EP0918205A1 - Projectile having radial direction of action - Google Patents

Abstract

The shell contains a charge (9) which operates at an angle (7) to the direction of travel (8). The shell is fitted with rocket jets (41) which can either spin or slow the shell down as it approaches the target area. The shell is fitted with an infrared sensor (6) which scans to the side of the direction of travel (12). When a target is detected the spinning charge is discharged at the target by ejecting backwards from the shell case resulting in an even slower rate of forward travel.

Description

The technical field of the invention is that of projectiles, in particular anti-shooters, acting radially from their target.

Known projectiles include a military head explosive, generally with a nucleating charge, of which initiation is triggered by the detection of a target at by means of a sensor.

The sensors usually used are of technology infrared or radar. Usually these projectiles have means for controlling their roll position so as to keep their load oriented in the direction desired.

Patent FR2406800 thus describes a projectile provided with a load formed with radial action. The downside of such projectile is that it is necessary to provide means complex ensuring its roll control so that the charge can hit a target. These means of control do can only be ordered after processing of target detection provided by a high-performance warhead sensor, sensor able to detect the target in particular before passing over it by the projectile.

It would also be possible to define a projectile in which the military head would be stabilized in roll so as to always be oriented in a vertical direction.

In addition to the complexity of such orientation control, a stabilization in roll of the military head will lead also a decrease in the area of effectiveness of the projectile, which will then have to practically fly over its target to be able to attack him.

In particular, it is not possible with such projectiles to attack a target arranged in an orientation different, for example a low-flying helicopter located at above or laterally to the projectile.

It is the object of the invention to propose a projectile allowing to overcome such drawbacks.

The projectile according to the invention therefore has an area efficiency and can, in a simple way and without impair flight stability, ensure detection and destruction of a target placed on the ground or possibly at above him or laterally.

Thus, the subject of the invention is a projectile, in particular an anti-tank missile projectile and comprising at least one payload combining at least one explosive military head and at least one target sensor, military head having a direction of action inclined relative to the axis of the projectile and whose initiation is triggered as a result of detection of a target by the sensor, the latter having a direction of observation close to the direction of action, projectile characterized in that it comprises means for scanning to ensure for the payload at a instant on trajectory, a ratio of speed longitudinal V on the speed of rotation Ω which is less than or equal to a limit value so as to ensure a sweep of the ground by the direction of observation with a step sufficiently reduced to allow detection of the target.

The limit value will advantageously be chosen equal to 3 m.

According to an essential characteristic of the invention, the scanning means include a device for increase the speed of rotation of the payload to a instant on trajectory and / or a device ensuring the payload translational braking.

According to a first embodiment, the device allowing to increase the load rotation speed useful comprises at least one pyrotechnic impeller whose direction of action is oriented so that it causes a rotation of the payload around its axis.

According to a second embodiment, the device for translational braking comprises at least one impeller pyrotechnics, the direction of action for all impellers being substantially confused with the axis of the payload.

According to another embodiment, the device for translational braking includes a means of increasing the aerodynamic drag of the payload.

According to a third embodiment, the payload is a submunition ejected from the projectile on its trajectory, under ammunition carrying a braking device and / or a device for rotating relative to the projectile.

The payload may be integral with the projectile which includes a braking device and / or a rotation.

The projectile may include a proximity rocket intended to trigger the scanning means on approach of a target.

The projectile may also include means for chronometry intended to trigger the scanning means a some time after firing the projectile.

The projectile may finally include a receiver of a remote control signal, signal intended to trigger the scanning means.

