EP3032213B1 - Systeme de ailette rabattable - Google Patents

Systeme de ailette rabattable Download PDF

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Publication number
EP3032213B1
EP3032213B1 EP15003429.6A EP15003429A EP3032213B1 EP 3032213 B1 EP3032213 B1 EP 3032213B1 EP 15003429 A EP15003429 A EP 15003429A EP 3032213 B1 EP3032213 B1 EP 3032213B1
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EP
European Patent Office
Prior art keywords
fin
axle
wing
axle holder
groove
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
EP15003429.6A
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German (de)
English (en)
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EP3032213A1 (fr
Inventor
Jörg Lutzenberger
Wolf-Diether Mast
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.)
MBDA Deutschland GmbH
Original Assignee
MBDA Deutschland GmbH
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Filing date
Publication date
Priority claimed from DE102015004703.5A external-priority patent/DE102015004703B4/de
Application filed by MBDA Deutschland GmbH filed Critical MBDA Deutschland GmbH
Publication of EP3032213A1 publication Critical patent/EP3032213A1/fr
Application granted granted Critical
Publication of EP3032213B1 publication Critical patent/EP3032213B1/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
    • F42B10/16—Wrap-around fins

Definitions

  • the subject matter of this invention is the flap-wing system described below, in particular a self-locking folding-wing concept, which has been realized with the objectives of robustness, reliability and minimization of the manufacturing costs. This was achieved through the use of as few components as possible, a functional and production-optimized design of the production parts and the use of standard components.
  • Folding wing systems are known from the prior art. Folding wing systems are always used when a missile needs a wing to stabilize its flight, but at the same time should be started from a, usually cylindrical, launch tube. In this case, flap wing systems are used with the wing folded in to accommodate the missile in the launch tube. As soon as the missile is launched and leaves the launch tube, the wing goes into unfolded state, so that the missile can be steered.
  • known systems In known systems, however, it is disadvantageous that they are very complicated and thus expensive to manufacture. In addition, known systems are not usable for a plurality of missiles, in particular, known systems are not scalable or adaptable.
  • the object is achieved by a folding wing system that a wing root and a
  • Wing top includes.
  • the upper wing part is rotatably mounted on the wing root.
  • the wing top is movable between a deployed position and a retracted position.
  • the movement is a rotation of the wing top relative to the wing root.
  • the wing root and the wing upper part can be locked against each other via a tongue-and-groove system when the wing upper part is in the unfolded position.
  • the locking by means of tongue and groove ensures that the upper wing part can not be moved out of the unfolded position. This ensures that the folding leaf system can develop its wing effect, without this being disturbed by accidental collapse of the upper wing part.
  • the wing root can be applied in particular to a missile shell from the outside and can be fastened thereto, in particular by fastening elements such as screws, rivets or an adhesive bond.
  • the folding wing is characterized by the possibility of scaling and simple adaptation to other missiles, since the wings do not interfere with the shell of the missile.
  • the wing root may be made integral with the missile section (e.g., precision extruders) or externally applied to the missile section.
  • the upper wing part is mounted on the wing root via an axis.
  • the wing root on a first axle
  • the upper wing part has a second axle.
  • the axle is arranged within the first axle receptacle and the second axle receptacle.
  • the first axle receptacle comprises at least a first axle receiving element
  • the second axle comprises at least one second axle receiving element.
  • Particularly advantageous are a plurality of first axle receiving elements and a plurality of second axle receiving elements, wherein in particular the number of first axle receiving elements and second Axle receiving elements is the same.
  • the axis is guided alternately within the first axle receiving element and the second axle receiving element. This results in a connection of the wing shell to the wing root in the manner of a hinge.
  • each first axle receiving element is associated with exactly one second axle receiving element.
