EP1524488B1 - Vorrichtung zum Ausklappen des Leitwerks eines Projektils - Google Patents

Vorrichtung zum Ausklappen des Leitwerks eines Projektils Download PDF

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Publication number
EP1524488B1
EP1524488B1 EP04292220A EP04292220A EP1524488B1 EP 1524488 B1 EP1524488 B1 EP 1524488B1 EP 04292220 A EP04292220 A EP 04292220A EP 04292220 A EP04292220 A EP 04292220A EP 1524488 B1 EP1524488 B1 EP 1524488B1
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EP
European Patent Office
Prior art keywords
fin
rod
support
projectile
respect
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Application number
EP04292220A
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English (en)
French (fr)
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EP1524488A1 (de
Inventor
Christian Trouillot
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
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Publication of EP1524488A1 publication Critical patent/EP1524488A1/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

Definitions

  • the projectile fins generally provide a stabilizing function. They are grouped at a rear part of the projectile to form a tail.
  • Some projectiles carry other fins that provide a guiding function. These fins are generally arranged in front of the projectile.
  • the wings For reasons of space and to allow firing from a weapon tube, the wings must be folded backwards or forwards along the projectile or indoors of this one before firing.
  • US 5762294 shows a mechanism whose operation is comparable to that of the invention.
  • a first rotary axis is perpendicular to the projectile.
  • the fin support is in direct contact with the fin.
  • the fin turns with the stand around the stem.
  • the FR2623898 thus describes a deployment device in which the fins are arranged along an outer wall of the projectile. Each fin is initially driven by a gear motor that rotates about an axis perpendicular to the plane of the fin.
  • This deployment mechanism is slow, which is why it is particularly suitable for projectiles such as dispersible submunitions. Moreover it requires the use of a gear motor for each fin. These geared motors are expensive and they use a significant volume inside the projectile. The use of such a mechanism is therefore limited to intelligent sub-munitions in which gearmotors are also essential to ensure after deployment a steering function.
  • the subject of the invention is a device for deploying a projectile fin having a hinge fastened to the body of a projectile and which allows a pivoting movement of the fin along at least one axis, the articulation comprising a support fin blade pivoted relative to an axis substantially perpendicular to the axis of the projectile, the fin being connected to the support by a rod whose axis is substantially parallel to the axis of the projectile when the fin is in the folded position and substantially perpendicular to the axis of the projectile when the fin is in the extended position, the rod itself being pivotable relative to the fin support during the tilting movement of the support, this pivoting of the rod being controlled by a driving medium.
  • the rod of the fin can translate relative to the support and the rod also carries a head which is in contact with a first fixed cam profile integral with the projectile body, a spring means being interposed between the head and the support so as to control the initial opening of the fin by tilting the support.
  • the head of the fin rod comprises an arm substantially perpendicular to the rod and cooperating with a second stationary cam profile integral with the projectile body, arm and second cam profile forming the drive means of the rod pivoting, tilting of the fin support relative to the body thus also causing the pivoting of the rod relative to the support.
  • the second cam profile may be extended by a groove in which the arm will be housed when the rod has pivoted about 90 °, groove then ensuring immobilization in rotation of the rod relative to the support.
  • the support comprises at least one helical light in which a pin integral with the rod and transverse to the latter flows, the pin and the light forming the drive means of the pivoting rod. the translation of the rod relative to the support thus causing, by the action of the pin on the light, a rotation of the rod relative to the support.