• la figure 1a représente schématiquement en coupe longitudinale un projectile suivant un premier mode de réalisation de l'invention,
• la figure 1b est une coupe transversale de ce projectile suivant le plan repéré AA sur la figure 1a,
• la figure 2a montre la mise en oeuvre du projectile suivant ce premier mode de réalisation,
• la figure 2b est une représentation de la trace au sol de la direction d'observation,
• la figure 3 est une coupe longitudinale schématique d'un projectile suivant un deuxième mode de réalisation de l'invention,
• la figure 4 montre la mise en oeuvre du projectile suivant ce deuxième mode de réalisation,
• la figure 5a est une coupe longitudinale schématique d'un projectile suivant un troisième mode de réalisation de l'invention,
• la figure 5b est une coupe transversale de ce projectile suivant le plan repéré BB sur la figure 5a,
• les figures 6a et 6b montrent deux étapes successives de la mise en oeuvre du projectile suivant ce troisième mode de réalisation,
• la figure 7 représente une sous munition suivant une variante de ce troisième mode de réalisation.

The invention will be better understood on reading the description which follows of several embodiments, description made with reference to the appended drawings and in which:

• FIG. 1a schematically represents in longitudinal section a projectile according to a first embodiment of the invention,
• FIG. 1b is a cross section of this projectile along the plane marked AA in FIG. 1a,
• FIG. 2a shows the implementation of the projectile according to this first embodiment,
• FIG. 2b is a representation of the trace on the ground of the direction of observation,
• FIG. 3 is a schematic longitudinal section of a projectile according to a second embodiment of the invention,
• FIG. 4 shows the implementation of the projectile according to this second embodiment,
• FIG. 5a is a schematic longitudinal section of a projectile according to a third embodiment of the invention,
• FIG. 5b is a cross section of this projectile along the plane marked BB in FIG. 5a,
• FIGS. 6a and 6b show two successive stages in the implementation of the projectile according to this third embodiment,
• Figure 7 shows a submunition according to a variant of this third embodiment.

Referring to Figures 1a and 1b, a projectile 1 according to a first embodiment comprises an envelope 2 containing a payload 3 and extended at its part rear with deployable tail 4.

The payload essentially comprises a head explosive military 5 and a target sensor 6.

The military head has an inclined direction of action 7 relative to the axis 8 of the projectile. This direction here is substantially perpendicular to the axis 8 of the projectile.

The military head is a nucleus-generating charge comprising in a known manner, an explosive charge 9 placed in a containment envelope 11, loading on which a coating 10 is applied.

Sensor 6 is an infrared sensor operating in the range of 3 to 5 micrometers for example it is arranged at neighborhood of a window 13, transparent to infrared and arranged in the envelope 2 of the projectile. Sensor 6 has a observation direction 12 which is parallel to the direction of action 7 of the load.

Envelope 2 of the projectile also contains a unit computer 14 which receives the signals supplied by a clock 15 and by the sensor 6. This calculation unit is intended for control, on the one hand the triggering of a device pyrotechnic 16 allowing the speed of rotation of the projectile (and its payload) and other part of causing the initiation of the explosive charge 9.

To this end, the calculation unit is linked by a first connection 17 to an igniter 18 which ignites a gas pyrotechnic generator 19.

It is also connected by a second connection 20 to a primer 21 intended to initiate the explosive charge 9.

The pyrotechnic device 16 is also visible on the sectional view of Figure 1b. The gas generator 19 is connected by radial pipes 22a, 22b to nozzles gas ejection 23a, 23b. These nozzles are oriented by relative to the shell 2 of the projectile so as to eject the gas in two directions 24a and 24b which are symmetrical relative to the axis 8 of the projectile and in a plane perpendicular to this one. The effect of the gases generated by the generator 19 will therefore rotate the projectile and its payload around its axis 8.

The operation of this projectile will now be described with reference to Figures 2a and 2b.

An infantryman 25 is equipped with a recoilless fire system 26 for launching a projectile 1 according to the invention.

This firing system will be conventionally equipped with a laser rangefinder (not shown) for determining the distance D1 separating the shooter from a target, such as a tank 27a or a helicopter 27b (here D1 is the average distance).

Distance measurement allows to introduce into the unit computation 14 a programming of the instant of triggering of the gas generator 19.

