EP0337880A1 - Lagerungs- und Abschusseinheit für eine Drahtlenkrakete - Google Patents

Lagerungs- und Abschusseinheit für eine Drahtlenkrakete Download PDF

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Publication number
EP0337880A1
EP0337880A1 EP89401005A EP89401005A EP0337880A1 EP 0337880 A1 EP0337880 A1 EP 0337880A1 EP 89401005 A EP89401005 A EP 89401005A EP 89401005 A EP89401005 A EP 89401005A EP 0337880 A1 EP0337880 A1 EP 0337880A1
Authority
EP
European Patent Office
Prior art keywords
missile
container
protection device
installation according
wire
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
EP89401005A
Other languages
English (en)
French (fr)
Other versions
EP0337880B1 (de
Inventor
Michel Maree
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.)
Airbus Group SAS
Original Assignee
Airbus Group SAS
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 Airbus Group SAS filed Critical Airbus Group SAS
Priority to AT89401005T priority Critical patent/ATE91015T1/de
Publication of EP0337880A1 publication Critical patent/EP0337880A1/de
Application granted granted Critical
Publication of EP0337880B1 publication Critical patent/EP0337880B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • 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 packaging and launching installation of a guided missile equipped with lateral ejection thrusters.
  • a guided missile is a missile which is launched from a container to which it remains connected after its launch by a flexible information transmission member called "wire" in the following description.
  • This wire is used to transmit orders to the missile during flight, in order to modify its trajectory.
  • This technique has been used for many years for short or medium range missiles (up to 10 km), in particular because of its low cost and its relative insensitivity to interference.
  • the wire consists of a mini-cable comprising at least two copper conductors and carrying filaments made of organic materials such as polyester, polyaramide, etc.
  • the information used to modify the trajectory of the missile can also be transmitted through an optical fiber possibly reinforced with synthetic fibers.
  • the solution generally employed to avoid thermal aggressions consists in reinforcing the first meters of this member, which amounts to increasing its diameter. This increase in diameter has the effect of increasing aerodynamic forces. Generally, these efforts are then countered by strongly reinforcing the bonding of the first meters of wire wound inside the missile. As illustrated very diagrammatically in Figure 2, the high bonding strength of leads, during the unwinding of the yarn 16, to the formation of a radius of curvature r very small.
  • this small radius of curvature is generally not very restrictive. Indeed, the ductility of copper is high and its electrical conductivity is not affected by this radius.
  • a known solution consists in ensuring that the missile's thrusters are only actuated when they are outside the container. This result is obtained by providing an additional device making it possible, during a first phase of the launch, to bring the missile partly out of the container so that the thrusters are outside the latter. The propellants are then ignited during a second launch phase.
  • the subject of the invention is precisely an installation for packaging and launching a guided missile, which can be used regardless of the nature of the wire and in particular when the latter comprises an optical fiber, and the implementation of which does not modify the missile firing sequence and does not affect launch accuracy, this ins tallation also being inexpensive and requiring no special treatment of the first meters of wire.
  • an installation for launching and launching a wire-guided missile equipped with lateral ejection thrusters comprising a container-launcher for conditioning the missile provided with a bottom supporting a coupling assembly for 'a flexible member for transmitting information wound in the missile and leaving the latter by a rear orifice, characterized in that a deformable tubular protection device is placed in the container, around the member for transmitting information, this protection device comprising a first end connected to the container around the attachment assembly and a second end connected to the missile, around said rear orifice, so as to automatically detach from the missile during a launch, when the thrusters arrive outside the container.
  • the protection device is preferably sealed and its ends are tightly connected respectively to the container and to the missile.
  • the second end of the protection device is fixed to a device for wedging and guiding the missile in the container, this device being able to slide in the container during of the launch and being connected to the missile around the rear orifice, so as to detach from it automatically when the thrusters arrive outside the container.
