EP2354755B1 - Vorrichtung zum simultanen Ausklappen von Steuerflächen eines Geschosses - Google Patents

Vorrichtung zum simultanen Ausklappen von Steuerflächen eines Geschosses Download PDF

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Publication number
EP2354755B1
EP2354755B1 EP11290029A EP11290029A EP2354755B1 EP 2354755 B1 EP2354755 B1 EP 2354755B1 EP 11290029 A EP11290029 A EP 11290029A EP 11290029 A EP11290029 A EP 11290029A EP 2354755 B1 EP2354755 B1 EP 2354755B1
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EP
European Patent Office
Prior art keywords
projectile
control surfaces
deployment device
ferrule
axis
Prior art date
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Active
Application number
EP11290029A
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English (en)
French (fr)
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EP2354755A1 (de
Inventor
Geoffroy Deschatre
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
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Nexter Munitions SA
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Publication date
Application filed by Nexter Munitions SA filed Critical Nexter Munitions SA
Priority to PL11290029T priority Critical patent/PL2354755T3/pl
Publication of EP2354755A1 publication Critical patent/EP2354755A1/de
Application granted granted Critical
Publication of EP2354755B1 publication Critical patent/EP2354755B1/de
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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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • 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
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins

Definitions

  • the technical field of the invention is that of deployment devices projectile control surfaces.
  • control surfaces In order to bring greater precision to modern ballistic or propelled projectiles, these are equipped with control surfaces to correct the trajectory or stabilize the projectile. These control surfaces are driven by electric motors. Given the congestion represented by the control surfaces, these are generally contained in the body of the projectile during the phases of handling and installation in a weapon tube and during the internal ballistic phase. The control surfaces are then deployed in flight.
  • the patent EP-1550837 proposes to deploy the control surfaces to resort to springs equipping each control surfaces individually.
  • This device has a major disadvantage. In order not to compromise the stability of the projectile, it is essential that the deployment of all control surfaces is simultaneous, but this device does not provide all the necessary guarantees because it has the disadvantage that the springs have effects independent of each other. other. As a result of the differences in elasticity or other mechanical characteristics of the springs may cause a deferred exit of the control surfaces relative to each other.
  • DE-3838735 describes a device for simultaneous deployment of fins.
  • this device requires a single sliding element having a toothing on its periphery and meshing with the gears of the base of the fins.
  • the invention proposes to provide a solution ensuring simultaneous deployment of all the control surfaces.
  • the deployment energy is provided by a single spring which simultaneously slides racks allowing the simultaneous deployment of the control surfaces while allowing them once deployed to be pivoted on themselves, by the control of an engine, to ensure the steering of the projectile.
  • the invention relates to a device for deploying control surfaces of a projectile for which each rudder is intended to be pivoted by a motor after deployment to provide steering, each rudder being held inside the projectile and deployed to the outside the projectile by the expansion of an elastic means, each rudder unfolding by rotation relative to a steering support and a transverse axis of deployment to the axis of the projectile.
  • This device for deploying control surfaces is characterized in that the elastic means is a common means which ensures the deployment of all the control surfaces, the expansion of the elastic means generating a thrust force directed along the axis of the projectile and exerting on a thrust plate which transmits the thrust force to as many sliders as there are control surfaces to be deployed, each slide cooperating without sliding with a complementary profile integral with a base of the rudder to rotate it by relative to its support and a first releasable locking means also ensuring the retention of the elastic means in the compressed position.
  • the first locking means is constituted by a substantially cylindrical ferrule which separates the thrust plate from the sliders when the resilient means is compressed, the ferrule comprising pins on which abutment radial arms carried by the thrust plate, the ferrule being pivotable along the axis of the projectile to release the thrust plate and cause the relaxation of the elastic means, the radial arms then pushing the slides.
  • the device comprises a second releasable locking means which keeps the control surfaces in the folded position.
  • the device comprises a third locking means maintaining the control surfaces in the deployed position.
  • the ferrule comprises an internal toothing cooperating with a second pinion driven by a motor to allow the pivoting of the ferrule and the unlocking of the elastic means.
  • the second locking means comprises fingers integral with the ferrule, each finger engaging in a longitudinal groove of the slide, the fingers being disengaged from their grooves during the pivoting of the ferrule.
  • the third locking means is constituted for each rudder by at least one ball stop engaging in a recess of the slide when the control surfaces are deployed.
  • the slide is a rack which cooperates with a complementary profile formed by a first toothed gear integral with the base of the rudder.
  • the thrust plate which is slidably mounted on an axis coaxial with the projectile, may comprise a tooth which will ensure its guidance on this axis, a tooth which circulates in a longitudinal groove which ends with a helicoidal portion, the thrust plate pivoting thus partially around the axis at the end of its axial displacement so that each arm is moved away from the slide it pushed.
