EP1532418B1 - VERSCHMUTZUNGSUNEMPFINDLICHE Munition - Google Patents

VERSCHMUTZUNGSUNEMPFINDLICHE Munition Download PDF

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Publication number
EP1532418B1
EP1532418B1 EP03753577.0A EP03753577A EP1532418B1 EP 1532418 B1 EP1532418 B1 EP 1532418B1 EP 03753577 A EP03753577 A EP 03753577A EP 1532418 B1 EP1532418 B1 EP 1532418B1
Authority
EP
European Patent Office
Prior art keywords
connector
launcher
rocket
cable
munition
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.)
Expired - Lifetime
Application number
EP03753577.0A
Other languages
English (en)
French (fr)
Other versions
EP1532418A1 (de
Inventor
Gérome Thales Intel. Property REMY
Daniel Thales Intel. Property GILIS
Bruno Thales Intellectual Property GAMBY
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.)
Les Forges de Zeebrugge SA
Original Assignee
Les Forges de Zeebrugge SA
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 Les Forges de Zeebrugge SA filed Critical Les Forges de Zeebrugge SA
Publication of EP1532418A1 publication Critical patent/EP1532418A1/de
Application granted granted Critical
Publication of EP1532418B1 publication Critical patent/EP1532418B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/055—Umbilical connecting means

