EP1550837B1 - Vorrichtung zur Entfaltung und Steuerung der Steuerflächen eines Projektils - Google Patents

Vorrichtung zur Entfaltung und Steuerung der Steuerflächen eines Projektils Download PDF

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Publication number
EP1550837B1
EP1550837B1 EP04292854A EP04292854A EP1550837B1 EP 1550837 B1 EP1550837 B1 EP 1550837B1 EP 04292854 A EP04292854 A EP 04292854A EP 04292854 A EP04292854 A EP 04292854A EP 1550837 B1 EP1550837 B1 EP 1550837B1
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EP
European Patent Office
Prior art keywords
control surfaces
projectile
deployment
control
orientation device
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Active
Application number
EP04292854A
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English (en)
French (fr)
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EP1550837A1 (de
Inventor
Dominique Dion
René Dodu
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
Publication of EP1550837A1 publication Critical patent/EP1550837A1/de
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Publication of EP1550837B1 publication Critical patent/EP1550837B1/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
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins
    • 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 technical sector of the present invention is that of devices for deploying and driving projectile fins, and more particularly for control surfaces, that is to say wings that can pivot, when they are in the deployed position, under the action of a driving engine.
  • the control surfaces play a steering role of the projectile but can also have a stabilizing role, similar to that of the aircraft control surfaces, being controlled in rotation by a motor driven by an electronic system.
  • the steering of the projectile makes it possible to correct its trajectory in flight in order to rectify any pointing errors or to direct it towards a target after detection of the latter.
  • Such control surfaces have the main disadvantage of having, to be effective, large dimensions (the length of the rudder is usually of the order of the caliber), which makes it impossible to fire the projectile from a weapon caliber .
  • the projectile that carries it may be a missile, a rocket, or a sub-projectile carried by a gyro-stabilized large caliber cargo projectile. These mechanisms however remain cumbersome and heavy, which has the effect of reducing the payload of the projectile.
  • US Pat. No. 6,446,906 (which forms the basis for the preamble of claim 1) discloses an unblocking device and orientation of control surfaces, the orientation of the control surfaces is provided by two motors each acting on a pair of control surfaces. .
  • US Pat. No. 6,186,443 also describes a device for deploying and driving an air vehicle wing. Such a device is however suitable only for the deployment of a wing and not the simultaneous deployment of several control surfaces. It is therefore not adaptable to projectiles, without reducing the space allocated to the payload.
  • the patent application WO 02/18867 describes a device for deploying control surfaces. This document proposes in particular a device for simultaneous deployment of the control surfaces, then an individual steering mechanism for each rudder, which further increases the load of the device.
  • the object of the present invention is to provide a deployment and drive device for control surfaces of a projectile, device ensuring a simultaneous deployment of control surfaces, secure, compact and lightweight, while being simple to achieve, for less cost and requiring only a minimum of energy.
  • the invention therefore relates to a device for deploying and driving control surfaces of a projectile, the deployment being carried out by spring means between a transport position in which the control surfaces are folded inside the projectile and held against the action of the spring means by means of a locking means, and an extended position in which the control surfaces are orientable relative to the projectile, characterized in that it comprises engines ensuring in a first time the deployment of the control surfaces and in a second step the orientation of the latter, the control surfaces locking means being a unique means ensuring the immobilization of all the control surfaces and allowing the simultaneous release of the latter, and the locking means being immobilized by a first locking means which is released by pivoting the body of the motors around the bearings.
  • the first locking means immobilizing the single locking means is constituted by fingers each actuated by a spring and cooperating with a ring integral with the body of each motor.
  • the ring carries a notch within which penetrates one end of the finger, this movement of the finger then releasing the locking means and also ensuring the rotational locking of the motor body.
  • control surfaces are two by two integral with the same control axis arranged transversely to the projectile, each axis being rotated by a motor.
  • the motor drives the control shaft by means of a lever acting on a rod connected to the axis.
  • each rudder is integral with the control shaft via a support and an arm articulated relative to said support.
  • the arm is subjected to the action of a spring to rotate the rudder relative to the support.
  • the device comprises a second locking means, locking the control surfaces and the support in an extended position.
  • the second locking means is a pin which is positioned in a hole in the rudder, so as to secure the rudder with the support.
  • a first advantage of the device according to the invention lies in the fact that, unlike current systems, the invention uses only two motors for the deployment and control of the control surfaces, which allows a reduction in manufacturing costs , a decrease in the need for electrical energy of the system and a better compactness.
  • Another advantage lies in the fact that the deployment of the control surfaces is carried out simultaneously. In this way, the risks of destabilization of the projectile are considerably reduced.
  • control surfaces can only be deployed after being unlocked, which reduces the risk of injury or damage when the handling of equipped projectiles.
  • FIGS. 1a and 1b are perspective views of a device for deploying and driving control surfaces of a projectile, according to the invention. These views show the device in its locked position, after deployment of the control surfaces. In view 1b, for a better understanding of the invention, only the essential elements have been represented.
