EP1887307A2 - Device for an optical fiber when starting a missile - Google Patents

Device for an optical fiber when starting a missile Download PDF

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Publication number
EP1887307A2
EP1887307A2 EP07015057A EP07015057A EP1887307A2 EP 1887307 A2 EP1887307 A2 EP 1887307A2 EP 07015057 A EP07015057 A EP 07015057A EP 07015057 A EP07015057 A EP 07015057A EP 1887307 A2 EP1887307 A2 EP 1887307A2
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EP
European Patent Office
Prior art keywords
missile
launcher
coil
stern
tail
Prior art date
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Granted
Application number
EP07015057A
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German (de)
French (fr)
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EP1887307A3 (en
EP1887307B1 (en
Inventor
Horst Christof
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LFK Lenkflugkoerpersysteme GmbH
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LFK Lenkflugkoerpersysteme GmbH
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Publication of EP1887307A3 publication Critical patent/EP1887307A3/en
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Publication of EP1887307B1 publication Critical patent/EP1887307B1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/01—Arrangements thereon for guidance or control
    • F42B15/04—Arrangements thereon for guidance or control using wire, e.g. for guiding ground-to-ground rockets

Definitions

  • the invention relates to a device for a usable for the transmission of steering signals head of a missile, which is mounted in a launcher to the ignition of its engine, wherein a holder for the conductor is mounted in the launcher and at least one coil is attached to the rear of the missile and wherein the conductor within the launcher is surrounded by a telescopically extending tubular device whose first end is secured in the region of the bracket mounted at the rear end of the launcher and the second end abuts the tail of the launcher at launch approximately to the outer end of the launcher ,
  • Ground / ground or ground / air missiles launched from launcher devices are typically connected to the launcher via an optical fiber and also to a missile control device during its mission.
  • the optical waveguide serves the bidirectional data connection between the device for controlling the rear end and the control electronics in the missile.
  • the optical waveguide is divided depending on the load occurring in several differently assembled sections.
  • a part of the optical waveguide is wound in the launcher on a first coil.
  • Another major part of the optical fiber is located on another coil, which is carried by the missile at the rear.
  • the portion of the optical fiber located between the tail of the missile and the first coil is exposed to the engine's hot gas jet at least over time while the missile is still within the launcher.
  • the DE 1 578 073 A describes a telescopically extending at the start of the missile tubular device for the protection of the wire-shaped and Data transfer of usable conductor.
  • the device is mounted on a bracket at the rear end of the launcher.
  • the second end of the device is connected to the end of the missile via a predetermined breaking point, is applied to about the outer end of the launcher and ruptures on leaving the launcher.
  • This protective sheath is made of reinforced material and surrounds the optical fiber over a certain length, which is shorter than the launcher from which the missile is launched.
  • the storage of the optical waveguide surrounded by a protective sleeve on the missile is elaborately designed and requires at least one direction reversal with narrow loop formation of the optical waveguide.
  • a third coil is arranged between the first and the further coil of the optical waveguide.
  • This third coil is initially suspended at the tail of the missile at launch and is abruptly braked shortly before reaching the end of the launcher, so that the now only beginning unwinding of the optical fiber from the first coil attached to the missile also starts jerky.
  • the corresponding optical waveguide section is subjected to very high mechanical loading, which may lead to the failure of the ability to transmit data and thus make the successful completion of the mission impossible.
  • the device consists of a plurality of concentric nested tube sections which are spring loaded before the missile start and biased between the rear of the missile and the rear end of the launcher are arranged.
  • This achieves two decisive advantages.
  • the optical fiber from the ignition of the engine of the missile is protected until it leaves the launcher against harmful effects, since the device automatically unfolds in the manner of a telescope or unrolling device envelops the optical fiber and it is due to the bias of the device tearing avoided the breaking point.
  • no end portion of the optical waveguide is needed, which is protected against the engine windrows in a special way.
  • the device consists of a flat spiral spring with adjacent turns, which is arranged biased in the launcher. Both solutions meet the task in a simple way.
  • the device consists of a plurality of concentric nested tube sections, which are spring-loaded before the missile start and biased between the rear of the missile and the rear end of the launcher are arranged.
  • the device may consist of a flat spiral spring with adjacent turns, which is arranged biased in the launcher. Both solutions meet the task in a simple way.
  • the second end of the device is fastened to the tail of the missile by means of a separable connecting element.
  • the coupling of the device to the rear is improved without the required separation is difficult.
  • first end of the telescopically extending tubular device completely surrounds the first coil. This also protects the first coil from the engine wind.
  • the length of the telescopically extending device in a relaxed state is greater than or approximately equal to the length of the interior of the launcher.
  • the single drawing shows three successive phases of missile launch from a launcher utilizing the present invention.
  • the situation before the start of the missile 1 from the launcher 2 is reproduced.
  • the engine is not ignited yet.
  • the device 6 according to the invention is mounted between the tail 9 of the missile 1 and the rear end 12 of the launcher 2 biased. It surrounds with its first end 7, the first coil 3 of the optical waveguide 5 and is due to the inherent bias on the tail 9 of the missile.
  • the pushed-together device 6 completely surrounds the portion of the optical waveguide 5 located between the first coil 3 and the tail 9.
  • the launch has already been initiated and the already ignited engine of the missile has accelerated this far enough that his tail 9 is in the snapshot shown approximately in the middle of the launcher.
  • the device according to the invention has already relaxed a bit, which means of three sections 10 of the telescopically extending device 6 is shown.
  • the upper part of the device 6 is shown cut open, so that the unwinding of the coils 3 and 4 optical waveguide 5 is clearly visible. It lies completely protected in the interior of the device 6 in relation to the drive-off windrows emerging in the region of the tail of the missile.
  • the inventive device 6 is now extended to its maximum length and has no contact with the tail 9 of the missile 1. Good to recognize the six Pipe sections 10, which form the device 6.
  • the optical waveguide 5 is without any mechanical connection or support loosely within the device 6 and is therefore not limited by deflections, guides or similar devices in its mobility. A bending of the optical waveguide or a braking of only a part of the optical waveguide does not take place during the start, so that an interruption of the data traffic on the optical waveguide during the starting process is practically impossible.
  • the device may also consist of a flat coil spring, which is biased in the built-in or ready to start state and relaxes during the missile launch to a spirally wound tube.
  • the device may be completely closed at its first end 7 in order to avoid an effect of the engine swaths on the first coil 3.
  • the length of the device is ideally dimensioned such that the device 6 rests with its second end 8 on the tail 9 of the missile 1 until it has completely left the launcher 2

