EP1855076B1 - Wrap-around fins for a missile - Google Patents

Wrap-around fins for a missile Download PDF

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Publication number
EP1855076B1
EP1855076B1 EP07008992A EP07008992A EP1855076B1 EP 1855076 B1 EP1855076 B1 EP 1855076B1 EP 07008992 A EP07008992 A EP 07008992A EP 07008992 A EP07008992 A EP 07008992A EP 1855076 B1 EP1855076 B1 EP 1855076B1
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EP
European Patent Office
Prior art keywords
missile
wrap
winding
wings
rest position
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Active
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EP07008992A
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German (de)
French (fr)
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EP1855076A1 (en
Inventor
Jürgen Rühe
Friedrich Plank
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LFK Lenkflugkoerpersysteme GmbH
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LFK Lenkflugkoerpersysteme GmbH
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Publication of EP1855076A1 publication Critical patent/EP1855076A1/en
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    • 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, where n is greater than or equal to 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 move into the working position by means of a drive.
  • 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 which forms a basis for the preamble of claim 1, a tail with deployable wings has become known, which consists of wing surfaces that are permanently connected to each other at 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 is simplified a section of a missile fuselage 5 shown.
  • 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 in FIG. 1 All the four winding blades are shown in the rest position in which the winding blade 1 is hooked to the winding wing 4, as well as winding wings 2 with winding wings 1 and 3 Winding wings with winding wings 2. Die Mutual entanglement takes place in that in the exemplary embodiment, the first connecting means 6a, which is arranged in the tip-side region of the respective outer winding blade, 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 bar slightly spaced from the surface of the underlying winding blade, which in the illustrated rest position of the winding wings with its free edge in the interior of the first connecting means 6a engages.
  • this holding means is designed as a pin, which is fastened 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 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 Kappvorettivon 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.

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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)
  • 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)

Abstract

A device on wrapped wings (1, 2, 3) of a flying object (5) having n (at least 2) wings rotatably mounted on the object outer surface on axes in the flying direction, lying on the surface in rest position and opened by a drive into working position, comprises first fixtures on the tip side regions of (n - 1) wings, corresponding in the rest position to further fixtures on the outer side of the wing underneath and gripping a controlled-release holder on the tip side region of the n'th wing.

Description

Die Erfindung betrifft eine Vorrichtung an Wickelflügeln eines Flugkörpers, der n Wickelflügel, wobei n größer oder gleich 2 ist, aufweist, welche wurzelseitig im Bereich der Außenfläche des Flugkörpers um in Flugrichtung liegende Achsen drehbar gelagert sind und in der Ruheposition an der Außenfläche des Flugkörpers anliegen und mittels eines Antriebs in die Arbeitsposition übergehen.The invention relates to a device on winding wings of a missile, the n winding blades, where n is greater than or equal to 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 move into the working position by means of a drive.

Flugkörper werden aus einem Behälter in einer Abschussvorrichtung gestartet, dessen Innendurchmesser kaum größer als der Außendurchmesser des Flugkörpers ist. Zur Stabilisierung der Fluglage des Flugkörpers sind aerodynamische Wirkflächen erforderlich. Diese sind in bekannter Weise entweder in Ausnehmungen der Außenfläche des Flugkörpers eingeklappt oder werden in zusammengefaltetem Zustand eng an die Außenfläche des Flugkörper gewickelt befestigt. Beim Start werden diese aerodynamischen Wirkflächen unmittelbar nach dem Verlassen des Behälters der Abschussvorrichtung mittels geeigneter Vorrichtungen von der Ruheposition in die Arbeitsposition übergeführt und sollen dort in stabiler Anordnung während des gesamten Fluges verbleiben.Missiles are launched from a container in a launcher whose inner diameter is barely greater than the outer diameter of the missile. To stabilize the attitude 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.

