EP1628112A1 - Flügelanordnung - Google Patents

Flügelanordnung Download PDF

Info

Publication number
EP1628112A1
EP1628112A1 EP05016830A EP05016830A EP1628112A1 EP 1628112 A1 EP1628112 A1 EP 1628112A1 EP 05016830 A EP05016830 A EP 05016830A EP 05016830 A EP05016830 A EP 05016830A EP 1628112 A1 EP1628112 A1 EP 1628112A1
Authority
EP
European Patent Office
Prior art keywords
wing
wing element
missile
arrangement
connecting means
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.)
Withdrawn
Application number
EP05016830A
Other languages
German (de)
English (en)
French (fr)
Inventor
Erich Plocher
Michael Feuerstein
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 BGT Defence GmbH and Co KG
Original Assignee
Diehl BGT Defence GmbH and Co KG
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 Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Publication of EP1628112A1 publication Critical patent/EP1628112A1/de
Withdrawn legal-status Critical Current

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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 wing arrangement for a missile comprising two wing elements.
  • Missiles are partially fired from launch containers or pipes in which only limited space is available for the missile. For this reason, such missiles must be built very compact. Especially arranged on the missiles wings require a certain amount of space. Therefore missiles that are fired in such a way, usually wing arrangements, which are located before the launch of the missile close to the fuselage or in a recess in the fuselage of the missile. These wing assemblies unfold their full effectiveness with respect to their wing surface only after firing, for example, by being folded out laterally or swung out.
  • a first wing member from a provided in the fuselage of a missile recess can be swung laterally by 90 degrees, so that its wing surface is no longer parallel to the fuselage of the missile, but perpendicular to whose hull is aligned.
  • the wing element is then rotated by a further 90 degrees about its longitudinal axis, so that its wing surface in the end position is parallel to the longitudinal axis of the missile.
  • a second Wing element included which is telescoped out of this after completion of the pivoting operation of the first wing member to increase the wing area.
  • a wing assembly for a missile comprising two wing elements according to the invention that a first wing member along its longitudinal axis via a connecting means on the missile is hinged folded and that a second wing member is connected to the first wing member such that it is a to Longitudinal axis of the first wing element perpendicular axis is pivotally.
  • the invention is based in a first step on the consideration that in principle a larger wing span can be achieved by a combination of two wing elements via a folding pivot mechanism.
  • a hinged pivoting mechanism is not suitable, because it is accompanied by a reduced mechanical wing stability.
  • the invention is based on the consideration that an attachment of a wing element along its longitudinal axis via a connecting means for a greater stability of the wing member provides compared to an attachment in the region of its transverse axis. Due to the greater connection to the hull, the mechanical stability is increased so far that even a wing assembly, in which a first wing member is arranged hinged and another wing member is connected thereto via a pivot mechanism, is feasible.
  • a better position stability with respect to the alignment of the wing element can be achieved because the position of the center of gravity of the wing element is closer to the missile. This ensures that, after folding out a wing element, there is a delay in time or, subsequently, another wing element can be easily pivoted, for example, without being prevented from doing so by any malpositioning of a first wing element.
  • the invention provides a wing assembly which meets high requirements for the stability of a wing on a missile, has a large wing span and can be arranged extremely space-saving on the fuselage or in a recess in the fuselage of a missile. Due to the large wing span a particularly well maneuverable missile can be achieved.
  • a missile with such wing assemblies is also suitable for use in high-density media such.
  • high-density media such as water
  • the wing assembly unfolds as desired after the launch of the missile and does not stop in an intermediate position.
  • the second wing element is at least partially pivotable in an interior of the first wing element.
  • a space saving is additionally achieved and thus allows an arrangement of a missile provided with such wing arrangements in a launch container of small dimensions.
  • the second is Wing element thereby protected from damaging, external influences before the actual use of the missile.
  • the two side walls of the first wing element can exert a supporting effect laterally on the wing surface of the second wing element. The risk of breakage or kinking of the second wing element during a missile mission is thereby substantially reduced.
  • the connecting means is designed as a hinge connection. About a hinge connection a certain folding angle is particularly accurate.
  • the first wing element can thereby be brought into a defined position with respect to the missile. Too wide unfolding of the first wing element in an aerodynamically unfavorable position or damage caused thereby to the missile are thus prevented.
  • It can be provided that are located both on the connecting means and on the first wing element bushings, for example in the form of hinge eyes through which a common shaft can be pushed.
  • bushes with a mechanical spring wound around them can be pushed over such a shaft, which are located in the region between two hinge eyes of the first wing element and connecting means. It makes sense that the springs are in applied first wing element in the tensioned state and fold the first wing element after removal of any provided securing means that holds the wing assembly before launching the missile in position from.
  • the number of springs and their hardness make it easy to regulate the speed with which the first wing element can be unfolded.
  • a hinge eye of the first wing element may, for example, have a stop which, in interaction with the connecting means, ensures that the first wing element can only open by a fold-out angle defined above the stop.
  • a hinge eye of the connecting means may also have such a stop with the same function.
  • the connecting means is already integrated into the fuselage of the missile or applied thereto, for example, by a welded, screwed or glued connection. It can also be provided that the connecting means is arranged in a recess within the fuselage of the missile, which can also accommodate the first and the second wing element. As a result, a missile is realized, which can be accommodated particularly well in small launch containers or tubes with a small inner diameter.
  • the second wing element is pivotally connected in the region of its root with the first wing element.
  • no or only a minimal recess in the fuselage of the missile or in the connecting means or in the first wing element must be provided upon pivoting of the second wing element over a certain angle in order to accommodate the directed by the pivoting movement into the missile interior part of the second wing element.
  • this can be realized a particularly long span of the wing, which has a positive effect on the flight characteristics of the missile.
