EP3835710B1 - Missile à déverrouillage pyrotechnique - Google Patents

Missile à déverrouillage pyrotechnique Download PDF

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Publication number
EP3835710B1
EP3835710B1 EP20212241.2A EP20212241A EP3835710B1 EP 3835710 B1 EP3835710 B1 EP 3835710B1 EP 20212241 A EP20212241 A EP 20212241A EP 3835710 B1 EP3835710 B1 EP 3835710B1
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EP
European Patent Office
Prior art keywords
coupling element
movement
missile
output
moved
Prior art date
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Active
Application number
EP20212241.2A
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German (de)
English (en)
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EP3835710A1 (fr
Inventor
Stefan Neukam
Klaus Bär
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.)
Diehl Defence GmbH and Co KG
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Diehl Defence GmbH and Co KG
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Publication of EP3835710A1 publication Critical patent/EP3835710A1/fr
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Publication of EP3835710B1 publication Critical patent/EP3835710B1/fr
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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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means

Definitions

  • the invention relates to a missile.
  • a specific component of a missile should only be activated / moved / ... at a specific time. To do this, this should be locked or unlocked.
  • the canards of a missile should only emerge from the missile at a desired time. It must be ensured that they remain locked in their waiting position until this point and can be unlocked and set up at the right moment.
  • a device for holding and extending canards is known.
  • a device for reducing the sensitivity of tailplane-stabilized combat bodies to lateral flow is known.
  • From the DE 37 21 512 C1 A missile with an over-caliber tail is known, the rudder blades of which are folded into the missile structure for storage, transport and launch and are locked in this position at the front until they are released to unfold by a safety device depending on the launch acceleration.
  • the object of the invention is to propose a solution for a corresponding missile with such a component.
  • the missile contains a device for locking and/or unlocking, in particular only for unlocking, a component locked by a latch.
  • the device comprises at least one latch which can be moved between a block position that locks the component and a release position that releases the component or is moved during unlocking.
  • the device comprises a pyrotechnic force element with an output (output element, output part, ...) which can be or is moved pyrotechnically from a passive position to an active position in response to a trigger signal. The output is therefore moved pyrotechnically.
  • Pyrotechnics is part or the driving element of or in the power element.
  • the device comprises a coupling element through which at least one of the bolts is coupled to the output as follows: A mechanical movement of the bolt from the block position to the release position is caused by a movement of the output from the passive position to the active position or vice versa. A corresponding movement coupling is therefore carried out during operation.
  • latches per component can be provided in the missile and/or a multi-part component can be provided, the respective parts of which are held by one or more latches.
  • Several components can also be provided, each being locked by at least one of the latches, etc.
  • the transition from the release position to the block position can also be caused by the transition from the passive to the active position.
  • the variants can - in the case of several bars - be the same for all bars or be mixed and different. Locking can also take place instead of unlocking, etc.
  • the missile or the device or the locking/unlocking itself is very robust against environmental influences.
  • At least one of the bars is at least partially moved or movable by a rotary movement between the block position and the release position or is moved accordingly during operation.
  • the bolt rotates, in particular around a single, preferably several, axes of rotation, possibly combined with translation. Corresponding movements are particularly favorable for missiles.
  • At least one of the bars is designed in one piece with at least a portion of the coupling element.
  • an or several bars are made in one piece with the entire coupling element.
  • the one-piece object is a stable, rigid, but deformable object (due to the movement of the output) as intended. This leads to a particularly simple and interference-proof design of the device.
  • the coupling element is or is moved by the movement of the output and the bolt is moved based on the movement of the coupling element and/or the coupling element is deformed by the movement of the output and the bolt is moved based on the deformation of the coupling element.
  • the output can therefore cause both movements and deformations on the coupling element.
  • deformation is accompanied by movement.
  • the coupling element is or is moved exclusively by the movement of the output and the bolt is moved based on the movement of the coupling element. So there is no deformation.
  • Such a device can be implemented in particular with very little force (the output has to apply little force).
  • the coupling element is a joint arrangement with at least one joint, i.e. H. the coupling element contains at least one joint.
  • This embodiment is particularly suitable in combination with the exclusive movement without deformation, as explained above.
  • a combination of deformation and joint arrangement is also conceivable.
  • the force element has a base body and the output is movable relative to the base body between the passive position and the active position or is moved accordingly.
  • the output in particular carries out a linear movement with respect to the base body.
  • Such force elements are commercially available.