  • the protection device comprises a sleeve made of flexible material. If it is necessary to give this sleeve a certain rigidity, guide pieces of the sleeve during deployment are fixed to the container, around the attachment assembly and inside the sleeve.
  • the protection device comprises rigid telescopic ferrules. These ferrules can either be provided with guidance and positioning appendages, or connected together by a sleeve made of a flexible material. The latter solution is used in particular when sealing is necessary.
  • FIG. 3a schematically represents an installation for packaging and storing a wire-guided missile 10 equipped with lateral ejection thrusters 14, under the storage conditions of this missile.
  • This installation comprises, in a known manner, a cylindrical conditioning and launching container 12 in which the missile 10 is housed entirely.
  • This container is provided with a bottom supporting in its central part an attachment assembly 18.
  • a flexible transmission member information such as an optical fiber 16 is wound in a rear central part of the missile 10. The end of this fiber leaves the missile 10 through an annular orifice 20 (FIG. 4a) formed at the rear of the latter, for be fixed to the attachment assembly 18 of the container 12.
  • a deformable tubular protection device 22 is placed in the container 12, between the bottom of the latter and the rear of the missile 10, so as to surround the part of the optical fiber 16 which unwinds between the bottom of the container and the rear of the missile when the propellants are fired 14.
  • the deformable tubular protection device 22 has a diameter approximately equal to the outside diameter of the missile and it is arranged coaxially inside the container 12.
  • the end of the protection device 22 located at the rear relative to the direction of advance of the missile when it is launched is fixed on the bottom of the container 12, around the attachment assembly 18.
  • the front end of the protection device 22 is fixed in turn on a member 24 ensuring the setting and guiding of the rear end of the missile inside the container 12.
  • This member 24 behaves like a carriage capable of sliding freely inside the container when the missile is launched and it is connected to the outer casing 10a (FIG. 4a) of the rear part of the missile surrounding the orifice 20, so as to move inside the container 12 with the missile 10 as long as the deformable protection device 22 is not fully deployed, as illustrated in FIG. 3b.
  • the connection of the member 24 on the rear end of the missile is however designed so that the member 24 is automatically detached from the missile when the protection device 22 is fully deployed as illustrated in FIG. 3c. Under these conditions, the propellants 14 are outside the container 12.
  • the member 24 can serve as an intermediary for a device (not shown) allowing the missile to be locked inside the container.
  • a second member 26 for wedging and guiding the front part of the missile is mounted inside the container 12. Like the member 24, this member 26 moves with the missile 10 by sliding freely inside the container when the missile fired. However, when the member 26 arrives near the outlet end of the container 12, a device (not shown) such as a stop automatically detaches it from the missile.
  • the members 24 and 26 can have any shape and, if necessary, be made in several parts. They can also, in some cases, be deleted.
  • the front end of the protection device 22 according to the invention is then connected directly to the rear part of the outer shell of the missile, around the annular orifice 20, so as to detach from it automatically when the protection device is fully deployed, as described above.
  • the deformable tubular protection device 22 makes it possible to prevent the part of the optical fiber 16 which unwinds when the propellants 14 of the missile are ignited from being damaged when these thrusters are still inside the container 12.
  • the protection device 22 then constitutes a tubular screen which channels the jets of hot gases leaving the propellants in the annular space delimited between the container 12 and this device 22.
  • this device is deformable, it deploys automatically as the distance between the rear of the missile 10 and the bottom of the container 12 increases, so that its role as a screen is ensured as long the propellants are inside the container.
  • the jets of hot gas leaving the propellants are no longer folded down by the walls of the container towards the optical fiber 16, so that protection of the latter is no longer necessary.
  • the protection device 22 then detaches automatically from the missile, which continues to run freely.
  • the protection device in the embodiment of FIG. 4a, consists of a sleeve 22a made of a flexible and waterproof material such as an elastomer.
