit,. Minimum speed of the aircraft required,. Minimum altitude of the aircraft in relation to the ground reached, and. Minimum value of the inclination of the aircraft.

We will now describe the particular structure of the means illustrated in Figures 1 to 4, prohibiting the initiation transmission to the payload, as a projectile 200 is placed in the charger 100.

The launching tubes 100 integrated in the loader 10, illustrated in Figures 1 to 4, each comprise a rectilinear sheath of constant section 110 provided at its rear end with a base 120 forming an impeller. The launcher tube 100 may be made of any suitable material, for example metal, such as aluminum, or thermoplastic material.

The launcher tube 100 is preferably monodirectional, i.e., it is adapted to propel the projectile 200 in one direction only and not to simultaneously projectiles in two opposite directions.

The base 120 is fixed by any appropriate means on the sheath 110, for example by crimping or gluing. It houses a primer not shown in the accompanying figures to simplify the illustration, for example either a percussion-controlled primer or an electrically controlled primer (activated by the means 12), and a propulsion charge also not shown on the figures, which opens out into the chamber of the tube 100. The primer and the propulsion charge are placed in the housing referenced 122 of the base 120.

If necessary, a flap or protective film 126 may be interposed between the aforementioned propellant charge and the internal chamber of the tube 100.

As seen in Figures 1 to 4 attached, a piston 150 is placed in the bottom of the tube chamber 100, adjacent to the base 120.

The piston 150 has a complementary section of the tube 100. It is preferably made of metal. It preferably comprises an O-ring 152 or equivalent on its periphery, suitable for sealing between the periphery of the piston 150 and the inner wall of the tube 100 in order to avoid transmission of gas at this level. The seal 152 thus avoids inadvertent initiation of the material placed in the projectile 200 by the gases generated by the load placed in the housing 122.

In contrast the piston 150 has a through channel 154 whose function will be specified later. Initially this channel 154 is closed by the flap or protective film 126.

It will also be noted that the tube 100 is preferably provided at its mouth, that is to say opposite its base 120, with an inner ring 130. The ring 130 forms a local diameter narrowing for the tube 100. It serves a dual function: firstly it serves as a stop limiting the movement of the piston 150 and secondly it serves as a damper for the piston 150. The ring 130 can give rise to many modes of production. According to the representation given in Figure 1, the ring 130 is integral with the tube 100. Alternatively, it may be a separate part, held on the mouth of the tube by any suitable means, for example by the peripheral flange 104 of the front transverse wall 103 of the tube. Preferably the tube 100 is also initially closed transversely, at its end opposite the base 120, by a partition or front wall 103 made of material. In this case, however, preferably the partition 103 is divided between a circular central seal 106 of the same section as the projectile 200 and the aforementioned peripheral rim 104, by a precut line 105. Alternatively the tube 100 may be initially closed at its mouth by a plug 160, for example of plastics material, and preferably provided with an O-ring seal at the periphery. The cap 160 can be held on the tube 100 by any appropriate means, for example by crimping or gluing. Such a stopper 160 which forms a wedge disc may comprise a steel insert whose purpose is to gradually cut the sheath 110 in order to isolate and separate the cover 106.

The ring 130 has an internal diameter which is preferably identical to that of the flange 104. The projectile 200 comprises at least one bread 210 of material capable of generating infrared radiation (or another type of radiation depending on the desired effect) during its combustion.

In Figures 1 to 4 attached there is shown a single cylindrical roll 210. Where appropriate the projectile 200 can however accommodate a plurality of stacked elementary loaves.

If necessary the bread 210 or the stack of breads 210 may comprise stiffening fibers.

More precisely, the projectile 200 illustrated in FIGS. 1 to 4 appended comprises cords 220 of priming composition distributed in longitudinal grooves formed in the outer surface of the projectile 200.

The section or caliber of the projectile 200 is complementary (slightly lower) to the section of the passage defined by the peripheral rim 104. It is therefore smaller than that of the piston 150 which is complementary to the inner section of the sleeve 110.

