EP2913628B1 - Fusée d'ogive de projectile d'artillerie comportant un dispositif de freinage en translation - Google Patents

Fusée d'ogive de projectile d'artillerie comportant un dispositif de freinage en translation Download PDF

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Publication number
EP2913628B1
EP2913628B1 EP15152942.7A EP15152942A EP2913628B1 EP 2913628 B1 EP2913628 B1 EP 2913628B1 EP 15152942 A EP15152942 A EP 15152942A EP 2913628 B1 EP2913628 B1 EP 2913628B1
Authority
EP
European Patent Office
Prior art keywords
flap
fuze
flaps
notch
rocket
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP15152942.7A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2913628A1 (fr
Inventor
Nicolas Eches
Catherine Manuel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nexter Munitions SA
Original Assignee
Nexter Munitions SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Nexter Munitions SA filed Critical Nexter Munitions SA
Priority to PL15152942T priority Critical patent/PL2913628T3/pl
Publication of EP2913628A1 publication Critical patent/EP2913628A1/fr
Application granted granted Critical
Publication of EP2913628B1 publication Critical patent/EP2913628B1/fr
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Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/50—Brake flaps, e.g. inflatable

Definitions

  • the technical field of the invention is that of artillery projectile warhead rockets that incorporate a translational braking device to increase the aerodynamic drag of the projectile.
  • Rockets with ogive braking can increase the accuracy of artillery fire by taking into account dispersions due to variations in the initial velocity of the projectile. In fact, it is then possible to point the weapon so as to fire farther than the target, a firing line measures the actual speed of the projectile at the exit of the barrel of the weapon and a braking command is then transmitted to the projectile so as to reduce its range and thus bring it to the desired point of impact.
  • the flaps of the rocket described by the EP1045221 each comprise two closed grooves substantially parallel to a direction perpendicular to the axis of the rocket, each groove cooperating with a rod which is fixed relative to the rocket. Thus the flaps are translated radially.
  • Each flap comprises a notch which partially surrounds an axial support of the rocket, each flap thus has a U-shape.
  • This architecture makes it possible to obtain an increased mechanical resistance of the shutters to the aerodynamic forces while ensuring a symmetry of perfect deployment.
  • the subject of the invention is an ogive rocket for a gyro-stabilized artillery projectile, a rocket incorporating a translational braking device comprising at least two radially deployable flaps on a trajectory so as to increase the aerodynamic drag of the projectile, each flap comprising at least two closed grooves substantially parallel to a direction perpendicular to the axis of the rocket, each groove cooperating with a rod which is fixed relative to a body of the rocket, grooves disposed on either side of a notch which is intended to allow the positioning of the flap in the folded position around a central part of the body of the rocket, rocket characterized in that the notch of each flap comprises end nozzles which are engaged in fingerprints of complementary shapes which are carried by a holding part connected to the rocket.
  • the holding piece may comprise an internal medial portion which is engaged in the notch of a flap in the folded position, the middle portion which is extended by two wings, each wing having a cavity receiving one of the flaps of the flap.
  • the holding part may comprise a circular outer profile which will extend the outer profile of the shutter.
  • the rocket may comprise three regularly angularly distributed flaps, three rods also regularly distributed angularly guiding the various flaps, each rod also ensuring the maintenance of a holding part.
  • each flap can be housed in a groove of the body of the rocket groove which is delimited by partitions or surfaces of the body which are parallel to each other.
  • At least one partition has a clearance allowing the passage of a pin carried by a flap disposed on one side of said partition, pin which engages in a notch carried by another flap disposed of the other side of said partition.
  • an artillery projectile 1 is provided at its rear portion with a belt 2 intended to take the stripes of a weapon tube (not shown) and to seal the propellant gases when firing the projectile .
  • This projectile carries at its front part a rocket 3 according to the invention, rocket which is intended in a conventional manner and according to the type of projectile considered (explosive projectile or cargo projectile) to provide either the initiation of an explosive charge disposed inside the projectile, or the ignition of a gas-generating charge for ejecting a payload arranged inside the trajectory of the projectile.
  • the rocket comprises an electronic control device 4 which causes the initiation of a pyrotechnic charge 5 (which is depending on the case a detonation relay or a gas generator).
  • this rocket 3 also incorporates a device for braking in translation 6 enabling the radial deployment on the trajectory of braking flaps 7.
  • the deployment of the flaps 7 is controlled by the electronic control device 4 in response to an order received. on trajectory via a receiver 8 or developed by the electronic control device 4 as a result of a pre-shooting program, or else that is modified in the first moments after firing to take into account the initial speed the projectile.
  • the trajectory programming will be provided via the receiver 8 which may be radar technology.