Als Ausführungsform für derartige aerodynamische Wirkflächen bietet sich die Verwendung so genannter Wickelflügel an. Aus der DE 35 33 994 A1 , welch eine Grundlage für den Oberbegriff des Anspruchs 1 bildet, ist ein Leitwerk mit entfaltbaren Flügeln bekannt geworden, welches aus Flügelflächen besteht, die spitzenseitig dauerhaft miteinander verbunden sind, sich aufgrund ihrer Vorspannung selbsttätig entfalten und sich dachförmig aufstellen. An der Flügelwurzel hat eine Flügelfläche zwei starre und drei bewegliche Drehlager. Die beiden ortsfesten Drehlagerungen sind als gelenkiges Festlager und die andere als gelenkiges Gleitlager ausgeführt. Dadurch lassen sich die Flügelflächen zusammenfalten und auf dem Umfang des Flugkörpers aufwickeln. Wenn mehrere derartige Flügel am Flugkörper montiert sind, liegen diese im aufgewickelten Zustand unmittelbar übereinander und werden am Umfang des Flugkörpers bis zur Freigabe festgehalten. Eine Vorrichtung zum Festhalten der aufgewickelten Flügel in der Ruheposition ist jedoch nicht angegeben.As an embodiment of such aerodynamic active surfaces, the use of so-called Winding wings offers. From the DE 35 33 994 A1 which forms a basis for the preamble of claim 1, a tail with deployable wings has become known, which consists of wing surfaces that are permanently connected to each other at 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.

Aus der DE 1 950 638 ist ein Flugkörper mit entfaltbaren Stabilisierungsflächen bekannt geworden, die bis zum Entfaltvorgang mittels eines gesteuert lösbaren Haltemittels am Flugkörperrumpf festgehalten werden. Die Auslösung erfolgt aufgrund der Unterbrechung einer Wirkverbindung zwischen dem Flugkörpertriebwerk und der Verriegelung. Die Unterbrechung wird beispielsweise durch einen Brennsatz nach Ablauf einer definierten Abbrandzeit vollzogen.From the DE 1 950 638 is 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.

Schließlich beschreibt die EP 0 448 437 A1 einen Flugkörper mit Klappflügeln, die über ein ringförmiges Element mechanisch miteinander gekoppelt sind. Das ringförmige Element wird beispielsweise über einen Motor und ein Untersetzungsgetriebe rotatorisch bewegt um die Klappflügel von der Ruhe- in die Arbeitsposition zu überführen. Diese Art von Antrieb weist jedoch den Nachteil eines enormen Platzbedarfs gerade in dem Betreib des Innenraumes des Flugkörpers auf, der für das Triebwerk benötigt wird.Finally, that describes 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. However, 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.

Es ist Aufgabe der Erfindung, eine einfache, kompakte und unter allen Umweltbedingungen sicher funktionierende Vorrichtung anzugeben, welche die am Flugkörperrumpf anliegenden Wickelflügel in der Ruheposition festhält und bei einer Auslösung der Wickelflügel nachdem der Flugkörper den Ausstoßbehätter verlassen hat diese sicher freigibt.It is an object of the invention to provide a simple, compact and safely operating under all environmental conditions device that holds the voltage applied to the missile fuselage wings in the rest position and at a release of the winding wings after the missile leaves the Ausstoßbehätter this safely releases.

Die Aufgabe wird erfindungsgemäß dadurch gelöst, dass an n-1 Wickelflügeln im spitzenseitigen Bereich erste Verbindungsmittel angeordnet sind, welche in der Ruheposition der Wickelflügel mit weiteren Verbindungsmitteln korrespondieren, welche an der in der Ruheposition nach außen weisenden Seite der jeweils darunter befindlichen Wickelflügel angeordnet sind und dass am n-ten Wickelflügel im spitzenseitigen Bereich wenigstens ein im Flugkörper gelagertes und gesteuert lösbares Haltemittel eingreift.The object is achieved in that at n-1 winding blades in the tip-side region 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.

Diese Lösung ermöglicht auf einfache Weise die stabile Halterung der um den Flugkörperrumpf gewickelten Wickelflügel bis zur Auslösung des Entfaltungsvorgangs. Besonders hervorzuheben ist die einfache und funktionelle Gestaltung der miteinander korrespondierenden Verbindungsmittel und des Haltemittels.This solution makes it possible in a simple manner, the stable mounting of the wound around the missile body winding wings to trigger the deployment process. Particularly noteworthy is the simple and functional design of the mutually corresponding connection means and the holding means.