  • the rear end of the sleeve 22a is tightly fixed on the outer peripheral surface of the attachment assembly 18.
  • the front end of the sleeve 22a is tightly fixed on the central part of the wedging member 24 and guidance. This latter member is fitted on the rear part of the outer casing 10a of the missile, so as to be made integral with the latter by the friction forces.
  • a seal 28 is placed inside the member 24 and cooperates sealingly with the cylindrical outer envelope 10a of the missile.
  • a second seal 30 is placed on a central projecting part 32 formed on the attachment assembly 18 and on which is fitted a ferrule 34 of the missile 10 internally delimiting the annular orifice 20 formed at the back of the latter.
  • the sleeve 22a When the missile 10 is stored inside its container 12, the sleeve 22a is coiled in successive folds in an area situated around the attachment assembly 18 and delimited between the bottom of the container and the frustoconical rear part of the envelope 10a of the missile. As indicated previously, the length of the deployed sleeve 22a is chosen so that it ensures the automatic separation of the member 24 and the missile when the lateral thrusters of the latter arrive outside the container 12.
  • FIG. 4b a variant of the embodiment of FIG. 4a is shown, usable in particular when it is necessary to give the flexible sleeve 22a a certain rigidity.
  • sleeve guide pieces such as rods 36 are fixed to the bottom of the container, around the attachment assembly 18, and inside the sleeve 22a.
  • These rods 36 are regularly distributed around the axis of the container 12 and extend approximately parallel to the generatrices of the outer shell of the missile, when the latter is in the storage position. They thus delimit the inner envelope of the sleeve 22a.
  • the front ends of the rods 36 pass through the wedging and guiding member 24, which slides freely on these rods and inside the container 12 during ignition.
  • FIG. 4c shows a second embodiment of the invention in which the deformable tubular protection device is constituted by a set of rigid telescopic ferrules 22b, of cylindrical shape.
  • the ferrule 22b of larger diameter is fixed to the device 24 for setting and guiding the missile while the ferrule 22b of smaller diameter is mounted on the attachment assembly 18 of the container 12.
  • the diameter of the other ferrules 22b decreases progressively from the missile towards the bottom of the container. Consequently, when the protection device constituted by the set of ferrules 22b is deployed, it is in the form of a slightly frustoconical tube whose diameter decreases towards the bottom of the container.
  • This structure gives the device 22b good resistance to the pressure of the gases leaving the missile propellants and promotes the relaxation of these gases.
  • the rear ends of the ferrules 22b have guide and positioning appendages 23 projecting radially inwards as far as the adjacent ferrule of smaller diameter and the front ends of the ferrules 22b are provided with guide and positioning appendages projecting radially outward to the adjacent ferrule of larger diameter.
  • these appendages 23, 25 automatically control the successive deployment of the ferrules during firing, as well as their positioning and their maintenance.
  • the total length of the protection device constituted by all of the fully deployed telescopic ferrules 22b is calculated such that these ferrules and the member 24 automatically detach from the missile when the propellants of the latter arrive outside the container 12.
  • FIG. 4d illustrates a variant of the embodiment of FIG. 4c.
  • the protection device is constituted by a series of telescopic ferrules 22b arranged in the same way as in the embodiment of FIG. 4c, but devoid of appendages.
  • the ferrules 22b can be either cylindrical or slightly frustoconical.
  • the front ends of the neighboring ferrules 22b are connected together by a sleeve 27, made of a flexible and waterproof material such as an elastomer.
  • the sleeve 27 is folded between the adjacent rigid ferrules 22b.
  • this variant makes it possible, like the embodiment of FIG. 4a, to seal the volume in which the optical fiber 16 is wound inside the missile.
  • seals comparable to seals 28 and 30 in FIG. 4a can be provided.
  • it makes it possible to benefit from the advantages mentioned above of the embodiment of FIG. 4c.
  • the invention is not limited to the embodiments which have just been described by way of example, but covers all variants thereof.
  • the protection device can be connected directly to the missile, the setting and guiding member being omitted.
  • these guide pieces can take a different shape from the rods 36, in particular the shape of a tapered ferrule carrying a series of rods oriented parallel to the axis of the container.