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Optical Couplings Of Light Guides (AREA)
  • Mechanical Light Control Or Optical Switches (AREA)
  • Optical Communication System (AREA)

Abstract

The device for optical transmitter of a missile for transmission of master signal, comprises a support mounted for the transmitter (5), which is surrounded within a launcher (2) by a telescope-like tubular device (6), whose first end completely surrounds a coil (3) secured on stern of the missile (1) and second end is secured to the stern of the missile by a separatable fastener. The transmitter is arranged in the launcher up to ignition of its engine. The tubular device has concentric tube sections lying with one another, and a flat spiral spring. The device for optical transmitter of a missile for transmission of master signal, comprises a support mounted for the transmitter (5), which is surrounded within a launcher (2) by a telescope-like tubular device (6), whose first end completely surrounds a coil (3) secured on stern of the missile (1) and second end is secured to the stern of the missile by a separatable fastener. The transmitter is arranged in the launcher up to ignition of its engine. The tubular device has concentric tube sections lying with one another, and a flat spiral spring, which is prestressed between the stern of the missile and rear end of the launcher. The tube sections are spring loaded and prestressed between the stern of the missile and rear end of the launcher and are arranged above the starting of the missile. The second end of the tubular device is secured to the stern of the missile by a separatable fastener. The length of the tubular device is larger or equal to the length of the interior area of the launcher.

