EP2083238B1 - Aile pliable dotée d'un dispositif de dépliage - Google Patents

Aile pliable dotée d'un dispositif de dépliage Download PDF

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Publication number
EP2083238B1
EP2083238B1 EP20090000744 EP09000744A EP2083238B1 EP 2083238 B1 EP2083238 B1 EP 2083238B1 EP 20090000744 EP20090000744 EP 20090000744 EP 09000744 A EP09000744 A EP 09000744A EP 2083238 B1 EP2083238 B1 EP 2083238B1
Authority
EP
European Patent Office
Prior art keywords
fin
folding
root
wing
traction cable
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
EP20090000744
Other languages
German (de)
English (en)
Other versions
EP2083238A3 (fr
EP2083238A2 (fr
Inventor
Klaus Baumgartner
Herbert Gleisinger
Jürgen Rühe
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 EP2083238A2 publication Critical patent/EP2083238A2/fr
Publication of EP2083238A3 publication Critical patent/EP2083238A3/fr
Application granted granted Critical
Publication of EP2083238B1 publication Critical patent/EP2083238B1/fr
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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
    • 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 invention relates to a folding wing with an actuating means arranged within the folding wing, which is connected to a pull rope, which is guided via at least one device for changing direction and which is fastened at the other end to a part of the folding wing.
  • Missiles are usually stored in a launcher until their launch.
  • This launcher is dimensioned in the dimensioning of the interior so that the missile can only be accommodated therein with hinged wings or tail wings. This has led to the development of various embodiments of folding wings and corresponding devices for the deployment of the folding wings.
  • a deployment system for folding wings in which an actuator causes a pulling operation on a rope, whereby the pivotally mounted part of the folding wing is transferred from the transport to the functional position.
  • the actuator works hydraulically or electromagnetically.
  • the triggering of the actuator leads to a linear movement of an actuating means, wherein the pull rope is deflected both at the free end of the actuating means and on a deflection roller.
  • the proposed actuator requires in any case additional installation space for the required for triggering other facilities.
  • this is the reservoir for the hydraulic fluid and the means for generating the required pressure.
  • an appropriately sized power source must be provided.
  • the folding wing consists of a wing root, an inner wing surface and an outer wing surface, wherein the wing root is connected to the trunk via a rotating device, that the inner wing surface at its root via a first axis of rotation with the wing root is connected, that the outer wing surface is articulated via a further axis of rotation at the outer edge of the inner wing surface, both axes of rotation approximately parallel to each other and in the direction of flight, that a coil spring to which a pull rope is fixed, biased in the rest position of the folding wing in the inner wing surface is arranged, that the traction cable is guided by the coil spring via a first guide roller which is connected transversely but not longitudinally movable by means of a first fastening means with the wing root, and is then guided over a second deflection roller welc he he he means of a second fastener is transverse but not longitudinally movably attached to the root of the outer wing surface
  • Such a device for folding wing unfolding can be easily integrated in the interior of a part of the folding wing due to their flat and compact design.
  • the device also requires no additional resources that would otherwise have to be accommodated in the folding wing or in the fuselage.
  • this device is also much easier than known embodiments. It is only a device for releasing the prestressed coil spring required. Thus, it is easily possible to accommodate this device in a slim folding wing. It continues advantageous that this device requires no auxiliary devices for energy storage and thus is easier than known devices. This can be avoided especially in aerodynamic active surfaces unwanted additional weight.
  • FIG. 1 shows a folding wing for a missile according to the invention in the rest position in which it would be in the installed state before the start. For the sake of clarity parts belonging to the missile have been completely omitted.
  • the mechanical connection between the missile body and the wing root 13 is accomplished by means of a robust rotator 6, which will not be further described here.
  • the inner wing surface 12 of the folding wing is articulated and fixed by means of an external axis of rotation 10, which is aligned approximately in the direction of flight.
  • a further, also external axis of rotation 11 forms in the same way the connection between the inner wing surface 12 and the outer wing surface 9.
  • the unfolding device for the folding wing is housed substantially in the interior of the inner wing surface 12. To illustrate their installation position is in the FIG. 1 the side wing panel has been removed. Inside is the drive device 1, which is shown without the coil spring 20, which in FIG. 3 is reproduced. The drive means is together with the coil spring 20 in the illustrated position of the flap in a biased state. Here, the drive device 1 is not locked, but the folding wing is with a simple releasable attachment 5, which at the outer edge of the outer wing surface 9 (see. FIG. 3 ) is held until the appropriate time. The drive device thus remains under bias until it is triggered.
  • the first deflection roller 2 is fastened to the wing root 13 by means of a first fastening means 31.
  • the attachment means 31 is, for example, a wire rope which, although flexible in the transverse direction, is not extensible in the longitudinal direction. The same applies to the further attachment means 32, with which the further deflection roller 3 is fastened to the root of the outer folding wing 9.
  • the coil spring has the advantage of a long spring travel, with the help from the triggering of the attachment 5 of the folding wing, the traction cable is pulled and wound in the drive device 1.
  • a uniform force train on the pull cable 21 acts on the two pulleys 2, 3.
  • the wound up by the drive device 1 path length of the pull rope 21 is distributed to the pulleys so that each of both about a quarter of the distance traveled by the traction cable on the moved to another pulley.
  • the thereby exerted by the pulleys 2, 3 on the fastening means 31, 32 force increases inversely proportional. In this way, a strong train between the attachment points 18, 19 of the two fastening means 31, 32.
  • This tensile force is sufficient for the deployment of the folding wing 9, 12, 13 in any case. This applies to environmental conditions, such as air and water.
  • the bias and the path length of the coil spring and the pull rope are sufficiently dimensioned so that in all circumstances the working position of the folding wing, in the FIGS. 2 and 3 is achieved is achieved.
  • the latches 7, 8 snap between the wing root and the inner wing surface on the one hand and the inner and outer wing surface on the other hand.
  • the latches can be designed, for example, in the form of slides, which engage in corresponding openings in the respective counterpart spring-driven 14, 15.
  • angles 109 ° and 35 ° between the individual parts 13, 12, 9 of the folding leaf are specified. These angles have been found in practice to be particularly favorable for the compact application of the folding wing to the missile fuselage. Since the angles of the respective outer dimensions of the inner and the outer wing surface are dependent, deviations from these angles may also result depending on the dimensions.
  • FIG. 2 In the FIG. 2 is the fully unfolded folding wings 9, 12, 13 shown from its opposite side.
  • the outer axes of rotation 10 and 11 are clearly visible, which make the connection between the wing root 13 and the inner wing surface 12 on the one hand and the inner wing surface 12 and the outer wing surface 9 on the other.
  • the releasable attachment 5 for the hinged folding wing As shown in the FIG. 1 is shown arranged. This corresponds to a corresponding unlockable part in the area of the missile fuselage, which is actuated at the start of the missile after leaving the launching tube and thus releases the unfolding process.
  • FIG. 3 finally shows the fully unfolded folding wing from the view side as in FIG. 1 ,
  • the coil spring 20 and a part of the traction cable 21 have been angled to the drive device 1 during the unfolding process and are still under pretension.
  • the latches 7, 8 are locked.
  • the pulleys 2, 3 are located locally much closer together than in the FIG. 1 ,
  • the unfolded folding wing is in a stable, resilient and without aids no longer reversible locking state.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aerials With Secondary Devices (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Storing, Repeated Paying-Out, And Re-Storing Of Elongated Articles (AREA)