The projectile 200 also has a pyrotechnic delay 230 at its rear end, opposite the passage 154. As has been explained previously, in the context of the present invention, the device comprises means which prohibit an initiation transmission to the bread 210, as long as the projectile has not left the associated launcher tube 110, more precisely here before the separation of the piston 150 and the projectile 200.

Such means can be the subject of many embodiments.

They preferably comprise mechanical screen means integral with the piston 150 and initially placed between the delay 230 and the load 210. Such a mechanical screen preferably has a geometry complementary to that of a housing formed between the delay 230 and the load. 210. It provides sealing functions at this level. This screen preferably covers orifices formed in a housing that houses the delay. According to the particular embodiment shown in the figures

1 to 4 appended, the piston 150 is provided on its front face with a cylindrical skirt 158 centered on the longitudinal axis of the projectile 200, which is engaged in an annular chamber formed between a cylindrical housing 232 housing the pyrotechnic delay 230 and the rear part of the bread 210. The housing 232 also has a plurality of through holes 234 equidistributed angularly.

In storage the skirt 158 of the piston covers the orifices 234 and prohibits the initiation of the bread 210, by the relay 230. It is so until the projectile 200 is not separated from the piston 150. On the contrary, as seen in FIG. 4, when the projectile 200 is separated from the piston 150, the orifices 234 are discovered and allow fire to be transmitted to the bread 210.

Those skilled in the art will understand that the presence of such means 158 prohibiting a bread initiation transmission 210 before the separation of the piston 150 and the projectile 200, and therefore before the projectile 200 leaves the charger, allows the to ensure high safety in combination with shutter 20, high reliability and optimum exploitation of the radiation emitted since the emission of radiation begins after the projectile 200 has been released. The charger according to the present invention offers a high degree of safety because it prevents the implementation of the energy charge 210 as long as the projectile 200 is placed in the tube 100 of the charger. The operation of the device which has just been described is essentially as follows.

At rest, the bread of infrared material 210 is perfectly protected in the socket 110 of the launcher tube 100.

The output of a projectile 200 is prohibited by the flap 20. When an appropriate command is generated, for example following the detection of a threat, the flap 20 is moved to the neutral position. In parallel, the initiator and thence the propulsion charge, placed in the chamber 122, are initiated by the means 12. This charge generates gases which induce the rupture of the flail 126, then the displacement towards the front of the piston 150 and therefore the projectile 200 after shearing the break line 105.

As previously indicated, the seal 152 prohibits any initiation of the lateral surface of the projectile 200.

Furthermore the skirt 158 prohibits initiation of the delay 230. After moving in the launcher tube 100, the piston 150 reaches the ring 130 as seen in Figure 3. Its stroke is then stopped.

By cons as seen in Figure 4 the projectile 200 is propelled out of the launcher. And when the projectile 200 is thus separated from the piston 150, the skirt 158 releases the openings 234. The bread 210 is then initiated by the delay 230 and generates infrared radiation.

The means for confining the piston 150 inside the launcher tube 100 may be subject to different embodiments. These means may be formed of a groove formed in the front part of the launcher tube 100 and intended to receive the seal 152 of the piston 150. These means may also be formed of a part, for example stamped steel which is adapted to cooperate with the aforementioned groove. This piece can either be initially arranged in the groove to form a stop piston 150 or be integral with the piston 150, in which case the piece accompanies the piston 150 in its stroke and stops in the groove when it reaches it .

The means limiting the stroke of the piston 150 may be formed of point deformations towards the inside of the wall of the tube 100 to form a stop to the piston 150. It has been described previously embodiments of the device according to the present invention according to which the piston 150 is confined inside the launcher tube 100 by the ring 130. This ring thus causes the separation of the piston 150 and the projectile 200. According to an alternative embodiment also in accordance with the present invention, it is nevertheless possible to provide a device in which the piston 150 is allowed to exit the launcher tube 100, means being further provided to ensure the separation of the piston 150 and the projectile 200 when the latter exits the launcher tube 100. Such means may for example be formed of means adapted to braking the piston 150 when it reaches the mouth outlet of the launcher tube 100, the projectile 200 continuing its trajectory by inertia .