Description

Die Erfindung betrifft eine Vorrichtung für einen zur Übertragung von Lenksignalen nutzbaren Leiter eines Flugkörpers, welcher in einer Abschussvorrichtung bis zur Zündung seines Triebwerks gelagert ist, wobei eine Halterung für den Leiter in der Abschussvorrichtung montiert ist und wenigstens eine Spule am Heck des Flugkörpers befestigt ist und wobei der Leiter innerhalb der Abschussvorrichtung von einer sich teleskopartig verlängernden rohrförmigen Vorrichtung umgeben ist, deren erstes Ende im Bereich der am rückwärtigen Ende der Abschussvorrichtung montierten Halterung befestigt ist und deren zweites Ende beim Start des Flugkörpers an dessen Heck bis etwa zum äußeren Ende der Abschussvorrichtung anliegt.The invention relates to a device for a usable for the transmission of steering signals head of a missile, which is mounted in a launcher to the ignition of its engine, wherein a holder for the conductor is mounted in the launcher and at least one coil is attached to the rear of the missile and wherein the conductor within the launcher is surrounded by a telescopically extending tubular device whose first end is secured in the region of the bracket mounted at the rear end of the launcher and the second end abuts the tail of the launcher at launch approximately to the outer end of the launcher ,

Boden/Boden- oder Boden/Luft-Flugkörper, die aus Abschussvorrichtungen gestartet werden, sind in der Regel über einen Lichtwellenleiter mit der Abschussvorrichtung und darüber hinaus mit einer Einrichtung zur Steuerung des Flugkörpers während seiner Mission verbunden. Der Lichtwellenleiter dient dabei der bidirektionaler Datenverbindung zwischen der Einrichtung zur Steuerung am rückwärtigen Ende und der Steuerelektronik im Flugkörper.Ground / ground or ground / air missiles launched from launcher devices are typically connected to the launcher via an optical fiber and also to a missile control device during its mission. The optical waveguide serves the bidirectional data connection between the device for controlling the rear end and the control electronics in the missile.

Der Lichtwellenleiter ist dabei in Abhängigkeit von der auftretenden Belastung in mehrere unterschiedlich konfektionierte Abschnitte aufgeteilt. Ein Teil des Lichtwellenleiters ist in der Abschussvorrichtung auf einer ersten Spule aufgewickelt. Ein weiterer größerer Teil des Lichtwellenleiters befindet sich auf einer weiteren Spule, welche vom Flugkörper am Heck mitgeführt wird. Beim Start aus der Abschussvorrichtung ist der Teil des Lichtwellenleiters, der sich zwischen dem Heck des Flugkörpers und der ersten Spule befindet, dem Heißgasstrahl des Triebwerks zumindest über die Zeit ausgesetzt, während der sich der Flugkörper noch innerhalb der Abschussvorrichtung befindet.The optical waveguide is divided depending on the load occurring in several differently assembled sections. A part of the optical waveguide is wound in the launcher on a first coil. Another major part of the optical fiber is located on another coil, which is carried by the missile at the rear. At launch from the launcher, the portion of the optical fiber located between the tail of the missile and the first coil is exposed to the engine's hot gas jet at least over time while the missile is still within the launcher.

Die DE 1 578 073 A beschreibt eine sich beim Start des Flugkörpers teleskopartig verlängernde rohrförmige Vorrichtung zum Schutz des drahtförmigen und zur Datenübertragung nutzbaren Leiters. Die Vorrichtung ist am rückwärtigen Ende der Abschussvorrichtung an einer Halterung montiert. Das zweite Ende der Vorrichtung ist mit dem Ende des Flugkörpers über eine Sollbruchstelle verbunden, liegt bis etwa zum äußeren Ende der Abschussvorrichtung an und reisst beim Verlassen der Abschussvorrichtung ab.The DE 1 578 073 A describes a telescopically extending at the start of the missile tubular device for the protection of the wire-shaped and Data transfer of usable conductor. The device is mounted on a bracket at the rear end of the launcher. The second end of the device is connected to the end of the missile via a predetermined breaking point, is applied to about the outer end of the launcher and ruptures on leaving the launcher.

Zum Schutz gegen derartige Hitzeeinwirkungen sind Schutzhüllen entwickelt worden, wie sie beispielsweise in der EP 0 660 071 A1 beschrieben sind. Diese Schützhülle besteht aus verstärktem Material und umgibt den Lichtwellenleiter über eine bestimmte Länge, die kürzer als die Abschussvorrichtung ist, aus welcher der Flugkörper gestartet wird. Die Lagerung des mit einer Schutzhülle umgebenen Lichtwellenleiters am Flugkörper ist aufwändig gestaltet und bedingt zumindest eine Richtungsumkehr mit enger Schlaufenbildung des Lichtwellenleiters.To protect against such effects of heat protective covers have been developed, as for example in the EP 0 660 071 A1 are described. This protective sheath is made of reinforced material and surrounds the optical fiber over a certain length, which is shorter than the launcher from which the missile is launched. The storage of the optical waveguide surrounded by a protective sleeve on the missile is elaborately designed and requires at least one direction reversal with narrow loop formation of the optical waveguide.

