EP2320190A1 - Device for programming a fuze of a projectile - Google Patents

Abstract

The device (1) has programming bobbins (2) that are integrated to a cylindrical wall (3) of a gap in which a projectile is axially translated. The bobbins are realized under form of elementary bobbins, where the bobbins are provided along multiple lines (11a-11f). The lines are parallel to an axis (10) of the gap. The bobbins of the one of the lines are longitudinally shifted with respect to the bobbins of the other lines. Each bobbin is equipped with a control electronic unit.

Description

The technical field of the invention is that of devices for programming a projectile rocket.

A rocket is an electronic or electromechanical device that controls the firing of the projectile charge explosive.

The rockets can be of chronometric or proximal type or control the operation on impact on a target. They are sometimes multi-mode and can then give the projectile, the choice of the user, an impact or chronometric operation.

Multi-mode or chronometric rockets must be programmed before firing. The programming is for example the choice of the operating mode (multi-mode rocket) and / or the delay between the shooting and the detonation (chronometry information).

Today programming is introduced into the rocket most often by induction by means of programming coils.

The patent US5117733 describes an example of an induction coil for programming medium-sized projectile rockets during the rotation of the projectile in a star feed of a weapon.

This device comprises two coils: a coil that detects the approach of a projectile and a coil that provides the programming of the rocket. When a projectile is detected by the first coil, the second coil is activated and it transmits the programming signal for the rocket.

Such a device thus implements a single programming coil which has a chosen profile so that a portion of the coil is always facing the rocket during part of the movement of progress of the projectile in the feed corridor. of the weapon.

Such a solution is however very disadvantageous from the industrial point of view, because the energy level implemented by this single coil leads to define an electronics of Oversized control for the need. Such electronics are hardly compatible power networks available at a turret of a weapon system.

Moreover, the electromagnetic losses in the weapon structure and the induced radiation are very important.

For integration constraints it may be necessary to ensure the programming of the rocket during a phase in which the projectile translates along its axis. Such a displacement occurs especially during the introduction phase of the projectile in the chamber of the weapon.

The device proposed by US5117733 is not suitable for programming a rocket animated by such a translational movement. Indeed in the structure described by US5117733 the course of the projectile bearing the rocket is a circular path and the rocket is during this course always facing the programming coil with a coil / rocket coupling which is optimal because the receiving coil of the rocket is still substantially opposite the middle zone of the programming coil where the flow is maximum.

If one sets up such a coil in an arc at a portion of a rectilinear corridor, the coupling is correct but due to the translational movement of the projectile, the latter moves away quickly from this coil.

The implementation of US5117733 therefore impose the realization of coils of significant dimensions covering the length of the corridor. Such coils would consume a lot of energy. It then becomes necessary to have several coils in an arc (similar to that described by US5117733 ) and parallel to each other so that the rocket is always facing one of these coils during its translation in front of the coils.

However, this solution would then present other problems.

First of all the structure of such coils is complex. The windings of flat wires and the assembly of ferrites gripped by the turns are difficult to achieve.

Then, the coils arranged side by side show inter-coil areas in which the magnetic field decreases, which affects the efficiency of the programming and the energy load of the rocket.

Finally, the level of energy required to power all the coils simultaneously is important and would lead again to define an oversized control electronics for the need.

The aim of the invention is to overcome such drawbacks by proposing a programming device in which the coils used are inexpensive coils and are arranged and powered so as to ensure optimum coupling with the projectile rocket while limiting the energy needs.

Thus, the subject of the invention is a device for programming a projectile rocket by means of at least one programming coil inductively transmitting a programming signal to a reception means integral with the rocket, a device characterized in that the coils are integral with a substantially cylindrical wall of a corridor in which the projectile translates axially, the coils being made in the form of several elementary coils each surrounding a ferrite core parallel to the axis of the corridor and the coils being distributed along a plurality of lines parallel to the axis of the corridor, the coils of a line being offset longitudinally with respect to the coils of the neighboring line or lines.

