EP1818646B1 - Ailes déployables flexibles pour missile - Google Patents

Ailes déployables flexibles pour missile Download PDF

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Publication number
EP1818646B1
EP1818646B1 EP07002246.2A EP07002246A EP1818646B1 EP 1818646 B1 EP1818646 B1 EP 1818646B1 EP 07002246 A EP07002246 A EP 07002246A EP 1818646 B1 EP1818646 B1 EP 1818646B1
Authority
EP
European Patent Office
Prior art keywords
fin
wrap
wing
missile
around
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.)
Not-in-force
Application number
EP07002246.2A
Other languages
German (de)
English (en)
Other versions
EP1818646A1 (fr
Inventor
Kuno Roder
Christoph Schleinzer
Jürgen Rühe
Maarten Van Oost
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
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MBDA Deutschland GmbH filed Critical MBDA Deutschland GmbH
Publication of EP1818646A1 publication Critical patent/EP1818646A1/fr
Application granted granted Critical
Publication of EP1818646B1 publication Critical patent/EP1818646B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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 invention relates to a winding wing of a missile according to the preamble of claim 1, comprising two wings forming wing wings, which are at least partially connected to each other in the edge region and the root side in the outer surface of the missile about axes lying in the direction of rotation are rotatably mounted and in the rest position rest on the outer surface of the missile and after deployment in the working position of the winding blade have a predeterminable by means of at least one spring-driven spacer distance of the inner sides of the wing surfaces, wherein in the interior of the winding blade a prestressed spreading device is arranged for the wing surfaces.
  • Missiles are launched from a container in a launcher whose inner diameter is barely greater than the outer diameter of the missile.
  • aerodynamic active surfaces are required. These are folded in a known manner either in recesses of the outer surface of the missile or are mounted in the folded state closely wound on the outer surface of the missile. At the start these aerodynamic active surfaces are transferred immediately after leaving the container of the launcher by means of suitable devices from the rest position to the working position and should remain there in a stable arrangement throughout the flight.
  • winding wings From the DE 36 18 956 C1 is a tail known with deployable wings, which consists of wing surfaces that are connected to each other on the tip side. At the wing root, each of the two wing surfaces has pivot bearings. One of the pivot bearings is a hinged bearing and the other is designed as a hinged plain bearing. As a result, the wing surfaces fold up and wind up on the circumference of the missile. If several such wings are mounted on the missile, they are in the wound state directly above each other and are held by a suitable releasable device on the circumference of the missile until release.
  • the DE 40 25 515 A describes a winding wing for a missile.
  • the winding wing consists of two interconnected metal surfaces, between which resilient prestressed web plates are arranged, which engage in the openings in one of the sheet metal surfaces after the successful erection of the wings. Even with this solution, the desired flexural rigidity was not achieved.
  • a winding wing for a missile has become known, which consists of two at the front and at the rear edge interconnected metal surfaces.
  • a spring-loaded spreader plate is rotatably arranged in the space between the metal surfaces, which is to stabilize the wing surfaces in the erected state in the wing root against buckling.
  • the spring drive of the spreader requires installation space within the contour of the missile body and does not guarantee the required here stability of the unfolded wing.
  • the invention is therefore, issuing from the DE 4 025 515 A ,
  • the object of the invention to improve the principle of a Winding wing to the effect that on the one hand, the benefits of a windable wing can still be used and at the same time a much higher mechanical stiffness against flutter and torsion at the occurrence of said loads is achieved.
  • the spreading device consists of at least two preformed leaf springs, which are interconnected in the region of a common edge and that each spacer element is formed by a flap, the spring-loaded to a axis disposed within the spreading device is rotatably mounted, wherein the width of the flap corresponds to the distance of the inner sides of the wing surfaces in the working position, and that the flap rests in the working position on a resilient stop.
  • the arching of the wing surfaces in two directions creates a stiffness that can not be achieved by a curved in one direction wing surface.
  • several pivotable spacers spread in the working position of the winding blade between the inner sides of the wing surfaces.
  • the spreading device consists of preformed leaf springs, which have an approximately S-shaped curvature and are arranged opposite to the formation of a plane of symmetry.
  • This shape of the leaf springs is particularly well suited, since it can be compressed flat during the winding of the wing and exerts enough spring force on the inner sides of the wing surfaces during the unfolding process, so that the winding wing straightens up easily after release.
  • one end of the S-shaped leaf spring is shaped such that it extends approximately in the center plane of the winding blade, then this design of the leaf spring is particularly suitable for mounting spacers which determine the desired spacing of the inner sides of the wing surfaces.