Darüber hinaus sind Lösungen bekannt geworden, bei denen eine dritte Spule zwischen der ersten und der weiteren Spule des Lichtwellenleiters angeordnet ist. Diese dritte Spule hängt beim Start zunächst am Heck des Flugkörpers und wird kurz vor dem Erreichen des Endes der Abschussvorrichtung schlagartig abgebremst, so dass der nun erst beginnende Abwickelvorgang des Lichtwellenleiters von der am Flugkörper befestigten ersten Spule ebenso ruckartig beginnt. Damit wird der entsprechende Lichtwellenleiterabschnitt mechanisch sehr hoch belastet, was unter Umständen zum Ausfall der Fähigkeit, Daten übertragen zu können, führt und damit den erfolgreichen Abschluss der Mission unmöglich macht.In addition, solutions have become known in which a third coil is arranged between the first and the further coil of the optical waveguide. This third coil is initially suspended at the tail of the missile at launch and is abruptly braked shortly before reaching the end of the launcher, so that the now only beginning unwinding of the optical fiber from the first coil attached to the missile also starts jerky. Thus, the corresponding optical waveguide section is subjected to very high mechanical loading, which may lead to the failure of the ability to transmit data and thus make the successful completion of the mission impossible.

Es ist deshalb Aufgabe der vorliegenden Erfindung, eine Vorrichtung für einen Lichtwellenleiter zu entwickeln, welche beim Start eines Flugkörpers aus einer Abschussvorrichtung den gerade abgewickelten Teil des Lichtwellenleiters gegen die Einflüsse des Abgasstrahls des Triebwerks schützt, keine Sollbruchstelle benötigt und während des Startvorgangs jegliche ruckartige Belastung des Lichtwellenleiters vermeiden hilft.It is therefore an object of the present invention to develop a device for an optical waveguide which protects the start of a missile from a launcher just unwound part of the optical fiber against the influences of the exhaust jet of the engine, no breaking point required and during the startup any jerky load of Avoid fiber optic cable helps.

Die Aufgabe wird erfindungsgemäß dadurch gelöst, dass die Vorrichtung aus einer Vielzahl konzentrisch ineinander liegender Rohrabschnitte besteht, welche vor dem Flugkörperstart federbelastet und vorgespannt zwischen dem Heck des Flugkörpers und dem rückwärtigen Ende der Abschussvorrichtung angeordnet sind. Damit werden zwei entscheidende Vorteile erzielt. Zum einen ist der Lichtwellenleiter von der Zündung des Triebwerks des Flugkörpers an bis zum Verlassen der Abschussvorrichtung gegen schädigende Einflüsse geschützt, da die sich selbsttätig in der Art eines Teleskops entfaltende oder entrollende Vorrichtung den Lichtwellenleiter umhüllt und es wird aufgrund der Vorspannung der Vorrichtung das Abreissen an der Sollbruchstelle vermieden. Zum anderen wird kein Endabschnitt des Lichtwellenleiters benötigt, der gegen die Triebwerksschwaden in besonderer Weise geschützt ist. Da an der Trennstelle zwischen dem verstärkten und dem unverstärkten Lichtwellenleiterabschnitt normalerweise eine beim Start des Flugkörpers sich mitbewegende Spule angeordnet ist, die an der Öffnung des Abschussbehälters abgebremst werden muss, kann unter Nutzung der Erfindung auf diese Spule verzichtet werden. Dadurch entfällt auch die heftige Bremsung dieser Spule, durch die auf den Lichtwellenleiter eine entsprechend hohe Belastung ausgeübt würde.The object is achieved in that the device consists of a plurality of concentric nested tube sections which are spring loaded before the missile start and biased between the rear of the missile and the rear end of the launcher are arranged. This achieves two decisive advantages. First, the optical fiber from the ignition of the engine of the missile is protected until it leaves the launcher against harmful effects, since the device automatically unfolds in the manner of a telescope or unrolling device envelops the optical fiber and it is due to the bias of the device tearing avoided the breaking point. On the other hand, no end portion of the optical waveguide is needed, which is protected against the engine windrows in a special way. Since at the point of separation between the reinforced and the unreinforced optical waveguide section normally arranged at the start of the missile moving coil is arranged, which must be braked at the opening of the launching container, can be dispensed with using the invention on this coil. This also eliminates the violent braking of this coil, through which a correspondingly high load would be exerted on the optical waveguide.