  • the first axle receiving element has a groove, while the associated second axle receiving element has a corresponding spring.
  • the first axle receiving element has a spring, while the associated second axle receiving element has a corresponding groove.
  • the spring can be introduced into the groove parallel to the axis by a relative movement between the upper wing part and the wing root.
  • the groove and the spring each have a tapering region with tapered flanks and an end region with parallel flanks. It is particularly advantageous if the tapered flanks bevels in the parallel Flanks are.
  • the tapering region of the spring first of all the tapering region of the spring has to be introduced into the tapering region of the groove, which is simplified by the tapered flanks or chamfers.
  • the flanks of the end portions block relative movement between the tongue and groove in all directions except along the direction of insertion of the spring into the groove.
  • a rotation of the blade upper part about the axis is prevented.
  • the elastic element is a compression spring.
  • the compression spring is supported particularly advantageous at a first end of the axle and on a first axle receiving element.
  • a second end of the axle is supported on a second axle receiving element.
  • the translation required for locking preferably takes place counter to the direction of flight of the folding leaf system, so that mass inertia during acceleration and aerodynamic forces can enhance the effect of the elastic element and not weaken it.
  • the first axle receiving member or the second axle receiving member preferably includes a stop that blocks movement of the blade top relative to the wing root beyond the deployed position. This ensures that in that, when the wing top part is unfolded relative to the wing root, the wing top part is stopped in the unfolded position so that the spring can be introduced into the groove, whereby the blocking or locking of the wing top part takes place relative to the wing root.
  • the folding leaf system also preferably has an elastic rotary element, wherein a spring force of the elastic rotary element urges the wing upper part in the unfolded position.
  • an external force must act on the folding leaf system, in particular on the wing top, to hold the wing top in the folded position.
  • the spring force of the elastic rotary member causes the blade top to move relative to the wing root to move to the deployed position.
  • the wing upper part is pressed by the elastic rotary member against the stop. If, in addition, the described elastic element is mounted on the axle, a locking of the folding leaf system automatically takes place, since the spring is introduced into the groove by the elastic spring force of the elastic element.
  • the elastic rotary element is particularly advantageous a leg spring.
  • the elastic rotary element has a first leg which is inserted into a bore of the upper wing part.
  • the elastic rotary element has a second leg, which is angled relative to the first leg by a bias angle.
  • the second leg is advantageously on the wing root or lies in a pocket provided in the wing root.
  • FIG. 1 schematically shows a folding wing system 10 according to an embodiment of the invention.
  • the folding wing system 10 comprises a wing top 4 and a wing root 3 and an axis 5, wherein the axis 5 of the Wing upper part 4 rotatably supported on the wing root 3.
  • the wing root 3 is detailed in FIG. 8 shown while the wing top 4 in detail FIG. 7 is shown.
  • the wing root 3 comprises a first axle receptacle 11 and the wing upper part 4 comprises a second axle receptacle 12, the first axle receptacle 11 having a plurality of first axle receiving elements 15, while the second axle receptacle 12 comprises a plurality of second axle receiving elements 16.
  • the folding leaf system 10 has a plurality of elastic rotary elements 1 or leg springs 1.
  • leg springs 1 are shown, which are arranged substantially symmetrically about a center, wherein the center of the axis 5 divided into two substantially equal length axle parts.
  • the structure of the torsion springs 1 is in FIG. 3 shown.
  • the torsion springs 1 comprise a first leg 17, a spring body 19, and a second leg 18.
  • the torsion springs 1, the spring body 19 are mounted on the axis 5 with the upper wing part 4, based on the second leg 18 on the side of the wing root third from. On holes or pockets in the wing root 3 can be dispensed with.
  • the second leg 18 can be supported on the side of the wing root 3, the leg spring 1 as in FIG. 3 represented, designed.
  • the second leg 18 is a bias angle ⁇ with respect to the first leg 17th angled.
  • the bias voltage can be defined.