  • a projectile 1 is equipped with rudders 2a, 2b, 2c and 2d shown deployed and arranged at a front part of the projectile 1.
  • rudders 2a, 2b, 2c and 2d shown deployed and arranged at a front part of the projectile 1.
  • the deployment device of the control surfaces 4 is contained in the front part of the projectile 1 and is therefore not visible in the drawing in its entirety. In the folded position, the control surfaces 2a to 2d are inserted into the slots 3 (configuration not shown in the figure).
  • the deployment device comprises a body 5 which houses the control surfaces 2a to 2d in the folded position (only two control surfaces are visible on the figure 2 ).
  • the base of each rudder 2a to 2d comprises a toothing forming a pinion 6.
  • This pinion base 6 is traversed by an axis 7 integral with a support 8.
  • each support 8 is intended to be pivoted along an axis perpendicular to the axis of the projectile to enable control. This pivoting is provided by a motor (not shown).
  • the pinion 6 meshes with a toothed slider (also called rack 9) which slides in a groove of the body 5.
  • the deployment device 4 comprises in its foremost part a cover 10 (only one sector of the cover 10 is shown) integral with the body 5.
  • This cover 10 comprises in its center a housing accommodating the end of a compressed elastic means which is here a spring 11 with helical turns.
  • a first end of the spring 11 is supported on a cross-shaped thrust plate 12 which has radial arms (as many radial arms as there are racks 9).
  • the arms of the thrust plate are each supported on a lug 13a to 13d integral with a ferrule 13 (the lug 13c is not visible on the figure 2 because masked by the hood portion 10).
  • the shell 13 is more particularly visible on the figure 8 . It is substantially cylindrical and has a ring gear with internal teeth 14 on its inner periphery. This ring gear 14 meshes with a pinion 15 driven by a motor (not shown).
  • the lugs 13a, 13b, 13c and 13d are configured in the form of flat tabs which extend radially inwardly of the shell 13 and which are regularly distributed angularly.
  • the control surfaces 2a to 2d are folded and the lugs 13a to 13d of the shell 13 separate the racks 9 from the arms of the thrust plate 12. In this way the racks 9 do not undergo the force generated by the spring 11 thus avoiding the deployment of the control surfaces 2a to 2d.
  • the ferrule 13 opposing the crossplate 12 thus forms a first locking means ensuring the retention of the elastic means 11 in the compressed position.
  • control surfaces 2a to 2d are deployed and out of the body 5.
  • the shell 13 has turned a quarter turn in the direction 16 relative to the position it occupies on the figures 2 and 3 .
  • the spring 11 is released and pushes the thrust plate 12 against the racks 9.
  • Each arm of the plate 12 pushes a rack 9.
  • the racks 9a to 9d have been thrust of the plate 12 which causes them to penetrate deeper into each of the supports 8 control surfaces. In their final depressed position, the racks 9a to 9d penetrate deeper into the supports 8 of control surfaces passing right through them.
  • each of the racks 9a to 9d can independently follow the movements of control rudders controlled via the motors (not shown).
  • figure 6 which represents in detail a partial section along the orthogonal planes C identified at figure 3 of the device 4 in the configuration of the control surfaces 2a to 2d folded.
  • the shell 13 separates the thrust plate 12 from the rack 9a.
  • the rack 9a has on each of its lateral faces (symmetrical with respect to the teeth of the rack) a longitudinal groove 99a.
  • the rack thus has two grooves 99a.
  • One of these grooves 99a will be better seen at figure 7 where it can be seen that the grooves 99a only open at one end of the rack 9 and that they are used for the translational guiding of the rack 9a in the support 8, which comprises two tabs 88 engaged in the grooves 99a (one of the tabs 88 will be better seen on the figure 6 ).
  • the ferrule 13 comprises at the lug 13a a locking pin 16a which is placed on the face directed towards the rack 9a (the configuration of the shell 13 alone is better represented on the figure 8 which gives a glimpse of this one of the side oriented towards the racks 9).
  • the finger 16a is engaged in a single groove 99a of the rack 9a, at the end of the rack 9a where this groove 99a does not open. In this way the finger 16a locks the sliding of the rack 9a which also locks (via the pinion 6) the rudder 2a in the folded position in the body 5.
  • the cup of the figure 6 shows more particularly the rack 9a, but all the racks are structurally identical and the shell 13 also has identical locking fingers 16 disposed at each rack and engaged in a groove of the rack. Each locking pin 16a to 16d is secured to a lug 13a to 13d of the shell 13 (see FIG. figure 8 ).
  • each rack 9 comprises a housing 17 and each support 8 of rudder comprises a ball stop 18.
  • a housing 17 is formed on the rack 9 at a location such that when the rudder 2 is deployed, the stop ball 18 is engaged in the housing 17 thus forming a lock.
  • the stop thus immobilizes the rack 9 in translation with respect to its support 8, which also locks the rudder in the deployed position by means of the pinion 6.
  • the figure 9 shows in a partial manner another embodiment of the invention.
  • the thrust plate may, at the end of its axial displacement, partially pivot about the axis 28 on which it is mounted (axis coaxial with the axis of the projectile). This pivoting allows to separate each arm 12a to 12d of the thrust plate of the slider 9 that this arm has moved.
  • the axis 28 comprises a guide groove 28a which has a straight portion and which ends, at its end closest to the racks 9, by a helical portion.
  • this groove 28a circulates a tooth 30 integral with the thrust plate 12.
  • the helical pitch of the helical portion of the guide groove 28a will be chosen so as to rotate the thrust plate 12 by an angle such that at the end of the rotation each of the arms of the thrust plate 12 is no longer positioned in front of the slides 9.
  • the sliders 9 have been brought to the end of their stroke.
  • the angle of rotation ⁇ of the thrust plate 12 is of the order of one eighth of a revolution.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Transmission Devices (AREA)
  • Aerials With Secondary Devices (AREA)