Eine vorteilhafte Weiterentwicklung der Erfindung liegt darin, dass die Vorrichtung aus einer flächigen Spiralfeder mit aneinander liegenden Windungen besteht, welche vorgespannt in der Abschussvorrichtung angeordnet ist. Beide Lösungen erfüllen auf einfache Weise die gestellte Aufgabe.An advantageous development of the invention is that the device consists of a flat spiral spring with adjacent turns, which is arranged biased in the launcher. Both solutions meet the task in a simple way.

Eine vorteilhafte Weiterentwicklung der Erfindung liegt darin, dass die Vorrichtung aus einer Vielzahl konzentrisch ineinander liegender Rohrabschnitte besteht, welche vor dem Flugkörperstart federbelastet und vorgespannt zwischen dem Heck des Flugkörpers und dem rückwärtigen Ende der Abschussvorrichtung angeordnet sind. Alternativ dazu kann die Vorrichtung aus einer flächigen Spiralfeder mit aneinander liegenden Windungen bestehen, welche vorgespannt in der Abschussvorrichtung angeordnet ist. Beide Lösungen erfüllen auf einfache Weise die gestellte Aufgabe.An advantageous development of the invention is that the device consists of a plurality of concentric nested tube sections, which are spring-loaded before the missile start and biased between the rear of the missile and the rear end of the launcher are arranged. Alternatively, the device may consist of a flat spiral spring with adjacent turns, which is arranged biased in the launcher. Both solutions meet the task in a simple way.

In vorteilhafter Weise wird vorgeschlagen, dass das zweite Ende der Vorrichtung am Heck des Flugkörpers mittels eines trennbaren Verbindungselements befestigt ist. Somit wird die Kopplung der Vorrichtung an das Heck verbessert ohne dass die erforderliche Trennung erschwert wird.It is advantageously proposed that the second end of the device is fastened to the tail of the missile by means of a separable connecting element. Thus, the coupling of the device to the rear is improved without the required separation is difficult.

Es hat sich als geeignet erwiesen, wenn das erste Ende der sich teleskopartig verlängernden rohrförmigen Vorrichtung die erste Spule vollständig umgibt. Damit wird auch die erste Spule vor den Triebwerksschwaden geschützt.It has proved to be suitable if the first end of the telescopically extending tubular device completely surrounds the first coil. This also protects the first coil from the engine wind.

Schließlich hat es sich als vorteilhaft erwiesen, dass die Länge der sich teleskopartig verlängernden Vorrichtung in entspanntem Zustand größer oder etwa gleich der Länge des Innenraums der Abschussvorrichtung ist.Finally, it has proved to be advantageous that the length of the telescopically extending device in a relaxed state is greater than or approximately equal to the length of the interior of the launcher.

Ein Ausführungsbeispiel der Erfindung ist schematisch vereinfacht in der Zeichnung dargestellt und wird im Folgenden näher beschrieben.An embodiment of the invention is shown schematically simplified in the drawing and will be described in more detail below.

Die einzige Zeichnung zeigt drei aufeinander folgende Phasen eines Flugkörperstarts aus einer Abschussvorrichtung unter Nutzung der vorliegenden Erfindung. In der oben dargestellten Phase ist die Situation vor dem Start des Flugkörpers 1 aus der Abschussvorrichtung 2 wiedergegeben. Das Triebwerk ist noch nicht gezündet. Zwischen dem Heck 9 des Flugkörpers 1 und dem rückwärtigen Ende 12 der Abschussvorrichtung 2 ist vorgespannt die erfindungsgemäße Vorrichtung 6 montiert. Sie umgibt mit ihrem ersten Ende 7 die erste Spule 3 des Lichtwellenleiters 5 und liegt aufgrund der ihr innewohnenden Vorspannung am Heck 9 des Flugkörpers an. Somit umgibt die zusammen geschobene Vorrichtung 6 vollständig den zwischen der ersten Spule 3 und dem Heck 9 befindlichen Abschnitt des Lichtwellenleiters 5.The single drawing shows three successive phases of missile launch from a launcher utilizing the present invention. In the phase shown above, the situation before the start of the missile 1 from the launcher 2 is reproduced. The engine is not ignited yet. Between the tail 9 of the missile 1 and the rear end 12 of the launcher 2 biased the device 6 according to the invention is mounted. It surrounds with its first end 7, the first coil 3 of the optical waveguide 5 and is due to the inherent bias on the tail 9 of the missile. Thus, the pushed-together device 6 completely surrounds the portion of the optical waveguide 5 located between the first coil 3 and the tail 9.