  • the base body is attached to a fixed structure (e.g. base structure/support structure/shell/...) of the missile, so that the output acts as an actuator that moves relative to the fixed structure.
  • the device contains at least one support that is stationary relative to the base body.
  • the coupling element rests on the support (at least in the active or passive position of the output).
  • the support is or forms a rotating and/or displacement point for the movement (rotation and/or translation) of the coupling element.
  • the support is formed by a part of the above-mentioned fixed structure of the missile, so that the output acts as an actuator that moves relative to the support.
  • the device contains at least two supports and the coupling element is a - in particular deformable - body which rests on both supports (at least in the active or passive position of the output).
  • the output is connected to the coupling element between the supports in a deforming and/or moving manner (see the options above).
  • the force element is triggered or the output moves, the coupling element is deformed and/or moved between the two supports.
  • the coupling element or the body is or is pulled between the supports when it is deformed and / or moved by the output and at least one of the bars is positioned over one of the supports, in particular outwards ("outside”: In particular, a section of the coupling element or body that protrudes beyond the point of engagement of the output and/or the two supports, i.e. not between them, is formed. Due to the deformation and/or movement of the body between the supports, the part/section of the coupling element that projects beyond the supports and thus the bolt is also moved. This leads to a particularly simple solution in terms of construction.
  • the component is a wing of the missile.
  • the wing is in particular a tail unit, rudder, canard, etc.
  • Corresponding wings can be developed particularly easily thanks to the invention.
  • the bolt is at least rotated, i.e. moved in a rotational manner, in particular additionally moved in a translational manner. This has already been explained above in connection with the missile.
  • the coupling element is moved and/or deformed in order to move the latch. This has already been explained above in connection with the missile.
  • the coupling element is placed on two supports and deformed and/or moved between them. This has already been explained above in connection with the missile.
  • the invention is based on the following findings, observations and considerations and also has the following embodiments.
  • the embodiments are sometimes also called “the invention” for simplicity.
  • the embodiments can also contain parts or combinations of the above-mentioned embodiments or correspond to them and/or possibly also include previously unmentioned embodiments.
  • the invention is based on the idea of a rigid and/or articulated structure (output/coupling element/bolt), which holds a component, in particular canards, in a waiting position (locked position) via a latch, in particular a retaining lug (nose). If the release of the component, e.g. B. the canards, a pyrotechnic force element is ignited and deforms and / or moves them Structure. The retaining lugs (latches) move away from the component (canard) and unlock it, giving it e.g. B. the opportunity to position yourself.
  • the invention is very robust against environmental influences. There is no need for freely moving parts that can come loose due to vibrations or shocks. There are no bearings necessary or present that could solidify due to corrosion.
  • the invention has no gears or freely moving parts.
  • the required movement is generated in particular by deformation and/or displacement. This results in a high level of resistance to misbehavior and environmental influences.
  • the system has hardly any tolerances and is easy to manufacture. The system can be used where space is limited.
  • the invention is based on the basic idea and works by deforming and/or moving a structure (output/coupling element/bolt).
  • the structure is presented in particular as a beam with two supports, which are located away from the ends of the beam within the length of the beam.
  • a force is applied to the beam between the supports by a pyrotechnic force element (its output).
  • its output By loading the structure, the free ends of the beam are raised and unlock the canards suspended there. Due to a self-securing force element (the output is secured in particular in the active position) and a plastic deformation of the structure (the coupling element), the unlocking remains active and prevents locking again.
  • a pyrotechnic unlocking there is a pyrotechnic unlocking.
  • a structure (coupling element) is forced into a desired deformation by a pyrotechnic force element and the structure thereby releases the lock.
  • the invention can be used in a projectile to prevent accidental unlocking of the component or the canards and to achieve a desired unlocking via an electrical impulse from the electronics. This means that the component / the canards can be unlocked / come out of the projectile at a desired time.
  • Figure 1 shows a schematic diagram of a section of a missile 2, not shown, which contains a device 4.
  • the missile 2 extends along a central longitudinal axis 3.
  • the device 4 is used to unlock four (see also Fig. 3 ), each locked by a latch 6, not shown components 8, of which in Figure 1 only one is indicated as an example.
  • Figure 1a shows the component 8 in the locked state, when a nose 10 of a latch 6 engages behind a projection 12 of the component 8 and thus prevents the component 8 from moving in the direction of the arrow 14.
  • the device 4 has four bars 6, of which in Figure 1a only two are visible.
  • Figure 1a shows a block position PB of the bars 6, in which they lock the respective components 8.
  • the latches 6 can be moved into a release position FP, in which they release the respective component 8, as in Figure 1b is shown.
  • the component 8 can then move in the direction of the arrow 14.
