EP2569591A1

EP2569591A1 - Guided munition protected by an aerodynamic cap

Info

Publication number: EP2569591A1
Application number: EP11719013A
Authority: EP
Inventors: Patrick Cohe; Fabien Moreau
Original assignee: TDA Armements SAS
Current assignee: TDA Armements SAS
Priority date: 2010-05-12
Filing date: 2011-05-11
Publication date: 2013-03-20
Also published as: FR2960055B1; US20130193264A1; JP2013530367A; IL222976A0; WO2011141527A1; FR2960055A1

Abstract

The invention relates to guided munitions intended to destroy a target after at least a flight phase followed by a target approach phase. The munition comprises a munition body (10) of cylindrical shape with longitudinal axis ZZ' having, at a front end Eav of the munition which is the end intended to be directed towards the target, a front body (14) comprising an optic (26) of a device that guides said munition onto the target, a cap (20) for protecting the optic, secured to the munition body (10), characterized in that the protective cap (20) comprises at least one recess (60, 120) containing a pyrotechnic device (130, 132, 183, 184) intended to destroy said protective cap (20) to free the optic and make the munition guidance device operational during the target approach phase. Application: steered or guided munitions such as those of the rocket or projectile type, or missiles.

Description

GUIDED MUNITION PROTECTED BY AERODYNAMIC COIFFE

The invention relates to guided munitions comprising a protective cap of a device for guiding the munition towards a target to be destroyed.

Guided or piloted munitions, such as those of the rocket or projectile type or missiles, are equipped with optical and electronic guidance systems to ensure, after a flight phase followed by a target approach phase, high reliability. and impact accuracy of the ammunition on the target.

For example, the piloting of certain types of missiles or guided rockets is done using a laser beam. An optical missile detects the laser beam illuminating the target and a missile calculator determines the flight parameters to reach the target.

Generally, the guidance optics located at the front end of the missile, or the ammunition driven in a general case, that is to say at the end of the munition which is directed towards the target, comprises a cap protection, on the one hand, to protect the optical guiding impacts by bodies present in the air during the flight phase and, secondly, to prevent a rise in temperature of the missile control electronics associated with the optical guidance by aerodynamic friction of the head (or nose) of the ammunition.

This cap can thus protect the guiding optics of the ammunition, depending on the case, during a firing phase, for example, when crossing a seal; during a ballistic phase, in the case of a rocket or projectile; during a cruise phase, in the case of missiles. In the state of the art of guided munitions, either the guiding optics is directly exposed to the impacts due to bodies present in the air and aerodynamic friction, or, it is protected by a detachable cap, to the approach of the target, the body of the ammunition which involves a risk of damage to the empennage deployed at the rear of the rocket or missile by the protective cap detached from the body of the ammunition. In order to overcome the drawbacks of the state-of-the-art piloted munitions, the invention proposes a piloted munition intended to destroy a target after at least one flight phase followed by a target approach phase, said munition comprising a munition body of cylindrical shape with a longitudinal axis ZZ 'having, on the side of a front end Eav of the munition intended to be directed towards the target, a front body comprising an optics of a device for guiding said munition towards the target, a protection cap of the optics attached to the ammunition body,

characterized in that the protective cap, in the form of a warhead with an axis of revolution XX 'coincides with the longitudinal axis ZZ', consisting of a material capable of being sprayed in multiple fragments comprises at least one recess forming at least one cell containing a pyrotechnic device for providing a propulsive energy directly on the walls of the recess for spraying the protective cap into multiple fragments in order to release the optics and make operational the guide device of the ammunition during the approach phase of the target.

Advantageously, the protective cap comprises walls having embrittlement grooves to favor rupture zones of said walls during the destruction of the protective cap.

In one embodiment, the piloted munition comprises, between the protective cap and the front body of the munition body, a shield for protecting the optics of the guiding device.

In another embodiment, the protective shield comprises a cylindrical circular rounded shield body having two main faces and a circular edge of axis coaxial with the longitudinal axis ZZ ', the rounded shape of the shield body conforming to the shape of the surface of the front body of the ammunition body.

In another embodiment, the driven munition comprises a ring for clamping the protective cap on the ammunition body, the ring of clamping having, on the side of the front end Eav of the munition, a circular edge of tapered shape.

In another embodiment, the surface of the front body, of rounded shape, is without discontinuity and without asperities so as to have a continuous aerodynamic profile.