  • the issued second leg 18 of the leg spring 1 can slide on the side of the wing root 3.
  • the first leg 17 of each leg springs 1 is inserted into a respective bore of the upper wing part 4.
  • an elastic element 2 or a compression spring 2 is further mounted, which pulls the axis 5 via the nut 6 together with the upper wing part 4 to the rear and thus pressed together by the upper wing part 4 and wing root 3 hinge elements.
  • the compression spring 2 is supported on the washer 8 on the axis 5 via the washer 7.
  • the folding wing system 10 is constructed like a hinge.
  • the torsion spring 1 causes the rotational erection of the upper wing part 4,
  • the compression spring 2 is a translational movement of the wing upper part 4 relative to the wing root 3 for locking the end position, that is, the unfolded position.
  • the folding wing system 10 has a tongue-and-groove system 13, 14. This is in FIG. 4 and FIG. 5 shown.
  • FIG. 4 In each case, a first axle receiving element 15 and a second axle receiving element 16 are shown, whereas FIG. 5 shows the entire folding leaf system 10 according to the embodiment in a folded position.
  • the first Achsageelement 15 a spring 13 while the second Achsageelement 16 has a groove 14. According to the arrangement of groove 14 and spring 13 can be reversed.
  • the spring 13 and the groove 14 each have a tapering region 20 and an end region 21.
  • the tapering region 20 is characterized by conically tapered flanks, while the flanks in the end region 21 run parallel at least in sections. If a parallel course is completely dispensed with, a much stronger spring must be used for translation, since otherwise the upper wing part 4 can be folded over the conical flanks again.
  • the load transfer which is ensured by positive engagement with parallel flanks, must be realized by waiving parallel flanks by adhesion, which must be achieved by the higher bias in translation direction. This manifests itself in an increase in the frictional force on the bearing surfaces of the axle receiving elements 15, 16 and thus also causes a higher bias of the elastic rotary elements 1 for the rotational movement.
  • the positive connection is therefore preferable.
  • the tapering portion 20 of the spring 13 In order to insert the spring 13 into the groove 14, first the tapering portion 20 of the spring 13 must be inserted into the tapering portion 20 of the groove 14. Due to the conical tapered flanks this is simplified. Subsequently, the spring 13 can be completely inserted into the groove 14, wherein the end portions 21 overlap at least in sections. It is envisaged that the end regions 21 cause a form fit, so that all relative movements between the first axle receiving element 15 and second axle receiving element 16 with the exception of movements along the direction of insertion of the spring 13 are blocked in the groove 14. In particular, a rotation of the upper wing part 4 about the axis 5 is prevented, so that the upper wing part 4 is locked in the unfolded position and thus fixed.
  • the tapering regions 20 are in particular formed such that the parallel flanks of the end region 21 have chamfers. Thus, the taper portion 20 of the spring 13 and the groove 14 is very easy to manufacture.
  • the locking of the upper wing part 4 on the wing root 3 is then as follows: Through the chamfers within the tapering portion 20 of spring 13 and groove 14 is a simplified threading of the spring 13 into the groove 14. At the respective chamfer of the groove 14 is followed parallel straight course of the groove flanks, in which the correspondingly shaped spring 13 engages positively in the end position.
  • FIG. 5 shows the position of the retracted folding leaf system 10 and the grooves 14 and spring 13 of the first Achsagen comprise 15 and second Achsability electrode 16th
  • the first axle receiving elements 15 of the upper wing part 4 have stops 9, as in FIG. 6 is shown. These stop the rotation of the blade top 4 in the end position, ie, in the unfolded position, which results from the righting effect of the torque of the torsion springs 1.
  • the grooves 14 and the springs 13 are held in the aligned position, so that a simple and reliable locking takes place.
  • the folding wing system 10 is very simple and therefore inexpensive. In addition, the folding wing system 10 is easily scalable and thus adaptable for different missiles.
  • folding wing system 10 Another advantage of the folding wing system 10 is that it does not engage in the shell of the missile, so that a very simple and inexpensive installation of the folding leaf system 10 is made possible on the steering wing body.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Pivots And Pivotal Connections (AREA)