The firing line secured to the launcher 26 contains in different memories or registers the characteristics ballistic of the projectile (initial speed, coefficient of ballistic train), characteristics introduced in the form firing tables. She deduces from these tables, depending on the distance D1 at which the target is located, an instant to which the gas generator 19 must be initiated so that the projectile is rotated at a distance D from the shooter.

D will be chosen less than D1 by a few meters (about 15 m) to ensure stabilization of the new rotation regime before approaching or overflying the target.

This instant of initiation is introduced into the unity of calculation 14 in the form of a flight time of the projectile.

When the projectile fire is triggered, a sensor (not shown, for example an accelerometer) detects the shoot. The calculation unit 14 then takes into account the signals provided by the clock 15 to continuously determine the duration of flight of the projectile.

The projectile is animated at its exit from the launcher 26 of a moderate speed (around 10 t / s) which allows to ensure its stability on the trajectory. This rotation is obtained in a conventional manner by bending the fins of the tail 4.

When the scheduled flight time has elapsed, the unit 14 calculates the ignition of the gas generator 19.

This is dimensioned so as to cause a increased speed of rotation of projectile 1 around of its axis 8.

The speed increase should be such that the ratio V / Ω of the longitudinal velocity V of the projectile on its rotation speed Ω is less than or equal to a value limit so as to ensure a sweep of the ground by the direction of observation with a step (P) sufficiently reduced to allow target detection.

The limit value (called scanning step) will be generally chosen equal to 3 m so as to ensure at least two scans of a land target such as a tank.

A person skilled in the art will easily size the generator. gas allowing to communicate to a projectile having a speed V given in the vicinity of its effective range a rotation speed Ω which will ensure the scanning step wish.

Figures 2a and 2b show traces 28 of observation direction 12 intersections with the ground or a target plan.

The combination of the speed of rotation Ω and the axial velocity V of the projectile gives direction observation 12 a helical trajectory.

Traces 28 are substantially straight for a projectile whose direction of observation 12 is perpendicular to the axis of projectile 8 (as shown here). They would be hyperbolic if the direction of observation was tilted towards the front of the projectile.

Thanks to the invention, the pitch P is sufficiently reduced to ensuring the detection of an appropriate target such as a tank.

When sensor 6 detects a target whose signature infrared corresponds to that stored in the unit computation 14, the latter causes the initiation of the primer 21 and the military head shot 5.

The latter's direction of fire 7 being substantially parallel to the direction of observation, the nucleus generated by the charge will be projected towards the detected target.

The projectile's rotational movement ensures scanning by the direction of observation 12 of all the space around the projectile.

It is therefore possible to detect not only a target terrestrial 27a overflown by the projectile following a direction XX '(fig 2b), but also a target 27a which would located laterally with respect to a flight direction YY ' for the projectile (fig 2b).

As a result, compared to known projectiles, the direction of observation is fixed, an increase in the area effectiveness of the projectile which can detect and attack targets that it doesn't exactly fly over.

The projectile can also detect and attack a aerial target such as a helicopter 27b. The calculation unit 14 will advantageously contain in memory the characteristics infrared of the different targets that the projectile is likely to attack. It will then be possible to program before firing the type of target sought (tank or helicopter), in this case the calculation unit will not cause the firing of the charge only when a detected target will match actually to the desired target.

Advantageously, means will be provided ensuring the non taking into account the signals delivered by the sensor 6 during the flight time of the projectile up to distance D. This in order to avoid false target detection.

It will suffice for this to give the computing unit 14 a appropriate programming prohibiting any processing of signals for a given duration, that calculated by the fire control and corresponding to the course of distance D by the projectile.

The invention therefore makes it possible, with a relatively structure simple to define a multi-purpose projectile (anti-tank or anti helicopter).

As a variant, it is possible to cause the setting in rotation of the projectile, not following the flow of a programmed flight time, but as a result of the detection of approaching a target of given characteristics.