Claims (9)

  1. Vorrichtung zum Entfalten von Steuerflächen (4) eines Projektils (1), wobei jede Steuerfläche (2a bis 2d) dafür vorgesehen ist, nach Entfaltung von einem Motor gedreht zu werden, um ein Steuern zu gewährleisten, wobei jede Steuerfläche im Inneren des Projektils (1) festgehalten wird und durch die Entspannung eines elastischen Mittels (11) in den Außenbereich des Projektils entfaltet wird, wobei sich jede Steuerfläche (2a bis 2d) durch Drehung in Bezug auf einen Steuerflächenträger (8) und gemäß einer Entfaltungsachse quer zur Achse des Projektils entfaltet, wobei die Vorrichtung zum Entfalten von Steuerflächen (4) dadurch gekennzeichnet ist, dass das elastische Mittel (11) ein gemeinsames Mittel ist, welches die Entfaltung der gesamten Steuerflächen (2a bis 2d) gewährleistet, wobei die Entspannung des elastischen Mittels (11) eine Druckkraft erzeugt, die entlang der Achse des Projektils gerichtet ist und auf eine Druckplatte (12) wirkt, welche die Druckkraft an so viele Schieber (9) überträgt, wie es zu entfaltende Steuerflächen (2a bis 2d) gibt, wobei jeder Schieber (9) ohne Gleiter mit einem komplementären, fest mit einer Basis der Steuerfläche (2a bis 2d) verbundenen Profil (6) zusammenwirkt, um diese in Bezug auf ihren Träger (8) drehen zu lassen, wobei ein erstes lösbares Verriegelungsmittel (13) außerdem das Festhalten des elastischen Mittels (11) in zusammengedrückter Position gewährleistet.
  2. Vorrichtung zum gleichzeitigen Entfalten von Steuerflächen (4) eines Projektils (1) nach Anspruch 1, dadurch gekennzeichnet, dass das erste Verriegelungsmittel (13) von einem Ring (13) gebildet wird, der im wesentlichen zylindrisch ist und die Druckplatte (12) von den Schiebern (9) trennt, wenn das elastische Mittel (11) zusammen gedrückt ist, wobei der Ring (13) Nocken (13a bis 13d) umfasst, an denen radiale Arme (12a bis 12d) anliegen, die von der Druckplatte (12) getragen werden, wobei sich der Ring (13) um die Achse des Projektils drehen kann, um die Druckplatte (12) frei zu geben und das Entspannen des elastischen Mittels (11) zu bewirken, wobei die radialen Arme (12a bis 12d) dann die Schieber (9) drücken.
  3. Vorrichtung zum gleichzeitigen Entfalten von Steuerflächen (4) eines Projektils (1) nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass sie ein zweites, lösbares Verriegelungsmittel (16) umfasst, das die Steuerflächen (2a bis 2d) in gefalteter Position festhält.
  4. Vorrichtung zum gleichzeitigen Entfalten von Steuerflächen (4) eines Projektils nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass sie ein drittes Verriegelungsmittel (18) umfasst, das die Steuerflächen (2a bis 2d) in entfalteter Position festhält.
  5. Vorrichtung zum gleichzeitigen Entfalten von Steuerflächen (4) eines Projektils (1) nach Anspruch 2, dadurch gekennzeichnet, dass der Ring (13) eine Innenverzahnung (14) umfasst, die mit einem zweiten Ritzel (15) zusammenwirkt, welches von einem Motor angetrieben wird, um die Drehung des Rings (13) und die Entriegelung des elastischen Mittels (11) zu ermöglichen.