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)
  • Toys (AREA)
  • Buffer Packaging (AREA)
  • Ropes Or Cables (AREA)
  • Farming Of Fish And Shellfish (AREA)
EP89401005A 1988-04-14 1989-04-12 Lagerungs- und Abschusseinheit für eine Drahtlenkrakete Expired - Lifetime EP0337880B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT89401005T ATE91015T1 (de) 1988-04-14 1989-04-12 Lagerungs- und abschusseinheit fuer eine drahtlenkrakete.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8804951A FR2630202B1 (fr) 1988-04-14 1988-04-14 Installation de conditionnement et de lancement d'un missile filoguide
FR8804951 1988-04-14

Publications (2)

Publication Number Publication Date
EP0337880A1 true EP0337880A1 (de) 1989-10-18
EP0337880B1 EP0337880B1 (de) 1993-06-23

Family

ID=9365314

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89401005A Expired - Lifetime EP0337880B1 (de) 1988-04-14 1989-04-12 Lagerungs- und Abschusseinheit für eine Drahtlenkrakete

Country Status (5)

Country Link
EP (1) EP0337880B1 (de)
AT (1) ATE91015T1 (de)
DE (1) DE68907257T2 (de)
ES (1) ES2042022T3 (de)
FR (1) FR2630202B1 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1990013786A1 (en) * 1989-05-03 1990-11-15 Gec-Marconi Limited Data transmission lines
EP0685702A1 (de) 1994-06-02 1995-12-06 AEROSPATIALE Société Nationale Industrielle Abschussanlage für drahtgelenkte Raketten
FR2738214A1 (fr) * 1995-09-05 1997-03-07 Aerospatiale Systeme de telecommande d'un engin volant filoguide
GB2434193A (en) * 1994-01-22 2007-07-18 British Aerospace Missile launch apparatus
CN114184097A (zh) * 2021-12-01 2022-03-15 上海航天设备制造总厂有限公司 一种用于大直径箭体铁路运输防护衣和防护方法

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE202006020409U1 (de) 2006-08-10 2008-07-17 Lfk-Lenkflugkörpersysteme Gmbh Vorrichtung für einen Lichtwellenleiter beim Start eines Flugkörpers
DE102009060658B4 (de) 2009-12-22 2012-11-15 Diehl Bgt Defence Gmbh & Co. Kg Granate und Granatabschussvorrichtung

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3613618A (en) * 1965-12-02 1971-10-19 Licentia Gmbh Protective sheath for torpedo control wire
US3868883A (en) * 1964-02-20 1975-03-04 Mc Donnell Douglas Corp Guidance system
DE3132547C1 (de) * 1981-08-18 1982-12-09 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Abwickelvorrichtung für eine Lenkglasfaser eines Flugkörpers

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3868883A (en) * 1964-02-20 1975-03-04 Mc Donnell Douglas Corp Guidance system
US3613618A (en) * 1965-12-02 1971-10-19 Licentia Gmbh Protective sheath for torpedo control wire
DE3132547C1 (de) * 1981-08-18 1982-12-09 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Abwickelvorrichtung für eine Lenkglasfaser eines Flugkörpers

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1990013786A1 (en) * 1989-05-03 1990-11-15 Gec-Marconi Limited Data transmission lines
GB2434193A (en) * 1994-01-22 2007-07-18 British Aerospace Missile launch apparatus
GB2434191A (en) * 1994-01-22 2007-07-18 British Aerospace Missile launch apparatus
GB2434191B (en) * 1994-01-22 2007-12-05 British Aerospace Missile launch apparatus
GB2434193B (en) * 1994-01-22 2007-12-05 British Aerospace Missile launch apparatus
EP0685702A1 (de) 1994-06-02 1995-12-06 AEROSPATIALE Société Nationale Industrielle Abschussanlage für drahtgelenkte Raketten
FR2720822A1 (fr) * 1994-06-02 1995-12-08 Aerospatiale Installation de conditionnement et de lancement d'un missile filoguidé.
FR2738214A1 (fr) * 1995-09-05 1997-03-07 Aerospatiale Systeme de telecommande d'un engin volant filoguide
EP0762074A1 (de) * 1995-09-05 1997-03-12 AEROSPATIALE Société Nationale Industrielle Fernbedienungssystem für eine mit einem Draht gesteuerte Rakete
CN114184097A (zh) * 2021-12-01 2022-03-15 上海航天设备制造总厂有限公司 一种用于大直径箭体铁路运输防护衣和防护方法

Also Published As

Publication number Publication date
EP0337880B1 (de) 1993-06-23
DE68907257D1 (de) 1993-07-29
DE68907257T2 (de) 1993-12-16
ATE91015T1 (de) 1993-07-15
ES2042022T3 (es) 1993-12-01
FR2630202A1 (fr) 1989-10-20
FR2630202B1 (fr) 1990-08-17

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