  • the device 4 contains a pyrotechnic force element 16 with an output 18 in the form of an output element, here a tension bolt.
  • the force element 16 contains a base body 20, which is fixed in a cup-shaped recess 22 of a support structure 24 of the device 4 or the missile 2.
  • the output 18 is linear relative to the base body 20 in the direction of an arrow 26 in response to a trigger signal SA (only indicated symbolically here) pyrotechnically from a passive position PP ( Figure 1a ) into an active position PA ( Figure 1b ) movable.
  • SA a trigger signal
  • the device 4 contains a coupling element 27.
  • the coupling element 27 is fixed to the output 18 by a screw connection (thread in the output 18, hole in the coupling element 27, screwed-in screw with washer).
  • the bars 8 are motion-coupled with the output 18 as follows: a movement of the output 18 from the passive position PP to the active position PA in the direction of the arrow 26 causes a movement of the bars 6 from the block position PB to the release position PF. This is achieved by the tensile screw connection of the output 18 to the coupling element 27 explained above.
  • the corresponding movement coupling is through the Figures 1a , b shown.
  • the bars 6 are designed in one piece with the coupling element 27 or its respective sections 32, here end sections (see also Figure 3 ).
  • the coupling element 27 is designed here in the shape of a cross or two crossed bars.
  • the movement of the bars 6 takes place through a combination of a rotary or rotational movement (arrow 28) and a translational or displacement movement (arrow 30), which in Figure 1b is indicated.
  • the movement takes place on or around a support 36 or its pivot and displacement point 38.
  • Figure 1b It can be seen that the coupling element 27 is both moved and deformed by the movement of the output 18 in the direction of the arrow 26. The deformation occurs in the form of a bend in the area 34 of the coupling element 27. Due to the deformation and bending, the bars 6 are moved. In Figure 1b is thanks to the deformation that has occurred Figure 1b now also the (end) section 32 of a third arm/beam of the coupling element 27 and a third bar 6 formed onto it in its release position FP in the middle of the image.
  • the device 4 contains a total of four supports 36 on which the coupling element 27 rests.
  • the supports 36 form a respective pivot and displacement point 38 for the movement of the coupling element 27.
  • the supports 36 are here designed together as an annular collar 37 of the support structure 24, surrounding the central longitudinal axis 3 in a ring, whereby Figure 1a , b shows alternative variants (left and right in the picture) of a collar cross section. In reality, the collar 37 is particularly uniform.
  • the coupling element 27 is a body that is rigid in the positions PB, PF or states PA, PP, but can be deformed by the output 18 during the transition between them and rests on the four supports 36.
  • the output 18 is therefore deforming between the supports 36 on the coupling element 27, here by the above-mentioned screw connection in the output 18.
  • the coupling element 27 (in Figure 1 in the middle and downwards) between the supports 36.
  • the bars 6 each form sections 32 of the coupling element 27 that project outwards via the supports 36, i.e. viewed from the connection point of the output 18 beyond the supports 36.
  • the procedure is as follows:
  • the latches 6 are moved from the block position PB, which locks the components 8, into the release position PF, which releases the components 8.
  • the output 18 of the pyrotechnic force element 16 is moved pyrotechnically from the passive position PP into the active position PA in response to the trigger signal SA.
  • the coupling element 27 couples the bolt 6 with the output 18 according to a movement coupling in such a way that the movement of the output 18 from the passive position PP to the active position PA causes the mechanical movement of the bolt 6 from the block position PB to the release position PF.
  • the component 8 is thus released or unlocked by the latch 6.
  • the latch 6 is rotated (arrow 28) and moved (arrow 30).
  • the coupling element 27 is moved and deformed to move the latch 6.
  • the coupling element 27 is placed on four supports 36 and deformed between them, i.e. in Figure 1 pulled downwards and thereby bent.
  • Figure 2 shows the arrangement Figure 1 , but with an alternative coupling element 27.
  • This is now a joint arrangement and has a total of four joints 40.
  • the coupling element 27 is no longer deformed, but rather the coupling element 27 or its joints 40 are only moved.
  • the bars 6 are moved exclusively by the movement and no longer by the deformation of the coupling element 27. Otherwise, the above applies Figure 1
  • Figure 3 shows the top view in the direction of arrow III of the arrangements from the Figures 1 and 2 .
  • the joints 40 with their respective axes of rotation 42 according to Figure 2 are indicated by dashed lines as a variant of the deformable coupling element 27.
  • the circular collar 37, which forms the supports 36 and pivot and displacement points 38 in the area of the coupling element 27, is again clearly visible.
  • the Coupling element 27 with four arms and four integrally formed bars 6 is designed as a holding cross.
  • Figure 4 shows in a view according to the Figures 1 and 2 a section of an alternative missile 2.
  • the components 8 here are wings 44 in the form of canards.
  • Figure 4 shows the block position PB or passive position PP of the bolt 6 as well as a locked wing 44 in the picture on the right.
  • the release position PF of the bolt 6 and the associated position / state of the coupling element 27 are also shown in dashed lines for an active position PA.
  • an unlocked wing 44 that has emerged from the missile 2 or its casing 46 or outer contour is shown in dashed lines on the left.
  • the coupling element 27 is shown here again without a joint and is therefore deformed when unlocking.
  • the coupling element 27 can also be used Fig. 2 be used.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Transmission Devices (AREA)