  • a particularly noteworthy advantage of the winding blade according to the invention is that it can be made particularly easily in terms of the weight of the required components and that the spreading device unfolds in comparison to known embodiments with little effort an excellent spreading and support effect. Furthermore, it is ensured with the help of this design of a nipples that the nipples unfolds safely under all environmental conditions and maintains its shape during the mission.
  • FIGS. 1a and 1b an embodiment of a winding wing for a missile is shown.
  • the winding wing consists of two wing surfaces 1a and 1b, which may be made for example of a thin resilient metal sheet.
  • the two wing surfaces are connected to each other at least at the edges 3a and 3b.
  • the wing surfaces may be connected to each other at the tip side edge 3c.
  • a connection comes in consideration of the desired windability of the wing only a localized connection in question. Best proven the punctiform connection of the edges, which can be achieved for example by spot welding of the existing sheet metal wing surfaces 1a, 1b.
  • Both wing surfaces are connected via pivot bearing with axles 2 on the circumference of the missile, not shown, with the pivot bearing is designed to be laterally displaceable at least one wing surface, so that a mutual approach of the pivot bearing of the two wing surfaces when winding the winding blade can be made on the circumference of the missile.
  • the front wing surface 1 b has been removed to show the spreader 5 in the installed state.
  • the pivot bearing with the axis 2 can be seen, which allows the mechanical connection with the missile, not shown.
  • the front and rear edges 3a and 3b are indicated. At these edges, the wing surfaces 1a and 1b are firmly connected.
  • the spreading device 5 of the two wing surfaces 1 a and 1 b is arranged, which consists in the embodiment of four groups with two leaf springs 7a and 7b and a centrally arranged group with four leaf springs 7a and 7b.
  • This spreading device 5 is placed in the interior 4 of the winding blade, that the forces of the biased in the wound state of the winding blade leaf springs 7a and 7b as evenly distributed on the inner sides of the wing surfaces 1a and 1b act. Also indicated is the punctiform connection 14 of the free legs of the leaf springs 7a, 7b in the area of contact with the respective wing surface 1 a, 1 b.
  • FIG. 2a shows by way of example one of these groups of leaf springs 7a, 7b in detail.
  • the corresponding front view of the side of the edge 11 is in the FIG. 2b shown.
  • the spreading device 5 off FIG. 2a consists of two oppositely preformed leaf springs 7a, 7b, which are designed basically the same except for the designed as a torsion spring attacks10.
  • These leaf springs 7a, 7b consist for example of resilient material and are in the area of the edge 11 locally, in particular pointwise, interconnected 15. Regarding the formation of the cross section of the leaf springs 7a, 7b on FIG. 3b directed.
  • the leaf springs are also attached to the wing surfaces 1a, 1b at least in places, advantageously via point connections.
  • the spacer elements 6 are designed in the embodiment as flaps, which are driven by the torsion springs 9 pivoted from the rest position to the working position. In the rest position, the flaps are flush with the frame 12 in a plane together with the compressed and biased leaf springs 7a, 7b between the inner sides of the wound wing surfaces 1 a, 1 b.
  • the flaps 6 In the unfolding process of the winding blade pivots the pressure of the torsion springs 9, the flaps 6 until reaching the working position, in the FIG. 2a is shown. In the working position, the flaps 6 rest against stops 10 pivoted on their own power, which prevent further pivoting of the flaps 6 beyond the working position.
  • the width D of the flaps 6 corresponds to the locally different distance between the inner sides of the two wing surfaces 1a, 1b in the working position.
  • the resilient stops 10 are design as part of the already made of resilient material leaf springs 7a, 7b.
  • the spacer elements 6 can of course be made in the context of expert action in other design, if it is ensured that the same functionality is achieved. This is that the spacer elements are biased in the rest position and as flat as possible between the inner sides of the wing surfaces 1a, 1 b to arrange.
  • the illustrated embodiment has the advantage in this respect that the flaps used as spacers 6 together with the stops 10 in the rest position have approximately the same material thickness as the compressed leaf springs 7a, 7b.
  • the flaps are locked so far that the depending on the position within the winding blade slightly varying distance D of the inner walls of the wing surfaces 1a, 1b is exactly maintained and maintained during the flight phase. An impressions or fluttering of the wing surfaces is thus avoided.
  • FIG. 3a is exemplary for both wing surfaces in FIG. 2a represented as the front of the two wing surfaces shown wing surface 7a in the installed state.
  • the pre-bent bearings 13 arranged in the frame 12 for the axles 8 of the flaps serving as spacers 6 can also be seen.
  • the S-shaped curvature of the leaf spring 7 a is shown in the top view of FIG. 3b clearly shown.
  • the bending of the torsion springs 10 can be seen. It remains within the scope of the invention to the expert action to use the same effect other embodiments of the leaf springs or attacks.
  • the leaf spring 7b is constructed mirror-symmetrically to the leaf spring 7a. It also has the frame 12 and arranged in the frame correspondingly shaped axle bearings 13. However, the stopper 10 is not provided in the leaf spring 7b.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Springs (AREA)
  • Toys (AREA)
  • Auxiliary Devices For And Details Of Packaging Control (AREA)