We will now describe the variant of the means illustrated in Figures 5 and 6, prohibiting the initiation transmission to the payload 210, as a projectile 200 is placed in the charger. According to this variant, the means prohibiting the transmission of initiation to the payload are formed by means designed to delay the initiation of the load and allow this initiation only once the projectile out of the launcher tube.

The variant illustrated in these Figures 5 and 6 has many points in common to the structure illustrated in Figures 1 to 4, in particular as to the general structure of the charger, launching tubes 110 and projectiles. It will therefore not be described in detail later, and the elements of the variant illustrated in FIGS. 5 and 6 which are functionally equivalent to previously described means of the variant illustrated in Figures 1 to 4 carry identical reference numerals in the drawings.

As seen in Figures 5 and 6 attached, a piston 150 equipped with a seal 152, is placed in the bottom of the chamber of each launcher tube 110 adjacent to the base 120.

Each tube 110 is provided near its mouth with a stop means of the associated piston 150.

This stop means can give rise to many embodiments, as indicated above with reference to FIGS. 1 to 4.

The projectile 200 comprises at least one bread (or load) 210 of material capable of generating infrared radiation (or another type of radiation depending on the desired effect) during its combustion. In the context of FIGS. 5 and 6, the means which prohibit an initiation transmission to the bread 210 before the separation of the piston 150 and the projectile 200 consist of initiation means activated during this separation.

Such means can be the subject of many embodiments.

According to a preferred embodiment, these means comprise a wire 300 wound around a primary load 203 of the bread 210. The wire 300 is moreover integrally connected by one of its ends to the piston 150. This wire typically has a diameter a few millimeters. This wire 300 may in particular be provided with roughnesses at least partly on its surface intended to be brought into contact with the primary charge 203.

The primary charge 203 is disposed within a housing 204 included in the projectile 200. Preferably, this housing is located at the rear of the projectile, as shown in Figures 5 and 6 attached, so that the wire 300 is closer to the piston 150. However, it is possible to envisage another implantation within the projectile 200. The operation of the device illustrated in Figures 5 and 6 is essentially as follows.

At rest the projectile 200 is protected as described above with reference to Figures 1 to 4. Its initiation is prohibited. When an appropriate command is generated the projectile is propelled.

And when the projectile 200 is thus separated from the piston 150, the latter being retained, the wire 300 wound around the primary load 203 of the bread 210 takes place because it is integrally held by one of its ends 301 to the piston 150. The unwinding of the wire 300 then causes a phenomenon of friction warming of the primary charge 203 which is lit. This ignition of the primary charge 203 causes itself the initiation of the bread 210, which then generates infrared radiation. Of course, the present invention is not limited to the previously described embodiments, but extends to any variant within its spirit.

In particular, the flap 20 can be associated with other auxiliary safety functions. The flap 20 may for example be associated with switched electrical contacts in the closed state, to allow the activation of the means 12, when the flap is moved to the neutral position. Alternatively, when in the rest position, the flap 20 can act on the charger to mechanically move it or act on switched electrical contacts then in the open state, to prohibit the activation of the initiation .

Claims

1. Device comprising at least one launcher tube (100), an ejectable projectile (200) comprising at least one filler (210) at least partly made of an energetic material placed in the launcher tube (100) and an associated booster means to the launcher tube (100) and adapted to propel said projectile (200), characterized in that it comprises in combination on the one hand means (158, 300) which prohibit an initiation transmission to the load (210) before that the projectile (200) is not released from the launcher tube (100) and secondly a flap (20) which closes at rest the exit of the launcher tube (100) and which can be moved on command to a position neutral in which it releases the output of the launcher tube (100) to then allow the output of the projectile (200).