In another embodiment, the front body of the munition body comprises, on the side of the front end Eav, a front body portion of circular cylindrical shape of diameter D1, with an axis of revolution collinear with the longitudinal axis ZZ ', the front body portion having a rounded munition front body wall including the optics of the guide device, the roundness of the front ammunition body wall being directed toward the front end Eav to achieve a continuous aerodynamic shape ammunition when it lacks the protective cap.

In another embodiment, the protective cap, in the form of an ogive, with an axis of revolution XX ', has a first recess opening on a second recess of circular cylindrical shape with a diameter equal to the diameter D1 of the front body portion of the ammunition body, the first recess of the cap forming with the front body wall, of rounded shape, centered on the longitudinal axis ZZ ', a first cell having the protective shield. In another embodiment, the pyrotechnic device comprises a propellant charge and an igniter, the igniter having electrical contacts for its activation.

In another embodiment, the first cell comprises the pyrotechnic device.

In another embodiment, the protective shield comprises, close to its circular edge, a support of the igniter in a plane parallel to the longitudinal axis ZZ ', the support of the igniter acting as a spoiler for generating a force transversal when subjected to aerodynamic forces during the destruction of the cap, and unbalance in the case of a munition turning on itself.

In another embodiment, the protective cap further comprises, on the side of the front end Eav, a third cylindrical recess of axis collinear with the longitudinal axis ZZ 'separated from the first recess by a partition wall in a plane perpendicular to the longitudinal axis ZZ ', the third recess being closed by a tip to form a second cell containing the pyrotechnic device for destroying the protective cap.

In another embodiment, the protective shield comprises, close to its circular edge, a spoiler intended to generate a transverse force on the shield body when it is subjected to aerodynamic forces and ensure its ejection from the body of the munition, said spoiler also acting unbalance in the case of a munition turning on itself.

In another embodiment, the protective cap has a cap connection portion extending through a cap end ring having a cap edge of diameter D5 greater than the outer diameter D4 of the cap connecting portion to form a first cap portion. cap shoulder for locking the cap in translation, along the longitudinal axis ZZ ', on the front body of the munition body by the clamping ring.

In another embodiment, the munition comprises two layers of electrical conductors for activating the igniter:

a first ply having one end adhered to one of the main faces of the shield, on the side of the front body of the ammunition body, a central portion glued to the other main face of the shield on the side of the first recess of the cap, the other end of the first ply, in the first cell being electrically connected to the electrical contacts for activating the igniter, the passage of the first ply of a face main to the other shield being made through a groove on the edge of said shield,

a second ply of electrical conductors, on the side of the ammunition body, in electrical contact with the end of the first ply on the same side of the front body of the ammunition body.

In another embodiment, the front body portion extends towards the rear body of the munition by an intermediate body of circular cylindrical shape of the same axis of revolution ZZ 'and of diameter D2 greater than the diameter D1 of the front body portion to form a first body shoulder, the intermediate body extending through the rear body of the munition, of diameter D3 larger than the diameter D2 of said intermediate body, to form a second body shoulder. In another embodiment, the protective cap, secured to the body of the munition by the clamping ring, comprises a central part of conical cap or ogive extending, on the side of its largest diameter, by a connecting portion with the round cylindrical body of the ammunition body, of external diameter D4 less than the diameter D2 of the intermediate body, the cap connecting portion being extended by a cap end ring having a cap edge of diameter D5 greater than the diameter. external D4 of the cap connecting portion and less than the diameter D2 of the intermediate body so as to form a first shoulder of the cap for locking the cap in translation.

In another embodiment, the cap edge and the first body shoulder each comprise a respective hole for the insertion of an angular setting pin of the cap and the ammunition body, the inner wall of the first recess of the cap comprising a tooth inserted in the groove located on the circular edge of the protective shield, the angular wedge pin and the tooth inserted in the groove of the protective shield ensuring the electrical contact between the two layers and the orientation of the spoiler of said protective shield in an advantageous clearance angle. In another embodiment, the cap comprises a series of longitudinal weakening grooves on the walls of the first and second recesses, distributed regularly about the axis of revolution XX 'of the cap, the cap further comprising a groove of weakening circular around the periphery of its outer surface at a distance from the cap edge such that said circular weakening groove is at the tapered end of the clamping ring when the cap is mounted on the munition body. In another embodiment, the cap comprises, in addition, another circular weakening groove around the inner surface of the cap formed by the wall of the second recess, at a distance from the cap edge such that said other groove of embrittlement is at the end, of diameter D1, of the front body part of the side of the front body wall, when the cap is mounted on the ammunition body, the axis XX 'of the protective cap being then coincident with the longitudinal axis ZZ 'of the munition.