In vorteilhafter Weise sind die ersten Verbindungsmittel als Haken geformt, welche in der Ruheposition in gegengleich gestalteten weiteren Verbindungsmittel eingreifen. Somit wird auf einfachste Weise ermöglicht, dass sich die Wickelflügel nach der erfolgten Auslösung gleichzeitig mit Hilfe der in jedem Wickelflügel integrierten Antriebskraft entfalten können. Eine gegenseitige Behinderung beim Entfaltungsvorgang ist konstruktiv ausgeschlossen.Advantageously, the first connecting means are formed as hooks, which engage in the rest position in counter-designed further connecting means. Thus, it is possible in the simplest way that the winding wings can develop after the successful triggering simultaneously with the help of integrated in each winding wings driving force. Mutual disability during the unfolding process is structurally excluded.

Eine weitere vorteilhafte Ausgestaltungsform besteht darin, dass das Haltemittel aus einem mit dem n-ten Wickelflügel lösbar verbundenen Stift besteht, weicher mittels einer im Bereich der Außenfläche des Flugkörpers angeordneten gesteuert auslösbaren Kappvorrichtung durchtrennbar ist. Damit ist sichergestellt, dass die Wickelflügel zu einem wählbaren Zeitpunkt nach dem Verlassen der Abschussvorrichtung zur Entfaltung freigegeben werden kann.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.

Ein Ausführungsbeispiel der Erfindung ist in der Zeichnung schematisch vereinfacht dargestellt und wird im Folgenden näher beschrieben. Es zeigen:

Fig. 1:
einen Abschnitt eines Flugkörperrumpfes mit Wickelflügeln,
Fig. 2:
einen Schnitt durch einen Flugkörperrumpf mit Wickelflügeln,
Fig. 3:
eine Detailansicht eines Haltemittels.
An embodiment of the invention is shown schematically simplified in the drawing and will be described in more detail below. Show it:
Fig. 1:
a section of a missile fuselage with winding wings,
Fig. 2:
a section through a missile fuselage with winding wings,
3:
a detailed view of a holding means.

In der Figur 1 ist vereinfacht ein Abschnitt eines Flugkörperrumpfes 5 dargestellt. Um diesen Abschnitt des Flugkörperrumpfes sind insgesamt vier Wickelflügel 1, 2, 3 und 4 anliegend gewickelt, wobei der Wickelflügel mit dem Bezugszeichen 4 sich, aus dieser Perspektive nicht sichtbar, auf der Rückseite des dargestellten Abschnitts eines Flugkörperrumpfes befindet. Die Wickelflügel 1, 2, 3, 4 sind über Drehlager 7 mit dem Flugkörperrumpf verbunden. In der dargestellten Ruhe- oder Transportposition sind die Wickelflügel 1, 2, 3 über die vereinfacht dargestellten Verbindungselemente 6 miteinander lösbar verbunden. Diese Verbindung ist im Ausführungsbeispiel als Verhakung zweier gegengleich auf den aneinander anliegenden Wickelflügeln angeordneten Verbindungsmitteln 6 angedeutet, von denen nur das außen liegende Verbindungsmittel sichtbar ist.In the FIG. 1 is simplified a section of a missile fuselage 5 shown. 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. In the illustrated rest or transport position, 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.

Die Figur 2 zeigt einen Schnitt durch den in Figur 1 dargestellten Flugkörperrumpf 5 und die Wickelflügel 1, 2, 3, 4. Es sind alle vier Wickelflügel in der Ruheposition gezeigt, in der der Wickelflügel 1 mit dem Wickelflügel 4 verhakt ist, ebenso Wickelflügel 2 mit Wickelflügel 1 und Wickelflügel 3 mit Wickelflügel 2. Die gegenseitige Verhakung erfolgt dadurch, dass im Ausführungsbeispiel das erste Verbindungsmittel 6a, welches im spitzenseitigen Bereich des jeweils außen liegenden Wickelflügels angeordnet ist, aus einer Leiste mit einem etwa U-förmigen Querschnitt besteht. Das mit dem ersten Verbindungsmittel 6a korrespondierende und auf dem jeweils darunter liegenden Wickelflügel angeordnete weitere Verbindungsmittel 6b besteht im Beispiel aus Haken oder einer gegenüber der Oberfläche des darunter liegenden Wickelflügels etwas beabstandeten Leiste, welche in der dargestellten Ruheposition der Wickelflügel mit ihrer freien Kante in den Innenraum des ersten Verbindungsmittels 6a eingreift.The FIG. 2 shows a section through the in FIG. 1 All the four winding blades are shown in the rest position in which the winding blade 1 is hooked to the winding wing 4, as well as winding wings 2 with winding wings 1 and 3 Winding wings with winding wings 2. Die Mutual entanglement takes place in that in the exemplary embodiment, the first connecting means 6a, which is arranged in the tip-side region of the respective outer winding blade, 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 bar slightly spaced from the surface of the underlying winding blade, which in the illustrated rest position of the winding wings with its free edge in the interior of the first connecting means 6a engages.