  • the figure 2 shows this rocket in more detail.
  • the pyrotechnic charge 5 is disposed in a cup secured to the body and communicates through a priming channel 10 with an initiating component 11 (primer or igniter) with electrical release, which is itself connected to the electronic device order 4.
  • the initiation component 11 is carried by a movable flap 12 of a safety and arming device (not shown).
  • the body 13 of the rocket comprises at a front part three annular grooves 17a, 17b and 17c which are delimited by three parallel partitions 15a, 15b and 15c as well as by a rear annular bearing surface 16 of the body 13.
  • the grooves extend radially to a central portion 14 of the substantially cylindrical body and which is traversed by the channel 10.
  • the upper partition 15a receives an upper portion of the rocket enclosing the electronic device 4.
  • the annular grooves 17a, 17b, 17c receive the braking device 6 which comprises three flaps 7.
  • the braking device 6 which comprises three flaps 7.
  • three flaps 7 of identical shapes are integral with the body 13. These flaps are marked 7a, 7b and 7c on figures 3 , 4 and 6 to distinguish them from each other.
  • Each flap is capable of translating in a plane perpendicular to the axis 20 of the projectile. It is guided in its translation by two cylindrical rods 21 which are fixed (here only one rod 21b is visible). Each rod is disposed between the upper wall 15a and a hole 18 carried by the rear portion of the body 13. The rods 21 are all parallel to the axis 20 of the projectile and the rocket. They are forced into the holes 18.
  • the figure 3 shows the distribution of the rods 21.
  • Three rods 21a, 21b and 21c are provided and distributed angularly in a regular manner around the axis 20 of the rocket (equidistant from the axis 20 and with an angle of 120 ° between each position).
  • Each rod 21 is cylindrical and cooperates with four coaxial holes drilled in the three partitions 15a to 15c and only in the body 13 (the latter hole is marked 18 in the figures).
  • Each flap 7a, 7b and 7c comprises two closed grooves 22 and 23 generally parallel to a direction 24 perpendicular to the axis 20 of the projectile.
  • the grooves 22 and 23 and the direction 24 are marked on the figures 2 and 3 by the designations 22a, 22b, 22c, 23a, 23b, 23c and 24a, 24b, 24c to distinguish the flaps and their structural and geometric elements relative to each other.
  • the upper flap 7a has two grooves 22a, 23a parallel to a direction 24a.
  • the median flap 7b has two grooves 22b, 23b parallel to a direction 24b.
  • the lower flap 7c has two grooves 22c, 23c parallel to a direction 24c.
  • these grooves each comprise a corrugation 37.
  • this corrugation 37 shares each groove in two rectilinear aligned portions 38.1 and 38.2 which are separated by another rectilinear portion 38.3 parallel to the previous ones. Rounded portions connect the linear portions.
  • the amplitude of the corrugation is about 2 mm and its length about 4 mm.
  • Each groove cooperates with a rod 21 fixed relative to the projectile and more particularly each rod cooperates with two grooves of two adjacent flaps.
  • Each flap 7 is held between two parallel surfaces or partitions delimiting a groove 17.
  • the flap 7a is disposed in the groove 17a, between the upper partition 15a and the next partition 15b.
  • the flap 7b is disposed in the groove 17b, between the partitions 15b and 15c.
  • the flap 7c is disposed in the groove 17c between the partition 15c and the bearing surface 16 of the body 13.
  • Such an arrangement of the shutters ensures the protection of the shutters and their mechanical resistance to the acceleration developed during firing of the projectile.
  • a game of the order of a tenth of a millimeter is provided between each flap 7 and the groove 17 which receives it, as well as between the rods 21a, 21b and 21c and the grooves in order to allow the flaps to move from their position.
  • the partitions separating the flaps are not shown.
  • the central portion 14 of the body 13 of the rocket has been positioned in dotted lines.
  • Each flap is made for example of sheet steel 2 mm thick and carries the two grooves 22, 23 for receiving the rods 21.
  • the flaps may also be made of another material for example a light alloy (based on aluminum).
  • each flap has an outer profile 25 covering an arc of a circle whose diameter is substantially equal to the outer diameter of the rocket 3.
  • figure 5 thus shows a flap 7 alone.
  • Each flap also has a notch 26 intended to allow the positioning of the flap around the central portion 14 of the body 13 of the rocket.
  • the notch 26 comprises a hemicylindrical portion 27 of the same diameter as that of the central portion 14 and coaxial with the axis 20 thereof (that is to say also to the axis of the rocket and the projectile).
  • the hemicylindrical portion 27 of the indentation is connected to two flat surfaces 28 and 29 which are parallel to the grooves 22, 23.
  • a corrugation 40 is produced at the level of the flat surface 28 and a complementary recess 39 is arranged at the flat surface 29. These arrangements allow the lateral translation of the flap 7 with respect to the central portion 14 during the passage of the corrugations 37 by the stems 21.
  • the corrugations of the grooves 22 and 23 make it possible to ensure braking of the opening movement of the flap 7. Indeed, when the rod 21 reaches the level of the corrugation 37, the clearance between the groove and the rod is distributed differently, the flap translates laterally with respect to the central portion 14, the groove rubs against the rod, thereby consuming energy and reducing the speed of movement of the shutter.