The invention will be better understood with the aid of an exemplary embodiment of a guided munition according to the invention, in the particular case where this munition is a rocket, with reference to the indexed drawings in which:

- Figure 1 shows a partial view in axial section of an embodiment of a guided rocket according to the invention;

- Figure 2a shows a partial sectional view of a protective cap of the rocket of Figure 1;

- Figure 2b a partial perspective view of the cap of the figure

1;

- Figure 2c, a detail view of the cap showing embrittlement grooves;

FIG. 3a shows a perspective view of the rocket body of FIG. 1 comprising a protective shield;

FIG. 3b shows the protective shield alone of the rocket body of FIG. 3a;

FIG. 4a shows the rocket of FIG. 1 after destruction of the cap and before ejection of the protective shield; FIG. 4b shows the rocket of FIG. 1 after destruction of the cap and after ejection of the shield;

- Figure 5 shows an alternative embodiment of the rocket of Figure 1 according to the invention;

- Figure 6 shows a perspective view of the rocket body of Figure 5 having a shield.

FIG. 1 shows a partial view in axial section of an exemplary embodiment of a guided rocket according to the invention.

More specifically, Figure 1 shows a partial sectional view of the front end Eav of a guided rocket according to the invention. The front end Eav of the rocket is the one that is directed towards the target at the launch of the rocket (head or nose of the rocket) and which, therefore, has an aerodynamic shape for optimal penetration into the air. The other end of the rocket not shown in the figures is the rear end of the rocket usually having a tail.

The rocket of FIG. 1, of circular cylindrical shape, of longitudinal axis ZZ ', essentially comprises:

a rocket body 10 having a front body 14 and a rear body 16 essentially forming the rocket body 10,

- On the side of the front body 14 of the rocket, a protective cap 20 shaped warhead axis of revolution XX ',

a clamping ring 22 of the protective cap 20 on the rocket body 10,

- Between the protective cap 20 and the front body 14, a protective shield 24 of an optics 26 in the front body 14 of the rocket, an auto director of the rocket, not shown in the figures.

The front body 14 of the rocket has, on the side of the front end Eav a front body portion 28 of circular cylindrical shape of diameter D1, an axis of revolution collinear with the longitudinal axis ZZ '. The front body portion 28 extends towards the rear body 16 of the rocket by an intermediate body 30 of circular cylindrical shape of the same axis of revolution ZZ 'and of diameter D2 greater than the diameter D1 of the front body portion 28, to form a first body shoulder 32. The intermediate body 30 is extended by the rear body 16 of the rocket, diameter D3 greater than the diameter D2 of said intermediate body 30, to form a second body shoulder 34.

FIG. 2a shows a partial sectional view of the protective cap 20 of the rocket of FIG. 1, FIG. 2b a partial perspective view of the cap of FIG. 1, and FIG. 2c a detailed view A of FIG. the cap showing weakening grooves.

The protective cap 20, secured to the rocket body 10 by the clamping ring 22 (see FIG. 1) comprises a central part 40 of a conical or ogival-shaped cap extending towards its larger diameter by a connecting part of the cap 42 to rocket body 10 of circular cylindrical shape, of external diameter D4 less than the diameter D2 of the intermediate body 30.

The cap connecting portion 42 is extended by a cap end ring 50 having a cap edge 52 of diameter D5 greater than the outer diameter D4 of the cap connecting portion 42 and smaller than the diameter D2 of the intermediate body 30 of the cap. so as to form a first cap shoulder 54 intended to block the cap 20 in translation on the front body 14 of the rocket by the clamping ring 22, along the longitudinal axis ZZ '.

The protective cap 20 further comprises a first recess 60 opening out to a second recess 62 of circular cylindrical shape with a diameter equal to the diameter D1 of the front body portion 28 of the rocket.

The protective cap 20 and the part of the front body 28 inserted into the second recess 62 of diameter D1 are in contact, on the one hand, with their respective circular cylindrical inner surface of the cap 20 and outer of the front body part. 28.

The clamping ring 22 (see FIG. 1) coaxial with the longitudinal axis ZZ 'has two ends, one end of tapered shape, on the side of the front end Eav, and another end on the rocket body side, a surface outer portion 80 forming a portion of the outer surface of the rocket and inner circular cylindrical surfaces.