Claims (12)

  1. Missile (2) avec un dispositif (4) pour le verrouillage et/ou le déverrouillage d'un composant (8) verrouillé par un verrou (6),
    - avec l'au moins un verrou (6) qui peut être déplacé entre une position de blocage (PB) verrouillant le composant (8) et une position de libération (PF) libérant le composant (8),
    - avec un élément de force pyrotechnique (16) avec une sortie (18), qui, en réponse à un signal de déclenchement (SA), peut être déplacé par voie pyrotechnique d'une position passive (PP) à une position active (PA),
    - avec un élément de couplage (27) par lequel au moins l'un des verrous (6) est couplé en déplacement à la sortie (18) de telle sorte qu'un déplacement mécanique du verrou (6) de la position de blocage (PB) à la position de libération (PF) est conditionné par un déplacement de la sortie (18) de la position passive (PP) à la position active (PA) ou inversement,
    l'élément de force (16) présentant un corps de base (20) et la sortie (18) pouvant être déplacée par rapport au corps de base (20) entre la position passive (PP) et la position active (PA), et caractérisé en ce que le dispositif (4) contient au moins un appui fixe par rapport au corps de base (20), sur lequel repose l'élément de couplage, l'appui (36) étant un point de rotation et/ou de coulissement (38) pour le déplacement de l'élément de couplage (27).
  2. Missile (2) selon la revendication 1, caractérisé en ce qu'au moins l'un des verrous (6) est déplacé au moins en partie par un déplacement de rotation entre la position de blocage (PB) et la position de libération (PF) .
  3. Missile (2) selon l'une quelconque des revendications précédentes, caractérisé en ce qu'au moins l'un des verrous (6) est réalisé d'un seul tenant avec au moins une section (32) de l'élément de couplage (27).
  4. Missile (2) selon l'une quelconque des revendications précédentes, caractérisé en ce que l'élément de couplage (27) est déplacé et/ou déformé par le déplacement de la sortie (18) et le verrou (6) est déplacé à partir du déplacement et/ou de la déformation de l'élément de couplage (27).
  5. Missile (2) selon la revendication 4, caractérisé en ce que l'élément de couplage (27) est déplacé exclusivement par le déplacement de la sortie (18) et le verrou (6) est déplacé par le déplacement de l'élément de couplage (27).
  6. Missile (2) selon l'une quelconque des revendications précédentes, caractérisé en ce que l'élément de couplage (27) est un agencement articulé avec au moins une articulation (40).
  7. Missile (2) selon l'une quelconque des revendications précédentes, caractérisé en ce que le dispositif (4) contient au moins deux appuis (36) et l'élément de couplage (27) est un corps qui repose sur les deux appuis (36), la sortie (18) étant reliée à l'élément de couplage (27) entre les appuis (36).
  8. Missile (2) selon la revendication 7, caractérisé en ce que l'élément de couplage (27) est tiré entre les appuis (36) lors de la déformation et/ou du déplacement et au moins l'un des verrous (6) est réalisé sous la forme d'une section (32) de l'élément de couplage (27) dépassant de l'un des appuis (36).
  9. Missile (2) selon l'une quelconque des revendications précédentes, caractérisé en ce que le composant (8) est une aile (44) du missile (2).
  10. Procédé de verrouillage et/ou de déverrouillage d'un composant (8) d'un missile (2) verrouillé par un verrou (6), dans lequel
    - le verrou (6) est déplacé d'une position de blocage (PB) verrouillant le composant (8) à une position de libération (PF) libérant le composant (8),
    - une sortie (18) d'un élément de force pyrotechnique (16) étant déplacée par voie pyrotechnique d'une position passive (PP) à une position active (PA) en réponse à un signal de déclenchement (SA),
    - un élément de couplage (27) couplant en déplacement le verrou (6) à la sortie (18) de telle sorte que le déplacement de la sortie (18) de la position passive (PP) à la position active (PA) conditionne le déplacement mécanique du verrou (6) de la position de blocage (PB) à la position de libération (PF) ou inversement, caractérisé en ce que
    l'élément de couplage (27) est posé sur deux appuis (36) et est déformé et/ou déplacé entre ceux-ci.
  11. Procédé selon la revendication 10, caractérisé en ce que le verrou (6) est au moins tourné.
  12. Procédé selon l'une quelconque des revendications 10 à 11, caractérisé en ce que l'élément de couplage (27) est déplacé et/ou déformé afin de déplacer le verrou (6).
EP20212241.2A 2019-12-10 2020-12-07 Missile à déverrouillage pyrotechnique Active EP3835710B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102019008539.6A DE102019008539A1 (de) 2019-12-10 2019-12-10 Flugkörper mit pyrotechnischer Entriegelung

