EP1855076A1 - Ailes déployables flexibles pour missile - Google Patents

Ailes déployables flexibles pour missile Download PDF

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Publication number
EP1855076A1
EP1855076A1 EP07008992A EP07008992A EP1855076A1 EP 1855076 A1 EP1855076 A1 EP 1855076A1 EP 07008992 A EP07008992 A EP 07008992A EP 07008992 A EP07008992 A EP 07008992A EP 1855076 A1 EP1855076 A1 EP 1855076A1
Authority
EP
European Patent Office
Prior art keywords
missile
winding
wings
rest position
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.)
Granted
Application number
EP07008992A
Other languages
German (de)
English (en)
Other versions
EP1855076B1 (fr
Inventor
Jürgen Rühe
Friedrich Plank
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.)
LFK Lenkflugkoerpersysteme GmbH
Original Assignee
LFK Lenkflugkoerpersysteme 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 LFK Lenkflugkoerpersysteme GmbH filed Critical LFK Lenkflugkoerpersysteme GmbH
Publication of EP1855076A1 publication Critical patent/EP1855076A1/fr
Application granted granted Critical
Publication of EP1855076B1 publication Critical patent/EP1855076B1/fr
Active 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 device on winding wings of a missile, the n winding blades (n greater / equal 2), which are rotatably mounted on the root side in the region of the outer surface of the missile about axes lying in the direction of travel and rest in the rest position on the outer surface of the missile and by of a drive to the working position.
  • 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 launching device 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 offers. From the DE 35 33 994 A1 is a tail known with deployable wings, which consists of wing surfaces that are permanently connected to each other on the tip side, unfold automatically due to their bias and erect roof-shaped. At the wing root has a wing surface two rigid and three movable pivot bearings. The two fixed rotary bearings are designed as hinged bearing and the other as articulated plain bearings. 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 lie in the wound state directly above each other and are on the circumference of the missile until held for release. However, a device for holding the wound wings in the rest position is not specified.
  • a missile with deployable stabilization surfaces become known, which are held until Entfaltvorgang by means of a controlled releasable holding means on the missile fuselage.
  • the triggering is due to the interruption of an operative connection between the missile engine and the lock.
  • the interruption is carried out, for example, by a fuel charge after a defined burning time.
  • EP 0 448 437 A1 a missile with folding wings, which are mechanically coupled to each other via an annular element.
  • the annular element is rotationally moved, for example, via a motor and a reduction gear in order to transfer the folding wings from the rest position to the working position.
  • this type of drive has the disadvantage of an enormous amount of space just in the operation of the interior of the missile, which is needed for the engine.
  • first connecting means are arranged, which correspond in the rest position of the winding wings with other connecting means, which are arranged on the in the rest position outwardly facing side of the respectively underlying winding wings and that at the n-th winding wing in the tip-side region at least one supported in the missile and controlled releasable retaining means engages.
  • the first connecting means are formed as hooks, which engage in the rest position in counter-designed further connecting means.
  • a further advantageous embodiment consists in that the holding means consists of a pin detachably connected to the n-th winding blade, which can be severed by means of a controlled releasable cutting device arranged in the region of the outer surface of the missile. This ensures that the winding wings can be released for deployment at a selectable time after leaving the launcher.
  • FIG. 1 shows in simplified form a section of a missile fuselage 5.
  • a total of four winding wings 1, 2, 3 and 4 are wound around this section of the missile fuselage, wherein the winding wing with the reference numeral 4, not visible from this perspective, on the back of the illustrated Section of a missile fuselage.
  • the winding wings 1, 2, 3, 4 are connected via pivot bearing 7 with the missile fuselage.
  • the winding wings 1, 2, 3 are detachably connected to each other via the connecting elements 6 shown in simplified form.
  • This connection is indicated in the exemplary embodiment as entanglement of two oppositely arranged on the juxtaposed winding blades connecting means 6, of which only the external connection means is visible.
  • FIG. 2 shows a section through the missile fuselage 5 shown in FIG. 1 and the wind vanes 1, 2, 3, 4. All four wind vanes are shown in the rest position in which the wind wing 1 is hooked to the wind wing 4, as well as the wind wing 2
  • the two-way entanglement takes place in that in the exemplary embodiment, the first connecting means 6a, which is arranged in the tip-side region of each respective outer wind deflector, consists of a bar with an approximately U-shaped cross-section.
  • the further connecting means 6b corresponding to the first connecting means 6a and arranged on the respectively underlying winding blade consists in the example of hooks or a strip slightly spaced from the surface of the underlying winding blade, which in the shown rest position of the winding wings with its free edge into the interior of the first connecting means 6a engages.
  • the holder of the remaining winding blade 4 is carried out according to Figure 3 in the rest position of the winding blades on a controlled releasable holding means 8.
  • This holding means is designed in the embodiment as a pin, which is attached on the one hand to the missile body 5 and on the other hand connected to the tip end of the winding blade 4 such is that the tip-side end rests on the winding blade 3 or almost rests.
  • a controlled triggerable capping device 9 is arranged on the holding means 8, which cuts through the holding means 8 at a selectable point in time and consequently releases the winding vane 4.
  • a holding means 8 are, for example, Seilabschnifte and for the Kappvorraum 9 also pyrotechnic cutting devices that are electrically initiated.
  • a plurality of holding means 8 may be provided.
  • the unfolding process of the winding wings begins with the winding wing with the reference numeral 4. As soon as this has opened a piece he also raises the tip end of the winding wing by the reference numeral 1. In further progress, the tip-side end of the winding blade 1 shifts so far from its original position with respect to the surface of the winding wings 4 that the further connecting means 6b slides out of the interior of the first connecting means. Thus, the tip-side end of the winding blade 1 is released and the winding blade can stand upright.
  • connection means 6 between the Winding wings 1 and 2 and then between the Winding wings 2 and 3 instead.

