EP1887307B1 - Dispositif pour un guide optique pour le démarrage d'un corps volant - Google Patents

Dispositif pour un guide optique pour le démarrage d'un corps volant Download PDF

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Publication number
EP1887307B1
EP1887307B1 EP07015057A EP07015057A EP1887307B1 EP 1887307 B1 EP1887307 B1 EP 1887307B1 EP 07015057 A EP07015057 A EP 07015057A EP 07015057 A EP07015057 A EP 07015057A EP 1887307 B1 EP1887307 B1 EP 1887307B1
Authority
EP
European Patent Office
Prior art keywords
missile
launcher
launch
stern
optical waveguide
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.)
Not-in-force
Application number
EP07015057A
Other languages
German (de)
English (en)
Other versions
EP1887307A2 (fr
EP1887307A3 (fr
Inventor
Horst Christof
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 EP1887307A2 publication Critical patent/EP1887307A2/fr
Publication of EP1887307A3 publication Critical patent/EP1887307A3/fr
Application granted granted Critical
Publication of EP1887307B1 publication Critical patent/EP1887307B1/fr
Not-in-force 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
    • 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 an elongated tubular device, the first end of which is secured in the region of the bracket mounted to the rear end of the launcher and the second end of which abuts the tail of the launcher at launch until about 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 transmission usable conductor.
  • the device is at the rear end the launcher mounted on a bracket.
  • 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.
  • a steering missile storage and launch unit comprising a launcher having a support for the ladder and having a coil secured to the tail of the missile, the ladder within the launcher being surrounded by a telescopically extending device consists of a plurality of nested tube sections (starting point for the preamble of independent claim 1).
  • the US 4974793 A shows an extension of a protective device for an optical conductor against the exhaust gas jet of a missile by relaxing prestressed springs, wherein the protective device is attached to the missile.
  • the object is achieved by a device having the features of independent claim 1.
  • the optical fiber from the ignition of the engine of the missile is protected until it leaves the launcher against harmful effects, since the self-unfolding or unrolling device envelops the optical fiber and it is due to the bias of the device prevents the tearing at the predetermined breaking point.
  • no end portion of the optical waveguide is needed, which against the engine windrows is protected 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.
  • 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.
  • the length of the elongating device in the relaxed state is greater than or approximately equal to the length of the interior of the launcher.
  • the single drawing shows three consecutive phases of a missile launch from a launcher.
  • the situation before the start of the missile 1 from the launcher 2 is reproduced.
  • the engine is not yet ignited.
  • the device 6 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 has already relaxed somewhat, which is reproduced by means of the three sections 10 of the telescopically extending device 6.
  • 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 traction wings 11 exiting in the region of the tail of the missile.
  • 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 consists 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

Landscapes

  • 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 Communication System (AREA)
  • Mechanical Light Control Or Optical Switches (AREA)
  • Optical Couplings Of Light Guides (AREA)

Claims (5)

  1. Dispositif pour un conducteur (5) utilisable pour la transmission de signaux de guidage d'un missile (1), reposant dans un dispositif de lancement (2) jusqu'à la mise à feu de son propulseur, dans lequel un support pour le conducteur (5) est monté dans le dispositif de lancement (2) et au moins une bobine (3) est fixée à l'empennage du missile (1) et dans lequel le conducteur (5) dans le dispositif de lancement est entouré d'un dispositif tubulaire (6) pouvant s'allonger, dont la première extrémité est fixée à proximité du support monté à l'extrémité arrière du dispositif de lancement et dont la deuxième extrémité, lors du lancement du missile (1), s'appuie contre son empennage environ jusqu'à l'extrémité externe du dispositif de lancement (2), caractérisé en ce que le dispositif (6) est constitué d'un ressort en spirale en forme de surface disposé précontraint entre l'empennage (9) du missile (1) et l'extrémité arrière (12) du dispositif de lancement (2).
  2. Dispositif pour une fibre optique d'un missile selon la revendication 1, caractérisé en ce que le dispositif (6) est constitué d'un ressort en spirale en forme de surface disposé précontraint entre l'empennage (9) du missile (1) et l'extrémité arrière (12) du dispositif de lancement (2).
  3. Dispositif pour une fibre optique d'un missile selon la revendication 1, caractérisé en ce que la deuxième extrémité (8) du dispositif (6) est fixée à l'empennage (9) du missile (1) au moyen d'un élément de liaison séparable.
  4. Dispositif pour une fibre optique d'un missile selon une des revendications 1 à 3, caractérisé en ce que la première extrémité (7) du dispositif tubulaire (6) pouvant s'allonger de manière télescopique entoure totalement la première bobine (3).
  5. Dispositif pour une fibre optique d'un missile selon une des revendications 1 à 4, caractérisé en ce que la longueur dans l'état détendu du dispositif (6) pouvant s'allonger de manière télescopique, est supérieure ou environ égale à la longueur de l'espace intérieur du dispositif de lancement (2).
EP07015057A 2006-08-10 2007-08-01 Dispositif pour un guide optique pour le démarrage d'un corps volant Not-in-force EP1887307B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006037332A DE102006037332A1 (de) 2006-08-10 2006-08-10 Vorrichtung für einen Lichtwellenleiter beim Start eines Flugkörpers

Publications (3)

Publication Number Publication Date
EP1887307A2 EP1887307A2 (fr) 2008-02-13
EP1887307A3 EP1887307A3 (fr) 2010-02-10
EP1887307B1 true EP1887307B1 (fr) 2011-10-12

Family

ID=38508820

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07015057A Not-in-force EP1887307B1 (fr) 2006-08-10 2007-08-01 Dispositif pour un guide optique pour le démarrage d'un corps volant

Country Status (4)

Country Link
EP (1) EP1887307B1 (fr)
AT (1) ATE528611T1 (fr)
DE (2) DE202006020409U1 (fr)
NO (1) NO339592B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022003485A1 (de) * 2022-09-21 2024-03-21 Diehl Defence Gmbh & Co. Kg Spuleneinheit für einen Lenkflugkörper

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1578073A1 (de) * 1966-06-18 1971-04-22 Messerschmitt Boelkow Blohm Einrichtung zum Schutz einer der Signaluebertragung dienenden Drahtverbindung eines rueckstossgetriebenen,aus einem Abschussrohr startenden Flugkoerpers
FR2630202B1 (fr) 1988-04-14 1990-08-17 Aerospatiale Installation de conditionnement et de lancement d'un missile filoguide
US4974793A (en) 1989-12-15 1990-12-04 The Boeing Company Tapered chamber dispensing of optical fiber
US5385319A (en) 1993-11-22 1995-01-31 Hughes Missile Systems Company Missile with inside payout optical fiber canister
FR2720822B1 (fr) * 1994-06-02 1996-08-23 Aerospatiale Installation de conditionnement et de lancement d'un missile filoguidé.

Also Published As

Publication number Publication date
DE202006020409U1 (de) 2008-07-17
NO339592B1 (no) 2017-01-09
EP1887307A2 (fr) 2008-02-13
NO20074123L (no) 2008-02-11
DE102006037332A1 (de) 2008-02-14
EP1887307A3 (fr) 2010-02-10
ATE528611T1 (de) 2011-10-15

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