  • the device according to the invention comprises a base 1, substantially of revolution shape, supporting the entire device and secured to the projectile (not shown) equipped with said device, two engines 2 (only one of which is visible in FIG. 1a) carried by bearings 3 and arranged symmetrically with respect to the Z axis of the base, control surfaces 8, a single means 7 for locking the control surfaces, locking fingers 9, and pins 80 provided at their two ends with 81 rudder supports, thus each supporting two rudders in opposite manner.
  • the two axes 80 are arranged perpendicularly with respect to each other, but a different configuration could be provided without changing the spirit of the invention.
  • the use of perpendicular axes for the orientation of control surfaces is sufficiently known to those skilled in the art and does not require any particular description. However, we can refer to US Patent 6,446,906 and FR 02 12903 which largely describe such embodiments.
  • the motors 2 comprise a body 20 and an axis 21 which are movable in rotation with respect to each other.
  • a ring 4 having a notch 40 is integral with the body 20 of the engine.
  • the axis 21 of the motor 2 carries at its end a lever 5 acting on the axis 80 by means of a rod 6.
  • Figures 2 to 4 are sectional views of an exemplary embodiment of the device for deploying and driving control surfaces of a projectile.
  • Figure 2 shows the device in its locking position of the control surfaces in the folded position.
  • control surfaces 8 (not shown in this figure) are held in a carrying position in which they are folded inside the projectile by a single locking means 7. This locking means is held in position by fingers 9 inserting into a hole 70 of the blocking means.
  • Figure 3 is a partial sectional view corresponding to the area framed by broken lines in Figure 2; it illustrates an embodiment of the locking mode of the control surfaces in the folded position.
  • the base 1 comprises two countersinks 93 in which the fingers 9 are movable in translation.
  • the inner end of the countersink 93 (that is to say the end closest to the axis of symmetry of the base 1) is non-emergent and has a bore 94, of smaller diameter than the countersink and opening opposite the piercing 70 of the locking means 7.
  • the fingers 9 are of revolution shape, with a T-section, so as to have three parts: a cylindrical or frustoconical stud 92, a piston 91, of cylindrical shape and diameter slightly smaller than the diameter of the countersink 93 and a rod 90, cylindrical in shape and slightly smaller in diameter than the diameters of the holes 94 and 70.
  • the rod 90 passes through the bore 94 and is inserted into the hole 70 of the blocking means 7, now thus the latter in position.
  • a spring 10 disposed between the piston 91 and the flange 95 of the countersink 93, exerts on the finger 9 a outward force of the base, to move away from the locking means 7.
  • the pin 92 is then held in abutment against the ring 4.
  • Figure 4 illustrates the unlocking of the control surfaces in the folded position.
  • the rings 4 have rotated until their notches 40 are facing the fingers 9.
  • the fingers 9 have moved in the direction F of the effort created by the springs.
  • the pins 92 are inserted into the respective notches 40 and the rods 90 are output from the bore 70, thus unlocking the locking means 7.
  • the control surfaces have therefore deployed by pushing the locking means 7 in its housing 1a of the base 1.
  • Figures 5 and 6 are sectional views illustrating the modes of deployment and drive control surfaces.
  • Figure 5 shows the sectional view of the device, when the control surfaces 8 are fully in the folded position and
  • Figure 6 shows, on a same scale, the sectional view of the device, when the control surfaces 8 are fully deployed.
  • the locking means 7 maintains the control surfaces 8 in the folded position against the action f2 spring means 34 and prevents any deployment thereof.
  • the locking means 7 has been unlocked and moved under the action of the control surfaces 8, which have pivoted along the arrow f2 around the axis 19 to move from the folded position inside the base 1 (FIG 5) to a deployed position totally outside the base 1, and therefore the projectile.
  • the securing means of a rudder 8 to its control axis 80 consists of an arm 82 integral with the rudder and rotatably mounted relative to the axis 19.
  • the rudder 8 thus pivots about the axis 19.
  • a torsion spring 34 is provided around this axis to exert on the arm 82 of the rudder 8 a torque along the arrow f2 This torque allows in particular to move the locking means 7 and deploy the control surfaces 8 upon unlocking the locking means .
  • a pin 13 secured to the support 81 is pushed by a return spring (not shown).
  • This pawn 13 cooperates with a bore 12 formed in the arm 82, to secure in the deployed position the control surface 8 and the support 81, itself secured to the axis of control 80 as indicated above.
  • the rudder pivots about the axis 19, to be placed in the position shown in Figure 6.
  • the rudder is immobilized by the pin 13 which comes into the drilling 12.
  • the operation of the device is as follows: after validation of the deployment of the control surfaces (for example by an electronic system allowing the deployment of the control surfaces when the projectile reached a certain speed, or after a delay), the motors 2 are actuated in rotation.
  • the fingers 9 then move in translation under the action of the springs 10 and fit into the notches 40 of the rings 4, simultaneously releasing the locking means 7.
  • the control surfaces 8 push the locking means 7 and can then be deployed in the manner explained above.
  • the body 20 of the motors 2 is secured to the base 1 by the fingers 9, the pin 92 is inserted into the notch 40 of the ring 4, thus preventing rotation of the body 20 of the motor.
  • a motor 2 When a motor 2 is actuated, it is only its axis 21 that starts moving.
  • the rotation of the axis 21 causes a translation of the rod 6 by means of the lever 5, which causes a rotation of the drive shaft 80 and thus allows the orientation of the pair of control surfaces made integral with the axis drive.
  • the rod 6 will, for example, connected to the lever 5 and the axis 80 by links of the ball joint type.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Devices For Conveying Motion By Means Of Endless Flexible Members (AREA)
  • Laser Surgery Devices (AREA)
  • Aerials With Secondary Devices (AREA)
  • Preliminary Treatment Of Fibers (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)