  • the support comprises a tapping cooperating with a thread made on the rod, threading and tapping forming the driving means of the rod pivoting, the translation of the rod relative to the support causing thus, by the cooperation of the threading with the tapping, a rotation of the rod relative to the support.
  • the head of the rod may comprise an end which will be introduced into a complementary shaped opening when the fin is in its deployed position, thereby ensuring the locking of the deployed fin relative to the projectile.
  • the rod can be fixed to the fin at a distance from a median axis sharing the plane of the fin in two, so that the aerodynamic flow received by the fin also creates a torque that can cause the rod in rotation.
  • the fin may carry a cooperating heel in the deployed position with a groove.
  • the figure 1a shows a partial longitudinal section of a rear portion of a projectile 1.
  • the cut is performed at a deployment device 2 of a stabilizing fin 3.
  • the projectile usually carries between 3 and 8 identical stabilizing fins which each have an identical deployment device.
  • the fin 3 is here folded along the body of the projectile 1.
  • the plane of the fin is then placed along a wall of the projectile and is oriented substantially parallel to the axis 4 of the projectile.
  • the outer end 3a of the fin is oriented towards the front part of the projectile (reference AV) advantageously be provided at this end a shearable holding device (such a polyamide ring not shown).
  • the outer end 3a of the fin can receive a complementary device for initiating the opening of the fin by the effect of the aerodynamic flow, for example a detachable pallet.
  • a complementary device for initiating the opening of the fin by the effect of the aerodynamic flow for example a detachable pallet.
  • Such a palette aerodynamics is the subject of FR2721702 . It is not necessary to describe it in more detail.
  • the fin deployment device comprises a hinge, attached to the body of a projectile, and which comprises a fin support 5 pivotally mounted relative to a housing 6 integral with the body of the projectile 1.
  • the support 5 of the fin 3 can thus rock with respect to a substantially perpendicular axis 7 (in projection) to the axis 4 of the projectile.
  • the fin 3 is connected to the support 5 by a rod 8 whose axis is parallel to the plane of the fin, therefore substantially parallel to the axis 4 of the projectile when the fin is in the folded position.
  • the axis of the rod 8 will be substantially perpendicular to the axis of the projectile when the fin is in the deployed position or, depending on the stabilization needs, it may be inclined rearward (towards the AR mark) of the projectile of a wedge angle (this angle known as angle of arrow is usually between 0 ° and 45 °).
  • the rod 8 is pivotally mounted relative to the support 5 of the fin 3 and can also translate relative to the support 5.
  • the rod 8 carries at its end an enlarged head 9 which is kept in contact with the housing 6 by a spring 10.
  • the spring 10 is mounted on the rod 8 and is interposed between the enlarged head 9 and the support 5.
  • the enlarged head 9 comprises a lateral arm 11, substantially perpendicular to the rod 8, the arm whose function will be described later.
  • the housing 6 is housed in a radial cut 13 of the body of the projectile. It is secured to the latter by a suitable securing means, such as unrepresented screws or a rear flange. If it is desired to disengage in rotation the empennage relative to the projectile we can fix the housing 6 to a ring that will be free mounting in rotation relative to the projectile, for example by means of ball bearings.
  • the housing 6 is closed by a cover 6a ( figure 3 ) which is fixed by screws 12 ( figure 1a ).
  • the pivot axis 7 of the support 5 is mounted between the housing 6 and the cover 6a.
  • the housing 6 carries a first concave cam profile 14 which controls the tilting of the support 5 of the fin and on which the head 9 is applied by the spring 10. This cam will be called thereafter cam tilting.
  • This movement caused by the spring 10 is sufficient to ensure the initial opening of the fin, but it can be reinforced by an aerodynamic pallet fixed to the end 3a of the fin.
  • the housing 6 also carries a second convex cam profile 15, which controls the pivoting of the rod 8 of the fin, a profile on which the arm 11 of the head 9 is applied. This cam will subsequently be called the pivoting cam.