In der in der Mitte der Zeichnung dargestellten Phase ist der Start bereits eingeleitet worden und das bereits gezündete Triebwerk des Flugkörpers hat diesen soweit beschleunigt, dass sich sein Heck 9 in der dargestellten Momentaufnahme etwa in der Mitte der Abschussvorrichtung befindet. Die erfindungsgemäße Vorrichtung hat sich bereits etwas entspannt, was mittels der drei Abschnitte 10 der sich teleskopartig verlängernden Vorrichtung 6 wiedergegeben ist. Der obere Teil der Vorrichtung 6 ist aufgeschnitten dargestellt, so dass der sich von den Spulen 3 und 4 abwickelnde Lichtwellenleiter 5 gut erkennbar ist. Er liegt gegenüber den im Bereich des Hecks des Flugkörpers austretenden Treibwerksschwaden völlig geschützt im Inneren der Vorrichtung 6.In the phase shown in the middle of the drawing, the launch has already been initiated and the already ignited engine of the missile has accelerated this far enough that his tail 9 is in the snapshot shown approximately in the middle of the launcher. The device according to the invention has already relaxed a bit, which means of three sections 10 of the telescopically extending device 6 is shown. The upper part of the device 6 is shown cut open, so that the unwinding of the coils 3 and 4 optical waveguide 5 is clearly visible. It lies completely protected in the interior of the device 6 in relation to the drive-off windrows emerging in the region of the tail of the missile.

In der unten in der Zeichnung dargestellten Phase zeigt den Flugkörper 1 kurz nach dem Austritt aus der Abschussvorrichtung 2. Die erfindungsgemäße Vorrichtung 6 ist nun auf ihre maximale Länge ausgefahren und hat keinen Kontakt mehr zum Heck 9 des Flugkörpers 1. Gut zu erkennen sind die sechs Rohrabschnitte 10, welche die Vorrichtung 6 bilden. Der Lichtwellenleiter 5 liegt ohne jegliche mechanische Verbindung oder Halterung lose innerhalb der Vorrichtung 6 und wird aus diesem Grund nicht durch Umlenkungen, Führungen oder ähnliche Einrichtungen in seiner Beweglichkeit eingeschränkt. Ein Knicken des Lichtwellenleiters oder eine Bremsung auch nur eines Teils des Lichtwellenleiters findet während des Starts nicht statt, so dass eine Unterbrechung des Datenverkehrs auf dem Lichtwellenleiter während des Startvorgangs praktisch ausgeschlossen ist.In the phase shown below in the drawing shows the missile 1 shortly after exiting the launcher 2. The inventive device 6 is now extended to its maximum length and has no contact with the tail 9 of the missile 1. Good to recognize the six Pipe sections 10, which form the device 6. The optical waveguide 5 is without any mechanical connection or support loosely within the device 6 and is therefore not limited by deflections, guides or similar devices in its mobility. A bending of the optical waveguide or a braking of only a part of the optical waveguide does not take place during the start, so that an interruption of the data traffic on the optical waveguide during the starting process is practically impossible.

Gemäß den Unteransprüchen sind im Rahmen der Erfindung auch andere Bauweisen der Vorrichtung möglich. So kann die Vorrichtung auch aus einer flächigen Spiralfeder bestehen, die im Einbau- oder Startbereitschafts-Zustand vorgespannt ist und sich während des Flugkörperstarts zu einem spiralig gewickelten Rohr entspannt.According to the subclaims, other constructions of the device are possible within the scope of the invention. Thus, the device may also consist of a flat coil spring, which is biased in the built-in or ready to start state and relaxes during the missile launch to a spirally wound tube.