Each coil is more particularly connected to an electronic control means which ensures the simultaneous supply of all the coils arranged in a given plane perpendicular to the axis of the corridor, the coils of the different planes being supplied successively as the advance of the projectile in the corridor, the coils located in the same plane being fed when the rocket of the projectile is positioned in the vicinity of said plane.

According to a first embodiment, the two lines of lateral coils (lines which comprise only a neighboring line) are not offset longitudinally with respect to each other, all the other lines of coils arranged between these lateral lines being progressively shifted with a given pitch and following the direction of advance of the projectile.

According to a second embodiment, the coil lines are generally divided into two groups offset longitudinally with respect to each other, the lines of each group alternating with the lines of the other group.

Advantageously, the device will comprise at least a first position sensor connected to the electronic control means, sensor for determining the position of the rocket relative to the coils during the advance of the projectile.

The first position sensor may be disposed in a first housing interposed between two lines of coils and at an entrance end of the corridor.

The first position sensor may also be coupled to at least one second position sensor connected to the electronic control means, the second sensor for determining the speed of advance of the projectile in the corridor.

The second position sensor may be disposed in a second housing interposed between two lines of coils and at an exit end of the corridor.

The electronic control means may comprise a power stage comprising amplifiers each supplying one or more coils and a control stage controlling the different amplifiers, the control stage also ensuring the opening of a contactor interposed between a power supply. in power and the power stage when no signal is transmitted to the amplifiers.

• la figure 1 est une vue schématique et en perspective d'un dispositif de programmation selon un mode de réalisation de l'invention,
• la figure 2 est un schéma montrant le positionnement relatif d'un projectile et du dispositif de programmation selon l'invention,
• la figure 3 schématise un moyen de commande mis en oeuvre avec le dispositif selon l'invention,
• les figures 4a et 4b montrent suivant deux vues orthogonales une bobine élémentaire mise en oeuvre dans un dispositif selon l'invention,
• la figure 5 montre une répartition des bobines selon un premier mode de réalisation de l'invention,
• la figure 6 montre une répartition des bobines selon un deuxième mode de réalisation de l'invention.

The invention will be better understood on reading the following description of various embodiments, a description given with reference to the appended drawings and in which:

• the figure 1 is a schematic and perspective view of a programming device according to an embodiment of the invention,
• the figure 2 is a diagram showing the relative positioning of a projectile and the programming device according to the invention,
• the figure 3 schematizes a control means implemented with the device according to the invention,
• the Figures 4a and 4b show according to two orthogonal views an elementary coil implemented in a device according to the invention,
• the figure 5 shows a distribution of the coils according to a first embodiment of the invention,
• the figure 6 shows a distribution of the coils according to a second embodiment of the invention.

The figure 1 shows a device 1 for programming a projectile rocket which uses programming coils 2 which inductively transmit a programming signal to a receiving means integral with the rocket of the projectile (not shown in this figure).

The different coils 2 are integral with a substantially cylindrical wall 3 which is integral with a corridor of the weapon in which the projectile translates axially.

Such corridors are usually in the vicinity of the weapon chamber. The translational movement of a projectile along its axis usually occurs shortly before the introduction of the projectile into said chamber.

We have shown figure 2 a side view of the device 1 and is positioned a projectile 4 having at its warhead a fuse 5 incorporating a receiving means 6 of the programming signal, such as a receiver coil. The receiver coil could also be located at the base of the projectile or at the base of a shell of the ammunition (especially for the programming of large caliber ammunition, that is to say of a caliber greater than or equal to 90mm).

The Figures 4a and 4b show in an enlarged manner the structure of a coil 2 implemented in the device according to the invention. Such a coil 2 comprises a U-shaped ferrite core 7 around which is wound a conductor 8 which will be connected to an electronic control means. The particular shape of the ferrite core 7 defines the two poles 7a and 7b of the coil. The field lines 9 which will be generated by the coil extend from one pole 7a to the other pole 7b. Such coils are standard commercial components that are available for a wide variety of sizes (eg 25mm x 12mm x 12mm). They are usually used for the realization of electrical transformers.