Claims (3)

  1. Aile déployable pour un missile comprenant deux faces d'aile (1a, 1b) formant l'aile déployable, qui sont assemblées l'une à l'autre au moins localement dans la région des bords et qui sont montées de façon rotative, du côté de leur pied dans la région de la surface extérieure du missile, autour d'axes (2) situés dans la direction de vol et qui en position de repos sont appliquées sur la surface extérieure du missile et qui, après déploiement dans la position de travail de l'aile déployable, présentent une distance des faces intérieures des faces d'aile pouvant être prédéterminée au moyen d'un élément d'écartement à ressort (6), dans laquelle un dispositif d'expansion précontraint (5) pour les faces d'aile (1a, 1b) est disposé dans l'espace intérieur (4) de l'aile déployable,
    dans laquelle en outre
    - les faces d'aile (1a, 1b) sont assemblées l'une à l'autre au moins localement sur les bords avant et arrière (3a, 3b),
    et
    - ledit au moins un élément d'écartement à ressort (6) à l'état de repos est disposé à plat et est précontraint entre les faces d'aile (1a, 1b) et, après le déclenchement de l'aile déployable, il passe de sa position de repos à sa position de travail et, dès qu'il atteint la position de travail, il maintient les faces intérieures des faces d'aile à la distance (D) prédéterminée correspondant au profilage aérodynamique actif de l'aile déployable,
    caractérisée en ce que
    - le dispositif d'expansion (5) se compose d'au moins deux lames de ressort préformées (7a, 7b) de forme identique opposée, qui sont assemblées l'une à l'autre dans la région d'un bord commun (11),
    - chaque élément d'écartement (6) est formé par un clapet, qui est monté avec ressort (9) de façon rotative autour d'un axe (8) disposé à l'intérieur du dispositif d'expansion (5), dans lequel la largeur du clapet correspond à l'écartement (D) des faces intérieures des faces d'aile (1a, 1b) dans la position de travail, et
    - le clapet repose sur une butée élastique (10) dans la position de travail.
  2. Aile déployable selon la revendication 1, caractérisée en ce que le dispositif d'expansion (5) est disposé dans la région du plan de symétrie (S) entre les faces d'aile (1a, 1b).
  3. Aile déployable selon la revendication 3, caractérisée en ce que les lames de ressort (7a, 7b) présentent une courbure sensiblement en forme de S.
EP07002246.2A 2006-02-10 2007-02-02 Ailes déployables flexibles pour missile Not-in-force EP1818646B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006006160.8A DE102006006160B4 (de) 2006-02-10 2006-02-10 Wickelflügel für einen Flugkörper

Publications (2)

Publication Number Publication Date
EP1818646A1 EP1818646A1 (fr) 2007-08-15
EP1818646B1 true EP1818646B1 (fr) 2016-04-13

Family

ID=38024434

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07002246.2A Not-in-force EP1818646B1 (fr) 2006-02-10 2007-02-02 Ailes déployables flexibles pour missile

Country Status (3)

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EP (1) EP1818646B1 (fr)
DE (1) DE102006006160B4 (fr)
NO (1) NO339906B1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006044945A1 (de) 2006-09-22 2008-04-03 Lfk-Lenkflugkörpersysteme Gmbh Lagerung und Verriegelung für einen Wickelflügel
DE202006020972U1 (de) 2006-09-22 2011-06-01 LFK-Lenkflugkörpersysteme GmbH, 86529 Lagerung und Verriegelung für einen Wickelflügel
CN105806411B (zh) * 2016-04-12 2018-04-20 西北工业大学 飞机旋转折叠翼收放检测装置和方法
DE102019131443B4 (de) * 2019-11-21 2022-03-17 Schunk Kohlenstofftechnik Gmbh Flügel, der klapp­ oder verschwenkbar mit einem Körper verbunden ist

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2923241A (en) * 1957-09-09 1960-02-02 Aerojet General Co Folding stabilizing fins
US3103886A (en) * 1960-10-13 1963-09-17 Charles H Popenoe Coiling fin for tube launched missiles
DE8428118U1 (de) * 1984-09-25 1986-07-03 Rheinmetall GmbH, 4000 Düsseldorf Leitwerk mit entfaltbaren Flügeln
DE3618956C1 (de) * 1986-06-05 1987-11-19 Rheinmetall Gmbh Leitwerk mit entfaltbaren Fluegeln fuer Geschosse und Flugkoerper
SE460738B (sv) * 1988-03-16 1989-11-13 Bofors Ab Foer missiler och andra projektiler avsedd utfaellbar vinge
DE4025515C2 (de) * 1990-08-11 1994-05-11 Deutsche Aerospace Tragflügel für aus einem Rohr startende Flugkörper
DE4025516C2 (de) * 1990-08-11 1994-04-14 Deutsche Aerospace Flugkörpertragflächen-Verriegelungseinrichtung
US5125131A (en) * 1991-01-14 1992-06-30 Hughes Aircraft Company Hinge locking mechanism with disengage action
US5417393A (en) * 1993-04-27 1995-05-23 Hughes Aircraft Company Rotationally mounted flexible band wing

Also Published As

Publication number Publication date
EP1818646A1 (fr) 2007-08-15
DE102006006160B4 (de) 2017-05-24
DE102006006160A1 (de) 2007-08-23
NO339906B1 (no) 2017-02-13
NO20070770L (no) 2007-08-13

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