Claims (2)

  1. Aile pliable comprenant un moyen d'actionnement disposé à l'intérieur de l'aile pliable, lequel moyen d'actionnement est connecté à un câble de traction qui est guidé par le biais d'au moins un dispositif de manière à faire varier la direction et qui est fixé à l'autre extrémité à une partie de l'aile pliable,
    caractérisée en ce que
    - l'aile pliable se compose d'une emplanture d'aile (13), d'une surface d'aile intérieure (12) et d'une surface d'aile extérieure (9), l'emplanture d'aile (13) étant connectée au fuselage par le biais d'un dispositif rotatif (6),
    - la surface d'aile intérieure (12) est connectée au niveau de son emplanture par le biais d'un premier axe de rotation (10) à l'emplanture d'aile (13),
    - la surface d'aile extérieure (9) est articulée par le biais d'un axe de rotation supplémentaire (11) au bord extérieur de la surface d'aile intérieure (12), les deux axes de rotation (10, 11) s'étendant approximativement parallèlement l'un à l'autre et dans la direction de vol,
    - dans la position de repos de l'aile pliable, un ressort spiral (20) sur lequel est fixé un câble de traction (21) est disposé de manière précontrainte dans la surface d'aile intérieure (12),
    - le câble de traction (21), partant du ressort spiral (20), est guidé sur une première poulie de renvoi (2) qui est connectée (19) au moyen d'un premier moyen de fixation (31) à l'emplanture d'aile (13), et est ensuite guidé sur une deuxième poulie de renvoi (3) qui est fixée (18) au moyen d'un deuxième moyen de fixation (32) dans la région de l'emplanture de la surface d'aile extérieure (9), l'extrémité libre du câble de traction (21) étant connectée (30) à la surface d'aile intérieure (12).
  2. Aile pliable selon la revendication 1, caractérisée en ce que l'aile pliable, dans la position de repos, est maintenue au moyen d'un dispositif de fixation (5) amovible disposé sur la surface d'aile extérieure (9).
EP20090000744 2008-01-24 2009-01-21 Aile pliable dotée d'un dispositif de dépliage Active EP2083238B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE200810005705 DE102008005705A1 (de) 2008-01-24 2008-01-24 Klappflügel mit Entfaltvorrichtung

Publications (3)