Als Ausgestaltung ist es auch denkbar, das zweite Ende 8 der Vorrichtung 6 mit Hilfe einer leicht trennbaren Vorrichtung an das Heck 9 des Flugkörpers zu koppeln. Damit wird der Entspannungsvorgang der Vorrichtung unterstützt. Der Abtrennvorgang wirkt sich nicht unmittelbar auf den Lichtwellenleiter 5 aus, so dass diese Ausführungsform die gleichen Vorteile wie die bisher beschriebenen aufweist.As an embodiment, it is also conceivable to couple the second end 8 of the device 6 with the aid of an easily separable device to the tail 9 of the missile. This supports the relaxation process of the device. The separation process does not affect directly on the optical waveguide 5, so that this embodiment has the same advantages as those described so far.

Je nach Bauform der Abschussvorrichtung kann es hilfreich sein, dass die Vorrichtung an ihrem ersten Ende 7 vollständig geschlossen ist um eine Einwirkung der Triebwerksschwaden auf die erste Spule 3 zu vermeiden.Depending on the design of the launching device, it may be helpful for the device to be completely closed at its first end 7 in order to avoid an effect of the engine swaths on the first coil 3.

Die Länge der Vorrichtung ist in idealer Weise so bemessen, dass die Vorrichtung 6 mit ihrem zweiten Ende 8 solange am Heck 9des Flugkörpers 1 anliegt, bis dieser die Abschussvorrichtung 2 vollständig verlassen hatThe length of the device is ideally dimensioned such that the device 6 rests with its second end 8 on the tail 9 of the missile 1 until it has completely left the launcher 2

Im Rahmen des fachmännischen Handelns ist es natürlich möglich, gleichwirkende Varianten zu den bereits beschriebenen zur Anwendung zu bringen.In the context of expert action, it is of course possible to apply similar variants to those already described.

Claims (6)

Vorrichtung für einen zur Übertragung von Lenksignalen nutzbaren Leiter eines Flugkörpers, welcher in einer Abschussvorrichtung bis zur Zündung seines Triebwerks gelagert ist, wobei eine Halterung für den Leiter in der Abschussvorrichtung montiert ist und wenigstens eine Spule am Heck des Flugkörpers befestigt ist und wobei der Leiter innerhalb der Abschussvorrichtung von einer sich teleskopartig verlängernden rohrförmigen Vorrichtung umgeben ist, deren erstes Ende im Bereich der am rückwärtigen Ende der Abschussvorrichtung montierten Halterung befestigt ist und deren zweites Ende beim Start des Flugkörpers an dessen Heck bis etwa zum äußeren Ende der Abschussvorrichtung anliegt, dadurch gekennzeichnet, dass die Vorrichtung (6) aus einer Vielzahl konzentrisch ineinander liegender Rohrabschnitte (10) besteht, welche vor dem Flugkörperstart federbelastet und vorgespannt zwischen dem Heck (9) des Flugkörpers (1) und dem rückwärtigen Ende (12) der Abschussvorrichtung (2) angeordnet sind.Device for a usable for the transmission of steering signals head of a missile, which is mounted in a launcher to the ignition of its engine, wherein a holder for the conductor is mounted in the launcher and at least one coil is attached to the rear of the missile and wherein the conductor within the launcher is surrounded by a telescopically extending tubular device, the first end of which is fixed in the area of the bracket mounted at the rear end of the launcher and the second end of which abuts the tail of the launcher when it starts to approximately the outer end of the launcher, characterized in that the device (6) consists of a multiplicity of concentrically nested tube sections (10) which are spring-loaded prior to the launch of the missile and biased between the tail (9) of the missile (1) and the rear end (12) of the launching device (2) a are subordinate. Vorrichtung für einen Leiter eines Flugkörpers nach Anspruch 1, dadurch gekennzeichnet, dass die Vorrichtung (6) aus einer flächigen Spiralfeder besteht, welche vorgespannt zwischen dem Heck (9) des Flugkörpers (1) und dem rückwärtigen Ende (12) der Abschussvorrichtung (2) angeordnet ist.Device for a ladder of a missile according to claim 1, characterized in that the device (6) consists of a flat spiral spring which is prestressed between the tail (9) of the missile (1) and the rear end (12) of the launching device (2). is arranged. Vorrichtung für einen Lichtwellenleiter eines Flugkörpers nach Anspruch 1, dadurch gekennzeichnet, dass die Vorrichtung (6) aus einer flächigen Spiralfeder besteht, welche vorgespannt zwischen dem Heck (9) des Flugkörpers (1) und dem rückwärtigen Ende (12) der Abschussvorrichtung (2) angeordnet ist.Device for an optical waveguide of a missile according to claim 1, characterized in that the device (6) consists of a flat spiral spring which is prestressed between the tail (9) of the missile (1) and the rear end (12) of the launching device (2). is arranged. Vorrichtung für einen Lichtwellenleiter eines Flugkörpers nach Anspruch 1, dadurch gekennzeichnet, dass das zweite Ende (8) der Vorrichtung am Heck (9) des Flugkörpers (1) mittels eines trennbaren Verbindungselements befestigt ist.Device for an optical waveguide of a missile according to claim 1, characterized in that the second end (8) of the device at the rear (9) of the missile (1) is fastened by means of a separable connecting element. Vorrichtung für einen Lichtwellenleiter eines Flugkörpers nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass das erste Ende (7) der sich teleskopartig verlängernden rohrförmigen Vorrichtung (6) die erste Spule (3) vollständig umgibt.Device for an optical waveguide of a missile according to one of claims 1 to 4, characterized in that the first end (7) of the telescopically extending tubular device (6) completely surrounds the first coil (3). Vorrichtung für einen Lichtwellenleiter eines Flugkörpers nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Länge der sich teleskopartig verlängernden Vorrichtung (6) in entspanntem Zustand größer oder etwa gleich der Länge des Innenraums der Abschussvorrichtung (2) ist.Device for an optical fiber of a missile according to one of claims 1 to 5, characterized in that the length of the telescopically extending device (6) in the relaxed state is greater than or approximately equal to the length of the interior of the launcher (2).
EP07015057A 2006-08-10 2007-08-01 Device for an optical fiber when starting a missile Not-in-force EP1887307B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006037332A DE102006037332A1 (en) 2006-08-10 2006-08-10 Device for an optical waveguide at the start of a missile