  6. Vorrichtung zum gleichzeitigen Entfalten von Steuerflächen eines Projektils nach Anspruch 3, dadurch gekennzeichnet, dass das zweite Verriegelungsmittel (16) fest mit dem Ring (13) verbundene Finger (16a bis 16d) umfasst, wobei jeder Finger (16a bis 16d) in eine longitudinale Rille (99a bis 99d) des Schiebers (9) eingreift, wobei die Finger (16a bis 16d) bei der Drehung des Rings (13) aus ihren Rillen (99a bis 99d) frei kommen.
  7. Vorrichtung zum gleichzeitigen Entfalten von Steuerflächen (2a bis 2d) eines Projektils (1) nach Anspruch 4, dadurch gekennzeichnet, dass das dritte Verriegelungsmittel (18) für jede Steuerfläche (2a bis 2d) von wenigstens einem Druckkugellager (18) gebildet wird, das in eine Aussparung (17) des Schiebers (9) eingreift, wenn die Steuerflächen (2a bis 2d) entfaltet sind.
  8. Vorrichtung zum gleichzeitigen Entfalten von Steuerflächen (4) eines Projektils (1) nach einem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass der Schieber (9) eine Zahnstange (9) ist, welche mit einem komplementären Profil (6), das von einem ersten gezahnten Ritzel (6) gebildet wird und fest mit der Basis der Steuerfläche (2) verbunden ist, zusammenwirkt.
  9. Vorrichtung zum gleichzeitigen Entfalten von Steuerflächen (4) eines Projektils (1) nach einem der Ansprüche 2 bis 8, dadurch gekennzeichnet, dass die Druckplatte (12), welche auf einer koaxial zum Projektil liegenden Achse (28) gleitend montiert ist, einen Zahn (30) umfasst, welcher deren Führung auf dieser Achse (28) gewährleistet, wobei sich der Zahn (30) in einer longitudinalen Rille (28a) bewegt, welche durch einen spiralförmigen Abschnitt endet, wobei sich die Druckplatte so am Ende ihrer axialen Bewegung derartig teilweise um die Achse (28) dreht, dass jeder Arm (12a bis 12d) vom Schieber (9), den er gedrückt hat, beabstandet wird.
EP11290029A 2010-01-28 2011-01-19 Vorrichtung zum simultanen Ausklappen von Steuerflächen eines Geschosses Active EP2354755B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL11290029T PL2354755T3 (pl) 2010-01-28 2011-01-19 Urządzenie do synchronicznego rozkładania powierzchni sterowych pocisków

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1000344A FR2955653A1 (fr) 2010-01-28 2010-01-28 Dispositif de deploiement simultane de gouvernes d'un projectile

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EP2354755A1 EP2354755A1 (de) 2011-08-10
EP2354755B1 true EP2354755B1 (de) 2012-11-07

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US (1) US8592737B2 (de)
EP (1) EP2354755B1 (de)
ES (1) ES2398733T3 (de)
FR (1) FR2955653A1 (de)
PL (1) PL2354755T3 (de)

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US11150062B1 (en) * 2016-06-23 2021-10-19 Orbital Research Inc. Control actuation system, devices and methods for missiles, munitions and projectiles
FR3054030B1 (fr) * 2016-07-18 2018-08-24 Nexter Munitions Projectile comprenant un dispositif de deploiement d'une voilure ou ailette
US10308347B2 (en) * 2016-10-26 2019-06-04 Simmonds Precision Products, Inc. Wing tip aileron actuation system
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CN113091524B (zh) * 2021-03-18 2022-08-30 中北大学 可重复展开的一维弹道阻力片连续修正机构及方法
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Publication number Publication date
ES2398733T3 (es) 2013-03-21
US8592737B2 (en) 2013-11-26
PL2354755T3 (pl) 2013-03-29
FR2955653A1 (fr) 2011-07-29
EP2354755A1 (de) 2011-08-10
US20110180655A1 (en) 2011-07-28

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