In this case, a proximity detector will be provided, for example of radar, infrared, acoustic or magnetometric, arranged in the projectile warhead (instead of and place of the clock marked 15 in FIG. 1a) and capable of detect the approach of a target at a distance of the order of 15 m.

The calculation unit will use the signal supplied by this detector to initiate the initiation of the gas generator 19.

It is also possible to provide a means of remote control from the trigger firing system 25 of the gas generator 19.

In this case, a signal transmitter (of laser or radio optical technology) on the firing system and an appropriate receiver will be placed in the projectile.

The fire control will then determine the optimal moment of triggering by measuring the distance from the target and the target at which the projectile is located.

It will send the projectile an order to fire the gas generator when the distance between projectile and target will have the desired value.

It is also possible to use as a means of scanning a pyrotechnic impeller which does not have a gas generator but explosives. Such impellers explosives are well known to those skilled in the art and are described for example by patents FR2552871 and FR2590973, whose content relating to the description of the impellers to explosives is included here by reference.

In the embodiments described above, the projectile is provided with scanning means which allow to ensure for the payload, at a given time on trajectory, a ratio of the longitudinal speed V to the rotation speed Ω which is less than or equal to one limit value.

These scanning means are constituted by a device pyrotechnic 16 for rotation which includes a gas generator 19 allowing, for a speed longitudinal V given, to increase the speed of rotation Ω of the projectile. We thus obtain a V / Ω ratio which is lower than the limit scan step value P chosen.

It is possible to design a projectile for which will not modify the rotation speed Ω but it will reduce the longitudinal speed V to ensure a V / Ω ratio lower than the limit value.

In this case the scanning means will be constituted by a braking device.

FIG. 3 describes such an embodiment of the projectile according to the invention.

This projectile differs from that previously described in this that it has at its rear part in place of the pyrotechnic device for rotating a device 39 in translational braking.

This device comprises a pyrotechnic composition gas generator 37 initiated by an igniter 38 connected to the calculation unit 14 by a connection 33.

The rest of the internal projectile payload 3 is identical to that of the projectile previously described. The projectile therefore contains an explosive military head 5, a target sensor 6, a computing unit 14 and a clock 15.

The gases generated by composition 37 are directed by pipes 40 to ejection nozzles 41 regularly distributed radially and arranged in the envelope 2 of the projectile. These nozzles have axes which materialize directions of ejection 42, inclined relative to the axis 8 of the projectile, and oriented towards the front of the latter.

The result of the braking forces generated by each of the nozzles coincides with the axis 8 of the projectile.

The calculation unit 14 will cause at the desired time ignition of the gas generator 37 which will have the effect of braking the longitudinal speed V of the projectile.

The operation of this projectile will now be described with reference to Figure 4.

Projectile 1 is again fired by a firing system without recoil 26 implemented by an infantryman.

The calculation unit is programmed by the infantryman to from data supplied by the fire control (not shown).

Projectile 1 is then fired, it is animated during firing with a longitudinal speed of the order of 200 m / s and with a rotation speed of the order of 35 t / s.

When the projectile is at distance D programmed, the calculation unit causes the initiation of the gas generator 37. The axial speed of the projectile decreases about 50% and approaches 100 m / s. This results in a V / Ω ratio which becomes lower than the limit P allowing sweep the ground by the observation direction with a sufficiently small pitch to allow detection of the target.

The advantage of this embodiment is that the translational braking device does not use any moving part and therefore has excellent reliability.

As a variant it is of course there again possible to have a detector in the warhead proximity switch which will automatically trigger the braking of the projectile when approaching a target.

It is also possible to provide a remote control for the braking device from the firing system 26.

It is possible to provide other types of means of translational braking, for example means ensuring a increased aerodynamic drag of the projectile. We could for example provide a parachute which will be released at a instant given on trajectory. The parachute will be fixed free rotating relative to the projectile so as not to brake the rotation of this one.