According to a characteristic of the invention, the programming device uses a plurality of elementary coils in which the ferrite cores 7 are all parallel to the axis 10 of the corridor, which is also the axis along which the projectile 4 progresses along the direction F.

The coils 2 are also distributed along several lines 11 (11a ... 11i ... 11j ...) which are parallel to the axis 10 of the corridor.

According to the embodiment which is represented here ( figure 2 ), the device comprises six parallel lines 11a, 11b, 11c, 11d, 11e and 11f which each comprise five coils 2. The device therefore comprises thirty elementary coils 2.

With such an arrangement it becomes possible to optimally distribute the power of the programming signal between the different coils.

It is indeed useless to feed the coils disposed near the output 1b of the device when the projectile 4 is in the vicinity of the input 1a (and vice versa).

Each coil 2 is thus connected to an electronic control means which ensures the simultaneous supply of all the coils disposed in the same plane 12 which is perpendicular to the axis 10 of the corridor and which passes through the receiving means 6 integral with the rocket 5 of the projectile.

Depending on the configuration adopted, such a plan contains one or more coils.

It is thus ensured to use only the coils 2 best positioned to supply the rocket 5 and also limits the energy consumed.

To be able to feed only the coils best positioned relative to the rocket 5 it is necessary to identify the relative position of the rocket 5 and the coils.

For this, the proposed device implements a first position sensor 13a which is connected to the electronic control means. This sensor is positioned near the entrance end of the corridor. This position sensor may be associated with a projectile advance speed sensor which may be located upstream of the corridor.

It will also be possible to provide two position sensors arranged at the entrance of the corridor and offset axially with respect to each other. Such a solution, however, requires a sufficiently long corridor.

In the case where the projectile 4 is provided with a base rocket (and not a warhead rocket as shown in the figures) there may also be a second position sensor 13b disposed in the vicinity of the outlet. This sensor will detect the passage of the projectile ogive near the exit. At this time the base rocket is not yet disposed in the vicinity of the coils and the programming has not yet been done.

The measurement of the moment of entry of the warhead in the corridor associated with the measurement of the moment of exit of this warhead out of the corridor will make it possible to determine the speed of advance of the projectile and to control the sequence of supply of the different coils 2.

Alternatively, one can also use the output measurement of the ogive to stop the programming and optimize the energy delivered. This detection device provides the enormous advantage of being able to program the rocket projectile regardless of the speed of passage of the latter in front of the programmer.

As a variant, it will be advantageous to have a plurality of position sensors 13a and 13b disposed in the same plane at the entrance and exit of the corridor. These sensors will be mounted in parallel to each other. This will ensure a redundancy of the detection means which will secure device. The figure 1 thus shows three position sensors 13a and three position sensors 13b.

The offset of the lines 11 of the coils makes it easy to accommodate these three sensors in the spaces arranged by the offset.

The configuration proposed by the invention in which elementary coils of relatively small size and distributed along lines 11 are used makes it possible to guarantee a good coupling between the coil 2 and the reception means 6.

Indeed, when the coils located in the same plane 12i are fed, the receiving means 6 is in the vicinity of the central zone separating the two poles of the coil, therefore the zone in which the field is maximum.

Such a solution is more advantageous than that which consists in producing a single extended coil for a whole line. The coupling would then be optimal only at a middle part of the corridor while the energy required by the coil would be stronger.

The figure 3 schematically a control means 14 for controlling the different coils 2.

This control means 14 comprises a power stage consisting of amplifiers 15 ₁ 15 ₃₀ (an amplifier by coil 2) and a control stage 16 consisting of a programmable computer, e.g., a preprogrammed component (for clarity of the figure only a few amplifiers and some coils are shown).

The control means 14 also comprises a power supply stage 17 (for example a battery) which powers the various amplifiers 15 _{i as} well as the control stage 16.

In a conventional manner, the control stage 16 incorporates a clock 18 and one or more memories 19. It also receives the signals supplied by the position sensor (s) 13a, 13b and is connected to a turret computer (which provides the elements to be programmed) or directly to a programming interface 20 (a keyboard for example) by which a user enters the desired value (s) for the programming of the rockets.