Publications (2)

Publication Number Publication Date
EP3835710A1 EP3835710A1 (fr) 2021-06-16
EP3835710B1 true EP3835710B1 (fr) 2024-02-21

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EP20212241.2A Active EP3835710B1 (fr) 2019-12-10 2020-12-07 Missile à déverrouillage pyrotechnique

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EP (1) EP3835710B1 (fr)
DE (1) DE102019008539A1 (fr)
ZA (1) ZA202007590B (fr)

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3304030A (en) * 1965-09-24 1967-02-14 James E Weimholt Pyrotechnic-actuated folding fin assembly
DE2264337A1 (de) * 1972-12-30 1974-07-04 Dynamit Nobel Ag Verfahren zur stabilisierung der flugbahn und regelung der reichweite von raketenflugkoerpern
DE3222378A1 (de) * 1982-06-15 1983-12-15 Dynamit Nobel Ag, 5210 Troisdorf Vorrichtung zur verringerung der empfindlichkeit leitwerksstabilisierter, in luft und/oder wasser sich bewegender gefechtskoerper gegen seitliche anstroemung
DE3328520C1 (de) * 1983-08-06 1985-03-07 Diehl GmbH & Co, 8500 Nürnberg Schwenkleitwerk fuer Flugkoerper
DE3721512C1 (de) * 1987-06-30 1989-03-30 Diehl Gmbh & Co Flugkoerper mit ueberkalibrigem Leitwerk
GB2274904A (en) * 1993-02-05 1994-08-10 British Aerospace Deployable wing
US6446906B1 (en) * 2000-04-06 2002-09-10 Versatron, Inc. Fin and cover release system
US8338769B1 (en) * 2008-02-07 2012-12-25 Simmonds Precision Products, Inc. Pyrotechnic fin deployment and retention mechanism
FR2986319B1 (fr) * 2012-01-27 2014-03-14 Tda Armements Sas Troncon de pilotage pour munition guidee
US9012825B2 (en) * 2013-01-23 2015-04-21 Simmonds Precision Products, Inc. Systems and methods for retaining and deploying canards

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DE102019008539A1 (de) 2021-06-10
ZA202007590B (en) 2021-10-27
EP3835710A1 (fr) 2021-06-16

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