Figures 5a and 5b show a projectile in a third embodiment.

This mode differs from the previous ones in that the payload 3 consists of an ejectable submunition outside the envelope 2 of the projectile 1 at a given time on path.

The casing 2 of the projectile 1 thus comprises a part rear cylindrical 2a and a front ogivated part 2b which contains a chronometric rocket 43 connected to a charge of unloading 44.

The stripping charge is isolated from the submunition 3 by a piston 45. The submunition is made integral by rotation of the casing by pins (not shown) which will be sheared when ejected.

The rear part of the envelope 2a is closed by a bottom 46 bearing the tail 4.

The submunition 3 comprises a case 47 closed by two covers 48 and 49. Case 47 contains a military head explosive 5 as well as a target sensor 6. Again, head military and sensor respectively have directions of action and detection substantially perpendicular to axis 8 of the projectile which coincides with the axis of the sub ammunition.

The submunition 3 also contains a calculation unit 14 which receives the signals supplied by the sensor 6 and which commands the initiation of the detonator 21 of the military head 5 and the igniter 18 of a pyrotechnic gas generator 19.

The calculation unit is also connected to a sensor acceleration 50 which is intended to detect the instant ejecting the submunition from the envelope 2.

The gas generator 19 is also visible in section at Figure 5b. It is structurally analogous to that described previously with reference to Figures 1a, 1b.

Thus it has radial tubes 22a, 22b connecting the pyrotechnic composition 19 to gas ejection nozzles 23a, 23b. These nozzles are oriented relative to the envelope 47 of submunition 3 so as to eject the following gases two directions 24a and 24b which are symmetrical with respect to axis 8 of the projectile and submunition and in a plane perpendicular to this one. The effect of the gases generated by the generator 19 will therefore rotate the submunition around its axis 8.

Figures 6a and 6b show two successive phases of the operation of this particular embodiment.

The projectile is fired by a non-weapon system shown and rocket 43 received (as for the modes of previous productions) a program such as the initiation of the decanting composition 44 takes place at a distance D from the shooter less than the distance D1 shooter / target.

The gas pressure of the stripping composition is exerted on the piston 45 which pushes the submunition 3 in the direction of what causes the shearing of pins for retaining the bottom 46 of the projectile.

The submunition 3 therefore separates from the envelope 2 of the projectile (fig 6a). It continues its trajectory longitudinal with a speed V in the same direction as that that she previously had inside the projectile and substantially the same value (the mass of the submunition being much higher than that of the envelope 2 carrying the rocket 43).

Acceleration sensor 50 detects acceleration ejecting the submunition which has the effect to initialize the operation of the computing unit 14 which, after a fixed delay that it has in memory, will cause ignition of the gas generator 19 (fig 6b).

The submunition is then animated with a speed of upper rotation.

The speed increase will again be chosen such that the V / Ω ratio of the longitudinal speed V of the sub ammunition on its rotation speed Ω is less than or equal at a limit value P so as to ensure a sweep of the ground by the direction of observation 12 with a step (P) sufficiently small to allow detection of the target 27a.

This embodiment can, like the previous ones, ensure detection of aerial targets such as helicopters.

The advantage of using one or more submunitions is that the roll damping of the submunition (s) is weaker than that of the complete projectile. It results in maintaining a high Ω for the payload.

Another advantage of such an embodiment is that it allows by the use of several submunitions to increase the area of effectiveness of the projectile.

Again, as a variant, it is possible to replace the chronometric rocket 43 with a rocket of proximity which will detect the approach of a target of given characteristics and which will cause the ejection of the ammunition on approach to this target.

It is also possible to provide means allowing to remote control the ejection of the submunition to a moment desired by the shooter.

Finally it is possible to vary the V / Ω ratio by playing not on the rotation speed of the submunition but on its longitudinal speed V.

Figure 7 shows the implementation of a submunition 3 according to such an alternative embodiment.