Claims (9)

  1. Vorrichtung zum Entfalten und Mitnehmen von Steuerflächen (8) eines Projektils, wobei das Entfalten durch Federmittel (34) erfolgt zwischen einer Mitnahmeposition, in der sich die Steuerflächen in zusammengefalteter Position im Inneren des Projektils befinden und gegen die Wirkung der Federmittel mit Hilfe eines Blockiermittels (7) festgehalten werden, und einer entfalteten Position, in der die Steuerflächen in Bezug auf das Projektil ausrichtbar sind, wobei die Vorrichtung dadurch gekennzeichnet ist, dass sie Motoren (2) umfasst, die in einem ersten Schritt das Entfalten der Steuerflächen (8) und in einem zweiten Schritt deren Ausrichten gewährleistet, wobei das Blockiermittel (7) der Steuerflächen (8) ein einziges Mittel ist, das die Festsetzung sämtlicher Steuerflächen und die gleichzeitige Freigabe dieser Letzteren gewährleistet, und wobei das Blockiermittel (7) durch ein erstes Verriegelungsmittel (9) festgesetzt wird, das durch eine Drehung des Körpers (20) der Motoren (2) freigegeben wird.
  2. Vorrichtung zum Entfalten und Mitnehmen von Steuerflächen (8) eines Projektils nach Anspruch 1, dadurch gekennzeichnet, dass das erste Verriegelungsmittel (9), welches das einzige Blockiermittel (7) festsetzt, von Fingern (9) gebildet wird, die jeweils von einer Feder (10) betätigt werden und mit einem Ring (4) zusammenwirken, der mit dem Körper jedes Motors (2) fest verbunden ist.
  3. Vorrichtung zum Entfalten und Mitnehmen von Steuerflächen (8) eines Projektils nach Anspruch 2, dadurch gekennzeichnet, dass jeder Ring (4) eine Aussparung trägt, in deren Inneres ein Ende (92) eines der Finger (9) eindringt, wobei die Verlagerung der Finger nun das Blockiermittel (7) freigibt und außerdem die Blockierung in Drehrichtung des Körpers (20) des Motors (2) gewährleistet.
  4. Vorrichtung zum Entfalten und Mitnehmen von Steuerflächen (8) eines Projektils nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Steuerflächen (8) jeweils zu zweit fest mit einem gleichen Steuerbolzen (80) verbunden sind, der in Bezug auf das Projektil quer angeordnet ist, wobei jeder Bolzen (80) von einem Motor (2) zur Drehung angetrieben wird.
  5. Vorrichtung zum Entfalten und Mitnehmen von Steuerflächen (8) eines Projektils nach Anspruch 4, dadurch gekennzeichnet, dass der Motor (2) den Steuerbolzen (80) mittels eines Hebels (5) antreibt, der auf eine mit dem Bolzen (80) verbundene Stange (6) wirkt.
  6. Vorrichtung zum Entfalten und Mitnehmen von Steuerflächen (8) eines Projektils nach einem der Ansprüche 4 oder 5, dadurch gekennzeichnet, dass jede Steuerfläche (8) mit Hilfe eines Trägers (81) und eines in Bezug auf den genannten Träger angelenkten Armes (82) fest mit dem Steuerbolzen (80) verbunden ist.
  7. Vorrichtung zum Entfalten und Mitnehmen von Steuerflächen (8) eines Projektils nach Anspruch 6, dadurch gekennzeichnet, dass der Arm (82) der Wirkung einer Feder (34) unterworfen wird, um die Drehung der Steuerfläche (8) in Bezug auf den Träger (81) zu gewährleisten.
  8. Vorrichtung zum Entfalten und Mitnehmen von Steuerflächen (8) eines Projektils nach Anspruch 7, dadurch gekennzeichnet, dass sie ein zweites Verriegelungsmittel (13) umfasst, das die Steuerflächen (8) und den Träger (81) in einer entfalteten Position verriegelt.
  9. Vorrichtung zum Entfalten und Mitnehmen von Steuerflächen (8) eines Projektils nach Anspruch 8, dadurch gekennzeichnet, dass das zweite Verriegelungsmittel ein Klotz (13) ist, der sich in einer Bohrung (84) der Steuerfläche (8) so anordnet, dass die Steuerfläche (8) mit dem Träger (81) zusammengeschlossen wird.
EP04292854A 2003-12-31 2004-12-02 Vorrichtung zur Entfaltung und Steuerung der Steuerflächen eines Projektils Active EP1550837B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0315601A FR2864613B1 (fr) 2003-12-31 2003-12-31 Dispositif de deploiement et d'entrainement de gouvernes d'un projectile
FR0315601 2003-12-31