  • the undulations thus constitute a means of slowing down the movement of deployment of the shutter. This reduces the impact of abutment of each flap against the guide rods at the end of the deployment movement, which increases the reliability of the device.
  • the indented shape of the flaps 7 also allows to obtain a maximum flap surface for minimal space in the folded position.
  • All flaps 7 here have the same structure and they comprise means that allow the locking of the shutters relative to each other in the folded position.
  • each flap 7 carries a hole 30, this hole is intended to receive, at the level of the only first flap 7a, the rod 31 of a pyrotechnic piston 32 (see FIG. figure 2 ).
  • This pyrotechnic piston is here a pyrotechnic retractor which is integral with the body 13 of the rocket. It comprises a gas generating composition which is electrically initiated by the control device 4 and which has the effect of causing the rod 31 to be pulled out of the hole 30.
  • a pyrotechnic component is well known to those skilled in the art and it will not be described in more detail.
  • the rod 31 of the retractor ensures the locking of the first flap 7a in the folded position.
  • Each flap also carries a notch 33.
  • the notch 33a of the first flap 7a is intended to cooperate with a first pin 34b carried by the second flap 7b to maintain the folded position thereof (see figure 3 ).
  • the second flap 7b carries a second notch 33b (in dotted lines figure 3 ) which is intended to cooperate with a second pin 34c carried by the third flap 7c to maintain the folded position thereof.
  • the pins 34b, 34c are housed in holes 47. Only the flaps 7b and 7c carry a pin, the flap 7a is devoid of it.
  • the partitions 15b and 15c each comprise a clearance 48 which is delimited by two perpendicular planes. These clearances are visible at figure 3 with dots. A clearance is particularly visible at the figure 6 on which the partition 15b is shown.
  • a single pyrotechnic piston 32 thus ensures the locking of all three components and prevents the deployment of these as a result of the centrifugal efforts exerted on them when firing the projectile.
  • the holding pins are constituted by small cylindrical rods mounted in the holes 47 made on the flaps.
  • the figure 3 shows the three flaps in their folded and locked position.
  • the section of the rocket was made to remove the upper partition 15a. Only the first component 7a is completely visible. The three rods 21a, 21b and 21c are cut. The second component 7b is hidden by the partition 15b. The third part is also hidden.
  • This figure shows how the different holding means cooperate with one another so as to ensure a locking of the three shutters.
  • the pin 34c carried by the third flap 7c is positioned in the notch 33b of the second flap 7b (visible elements in dashed lines).
  • the notch 33b is parallel to the direction 24b and is therefore cut by the direction of deployment 24c of the third component
  • the third component can not open.
  • each flap 7a, 7b and 7c comprises two end nozzles 41 which are each engaged in an impression 42 carried by a holding piece 43.
  • These holding pieces 43 are all identical and are identified 43a, 43b and 43c on the figures 3 and 4 for distinguish the maintenance parts that are associated with each component.
  • Each holding piece 43 is connected to the rocket 3 by a rod 21a, 21b or 21c. It is positioned, just like the shutter it blocks, in the annular groove 17a, 17b or 17c.
  • Each holding piece 43 is constituted by a piece of steel sheet having substantially the same thickness as the flap considered.
  • Each holding piece 43a, 43b, 43c has an internal medial portion 44 which is engaged in the notch 26 of the flap in the folded position. This median portion 44 is extended by two wings 45. Each wing 45 has a cavity 42 receiving one of the nozzles 41 of the flap in question.
  • Each holding piece 43a, 43b, 43c finally has a circular outer profile 46 which extends the outer profile of the flap considered and closes the notch 26.
  • the nozzles 41 have a trapezoidal profile.
  • the wings 45 comprise imprints 42 which have a shape complementary to that of the nozzles 41.
  • the trapezoidal profile allows an unlocking without excessive efforts during the deployment of the flap 7.
  • the holding pieces 43a, 43b and 43c prevent the spacing of the nozzles 41 which would be caused by the action of the centrifugal forces. They thus prevent the opening of the indentation 26 which would cause jamming of the flap 7 with respect to its guide pins 21.
  • the invention thus makes it possible to make the operation of the braking device 6 reliable.
  • the invention it is also possible to implement the invention with a rocket whose braking device comprises only two flaps which are deployed in opposite directions to one another.
  • the flaps will be further separated from each other by an intermediate partition secured to the body and which will receive a first flap on one side and a second flap on the other side.
  • the flaps and the holding parts will then be housed in grooves delimited by the internal partition and by surfaces or surfaces of the rocket body which are parallel to this intermediate partition.
  • the guide rods 21 will then be integral with this intermediate partition which will also carry the two holding pieces.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
EP15152942.7A 2014-02-27 2015-01-28 Fusée d'ogive de projectile d'artillerie comportant un dispositif de freinage en translation Active EP2913628B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL15152942T PL2913628T3 (pl) 2014-02-27 2015-01-28 Zapalnik głowicy pocisku artyleryjskiego zawierający urządzenie hamujące translacyjnie