The clamping ring further comprises: - On the side of the end of the body of the rocket, a first internal surface 82 for clamping the clamping ring 22 on the circular cylindrical surface of diameter D2 of the intermediate portion 30 of the rocket body 10. The clamping ring 22 is held in a fixed position of the rocket body 10 by known clamping means,

- On the side of its tapered end, a second circular cylindrical inner surface 90 coaxial with the axis ZZ 'of the same diameter D4 of the cap connecting portion 42 and slidable on said cap connecting portion 42.

The internal surface 90 of the clamping ring 22 of diameter D4 is connected via a first ring shoulder 94 to a third circular cylindrical inner surface 96 coaxial with the axis ZZ ', then, by a second shoulder of ring 98, at the first internal surface 82 of clamping.

The cap 20 is held in a transverse position on the part of the front body 28 of the rocket body 10, in the one and the other direction along the axis ZZ ', by the clamping ring 22, the first collar shoulder 94 being in abutment with the first cap shoulder 54 and the cap edge 52 abutting the first body shoulder 32.

The first recess 60 of the cap 20 forms with a front body wall 1 10 of rounded shape centered on the longitudinal axis ZZ 'of the end of the front body 14 (see Figure 1), a first cell 104 comprising the shield of 24. The rounding of the front body wall 110 is directed towards the front end Eav to obtain an aerodynamic shape of the rocket when it lacks the protective cap and the shield.

The protective cap 20 further comprises, on the side of the front end Eav, a third recess 120 (see FIG. 2) of cylindrical shape with an axis collinear with the longitudinal axis XX "separated from the first recess 60 by a wall separation device 124 in a plane perpendicular to the longitudinal axis XX 'The third recess 120, opening on the side of the front end Eav of the rocket, is closed by a point 126 to form with the third recess 120 a second recess 128 containing, according to a main feature of the rocket guided according to the invention, a pyrotechnic device for destroying the protective cap 20. In the embodiment of FIG. 1, the pyrotechnic device essentially comprises a propellant charge 130 and an igniter 132 comprising electrical contacts 162 for its activation.

The tip 126 is rounded at its end to obtain the desired aerodynamic shape of the protective cap 20.

The cap 20 has a series of longitudinal weakening grooves 140 on the walls of the first 60 and second 62 recesses (see Figures 2a and 2b). These longitudinal grooves are regularly distributed around the axis of revolution XX 'of the cap.

The cap 20 further comprises a circular embrittlement groove 144 on the periphery of its outer surface at a distance from the cap edge 52 such that said circular weakening groove 144 is at the tapered end of the ring. when the cap is mounted on the rocket body 10. The cap comprises, in addition, another circular weakening groove 145 around the inner surface of the cap formed by the wall of the second recess 62, at a distance of distance from the cap edge 52 such that said other weakening groove 145 is at the end, of diameter D1, of the portion of the front body 28 of the side of the front body wall 1 10, when the cap 20 is mounted on the rocket body 10. The axis XX 'of the protective cap 20 is then coincident with the longitudinal axis ZZ' of the rocket.

The series of longitudinal weakening grooves 140 and the circular embrittlement grooves 144, 145 on the walls of the cap 20 serve to facilitate the degradation of the cap, at the time of operation of the pyrotechnic charge 130, thus clearing the periphery of the shield 24. This degradation of the protective cap extends from the other circular weakening groove 145 to the end of the front body portion 28 of diameter D1, on the side of the front body wall 1 10, until to the circular weakening groove 144 at the level of the tapered edge of the clamping ring 22.

FIG. 3a shows a perspective view of the rocket body of FIG. 1 comprising the protective shield. Figure 3b shows the protective shield only of the rocket body of Figure 3a The protective shield 24 comprises a shield body 25 of round cylindrical circular shape having two main faces, a rounded circular edge 27 and close to the circular edge 27 of the shield a spoiler 150. The protective shield is designed so that its shape circular cylindrical round of the shield marries the shape of the front body 14 of the rocket (see Figures 1, 3a and 3b).

The spoiler 150 of the protective shield 24 is intended to generate a transverse force when it is subjected to the aerodynamic forces during the destruction of the cap 20. This transverse force ensures a lateral ejection of the shield 24 and releases the optics 26 of the director rocket.