Landscapes

  • 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)
  • Toys (AREA)
  • Control And Other Processes For Unpacking Of Materials (AREA)
  • Auxiliary Devices For And Details Of Packaging Control (AREA)
  • Tires In General (AREA)
  • Air Bags (AREA)
  • Packaging Of Machine Parts And Wound Products (AREA)
EP07008992A 2006-05-12 2007-05-04 Ailes déployables flexibles pour missile Active EP1855076B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006022248A DE102006022248B3 (de) 2006-05-12 2006-05-12 Vorrichtung an Wickelflügeln eines Flugkörpers

Publications (2)

Publication Number Publication Date
EP1855076A1 true EP1855076A1 (fr) 2007-11-14
EP1855076B1 EP1855076B1 (fr) 2008-11-05

Family

ID=38038728

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07008992A Active EP1855076B1 (fr) 2006-05-12 2007-05-04 Ailes déployables flexibles pour missile

Country Status (4)

Country Link
EP (1) EP1855076B1 (fr)
AT (1) ATE413580T1 (fr)
DE (2) DE102006022248B3 (fr)
NO (1) NO339122B1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1953494A1 (fr) * 2007-01-31 2008-08-06 NEXTER Munitions Dispositif de pilotage d'une munition à gouvernes déployables
WO2013172992A1 (fr) 2012-05-18 2013-11-21 Textron Systems Corporation Configuration pliante pour véhicule aérien
US10429158B2 (en) 2015-11-06 2019-10-01 Mbda Deutschland Gmbh Folding wing for a missile and a missile having at least one folding wing arranged thereon

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015014367B4 (de) 2015-11-06 2020-07-16 Mbda Deutschland Gmbh Klappflügel für einen Flugkörper und Flugkörper mit mindestens einem daran angeordneten Klappflügel
DE102017113058B4 (de) 2017-06-14 2023-04-27 Deutsches Zentrum für Luft- und Raumfahrt e.V. Raumtransport-Fluggerät

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2793591A (en) * 1953-12-21 1957-05-28 Brandt Soc Nouv Ets Fin arrangement for a projectile
DE1950638A1 (de) 1969-10-08 1971-04-22 Messerschmitt Boelkow Blohm Flugkoerper mit entfaltbaren Stabilisierungsflaechen
US4004514A (en) * 1976-01-20 1977-01-25 The United States Of America As Represented By The Secretary Of The Navy Roll rate stabilized wrap around missile fins
DE2728388A1 (de) * 1976-06-25 1978-01-05 Europ Propulsion Leitwerk fuer ein projektil
DE3533994A1 (de) 1984-09-25 1986-04-30 Rheinmetall GmbH, 4000 Düsseldorf Leitwerk mit entfaltbaren fluegeln
EP0448437A1 (fr) 1990-03-09 1991-09-25 Thomson-Brandt Armements Perfectionnements à des empennages à ailettes déployables
JPH09159398A (ja) * 1995-12-01 1997-06-20 Komatsu Ltd 飛翔体の翼装置

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2793591A (en) * 1953-12-21 1957-05-28 Brandt Soc Nouv Ets Fin arrangement for a projectile
DE1950638A1 (de) 1969-10-08 1971-04-22 Messerschmitt Boelkow Blohm Flugkoerper mit entfaltbaren Stabilisierungsflaechen
US4004514A (en) * 1976-01-20 1977-01-25 The United States Of America As Represented By The Secretary Of The Navy Roll rate stabilized wrap around missile fins
DE2728388A1 (de) * 1976-06-25 1978-01-05 Europ Propulsion Leitwerk fuer ein projektil
DE3533994A1 (de) 1984-09-25 1986-04-30 Rheinmetall GmbH, 4000 Düsseldorf Leitwerk mit entfaltbaren fluegeln
EP0448437A1 (fr) 1990-03-09 1991-09-25 Thomson-Brandt Armements Perfectionnements à des empennages à ailettes déployables
JPH09159398A (ja) * 1995-12-01 1997-06-20 Komatsu Ltd 飛翔体の翼装置

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1953494A1 (fr) * 2007-01-31 2008-08-06 NEXTER Munitions Dispositif de pilotage d'une munition à gouvernes déployables
WO2013172992A1 (fr) 2012-05-18 2013-11-21 Textron Systems Corporation Configuration pliante pour véhicule aérien
EP2849996A4 (fr) * 2012-05-18 2015-07-29 Textron Systems Corp Configuration pliante pour véhicule aérien
US10429158B2 (en) 2015-11-06 2019-10-01 Mbda Deutschland Gmbh Folding wing for a missile and a missile having at least one folding wing arranged thereon

Also Published As

Publication number Publication date
DE102006022248B3 (de) 2007-11-08
NO20072442L (no) 2007-11-13
NO339122B1 (no) 2016-11-14
EP1855076B1 (fr) 2008-11-05
ATE413580T1 (de) 2008-11-15
DE502007000219D1 (de) 2008-12-18

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