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1400529A FR3017943B1 (fr) 2014-02-27 2014-02-27 Fusee d'ogive de projectile d'artillerie comportant un dispositif de freinage en translation

Publications (2)

Publication Number Publication Date
EP2913628A1 EP2913628A1 (fr) 2015-09-02
EP2913628B1 true EP2913628B1 (fr) 2017-01-11

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ID=51225578

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15152942.7A Active EP2913628B1 (fr) 2014-02-27 2015-01-28 Fusée d'ogive de projectile d'artillerie comportant un dispositif de freinage en translation

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Country Link
EP (1) EP2913628B1 (es)
ES (1) ES2618063T3 (es)
FR (1) FR3017943B1 (es)
PL (1) PL2913628T3 (es)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE1800208A1 (sv) * 2018-10-30 2020-05-01 Bae Systems Bofors Ab Bromsanordning, tändrör samt projektil

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9614133D0 (en) * 1996-07-05 1997-03-12 Secr Defence Means for increasing the drag on a munition
FR2786561B1 (fr) * 1998-11-30 2001-12-07 Giat Ind Sa Dispositif de freinage en translation d'un projectile sur trajectoire
FR2792400B1 (fr) * 1999-04-16 2002-05-03 Giat Ind Sa Dispositif de freinage en translation d'un projectile sur trajectoire

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
PL2913628T3 (pl) 2017-08-31
ES2618063T3 (es) 2017-06-20
FR3017943B1 (fr) 2016-02-12
FR3017943A1 (fr) 2015-08-28
EP2913628A1 (fr) 2015-09-02

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