The shield may be made of metal or plastic material resistant to the effects of the pyrotechnic charge.

In the embodiment of the rocket of FIG. 1, the cap 20 comprises a hole 158 for fixing the igniter 132 in the partition wall 124 of the first 60 and third 120 recesses of the cap, to initiate the propellant charge 130 in the second cell 128 of the rocket.

The rocket comprises two layers of electrical conductors intended to activate the igniter 132 (see FIG. 1):

a first ply 160 having one end glued to one of the main faces of the shield 24, on the side of the rocket front body, a central portion glued to the other main face of the shield 24 on the side of the first recess 60 of the cap 20. The other end of the first ply 160 in the first cell 104 is electrically connected to the electrical contacts 162 for activating the igniter 132. The passage of the first ply 160 from one main face to the other of the shield 24 made through a groove 29 on the edge of said shield 24.

a second ply 170 of electrical conductors, on the rocket body 10 side, is in electrical contact with the end of the first ply 160 of the same side of the rocket front body.

A contact pressure between the two plies 160, 170 is exerted by a presser 172 housed in a recess in the front body 14 of the rocket having a passage 173 for connecting this second ply 170 to an activation electronics, not shown in the figures. , the igniter 132. The first 160 and the second 170 electrical layers are in the same axial plane passing through the longitudinal axis ZZ 'so that they are in electrical contact. For this purpose, the cap edge 52 and the first body shoulder 32 each comprise a respective hole for the insertion of an angular setting pin 174 of the cap 20 and the rocket body 10. In addition, the inner wall of the first obviously 60 of the cap 20 has a tooth 146 inserted into the groove 29 located on the circular edge 27 of the protective shield 24. The angular setting pin 174 and the tooth 146 inserted in the groove 29 of the protective shield ensure the electrical contact between the two plies 160, 170 and the orientation of the spoiler 150 of the protective shield in an advantageous clearance angle.

In the case of a rocket rotating on itself, the spoiler 150 subjected to centrifugal force would create an unbalance and strengthen the transverse component that tends to eject the shield 24.

FIG. 4a shows the rocket of FIG. 1 after destruction of the cap 20 and before ejection of the protective shield 24 and FIG. 4b after ejection of the shield. After the ejection of the shield 24, the optics 26 of the homing device is clear of any obstacle and forms the new rounded aerodynamic profile of the rocket. It should be noted that this new profile, suitable for the pilot guidance phase, is continuous and smooth.

Figure 5 shows an alternative embodiment of the rocket of Figure 1 according to the invention.

In this variant of Figure 5 the first recess 60 comprise a shield 180 and, in the first cell 104 formed by the first recess 60 and said shield 180, a propellant charge 183 and an igniter 184 secured to the shield 180. The second cell 128 is empty.

Figure 6 shows a perspective view of the rocket body of Figure 5 having a shield.

The protective shield 180 comprises a shield body 188 of rounded cylindrical shape matching the rounded shape of the front body 14 of the rocket and, on the circular edge 189 of the shield 180, a support 190 of the igniter 184 in a plane parallel to the longitudinal axis ZZ '.

The support 190 has a fixing hole 192 for the igniter 184 which is electrically connected to the first 160 and second 170 layers of electrical conductors.

In this variant, the propellant charge 183 and the igniter 184 are near the shield 180.

As in the first embodiment of FIG. 1, the support element 190 of the igniter 184 of the shield 180 serves as a spoiler intended to generate a transverse force when it is subjected to aerodynamic forces during the destruction of the cap 20 protection, and unbalance in the case of a rocket turning on itself.

The advantage of this variant of Figure 5 is to simplify the protective cap 20, and ensure an ejection with the shield, on one side of the rocket, the metal remains of the pyrotechnic device with the fragments of the cap after its destruction.

In another variant embodiment of the rockets of FIGS. 1 and 5, the cap 20 comprises only a pyrotechnic charge activated by a pyrotechnic cord in place of the layers 160, 170 of electrical conductors. This other variant avoids the use of an igniter near the propellant charge and the expulsion during the destruction of the cap of the metal components that can damage the extended empennage of the rocket.

The nose of the rocket, or ammunition in the general case, includes optical and electronic equipment which, taking into account a long approach phase of the target and a supersonic speed, must be protected by the protective cap. For this purpose, the material used to make the protective cap is selected from ceramic materials or other sintered materials that have the property of not driving or very weakly in the mechanical structure of the rocket the calories due to the friction of the 'air. In addition, the mechanical characteristics of ceramic materials make it easy to spray (friable / brittle), either by detonation, depending on the type of pyrotechnic device chosen.