  • a stop is provided on the first wing element, which defines the maximum swiveling angle of the second wing element.
  • a certain swiveling angle is meaningful for the second wing element.
  • the attack can already be predetermined production technology, if the field of use of the missile is already defined precisely, for example in the form of a projection on the first wing element, or be designed to be variable depending on the application of the missile optimal Ausschwenkwinkel, for example in the form of a displaceable element.
  • Another advantage is achieved when the second wing member has a nose in the region of its root, which engages in the swung-out state in a provided in the connecting means pocket and so locks the second wing member. As a result, an exact alignment of the second wing element and thus good maneuverability during use of the missile is ensured.
  • the second wing element is partially disposed within the first wing element and engages in the pocket via a recess on the underside of the first wing element. Because of this, the first wing element is automatically held on the second wing element in position. An additional locking means to hold the first wing element in its position after unfolding is not mandatory. The forces acting on the second wing element in its swung-out state are absorbed by the connecting means. Thus, the power flow need not be conducted via the first wing element, shafts, locking means between the first wing element and connecting means, etc. As a result, excessive stress and associated damage to these wing components is prevented.
  • the second wing member is pivoted about relaxation of a mechanical spring, such as a leaf spring, after the launch of the missile and removal of any intended securing means from its space-saving position.
  • a mechanical spring such as a leaf spring
  • a locking means is provided for fixing the first wing element in its unfolded position.
  • the locking means may be, for example, a rotatable via a mechanical spring connected to the connecting element, which rotates when opening the first wing element in a recess in a hinge eye of the first wing element and thereby fixed in its unfolded position.
  • the wing assembly is held in the required orientation for placement in a launch container via a securing means in the form of a band which is annular around the diameter of the missile and the wing assembly.
  • This tape can then be solved by firing the missile, for example, pyrotechnic. Thereafter, unfolding or pivoting of the wing elements is possible.
  • FIG. 1 the individual components of a wing assembly 10 are shown in exploded view.
  • a first wing element 12 is hollow-walled, so that a second wing element 14 can be arranged partially within the first wing element.
  • the first wing member 12 is screwed to the second wing member 14 in the region of its root via a through its two side walls bore 16 and a bore 18 by means of a bolt 20 with internal thread and a corresponding counter bolt 22 with external thread.
  • the second wing element 14 can be pivoted about an axis which is perpendicular to the longitudinal axis of the first wing element 12 and which extends in the direction of the bolt connection from bolt 20 and counterbolt 22.
  • the first wing element 12 can be connected to a connecting means 24 by means of differently configured hinge eyes 26, which are located both on the connecting means 24 and on the first wing element 12, via shafts 28, 30.
  • the shafts 28, 30 are completely or partially pushed through the hinge eyes 26.
  • recesses 32 are provided to bushes 34 to the mechanical springs 36 are pushed to record.
  • the shaft 30 is also pushed through the bushes 34.
  • the mechanical springs 36 are arranged so that they are in a tensioned state when the first wing member 12 is in a state applied to the missile.
  • the connecting means 24 has a recess 38, in which a locking means 40 is rotatably arranged by means of unillustrated connecting pins and a mechanical spring, not shown.
  • the mechanical spring is arranged so that it is in a tensioned state when the first wing member 12 is in a state applied to the missile. Folding the first wing member 12 after removal of a securing means, not shown, due to relaxation of the previously tensioned springs 36, then the locking means 40 rotates due to the relaxation of his previously strained mechanical spring and locks in a specially designed recess 46 in the overlying Hinge eyelet 48 and thereby prevents folding back of the first wing member 12 (see Fig. 6).
  • the connecting means 24 has a pocket 50 into which the lower part 52 of the second wing element 14 projects when swinging out of the first wing element 12. Upon complete swinging out of the second wing member 14 this is located on a within the first wing member 12 stop 54 - here in the form of the configuration of the inner wall of the first wing member 12 - and ensures by its at the lower part 52 protruding nose 56 for fixing its position ( see Fig. 4).
  • Fig. 2 shows a previously described wing assembly 10 in the fully unfolded state of the first wing member 12 and fully swung out state of the second wing member 14.
  • the disc 58 with its four projections symbolizes this one introduced in a tube missile and the number of provided on him wing arrangements 10.
  • the outer diameter of the disc 58 represents the pipe diameter.
  • Fig. 3 shows a previously described wing assembly 10 in the fully folded state of the first wing member 12 to a missile and as far as possible pivoted into the first wing member 12 wing member 14.
  • first wing element 12 shown transparent. It can be seen that partly arranged within the first wing member 12 wing member 14 and the stopper 54, at which the second wing member would rest in a fully swung out state.
  • the locking region of the second wing element 14 with the connecting means 24 is shown in a partially transparent representation when the second wing element 14 is pivoted out completely. It can be seen how the lower part 52 and the nose 56 of the second wing element 14 reach into the pocket 50 of the connecting means 24 and thereby fix the second wing element 14 in its current position. The upper part of the nose 56 is from the wall of the adjacent hinge eye 26 enclosed.
  • Fig. 5 shows the already mentioned locking means 40.
  • the locking means 40 is arranged about an axis parallel to its bore 60 rotatably in the recess 38 shown in FIG.
  • Fig. 6 the locking means 40 and the associated overlying hinge eye 48 are shown.
  • the locking means 40 In applied to a missile state of the first wing member 12, the locking means 40 is positively against the hinge eye 48.
  • the hinge eye 48 has a recess 46 dimensioned such that when the first wing element 12 is folded out of the plane of the drawing, the locking means 40 rotates 90 degrees counterclockwise due to its tensioned mechanical spring (not shown) and engages in the recess 46.
  • a stop 62 is provided on the hinge eye 48, which ensures that the locking means can not accidentally perform a rotation of more than 90 degrees.
  • the locking means of the locking means 40 only serves to support the locking or fixing of the first wing member 12 in its unfolded position on the engagement of the lower part 52 and the nose 56 of the second wing member 14 in the pocket 50 of the connecting means 24th
  • wing arrangement 36 mechanical springs 12 first wing element 38 recess 14 second wing element 40 locking means 16 hole 46 recess 18 hole 48 hinge eye 20 bolts 50 recess 22 counter bolts 52 lower part 24 connecting means 54 stop 26 hinged eyelets 56 nose 28 wave 58 disc 30 wave 60 hole 32 recesses 62 stop 34 sockets