  • This second cam profile 15 determines the pivoting phase (start, speed) of the rod 8 relative to the support 5 of the fin 3 during the tilting movement of the support 5 with respect to the housing 6.
  • the Figures 2a and 2b show the device in deployed wing position.
  • the tilting of the support 5 of the fin about the axis 7 has caused jointly, thanks to the cooperation of the arm 11 and the second cam profile 15, the pivoting of the fin relative to the support 5.
  • the plane of the fin 3 is thus oriented radially relative to the projectile and the rod 8 carrying the fin is then substantially perpendicular to the axis 4 of the projectile.
  • the fin 3 is locked by its heel 23 arranged at the trailing edge and which penetrates into a groove 24 of the housing 6 (see also figure 3 ).
  • the adjustment of the arrow of the fin is done simply by adjusting the orientation of the abutment surface 27 of the head 9 on the housing 6 (see FIG. figures 1a and 4 ).
  • the deployment device shown in the figures shows a fin with a null arrow. It is represented by the broken line 25 on the figure 2a a different orientation for the abutment surface 27. This inclined abutment would guide the axis of the rod 8 carrying the fin in the direction 26 which corresponds for the fin 3 to a rearward arrow ⁇ ( AR) of the projectile.
  • the housing 6 has an internal groove 16 which extends the cam 15 pivoting.
  • the groove 16 is delimited by the cover 6a, by a wall 6b of the housing parallel to the cover 6a and by the first cam profile 14.
  • the arm 11 of the head 9 is housed in this groove 16 after deployment of the fin 3 (see Figure 2a and 2b ).
  • the groove 16 thus immobilizes the rod 8 in rotation with respect to the support 5.
  • the housing 6 will be defined in such a way that this immobilization occurs when the rod 8 has pivoted by the desired deflection angle, ie, in the example shown in the figures, by approximately 90 ° with respect to the support 5.
  • the groove 16, which is also delimited by the profile of the tilting cam 14, is extended at the end of the latter by an opening 17 (see FIG. figure 1a ).
  • the head 9 of the rod 8 is introduced into this opening 17 which has a suitable diameter (see FIG. figure 2a ).
  • the opening 17 thus ensures the locking of the fin 3 in its deployed position relative to the projectile 1.
  • the depth of the opening 17 also makes it possible to adjust the final position in height of the fin 3 relative to the projectile body 1.
  • the rod 8 is fixed to the fin 3 at a distance D of a median axis 18 sharing the plane of the fin in two.
  • the figure 3 also shows as an indication a cover 19 which ensures the closure of the upper part of the housing 6 and which allows to find the aerodynamic profile of the projectile body. This cover is not shown in the other figures.
  • the invention makes it possible with an extremely simple mechanical structure to ensure the complex movement of deployment of a projectile stabilizing fin.
  • This deployment device occupies a reduced internal volume in the body of the projectile.
  • the fins planes remain external to the body.
  • the fin housings can be adjusted to the dimensions of the fins, they are then properly held in place during the gun phase and protected from attacks of propellant gases.
  • figure 5 thus shows another embodiment which differs from the previous embodiment in that the head 9 extending the rod 8 of the fin 3 is devoid of arms 11. Moreover, the housing 6 does not have a second convex cam profile 15.
  • the principle of tilting of the fin is unchanged, against the pivoting of the fin is provided by a different drive means.
  • the driving means here consists of a pin 20 integral with the rod 8 and transverse thereto. This pin 20 circulates in a slot 21 formed in the support 5 and having a helical profile.
  • the translation of the rod 8 with respect to the support 5 therefore also causes the rod to rotate relative to the support 5.
  • the rod 8 can only translate in accordance with the helicoidal profile 21 which guides the pin 20.
  • the pitch of the propeller will be easily chosen by those skilled in the art so that the rod pivots 90 ° relative to the support 5 when the latter has itself rotated 90 ° relative to its axis 7.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Superconductors And Manufacturing Methods Therefor (AREA)
  • Jib Cranes (AREA)
  • Tents Or Canopies (AREA)
  • Amplifiers (AREA)
  • Bidet-Like Cleaning Device And Other Flush Toilet Accessories (AREA)
  • Massaging Devices (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (9)