Claims (8)

  1. Système à ailette rabattable (10), comprenant :
    - une emplanture (3),
    - une partie supérieure d'ailette (4) logée de manière rotative sur l'emplanture (3) par l'intermédiaire d'un axe (5),
    - dans lequel l'emplanture (3) comprend un premier logement d'axe (11) muni d'au moins un élément de logement d'axe (15) et dans lequel la partie supérieure d'ailette (4) comprend un deuxième logement d'axe (12) muni d'au moins un deuxième élément de logement d'axe (16), et dans lequel l'axe (5) est disposé à l'intérieur du premier logement d'axe (11) et du deuxième logement d'axe (12),
    - dans lequel la partie supérieure d'ailette (4), par rapport à l'emplanture (3), est déplaçable entre une position déployée et une position rentrée, et
    - dans lequel la partie supérieure d'ailette (4) et l'emplanture (3) sont verrouillables l'une contre l'autre par l'intermédiaire d'un système à rainure et languette (13, 14), lorsque la partie supérieure d'ailette (4) se trouve dans la position déployée,
    - dans lequel à chaque élément de logement d'axe (15) est associé un deuxième élément de logement d'axe (16), dans lequel le premier élément de logement d'axe (15) présente une rainure (14) et le deuxième élément de logement d'axe (16) associé présente une languette (13) correspondante, dans lequel la rainure (13) et la languette (14) présentent une partie de rétrécissement (20) dotée de flancs se rejoignant coniquement et une partie terminale (21) dotée de flancs s'étendant parallèlement au moins par sections,
    ou
    dans lequel le premier élément de logement d'axe (15) présente une languette (13) et le deuxième élément de logement d'axe (16) associé présente une rainure (14) correspondante, dans lequel la rainure (13) et la languette (14) présentent une partie de rétrécissement (20) dotée de flancs se rejoignant coniquement et une partie terminale (21) dotée de flancs s'étendant parallèlement au moins par sections.
  2. Système à ailette rabattable (10) selon la revendication 1, caractérisé en ce que la languette (14) peut être introduite dans la rainure (13) parallèlement à l'axe (5) par un mouvement relatif entre la partie supérieure d'ailette (4) et l'emplanture (3).
  3. Système à ailette rabattable (10) selon l'une quelconque des revendications précédentes, caractérisé en ce que les flancs se rejoignant coniquement sont des chanfreins dans les flancs parallèles au moins par sections.
  4. Système à ailette rabattable (10) selon l'une quelconque des revendications précédentes, caractérisé en ce que sur l'axe (5) est logé un élément élastique (2) qui presse chaque premier élément de logement d'axe (15) sur le deuxième élément de logement d'axe (16) respectivement associé.
  5. Système à ailette rabattable (10) selon l'une quelconque des revendications précédentes, caractérisé en ce que le premier élément de logement d'axe (15) ou le deuxième élément de logement d'axe (16) présente une butée (9) qui bloque un mouvement de la partie supérieure d'ailette (4) par rapport à l'emplanture (3) au-delà de la position déployée.
  6. Système à ailette rabattable (10) selon l'une quelconque des revendications précédentes, caractérisé par un élément de rotation (1) élastique, une force de ressort de l'élément de rotation (1) élastique poussant la partie supérieure d'ailette (4) en la position déployée.
  7. Système à ailette rabattable (10) selon la revendication 6, caractérisé en ce que l'élément de rotation (1) élastique présente une première branche (17) qui est guidée dans un trou de la partie supérieure d'ailette (4) .
  8. Système à ailette rabattable (10) selon l'une quelconque des revendications 6 ou 7, caractérisé en ce que l'élément de rotation (1) élastique présente une deuxième branche (18) qui est repliée d'un angle de prétension (a) par rapport à la première branche (17), la deuxième branche (18) étant adjacente à l'emplanture (3).
EP15003429.6A 2014-12-11 2015-12-02 Systeme de ailette rabattable Active EP3032213B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014018258 2014-12-11
DE102015004703.5A DE102015004703B4 (de) 2014-12-11 2015-04-09 Klappflügelsystem

Publications (2)

Publication Number Publication Date
EP3032213A1 EP3032213A1 (fr) 2016-06-15
EP3032213B1 true EP3032213B1 (fr) 2018-06-20

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EP15003429.6A Active EP3032213B1 (fr) 2014-12-11 2015-12-02 Systeme de ailette rabattable

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EP (1) EP3032213B1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102021005973A1 (de) 2021-12-03 2023-06-07 Diehl Defence Gmbh & Co. Kg Geschoss mit federlos ausschwenkbaren Finnen

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017113058B4 (de) 2017-06-14 2023-04-27 Deutsches Zentrum für Luft- und Raumfahrt e.V. Raumtransport-Fluggerät
CN110579139B (zh) * 2019-09-03 2023-10-20 中国空空导弹研究院 一种可调式扭簧驱动展开导弹舵面及装配工艺

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2356118A1 (fr) * 1976-06-25 1978-01-20 Europ Propulsion Empennage pour projectile
US4673146A (en) * 1983-08-15 1987-06-16 General Dynamics, Pomona Division Missile tail fin assembly
US6186442B1 (en) * 1998-09-04 2001-02-13 The United States Of America As Represented By The Secretary Of The Army Wing deployer and locker
US6739548B1 (en) * 2003-04-21 2004-05-25 The United States Of America As Represented By The Secretary Of The Army Fin lock system
DE102004039770A1 (de) 2004-08-16 2006-03-02 Diehl Bgt Defence Gmbh & Co. Kg Flügelanordnung

Non-Patent Citations (1)

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102021005973A1 (de) 2021-12-03 2023-06-07 Diehl Defence Gmbh & Co. Kg Geschoss mit federlos ausschwenkbaren Finnen
EP4191194A1 (fr) 2021-12-03 2023-06-07 Diehl Defence GmbH & Co. KG Projectile avec des ailettes déployables sans ressort

Also Published As

Publication number Publication date
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