The control stage 16 will be able to drive each amplifier 15 _{i individually} . In a manner conventional in the field of, for example, the control of audio amplifiers, the control of an amplification stage will consist in applying to the latter a signal σ _i of variable frequency and amplitude.

The variation of the amplitude of each signal σ _i will make it possible to drive the amplitude of the output signal of the amplifier 15 _i between a minimum value (zero) and a maximum value which is the maximum value provided by the sizing of the amplifier. 'amplifier.

The programming of the data is obtained by driving the signal σ _i in all or nothing respecting the binary coding proposed by the STANAG 4547 (NATO standard). The rocket will of course incorporate a demodulation stage for rendering the received programming.

An algorithm stored in the control stage 16 will make it possible to determine which value to give at each instant for each signal σ _i as a function of the programming given by the interface 20 which is desired and according to the location of the rocket. 5 of the projectile relative to each coil (or coil plane 12 _i ), which location is determined by the first position sensor 13a and the speed determining means (stored speed value 19 or measured value supplied by another sensor, such as the second sensor 13b).

According to another characteristic of the invention a contactor 21 is interposed between the power supply 17 and the different amplifiers 15 _i . This contactor is controlled by the control stage 16 so as to ensure power supply of the various amplifiers 15 _i only when a transmission is actually provided. Such an arrangement avoids excessive heating of all amplifiers standby and reduces energy consumption. Whether or not the latter are powered by a control signal, the signal of power is in principle always applied and it would result in a warm-up.

The control signal σ _i applied to each amplifier will also be of variable intensity depending on the location of the rocket 5 relative to the coil plane 12 _i considered. It is indeed unnecessary to feed the coils located at a distance from the plane 12 _i in which the rocket is located at a given instant. The information provided by the position sensors 13a and 13b is used to determine which coils to feed at a given time.

Alternatively, an amplifier 15 _i could also feed several coils connected in parallel (the coils located in the same plane 12 _i ).

A method of progressive control of the coils in correlation with the advance of a projectile is described in the patent application FR08-06484 tabled on November 18, 2008 and will be referred to for more details. According to this patent the supply of each coil is provided by control slots or by ramps of increasing intensity with the approach of the coil and decreasing with the removal of the coil.

We see on the figure 2 that the different coils disposed on the same line 11 _i are in contact at their poles. There is therefore when feeding the coils an inter coil area in which the magnetic field is lower.

According to another characteristic of the invention, the coils of a line 11 _i are offset longitudinally with respect to the coils of the neighboring line or lines.

The figure 5 thus shows a device according to a first embodiment of the invention in which the lines 11 _i of coils 2 are generally distributed in two groups offset longitudinally with respect to each other, the lines of each group alternating with the lines from the other group.

A first group consists of the coils of lines 11a, 11c and 11e. A second group consists of the coils of lines 11b, 11d and 11f.

The second group is offset longitudinally relative to the first by a distance δ substantially equal to half the length of an elementary coil 2.

Thus the coils of each group are arranged opposite the inter-coil spaces of the other group. This ensures a better distribution of the programming flow during the advance of the projectile in the corridor.

This is particularly important for optimizing energy coupling when the programming device also provides power to the rocket electronics.

We have shown on the figure 5 the different planes 12 _i which are fed successively as and the projectile advance in the corridor.

According to this embodiment, each plane comprises three different coils. Thus the plane 12 ₁ comprises the first coils of the lines 11b, 11d and 11f.

The device thus comprises ten successive parallel planes of 3 coils each.

This embodiment constitutes the optimal configuration. Indeed, each plane has the same number of coils and the signal therefore has a substantially constant power when moving the projectile from one plane to another.

As the projectile 4 progresses along the wall 3 of the corridor, the control means 14 will ensure the successive supply of all the coils located in the same plane 12 _i passing through the rocket 5 of the projectile 4 The control means 14 thus firstly feeds the first coils of the plane 12 ₁ and then that of the first coils of the plane 12 ₂ and so on until the last coils of the plane 12 ₁₀ .