Die Halterung des verbleibenden Wickelflügels 4 erfolgt gemäß Figur 3 in der Ruheposition der Wickelflügel über ein gesteuert lösbares Haltemittel 8. Dieses Haltemittel ist im Ausführungsbeispiel nach als Stift ausgeführt, der einerseits am Flugkörperrumpf 5 befestigt ist und andererseits mit dem spitzenseitigen Ende des Wickelflügels 4 derart verbunden ist, dass das spitzenseitige Ende am Wickelflügel 3 anliegt oder beinahe anliegt. Im Bereich des Flugkörperrumpfes 5 ist am Haltemittel 8 eine gesteuert auslösbare Kappvorrichtung 9 angeordnet, welche zu einem wählbaren Zeitpunkt das Haltemittel 8 durchtrennt und in Folge dessen den Wickelflügel 4 freigibt. Als Haltemittel 8 eignen sich beispielsweise auch Seilabschnifte und für die Kappvorrichtung 9 auch pyrotechnische Schneidvorrichtungen, die elektrisch initiierbar sind.The holder of the remaining winding blade 4 takes place according to FIG. 3 In the exemplary embodiment, this holding means is designed as a pin, which is fastened 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 that the tip-side end rests on the winding blade 3 or almost rests. In the area of the missile fuselage 5, 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. As a holding means 8 are, for example, Seilabschnifte and for the Kappvorrichtung 9 also pyrotechnic cutting devices that are electrically initiated.

Für die Kappvorrichtung 9 und auch die vorgenannten Verbindungsmittel 6 können im Rahmen des fachmännischen Handelns auch andere gleichartig wirkende Lösungen eingesetzt werden ohne dass der Rahmen der vorliegenden Erfindung verlassen wird. Beispielsweise können auch mehrere Haltemittel 8 vorgesehen sein.For the capping device 9 and also the aforementioned connecting means 6, other identically acting solutions can be used without departing from the scope of the present invention within the scope of expert action. For example, a plurality of holding means 8 may be provided.

Nach der erfolgten Trennung des Haltemittels 8 durch die Kappvorrichtung 9 beginnt der Entfaltungsvorgang der Wickelflügel beginnend mit dem Wickelflügel mit dem Bezugszeichen 4. Sobald sich dieser ein Stück geöffnet hat hebt er auch das spitzenseitige Ende des Wickelflügels mit dem Bezugszeichen 1 an. Im weiteren Fortgang verschiebt sich das spitzenseitige Ende des Wickelflügels 1 so weit gegenüber seiner ursprünglichen Position bezüglich der Oberfläche von Wickelflügel 4, dass das weitere Verbindungsmittel 6b aus dem Innenraum des ersten Verbindungsmittels gleitet. Damit wird das spitzenseitige Ende des Wickelflügels 1 freigegeben und der Wickelflügel kann sich frei aufrichten.After the successful separation of the holding means 8 by the capping device 9, 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.

Der gleiche Vorgang findet anschließend auch bei den Verbindungsmitteln 6 zwischen den Wickelflügeln 1 und 2 und dann zwischen den Wickelflügeln 2 und 3 statt. Damit sind alle spitzenseitigen Enden frei und der Entfaltungsvorgang kann ungehindert bei allen vier Wickelflügeln zu Ende geführt werden.The same process then takes place also in the connection means 6 between the Winding wings 1 and 2 and then between the Winding wings 2 and 3 instead. Thus, all tip-side ends are free and the unfolding process can be performed unhindered at all four winding wings to the end.