  1. Vorrichtung zum Entfalten (2) eines Projektil-Leitflügels (3), umfassend ein Gelenk, das am Körper eines Projektils (1) befestigt ist und das eine Drehbewegung des Leitflügels (3) gemäß wenigstens einer Achse ermöglicht, wobei das Gelenk einen Leitflügel-Träger (5) umfasst, der in Bezug auf eine zur Achse (4) des Projektils im wesentlichen senkrechte Achse (7) schwingbar montiert ist, wobei der Leitflügel (3) mit dem Träger (5) durch eine Stange (8) verbunden ist, deren Achse im wesentlichen parallel zur Achse (4) des Projektils ist, wenn sich der Leitflügel (3) in gefalteter Position befindet, und im wesentlichen senkrecht zur Achse (4) des Projektils steht, wenn sich der Leitflügel (3) in entfalteter Position befindet, wobei sich die Stange (8) selbst in Bezug auf den Leitflügel-Träger (5) bei der Schwingbewegung des Trägers drehen kann, wobei diese Drehung der Stange (8) durch ein Antriebsmittel gesteuert wird.
  2. Vorrichtung zum Entfalten nach Anspruch 1, dadurch gekennzeichnet, dass sich die Stange (8) des Leitflügels (3) in Bezug auf den Träger (5) verschieben kann, und dass die Stange (8) einen Kopf (9) trägt, der mit einem ersten Kurvenprofil (14) in Kontakt steht, das fest mit dem Körper des Projektils (1) verbunden ist, wobei ein Federmittel (10) zwischen den Kopf (9) und den Träger (5) eingefügt ist, derartig, dass das anfängliche Öffnen des Leitflügels (3) durch Schwingen des Trägers (5) betätigt wird.
  3. Vorrichtung zum Entfalten nach Anspruch 2, dadurch gekennzeichnet, dass der Kopf (9) der Stange (8) des Leitflügels (3) einen Arm (11) umfasst, der im wesentlichen senkrecht zur Stange (8) steht und mit einem zweiten Kurvenprofil (15) zusammenwirkt, das fest mit dem Körper des Projektils (1) verbunden ist, wobei der Arm (11) und das zweite Kurvenprofil (15) das Antriebsmittel der Stange (8) zur Drehung bilden, wobei das Schwingen des Leitflügel-Trägers (5) in Bezug auf den Körper so auch die Drehbewegung der Stange (8) in Bezug auf den Träger (5) nach sich zieht.
  4. Vorrichtung zum Entfalten nach Anspruch 3, dadurch gekennzeichnet, dass das zweite Kurvenprofil (15) durch eine Rille (16) verlängert ist, in der sich der Arm (11) einfügt, wenn die Stange (8) um etwa 90° gedreht werden wird, wobei die Rille nun die Festlegung der Stange (8) in Drehbewegung in Bezug auf den Träger (5) gewährleistet.
  5. Vorrichtung zum Entfalten nach Anspruch 2, dadurch gekennzeichnet, dass der Träger (5) wenigstens ein spiralförmiges Langloch (21) umfasst, in dem ein Metallstück (20) umläuft, das fest mit der Stange (8) verbunden ist und quer zu dieser ist, wobei das Metallstück (20) und das Langloch (21) das Antriebsmittel der Stange (8) zur Drehbewegung bilden, wobei die Verschiebung der Stange in Bezug auf den Träger so durch Aktion des Metallstückes in dem Langloch eine Drehung der Stange (8) in Bezug auf den Träger (5) bewirkt.
  6. Vorrichtung zum Entfalten nach Anspruch 2, dadurch gekennzeichnet, dass der Träger (5) ein Innengewinde (23) umfasst, das mit einem auf der Stange (8) ausgeführten Gewinde (22) zusammenwirkt, wobei Gewinde (22) und Innengewinde (23) das Antriebsmittel der Stange (8) zur Drehung bilden, wobei die Verschiebung der Stange (8) in Bezug auf den Träger so durch die Zusammenwirkung des Gewindes (22) mit dem Innengewinde (23) eine Drehung der Stange (8) in Bezug auf den Träger (5) bewirkt.
  7. Vorrichtung zum Entfalten nach einem der Ansprüche 2 bis 6, dadurch gekennzeichnet, dass der Kopf (9) der Stange (8) ein Ende umfasst, das sich in eine Öffnung (17) von komplementärer Form einführt, wenn der Leitflügel (3) sich in seiner entfalteten Position befindet, sodass so die Verriegelung des in Bezug auf das Projektil (1) entfalteten Leitflügels (3) gewährleistet wird.
  8. Vorrichtung zum Entfalten nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die Stange (8) am Leitflügel (3) in Abstand (D) von einer Mittelachse (18) befestigt ist, welche die Fläche des Leitflügels (3) in zwei teilt, derartig, dass die von dem Leitflügel (3) empfangene aerodynamische Strömung ebenfalls ein Drehmoment erzeugt, das dafür geeignet ist, die Stange (8) in Drehung zu versetzen.
  9. Vorrichtung zum Entfalten nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass der Leitflügel (3) einen Ansatz (23) trägt, der in entfalteter Position mit einer Rille (24) zusammenwirkt.
EP04292220A 2003-10-06 2004-09-16 Vorrichtung zum Ausklappen des Leitwerks eines Projektils Active EP1524488B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0311642A FR2860577B1 (fr) 2003-10-06 2003-10-06 Dispositif de deploiement d'une ailette d'un projectile
FR0311642 2003-10-06