This submunition (shown here after its ejection outside the projectile shell) differs from the previous one in that it comprises at its rear part a housing 51 to the interior of which is disposed a deployable parachute 52.

The submunition 3 is rotated and in translation by the projectile thanks to pins shearable (not shown).

After its ejection it is therefore still animated of a rotation speed substantially equal to that of the projectile.

Parachute 52 is automatically deployed when ejection as a result of aerodynamic forces. We will be able to possibly to promote and accelerate the extraction of parachute have a tearable link between it. and the bottom 46 which closes the projectile.

This link (not shown) will be chosen sufficiently fragile to break as soon as the bottom begins to exert a pull on him. This avoids any interference between the bottom and the parachute deployed.

The parachute 52 is connected to the submunition by a means link 53 which leaves the submunition free to rotate, for example a fixed axis relative to the submunition and on which turns a ring secured to the parachute.

With this particular embodiment, the unit of calculation does not control the deployment of the braking means aerodynamic. This braking means is deployed automatically after the deposition of the submunition, itself triggered at the appropriate time by the rocket chronometric of the projectile.

The submunition always contains a sensor acceleration 50 which detects the unloading instant and which initializes the calculation unit which is then operational.

With this embodiment the speed V is slowed down which ensures a lower V / Ω ratio or equal to the desired limit value.

It is of course possible to combine the different previously described embodiments and define a projectile comprising both axial braking means (projectile or submunition) and means allowing the increase of the rotation speed (from projectile or submunition).

All the projectile embodiments described in the present application were with reference to a shot by a recoilless weapon system.

It is of course possible to define a projectile according to the invention which can be drawn from another type weapon system including a tank gun.

It is also possible to define a projectile comprising several military heads and several sensors target or projectile whose military head is a charge generating bursts in a direction of action particular.

Claims (10)

Projectile (1), in particular an anti-tank missile projectile and comprising at least one payload (3) combining at least one explosive military head (5) and at least one target sensor (6), military head having a direction of action (7) inclined relative to the axis (8) of the projectile and the initiation of which is triggered following the detection of a target by the sensor (6), the latter having an observation direction (12) close to direction of action, projectile characterized in that it comprises scanning means (16, 39, 52) making it possible to ensure, for the payload, at a given instant on the trajectory, a ratio of the longitudinal speed V over the rotation speed Ω which is less than or equal to a limit value so as to ensure a sweep of the ground by the direction of observation (12) with a sufficiently reduced pitch to allow detection of the target. Projectile according to claim 1, characterized in that the scanning means comprise a device (16) allowing to increase the load rotation speed useful at a given time on trajectory and / or a device (39,52) ensuring the translational braking of the load useful. Projectile according to claim 2, characterized in that the device for increasing the speed of payload rotation includes at least one impeller pyrotechnic (19) whose direction of action (24a, 24b) is oriented so that it causes rotation of the payload around its axis (8). Projectile according to one of claims 2 or 3, characterized in that the braking device in translation comprises means (52) for increasing the aerodynamic payload drag. Projectile according to one of claims 2 or 3, characterized in that the braking device in translation includes at least one pyrotechnic impeller (37), the direction of action of all the impellers being substantially coincident with the axis (8) of the load useful. Projectile according to one of Claims 2 to 5, characterized in that the payload (3) is a submunition ejected from the projectile on trajectory, under ammunition carrying a braking device and / or a setting device in rotation relative to the projectile. Projectile according to one of Claims 2 to 5, characterized in that the payload (3) is integral with the projectile which includes a braking device and / or a rotation device. Projectile according to one of Claims 1 to 7, characterized in that it includes a proximity rocket (15) intended to trigger the scanning means on approach of a target. Projectile according to one of Claims 1 to 7, characterized in that it includes chronometric means intended to trigger the scanning means for a certain time after firing the projectile. Projectile according to one of Claims 1 to 7, characterized in that it includes a receiver of a signal remote control, signal intended to trigger the means of scanning.

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