It can be seen in the figure that the offset of the lines 11 _i makes it easy to house the sensors 13a and 13b between two adjacent lines. This limits the axial size of the programming device and facilitates its integration into a power system.

The figure 6 shows another embodiment of the invention in which the two lines of lateral coils 11a and 11f, ie the lines which comprise only one adjacent line, are not offset longitudinally with respect to the other.

All the other lines which are arranged between these two lateral lines (ie the lines 11b, 11c, 11e and 11f) are on the other hand gradually and regularly staggered with a pitch λ, given and in the direction of advance of the projectile .

Different planes 12 _{i are} thus materialized, which will comprise, as the case may be, one or two coils. The plans comprising two coils are the planes which combine two coils of the lateral lines 11a and 11f. Other plans include only one coil of a given line.

It can be seen in the figure that there are thus 25 parallel planes (12 ₁ to 12 ₂₅ ) and that there are four successive planes comprising only one coil between two planes comprising two coils. Such a configuration is slightly more bulky axially. However, it makes it possible to reduce the energy radiated (and consumed by the device). It reduces the number of coils that are powered at a given instant (one or two coils).

This embodiment also makes it possible to delimit housing to set up the position sensors 13a and 13b.

Claims (9)

Device (1) for programming a projectile fuze (5) by means of at least one programming coil (2) inductively transmitting a programming signal to a reception means (6) integral with the fuse, characterized in that the coils (2) are integral with a substantially cylindrical wall (3) of a corridor in which the projectile (4) translates axially, the coils being made in the form of a plurality of elementary coils each surrounding a core of ferrite parallel to the axis of the corridor and the coils being distributed along several lines (11a ... 11f) parallel to the axis (10) of the corridor, the coils of a line being offset longitudinally relative to the coils of the neighboring line or lines. Programming device according to claim 1, characterized in that each coil (2) is connected to an electronic control means (14) which ensures the simultaneous supply of all the coils (2) arranged in a given plane (12 _i ) perpendicular to the axis (10) of the corridor, the coils of the different planes being fed successively as the projectile advances in the corridor, the coils (2) located in the same plane (12 _i ) being fed when the rocket of the projectile is positioned in the vicinity of said plane. Programming device according to one of claims 1 or 2, characterized in that the two lines of lateral coils (11a, 11f) (lines which comprise only a neighboring line) are not offset longitudinally with respect to the other, all the other lines (11b ... 11e) of coils disposed between these lateral lines being gradually shifted with a given pitch (λ) and in the direction of advance of the projectile. Programming device according to one of claims 1 or 2, characterized in that the lines (11a ... 11f) of coils (2) are generally distributed in two groups offset longitudinally with respect to one another, the lines of each group alternating with the lines of the other group. Programming device according to one of claims 3 or 4, characterized in that it comprises at least a first position sensor (13a) connected to the electronic control means (14), which sensor makes it possible to determine the position of the rocket relative to the coils during the advance of the projectile. Programming device according to Claim 5, characterized in that the first position sensor (13a) is arranged in a first housing interposed between two lines (11i, 11j) of coils and at an input end (1a) of the corridor. Programming device according to one of claims 5 or 6, characterized in that the first position sensor (13a) is coupled to at least one second position sensor (13b) connected to the electronic control means (14), the second sensor enabling determine the speed of advance of the projectile in the corridor. Programming device according to claim 7 characterized in that the second position sensor (13b) is disposed in a second housing interposed between two lines of coils and at an outlet end (1b) of the corridor. Programming device according to claim 2 characterized in that the electronic control means (14) comprises a power stage comprising amplifiers (15 _{1 ... 1} 5 ₃₀ ) each supplying one or more coils and a control stage (16 ) controlling the different amplifiers (15 _i ), the control stage also ensuring the opening of a contactor (21) interposed between a power supply (17) and the power stage when no signal is transmitted to the amplifiers (15 _i ).

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