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Specific Sealing Or Ventilating Devices For Doors And Windows (AREA)
EP05016830A 2004-08-16 2005-08-03 Flügelanordnung Withdrawn EP1628112A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE200410039770 DE102004039770A1 (de) 2004-08-16 2004-08-16 Flügelanordnung

Publications (1)

Publication Number Publication Date
EP1628112A1 true EP1628112A1 (de) 2006-02-22

Family

ID=35295672

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05016830A Withdrawn EP1628112A1 (de) 2004-08-16 2005-08-03 Flügelanordnung

Country Status (3)

Country Link
EP (1) EP1628112A1 (no)
DE (1) DE102004039770A1 (no)
NO (1) NO20053824L (no)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009107126A1 (en) * 2008-02-26 2009-09-03 Elbit Systems Ltd. Foldable and deployable panel
US8847134B2 (en) 2012-02-16 2014-09-30 Lockheed Martin Corporation Deployable wing and fin control surface actuation
CN104677200A (zh) * 2015-01-21 2015-06-03 浙江理工大学 一种二次折叠翼面横向展开机构
EP3032213A1 (de) 2014-12-11 2016-06-15 MBDA Deutschland GmbH Klappflügelsystem
DE102015004703A1 (de) * 2014-12-11 2016-06-16 Mbda Deutschland Gmbh Klappflügelsystem
FR3035493A1 (fr) * 2015-04-21 2016-10-28 Nexter Munitions Projectile balistique comprenant un mecanisme d'ouverture d'ailes et procede d'utilisation d'un tel projectile balistique
SE2000144A1 (en) * 2020-08-19 2022-02-20 Saab Ab A wing arrangement, a projectile, a use and a method for deploying a wing blade