Publication Number Publication Date
EP2083238A2 EP2083238A2 (fr) 2009-07-29
EP2083238A3 EP2083238A3 (fr) 2013-05-22
EP2083238B1 true EP2083238B1 (fr) 2014-01-08

Family

ID=40578683

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20090000744 Active EP2083238B1 (fr) 2008-01-24 2009-01-21 Aile pliable dotée d'un dispositif de dépliage

Country Status (2)

Country Link
EP (1) EP2083238B1 (fr)
DE (2) DE102008005705A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3165870A1 (fr) 2015-11-06 2017-05-10 MBDA Deutschland GmbH Aile repliable pour missile et missile équipé d'au moins une aile repliable
EP3165869A1 (fr) 2015-11-06 2017-05-10 MBDA Deutschland GmbH Aile repliable pour missile et missile équipé d'au moins une aile repliable
DE102017113058A1 (de) 2017-06-14 2018-12-20 Deutsches Zentrum für Luft- und Raumfahrt e.V. Raumtransport-Fluggerät und Wiedereintritts-Fluggerät
US11685510B2 (en) 2018-11-01 2023-06-27 Viettel Group Wing deployment mechanism and design method using pneumatic technique

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104677199B (zh) * 2015-01-21 2016-07-13 浙江理工大学 一种单驱动多折叠舵面同步展开机构
CN108688793B (zh) * 2018-07-27 2023-11-24 中国工程物理研究院总体工程研究所 筒式发射无人机机翼折叠展开机构
RU2730903C1 (ru) * 2019-09-10 2020-08-26 Акционерное общество "Машиностроительное конструкторское бюро "Факел" имени Академика П.Д. Грушина" Механизм раскрытия и стопорения аэродинамического руля с двумя осями складывания
CN112985190A (zh) * 2021-04-13 2021-06-18 西安航天动力技术研究所 一种涡卷弹簧式折叠弹翼展开机构
RU2770956C1 (ru) * 2021-12-21 2022-04-25 Акционерное общество "Машиностроительное конструкторское бюро "Факел" имени академика П.Д. Грушина Механизм раскрытия и стопорения рулей с двумя складывающимися секциями

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2045687C2 (de) * 1970-09-16 1982-08-12 Technisch-Mathematische Studiengesellschaft mbH, 5300 Bonn Thermische Auslösevorrichtung für Flugkörperfunktionen
GB2140136B (en) * 1983-05-14 1987-05-07 British Aerospace Folding fin assembly for missiles
DE3838735C2 (de) * 1988-11-15 1997-12-18 Diehl Gmbh & Co Klapp-Flügel, insbes. für ein Geschoss
GB2369177A (en) 1989-06-02 2002-05-22 British Aerospace Aerofoil deployment system
US5762294A (en) * 1997-03-31 1998-06-09 The United States Of America As Represented By The Secretary Of The Army Wing deployment device
US7040210B2 (en) * 2003-02-18 2006-05-09 Lockheed Martin Corporation Apparatus and method for restraining and releasing a control surface

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3165870A1 (fr) 2015-11-06 2017-05-10 MBDA Deutschland GmbH Aile repliable pour missile et missile équipé d'au moins une aile repliable
EP3165869A1 (fr) 2015-11-06 2017-05-10 MBDA Deutschland GmbH Aile repliable pour missile et missile équipé d'au moins une aile repliable
DE102015014368A1 (de) 2015-11-06 2017-05-11 Mbda Deutschland Gmbh Klappflügel für einen Flugkörper sowie einen Flugkörper mit mindestens einem daran angeordneten Klappflügel
DE102015014367A1 (de) 2015-11-06 2017-05-11 Mbda Deutschland Gmbh Klappflügel für einen Flugkörper und Flugkörper mit mindestens einem daran angeordneten Klappflügel
US10317179B2 (en) 2015-11-06 2019-06-11 Mbda Deutschland Gmbh Folding wing for a missile and a missile having at least one folding wing arranged thereon
DE102015014367B4 (de) 2015-11-06 2020-07-16 Mbda Deutschland Gmbh Klappflügel für einen Flugkörper und Flugkörper mit mindestens einem daran angeordneten Klappflügel
DE102017113058A1 (de) 2017-06-14 2018-12-20 Deutsches Zentrum für Luft- und Raumfahrt e.V. Raumtransport-Fluggerät und Wiedereintritts-Fluggerät
DE102017113058B4 (de) 2017-06-14 2023-04-27 Deutsches Zentrum für Luft- und Raumfahrt e.V. Raumtransport-Fluggerät
US11685510B2 (en) 2018-11-01 2023-06-27 Viettel Group Wing deployment mechanism and design method using pneumatic technique

Also Published As

Publication number Publication date
EP2083238A3 (fr) 2013-05-22
DE102008005705A1 (de) 2009-07-30
DE202008018033U1 (de) 2011-04-14
EP2083238A2 (fr) 2009-07-29

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