Publications (2)

Publication Number Publication Date
EP1524488A1 EP1524488A1 (de) 2005-04-20
EP1524488B1 true EP1524488B1 (de) 2008-07-23

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EP04292220A Active EP1524488B1 (de) 2003-10-06 2004-09-16 Vorrichtung zum Ausklappen des Leitwerks eines Projektils

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US (1) US7059561B2 (de)
EP (1) EP1524488B1 (de)
AT (1) ATE402389T1 (de)
DE (1) DE602004015221D1 (de)
FR (1) FR2860577B1 (de)
IL (1) IL164293A (de)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7642492B2 (en) * 2005-01-26 2010-01-05 Raytheon Company Single-axis fin deployment system
FR2895071B1 (fr) 2005-12-19 2008-01-18 Giat Ind Sa Dispositif de verrouillage anti-rebond d'une ailette deployable d'un projectile.
US7856929B2 (en) 2007-06-29 2010-12-28 Taser International, Inc. Systems and methods for deploying an electrode using torsion
FR2949848B1 (fr) * 2009-09-10 2012-09-28 Nexter Munitions Dispositif d'ouverture et verrouillage d'une ailette canard.
US8754352B2 (en) * 2010-04-07 2014-06-17 Bae Systems Information And Electronic Systems Integration Inc. Compression spring wing deployment initiator
FR3041744B1 (fr) * 2015-09-29 2018-08-17 Nexter Munitions Projectile d'artillerie ayant une phase pilotee.
AU2017300113B2 (en) * 2016-07-21 2020-04-02 Chairman, Defence Research &Development Organisation (Drdo) Bi-directional wing unfolding mechanism
CN106927017B (zh) * 2017-03-29 2023-12-12 河北全疆科技有限公司 一种多旋翼无人机机臂折叠机构
EP3403922A1 (de) * 2017-05-18 2018-11-21 Airbus Operations GmbH Flügelanordnung für ein flugzeug
US11300390B1 (en) * 2018-03-05 2022-04-12 Dynamic Structures And Materials, Llc Control surface deployment apparatus and method of use
US11067371B2 (en) * 2019-03-22 2021-07-20 Bae Systems Information And Electronic Systems Integration Inc. Trimmable tail kit rudder
DE102020105188B4 (de) * 2020-02-27 2023-08-31 Deutsches Zentrum für Luft- und Raumfahrt e.V. Flugkörper-Finnenausklappeinrichtung, Flugkörper und Verfahren zum Betrieb eines Flugkörpers

Family Cites Families (11)

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Publication number Priority date Publication date Assignee Title
US3063375A (en) * 1960-05-19 1962-11-13 Wilbur W Hawley Folding fin
DE3010027C2 (de) * 1978-09-26 1985-07-11 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Schwenkbare Anordnung eines Leitwerks, insbesondere bei Flugkörpern oder Geschossen
US4323208A (en) * 1980-02-01 1982-04-06 British Aerospace Folding fins
US4664339A (en) * 1984-10-11 1987-05-12 The Boeing Company Missile appendage deployment mechanism
DE3507677A1 (de) * 1985-03-05 1986-09-11 Diehl GmbH & Co, 8500 Nürnberg Flugkoerper mit ueberkalibrigem leitwerk
US4869442A (en) * 1988-09-02 1989-09-26 Aerojet-General Corporation Self-deploying airfoil
IL107844A (en) * 1993-12-02 1996-06-18 Ministry Of Defence Armaments Flying object control system
US5480111A (en) * 1994-05-13 1996-01-02 Hughes Missile Systems Company Missile with deployable control fins
US5762294A (en) * 1997-03-31 1998-06-09 The United States Of America As Represented By The Secretary Of The Army Wing deployment device
FR2797946B1 (fr) * 1999-08-31 2002-10-04 Aerospatiale Matra Missiles Dispositif de montage d'un appendice rigide sur un engin apte a etre lance depuis le tube, et engin correspondant
US6761331B2 (en) * 2002-03-19 2004-07-13 Raytheon Company Missile having deployment mechanism for stowable fins

Also Published As

Publication number Publication date
IL164293A0 (en) 2005-12-18
ATE402389T1 (de) 2008-08-15
FR2860577B1 (fr) 2006-01-27
IL164293A (en) 2012-02-29
US7059561B2 (en) 2006-06-13
DE602004015221D1 (de) 2008-09-04
US20050082420A1 (en) 2005-04-21
FR2860577A1 (fr) 2005-04-08
EP1524488A1 (de) 2005-04-20

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