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007002948B4 (de) * 2007-01-19 2009-04-02 Diehl Bgt Defence Gmbh & Co. Kg Vorrichtung zur Tragflächenentfaltung
RU2549047C1 (ru) * 2014-03-04 2015-04-20 Открытое акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" Устройство фиксации сложенных аэродинамических поверхностей летательного аппарата
DE102015014794A1 (de) * 2015-08-25 2017-03-02 Diehl Bgt Defence Gmbh & Co. Kg Flügelanordnung und Flugkörper mit Flügelanordnung

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1199664B (de) * 1962-09-11 1965-08-26 Dynamit Nobel Ag Klappleitwerk, insbesondere fuer Raketengeschosse
US3633846A (en) * 1970-05-28 1972-01-11 Us Navy Expandable aerodynamic fin
US4635881A (en) * 1984-05-09 1987-01-13 Diehl Gmbh & Co. Foldable wing, especially for a projectile
US4667899A (en) 1984-11-28 1987-05-26 General Dynamics, Pomona Division Double swing wing self-erecting missile wing structure
US4778127A (en) * 1986-09-02 1988-10-18 United Technologies Corporation Missile fin deployment device

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2635676A1 (de) * 1976-08-07 1978-02-09 Dynamit Nobel Ag Leitwerk fuer raketen
DE2649643A1 (de) * 1976-10-29 1978-06-15 Messerschmitt Boelkow Blohm Raketengetriebener flugkoerper mit entfaltbaren stabilisierungsflaechen
DE3010027C2 (de) * 1978-09-26 1985-07-11 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Schwenkbare Anordnung eines Leitwerks, insbesondere bei Flugkörpern oder Geschossen
AU524255B2 (en) * 1978-12-29 1982-09-09 Commonwealth Of Australia, The Deployable wing
DE2926933A1 (de) * 1979-07-04 1981-01-22 Grs Ges Fuer Raketen Systeme M Stabilisierungseinrichtung mit ausklappbaren starren stabilisierungsflaechen

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1199664B (de) * 1962-09-11 1965-08-26 Dynamit Nobel Ag Klappleitwerk, insbesondere fuer Raketengeschosse
US3633846A (en) * 1970-05-28 1972-01-11 Us Navy Expandable aerodynamic fin
US4635881A (en) * 1984-05-09 1987-01-13 Diehl Gmbh & Co. Foldable wing, especially for a projectile
US4667899A (en) 1984-11-28 1987-05-26 General Dynamics, Pomona Division Double swing wing self-erecting missile wing structure
US4778127A (en) * 1986-09-02 1988-10-18 United Technologies Corporation Missile fin deployment device

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009107126A1 (en) * 2008-02-26 2009-09-03 Elbit Systems Ltd. Foldable and deployable panel
US8324545B2 (en) 2008-02-26 2012-12-04 Elbit Systems Ltd. Foldable and deployable panel
US8378278B2 (en) 2008-02-26 2013-02-19 Elbit Systems Ltd. Foldable and deployable panel
US8847134B2 (en) 2012-02-16 2014-09-30 Lockheed Martin Corporation Deployable wing and fin control surface actuation
DE102015004703A1 (de) * 2014-12-11 2016-06-16 Mbda Deutschland Gmbh Klappflügelsystem
EP3032213A1 (de) 2014-12-11 2016-06-15 MBDA Deutschland GmbH Klappflügelsystem
US9939237B2 (en) 2014-12-11 2018-04-10 Mbda Deutschland Gmbh Folding fin system
DE102015004703B4 (de) 2014-12-11 2019-12-12 Mbda Deutschland Gmbh Klappflügelsystem
CN104677200A (zh) * 2015-01-21 2015-06-03 浙江理工大学 一种二次折叠翼面横向展开机构
FR3035493A1 (fr) * 2015-04-21 2016-10-28 Nexter Munitions Projectile balistique comprenant un mecanisme d'ouverture d'ailes et procede d'utilisation d'un tel projectile balistique
SE2000144A1 (en) * 2020-08-19 2022-02-20 Saab Ab A wing arrangement, a projectile, a use and a method for deploying a wing blade
WO2022039659A1 (en) * 2020-08-19 2022-02-24 Saab Ab A deployable wing arrangement for a projectile, a projectile comprising such a wing arrangement, an use of such a wing arrangement and a method for deploying a wing blade for a projectile
SE544987C2 (en) * 2020-08-19 2023-02-21 Saab Ab A wing arrangement, a projectile, a use and a method for deploying a wing blade

Also Published As

Publication number Publication date
NO20053824D0 (no) 2005-08-15
DE102004039770A1 (de) 2006-03-02
NO20053824L (no) 2006-02-17

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