With suitable materials, this invention could be used in a mortar or gun type system.

The configuration of the protective shield in the munition according to the invention makes it possible to protect the optics (for example a lens) of the guiding device during the flight of the munition until the ejection of the shield but also during the storage phases, logistics and the rest of the operational phase (tactical).

This invention also makes it possible to radically change the aerodynamic profile of the guided munition, in our case from an ogival shape to a hemispherical shape.

Claims

1. A piloted ammunition for destroying a target after at least one flight phase followed by a target approach phase, said munition comprising a cylindrical ammunition body (10) having a longitudinal axis ZZ 'having, on the d-side a front end Eav of the ammunition intended to be directed towards the target, a front body (14) comprising an optic (26) of a device for guiding said ammunition towards the target, a cap (20) for protecting the target optical integral with the munition body (10),

characterized in that the protective cap (20), in the form of a warhead with an axis of revolution XX 'coinciding with the longitudinal axis ZZ', consisting of a material capable of being sprayed in multiple fragments comprises at least a recess (60, 120) forming at least one cell (104, 128) containing a pyrotechnic device (130, 132, 183, 184) for supplying a propulsive energy directly to the walls of the recess (60, 120) for spraying the protective cap in multiple fragments to release the optics and make operational the guidance device of the ammunition during the approach phase of the target.

2. Piloted munition according to claim 1, characterized in that the protective cap (20) comprises walls having embrittlement grooves (140, 144, 145) to favor rupture zones of said walls during the destruction of the cap (20) protection.

3. Piloted munition according to one of claims 1 or 2, characterized in that it comprises, between the protective cap (20) and the front body (14) of the ammunition body (10), a shield (24, 180) for protecting the optics (26) of the guiding device.

4. Piloted munition according to claim 3, characterized in that the shield (24) of protection comprises a shield body (25) of cylindrical circular round shape having two main faces and a circular edge (27) of axis coaxial with the 'longitudinal axis ZZ', the rounded shape of the shield body conforming to the shape of the front body surface (14) of the ammunition body.

5. Piloted munition according to one of claims 1 to 4, characterized in that it comprises a clamping ring (22) of the cap (20) of protection on the ammunition body (10), the clamping ring ( 22) having, on the side of the front end Eav of the munition, a circular edge of tapered shape.

6. Piloted munition according to one of claims 1 to 5, characterized in that the surface of the front body (14), of rounded shape, is without discontinuity and without asperities so as to have a continuous aerodynamic profile.

7. Piloted munition according to one of claims 1 to 6, characterized in that the front body (14) of the ammunition body comprises, on the side of the front end Eav, a front body portion (28) of cylindrical shape circular circular diameter D1, axis of revolution collinear with the longitudinal axis ZZ ', the front body portion (28) having a front body wall (1 10) of rounded munition including the optics (26) of guiding device, the rounding of the front body wall (1 10) of ammunition being directed towards the front end Eav to obtain a continuous aerodynamic shape of the ammunition when it is devoid of the protective cap (20).

8. Piloted munition according to claim 7, characterized in that the cap (20) of ogival-shaped protection, axis of revolution XX ', has a first recess (60) opening on a second recess (62). circular cylindrical shape of diameter equal to the diameter D1 of the front body portion (28) of the munition, the first recess (60) of the cap (20) forming with the front body wall (1 10), rounded shape , centered on the longitudinal axis ZZ ', a first cell (104) having the protective shield (24, 180).

9. Piloted munition according to claim 1 to 8, characterized in that the pyrotechnic device comprises a propellant charge (130, 183) and an igniter (132, 184), the igniter having electrical contacts (162) for its activation .

10. Piloted munition according to claim 9, characterized in that the first cell (104) comprises the pyrotechnic device (183, 184).

1 1. Controlled munition according to one of claims 9 or 10, characterized in that the shield (180) of protection comprises, near its circular edge (189) a support (190) of the igniter (184) in a parallel plane to the longitudinal axis ZZ ', the support of the igniter acting as a spoiler for generating a transverse force when subjected to aerodynamic forces during the destruction of the cap 20, and unbalance in the case of a ammunition turning on itself.