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EP1887307A2 true EP1887307A2 (en) 2008-02-13
EP1887307A3 EP1887307A3 (en) 2010-02-10
EP1887307B1 EP1887307B1 (en) 2011-10-12

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EP (1) EP1887307B1 (en)
AT (1) ATE528611T1 (en)
DE (2) DE202006020409U1 (en)
NO (1) NO339592B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4343266A1 (en) * 2022-09-21 2024-03-27 Diehl Defence GmbH & Co. KG Coil unit for a guided missile

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1578073A1 (en) 1966-06-18 1971-04-22 Messerschmitt Boelkow Blohm Device for protecting a wire connection used for signal transmission of a recoil-driven missile launched from a launch tube
US4974793A (en) 1989-12-15 1990-12-04 The Boeing Company Tapered chamber dispensing of optical fiber
DE68907257T2 (en) 1988-04-14 1993-12-16 Aerospatiale Storage and launch unit for a wire guided missile.

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5385319A (en) 1993-11-22 1995-01-31 Hughes Missile Systems Company Missile with inside payout optical fiber canister
FR2720822B1 (en) * 1994-06-02 1996-08-23 Aerospatiale Installation for conditioning and launching a guided missile.

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1578073A1 (en) 1966-06-18 1971-04-22 Messerschmitt Boelkow Blohm Device for protecting a wire connection used for signal transmission of a recoil-driven missile launched from a launch tube
DE68907257T2 (en) 1988-04-14 1993-12-16 Aerospatiale Storage and launch unit for a wire guided missile.
US4974793A (en) 1989-12-15 1990-12-04 The Boeing Company Tapered chamber dispensing of optical fiber

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4343266A1 (en) * 2022-09-21 2024-03-27 Diehl Defence GmbH & Co. KG Coil unit for a guided missile

Also Published As

Publication number Publication date
ATE528611T1 (en) 2011-10-15
NO20074123L (en) 2008-02-11
NO339592B1 (en) 2017-01-09
DE102006037332A1 (en) 2008-02-14
EP1887307A3 (en) 2010-02-10
DE202006020409U1 (en) 2008-07-17
EP1887307B1 (en) 2011-10-12

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