Publications (2)

Publication Number Publication Date
EP1550837A1 EP1550837A1 (de) 2005-07-06
EP1550837B1 true EP1550837B1 (de) 2007-04-18

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US (1) US7175131B2 (de)
EP (1) EP1550837B1 (de)
AT (1) ATE360186T1 (de)
DE (1) DE602004005957T2 (de)
ES (1) ES2285382T3 (de)
FR (1) FR2864613B1 (de)

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US11340052B2 (en) 2019-08-27 2022-05-24 Bae Systems Information And Electronic Systems Integration Inc. Wing deployment initiator and locking mechanism
US11852211B2 (en) 2020-09-10 2023-12-26 Bae Systems Information And Electronic Systems Integration Inc. Additively manufactured elliptical bifurcating torsion spring
CN112659011B (zh) * 2020-11-12 2023-03-24 北京星航机电装备有限公司 一种舵面折叠、释放工装及舵面折叠和释放方法
CN112829924B (zh) * 2020-12-31 2022-12-13 上海机电工程研究所 一种可伸缩式鸭舵机构
CN113280689A (zh) * 2021-06-16 2021-08-20 重庆航天工业有限公司 一种舵系统
US20230356828A1 (en) * 2021-09-01 2023-11-09 Raytheon Company Control surface locking system for tactical flight vehicle
CN113804066B (zh) * 2021-09-18 2023-01-10 天津爱思达航天科技有限公司 一种带有同步旋转折叠翼的尾舱结构
CN114370790B (zh) * 2021-12-22 2024-02-06 山西中辐核仪器有限责任公司 一种弹道二维修正机构
CN114963884A (zh) * 2022-03-01 2022-08-30 宁波天擎航天科技有限公司 一种靶弹舵片气动可控展开机构及安装有该机构的靶弹
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Publication number Publication date
US20050151000A1 (en) 2005-07-14
FR2864613A1 (fr) 2005-07-01
FR2864613B1 (fr) 2006-03-17
DE602004005957D1 (de) 2007-05-31
ATE360186T1 (de) 2007-05-15
DE602004005957T2 (de) 2008-01-10
ES2285382T3 (es) 2007-11-16
US7175131B2 (en) 2007-02-13
EP1550837A1 (de) 2005-07-06

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