12. Piloted munition according to one of claims 8 or 9, characterized in that the cap (20) of protection further comprises, on the side of the front end Eav, a third recess (120) of cylindrical shape of axis collinear with the longitudinal axis ZZ 'separated from the first recess (60) by a partition wall (124) in a plane perpendicular to the longitudinal axis ZZ', the third recess (120) being closed by a point (126) to form a second cell (128) containing the pyrotechnic device (130, 132) for destroying the protective cap (20).

Piloted ammunition according to claim 4, characterized in that the shield (24) has, close to its circular edge (27), a spoiler (150) for generating a transverse force on the shield body (25). ) when subjected to aerodynamic forces and ensure its ejection of the body of the ammunition, said spoiler also acting unbalance in the case of a munition rotating on itself.

14. Piloted munition according to one of claims 1 to 13, characterized in that the protective cap (20) comprises a portion of cap connection (42) extending through a cap end ring (50) having a cap edge (52) of diameter D5 greater than the outer diameter D4 of the cap connecting portion (42) to form a first shoulder cap (54) for locking the cap (20) in translation, along the longitudinal axis ZZ ', on the front body (14) of the munition body (10) by the clamping ring (22).

15. Piloted munition according to claim 9, characterized in that it comprises two plies (160, 170) of electrical conductors for activating the igniter (132):

a first ply (160) having one end adhered to one of the main faces of the shield (24), on the side of the front body of the ammunition body, a central portion glued to the other main face of the shield (24) on the side of the shield; first recess (60) of the cap (20), the other end of the first sheet (160), in the first cell (104) being electrically connected to the electrical contacts (162) for activating the igniter (132) passing the first web (160) from one major face to the other of the shield (24) through a groove (29) on the edge of said shield (24),

a second ply (170) of electrical conductors, on the side of the munition body (10), in electrical contact with the end of the first ply (160) on the same side of the front body of the ammunition body.

16. Piloted munition according to one of claims 7 to 15, characterized in that the front body portion (28) extends towards the rear body (16) of the munition by an intermediate body (30) of circular cylindrical shape of same axis of revolution ZZ 'and of diameter D2 larger than the diameter D1 of the front body portion (28), to form a first body shoulder (32), the intermediate body (30) extending through the rear body ( 16) of the munition, of diameter D3 greater than the diameter D2 of said intermediate body (30), to form a second body shoulder (34).

17. Piloted munition according to claim 16, characterized in that the protective cap (20), integral with the body of the munition (10) by the clamping ring (22) has a tapered or arcuate cone-shaped central portion (40) extending on its larger diameter side by a cap connection portion (42) to the ammunition body (10) of circular cylindrical shape, of external diameter D4 less than the diameter D2 of the intermediate body (30), the cap connecting portion (42) being extended by a cap end ring (50) having a cap edge (52) of diameter D5 greater than the outer diameter D4 of the cap connection part (42) and less than the diameter D2 of the intermediate body (30) so as to form a first cap shoulder (54) intended to block the cap 20 in translation.

18. Piloted munition according to claim 17, characterized in that the cap edge (52) and the first body shoulder (32) each comprise a respective hole for the insertion of a pin (174) angular wedge of the cap (20) and the munition body (10), the inner wall of the first recess (60) of the cap (20) having a tooth (146) inserted in the groove (29) on the circular edge (27) of the protection shield (24), the angular wedge pin (174) and the tooth (146) inserted in the groove (29) of the protective shield ensuring the electrical contact between the two layers (160, 170) and the orientation of the spoiler (150) of said protective shield in an advantageous clearance angle.

Piloted munition according to claim 18, characterized in that the cap (20) has a series of longitudinal weakening grooves (140) on the walls of the first (60) and second (62) recesses, distributed regularly around the axis of revolution XX 'of the cap, the cap (20) further comprising a circular embrittlement groove (144) on the periphery of its outer surface at a distance from the cap edge (52) such that said groove Circular embrittlement (144) is at the tapered end of the clamping ring (22) when the cap is mounted on the munition body (10).

Piloted ammunition according to claim 19, characterized in that the cap (20) furthermore has another circular weakening groove (145) on the periphery of the inner surface of the cap formed by the wall of the second recess (62), at a distance from the cap edge (52) such that said other weakening groove (145) is at the end, of diameter D1, of the part of the front body (28). ) on the side of the front body wall (1 10), when the cap (20) is mounted on the ammunition body (10), the axis XX 'of the protective cap (20) being then merged with the longitudinal axis ZZ 'of the munition.