Claims (3)

  1. An arrangement on wrap-around fins (1, 2, 3, 4) of a missile (5) which has n wrap-around fins, where n is greater than or equal to 2, that are rotatably mounted about axes, lying in the direction of flight, on the root side in the region of the outer surface of the missile, and in the rest position lie against the outer surface of the missile (5) and go over into the working position by means of a drive, characterised in that
    - arranged on n-1 wrap-around fins (1, 2, 3) in the tip-side region there are first connecting means (6a) which in the rest position of the wrap-around fins correspond with further connecting means (6b) that are arranged on the side, pointing outwards in the rest position, of the wrap-around fins (1, 2, 4) that are located underneath in each case, and
    - at least one holding means (8) that is mounted in the missile (5) and is releasable in a controlled manner engages on the n-th wrap-around fin (4) in the tip-side region.
  2. An arrangement according to claim 2 [sic], characterised in that the first connecting means (6a) are formed as hooks which in the rest position engage in further connecting means (6b) configured in a correspondingly opposite manner.
  3. An arrangement according to claim 1 or 2, characterised in that the holding means 8() [sic] consists of a pin or cable section that is connected to the n-th wrap-around fin (4) in a releasable manner and can be severed by means of a lopping device (9) that is arranged in the region of the outer surface of the missile (5) and can be triggered in a controlled manner.
EP07008992A 2006-05-12 2007-05-04 Wrap-around fins for a missile Active EP1855076B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006022248A DE102006022248B3 (en) 2006-05-12 2006-05-12 Retaining device on wrapped wings of flying object, allowing reliable release of wings into working position, comprises controlled release holder on one wing and cooperating fixtures on others

Publications (2)

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

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP07008992A Active EP1855076B1 (en) 2006-05-12 2007-05-04 Wrap-around fins for a missile

Country Status (4)

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3165869A1 (en) 2015-11-06 2017-05-10 MBDA Deutschland GmbH Folding wing for a missile and a missile having at least one folding wing arranged thereon
EP3165870A1 (en) 2015-11-06 2017-05-10 MBDA Deutschland GmbH Folding wing for a missile and a missile having at least one folding wing arranged thereon

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FR2911954B1 (en) * 2007-01-31 2009-04-24 Nexter Munitions Sa DEVICE FOR CONTROLLING AMMUNITION WITH DEPLOYABLE GOVERNMENTS
US8899515B2 (en) * 2012-05-18 2014-12-02 Textron Systems Corporation Folding configuration for air vehicle
DE102017113058B4 (en) 2017-06-14 2023-04-27 Deutsches Zentrum für Luft- und Raumfahrt e.V. space transport aircraft

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NL100549C (en) * 1953-12-21 Brandt Soc Nouv Ets
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
FR2356118A1 (en) * 1976-06-25 1978-01-20 Europ Propulsion EMPENNAGE FOR PROJECTILE
DE8428118U1 (en) * 1984-09-25 1986-07-03 Rheinmetall GmbH, 4000 Düsseldorf Tail unit with deployable wings
FR2659433B1 (en) * 1990-03-09 1992-05-15 Thomson Brandt Armements IMPROVEMENTS ON FENDERING WING TANKS.
JP3781311B2 (en) * 1995-12-01 2006-05-31 株式会社小松製作所 Aircraft wing device

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3165869A1 (en) 2015-11-06 2017-05-10 MBDA Deutschland GmbH Folding wing for a missile and a missile having at least one folding wing arranged thereon
EP3165870A1 (en) 2015-11-06 2017-05-10 MBDA Deutschland GmbH Folding wing for a missile and a missile having at least one folding wing arranged thereon
DE102015014367A1 (en) 2015-11-06 2017-05-11 Mbda Deutschland Gmbh Folding wing for a missile and missile with at least one folding wing arranged thereon
DE102015014368A1 (en) 2015-11-06 2017-05-11 Mbda Deutschland Gmbh Folding wing for a missile and a missile with at least one folding wing arranged thereon
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 (en) 2015-11-06 2020-07-16 Mbda Deutschland Gmbh Folding wing for a missile and missile with at least one folding wing arranged thereon

Also Published As

Publication number Publication date
EP1855076A1 (en) 2007-11-14
DE102006022248B3 (en) 2007-11-08
NO20072442L (en) 2007-11-13
NO339122B1 (en) 2016-11-14
DE502007000219D1 (en) 2008-12-18
ATE413580T1 (en) 2008-11-15

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