2. Device according to claim 1, characterized in that it constitutes a charger (10) which comprises a plurality of launching tubes (100) each housing a projectile (200).

3. Device according to one of claims 1 or 2, characterized in that it is suitable for the protection of aircraft by generating infrared radiation.

4. Device according to one of claims 1 to 3, characterized in that the movement of the flap (20) from the rest position to the neutral position is controlled manually.

5. Device according to one of claims 1 to 3, characterized in that the movement of the flap (20) from the rest position to the neutral position is controlled automatically when the implementation is desired.

6. Device according to one of claims 1 to 3 and 5, applied to the protection of aircraft, characterized in that the movement of the flap (20) is controlled when at least one of the following events is detected:

. Powering up by a cockpit,. Minimum speed of the aircraft required,

. Minimum altitude of the aircraft in relation to the ground reached, and. Minimum value of the inclination of the aircraft.

7. Device according to one of claims 1 to 6, characterized in that the means (158) which prohibit an initiation transmission to the load (210) consist of means forming a mechanical screen (158) opposite an initiator associated with the load (210), which mechanical screen (158) is retracted automatically when the projectile (200) leaves the launcher tube (100).

8. Device according to one of claims 1 to 7, characterized in that the means (158) which prohibit an initiation transmission to the load (210) consist of means forming a mechanical screen (158) interposed between a initiator associated with the load (210) and the propellant means, which mechanical screen is automatically retracted when the projectile (200) leaves the launcher tube (100).

9. Device according to one of claims 1 to 8, characterized in that it comprises an initiation delay (230), a piston (150) placed in the launcher tube (100) between said projectile (200) and the propellant means, the launcher tube (100) and the piston (150) comprising means (130) capable of separating the piston (150) and the projectile (200) when the latter projects out of the launcher tube (100), the piston (150) comprising at least one through passage (154) capable of transmitting an initiation between the propellant means and the initiation delay (230) of said projectile (200), as well as means (158) which prohibit a transmission of initiation between the delay (230) and the load (210) before the separation of the piston (150) and the projectile (200).

10. Device according to claim 9, characterized in that it comprises means (158) forming a mechanical screen, integral with the piston (150) and initially placed between the delay (230) and the load (210).

11. Device according to one of claims 1 to 6, characterized in that the means (300) which prohibit an initiation transmission to the load (210) consist of means designed to delay initiation of the charge (210) and allow this initiation only once the projectile (200) out of the launcher tube (110).

12. Device according to one of claims 1 to 6 and 11, characterized in that the means (300) which prohibit an initiation transmission to the load (210) consist of initiation means comprising on the one hand a primary load (203) associated with the payload (210) and secondly a wire (300) or equivalent placed between the primary load (203) and a mass (150), such as a piston, the wire being adapted to be flared when the projectile (200) exits to initiate friction initiation of the primary charge (203).

13. Device according to one of claims 1 to 6, 11 and 12, characterized in that it comprises at least one piston (150) associated with the launcher tube (110) and placed between the projectile (200) and the propellant corresponding, the launcher tube (110) and the piston (150) comprising means adapted to ensure the separation of the piston (150) and the projectile (200) when the latter comes out of the launcher tube (100), the piston (150) being secured to one end of a wire (300) wound around a primary charge (203) of the projectile (200) so that when the piston (150) and the projectile (200) are separated, the wire (300) ) takes place and causes ignition of the primary charge (203) by friction, said primary charge (203) thus initiating the charge (210).

14. Device according to claim 13, characterized in that the wire (300) comprises at least partly a rough surface, part in contact with the primary charge (203).

15. Device according to one of claims 9, 10, 12 or 13, characterized in that the launcher tube (100) and the piston (150) comprise complementary means adapted to prohibit the exit of the piston (150) out of the tube launcher (100).

16. Device according to one of claims 9, 10, 12 or 13, characterized in that the piston (150) is adapted to exit the launcher tube (100) and the cartridge comprises means for separating the piston (150) and the projectile (200) when the latter exits the launcher tube (100).