Definitions

  • the present invention relates to connection techniques between a military ammunition launcher and ammunition. It applies in particular to rocket launches carried under helicopter or under plane.
  • a firing order is usually transmitted in electrical form. It may be necessary to transmit other data from the carrier to the ammunition.
  • the time is passed after which the ammunition (then called cargo) must be opened after firing to disperse submunitions (such as hollow charges or dars).
  • submunitions such as hollow charges or dars.
  • data is transmitted for guidance such as a photo or digital terrain model. This sends data of any order to be used during the flight of the ammunition.
  • This data is conveyed from the carrier to the ammunition (s) via a data transmission link.
  • This connection comprises a cable connecting the carrier and the launcher. The link extends into the launcher to the tube in which the ammunition is housed.
  • a connection between the ammunition and the launcher makes it possible to extend the data link to the ammunition.
  • the cable which is an integral part of the ammunition, makes it possible to transmit the data of removal or guidance to the head.
  • a document US-A-2,793,492 describes a munition intended to be placed in a housing of an ammunition launcher.
  • US Patent 4047464 describes a munition according to the preamble of claim 1.
  • An object of the invention is to avoid this fouling.
  • the subject of the invention is a munition intended to be placed in a housing of a military ammunition launcher, as described by the claims.
  • the cable includes a cable break point at the output of the ammunition connector.
  • the breaking point of the cable is achieved by a local weakening of the cable.
  • the elements of the locking system of the ammunition are formed by a cap.
  • the cap is formed by an independent part comprising a groove for inserting the cap on the cable.
  • the cap is formed by a molded part on the cable.
  • the invention can be applied to all types of launchers, including rocket lances 2. These rocket launcher 2 can be carried by a helicopter 1.
  • the launcher 2 is shown in side and front view on the Figures 2 and 3 .
  • the launcher includes housing for ammunition. In this example, the houses form tubes in which are placed the rockets 3. These housings can be seven in number (see figure 3 ), twelve, nineteen (see figure 5 ) for example.
  • the connection between the ammunition and the launcher 5 can be placed on the front of the launcher, that is to say the face from which the rockets depart.
  • a launcher connector may be associated with each slot or some of them only. Each launcher connector is intended to be connected to a rocket connector forming the termination of a cable 4.
  • the rocket connector and the cable 4 form an integral part of the rocket.
  • FIG 4 a detail view of the front face of the launcher, on which is shown an example of housing distribution.
  • the dwellings have a circle-shaped section. These circles have the same diameter D1. This diameter D1 is substantially equal to the caliber of the ammunition.
  • the centers of the circles can be equidistant on a triangular mesh.
  • the centers of three adjacent dwellings 6, 7, 8 form the vertices of an equilateral triangle 9 whose length of one side 10 is equal to the inter-center distance D2.
  • launching connectors may be arranged between the housing.
  • a launcher connector 11 can be placed between the housing 6, 7 and 8. There is a reduced space between three neighboring housing in which the connection between a munition and the launcher can be placed.
  • the cable 4 can be connected to the ogival head 33 of the rocket 3.
  • a hermiticity ring 33 can be placed at the connection.
  • the cable may have a length of the order of 1.5 m.
  • the cable may be a shielded coaxial cable. It comprises for example a conductive core (not shown) intended to be connected to the positive pole, surrounded by an insulating envelope (not shown).
  • the insulating envelope is itself surrounded by a conductive braid (not shown) intended to be connected to the negative pole.
  • the whole is surrounded by a protective sheath (not shown).
  • a connector terminates the free part of this cable.
  • the connector may comprise an outer body 34 and a plug 35.
  • the outer body 34 is an outer casing intended to protect the negative circuit and to enable the connector to be grasped. It can be formed of silicone, such as GEON 83794 GRAY.
  • the plug 35 can be a coaxial female plug for example.
  • This plug includes for example a conductive core 36, of hollow tubular shape, intended to be connected to the positive pole.
  • This tubular core 36 may be surrounded by an insulating elastic material 37, itself surrounded by a conductive material 38 forming the outside of the plug 35.
  • the conductive material 38 is intended to be connected to the negative pole.
  • the elements 36, 37, 38 of the plug 35 are coaxial. Longitudinal slots 39, of which there are three, for example, make it possible to reduce the section of the plug by elastic deformation.
  • This connector 5 comprises in particular a launcher connector 40 and a rocket connector 41.
  • the rocket connector 41 can be mechanically fixed to the launcher connector 40 by simple insertion, notably thanks to the elasticity of the plug 35 of the rocket connector 41.
  • the starter connector 40 comprises for example a body 47 of substantially cylindrical shape, a conductive rod 44 placed on the axis of this body 47.
  • the rod 44 is intended to be connected to the positive pole.
  • This rod 44 is housed inside 36 of the card 35 (see Figures 6 to 8 ) during the insertion of the rocket connector 41 in the launcher connector 40.
  • the rod 44 makes it possible to establish electrical contact with the positive pole of the rocket.
  • the body 47 further comprises a conductive member (not shown) on its inner surface. This conductive element can be formed by the body itself.
  • the conductive element is intended to be connected to the negative pole. The conductive element makes it possible to establish an electrical contact with the outside 38 of the plug 35 (see Figures 6 to 8 ) when the rocket connector 41 is inserted into the launcher connector 40.
  • a plug 45 may be provided to protect the rod 44 when the rocket connector 41 is not in the launcher connector 40.
  • This cap cylindrical in shape, comprises a central through hole that allows it to slide on the rod 44.
  • a spring 46 can be placed behind this plug, in the body 47 of the starter connector 40. This spring 46 is intended to be compressed by the rocket connector 41 when it is inserted on the launcher connector 40. The spring 46 exerts a force on the plug 45 to repel and thus protect the rod when there is no rocket connector 41 in the launcher connector 40. However, in the presence of a rocket connector 41, the spring 46 tends to push slightly the rocket connector 41 out of the launcher connector 40, and thus no longer ensure good electrical continuity.
  • the connector comprises a locking system 42, 48, such as a pin or bayonet system.
  • the locking system 42, 48 makes it possible to keep the launcher and rocket connectors connected after the departure of the launcher rocket.
  • the rocket connector 41 can not leave the launcher connector 40 when the rocket leaves its housing.
  • the cable 4 of the rocket tended then broke, the rocket connector 41 remaining in place.
  • the invention has many advantages. Before the firing of a rocket, the locking system 42, 48 makes it possible to hold the rocket connector 41 in place when the neighboring rockets are fired. In addition, in a difficult vibratory environment, the rocket connector 41 can no longer accidentally exit the launcher connector 40. This allows a perfect transmission of the electrical signal. Finally, the rocket leaves the launcher without its connector 41, providing less aerodynamic drag.
  • a first part of the cable is carried away by the rocket, a second part remains attached to the launcher.
  • This second part of cable may be torn off by the departure of neighboring rockets, and may damage the wearer.
  • a cable break point may be provided at the output 49 of the rocket connector. This breaking point can be achieved by a local weakening of the cable, by removing a portion of the conductive braid for example.
  • the locking system 42, 48 is a bayonet system.
  • This system comprises for example a cap 42 and lugs 48.
  • the cap 42 is in contact with the rocket connector 41.
  • the lugs 48 are part of the launcher connector 40.
  • the cap 42 comprises locking grooves in which are screwed the lugs 38. Once screwed, the cap 42 keeps the rocket connector 41 connected with the starter connector 40.
  • the lugs 48 of the starter connector 40 hold the cap 42 axially, which itself holds the rocket connector 41 on the launcher connector 40.
  • the bayonet system has many advantages. It is easy to maneuver and occupies a small footprint. This makes it possible to place locking systems in the space available between three neighboring casings of the launcher.
  • the cap 42 covers the rocket connectors 41 and launcher 40.
  • the size is determined by the diameter of the cap 42.
  • the cap may have a diameter D3 of 13 mm.
  • the locking system may comprise one or more pins 48 placed on the launcher connector 40.
  • the lugs are two in number and are diametrically opposed.
  • the lugs 38 are placed on the outer surface of the launcher connector 40.
  • the lugs being positioned on the outer surface of the connector, it is not necessary to adapt the shape of the rocket connector to the lugs 48.
  • the shape of the rocket connector 41 is defined only with respect to the internal surface of the launcher connector 40.
  • the invention makes it possible to have launch connectors compatible with all types of rocket connectors. This makes it possible to be compatible with predefined standards.
  • the cap 42 has an inner surface of substantially cylindrical shape.
  • Locking grooves 50 are placed inside the inner surface.
  • Each groove describes a circular arc of angle A in a plane perpendicular to the axis of the cylinder forming the inner surface.
  • the angle A can be 30 ° for example.
  • the locking grooves 50 are intended to accommodate the lugs 48 of the launcher connector to prevent the removal of the cap 42 axially.
  • Each locking groove 50 opens at one end to an inlet groove 51.
  • each inlet groove 51 is opposite a lug 48.
  • each lug can reach a locking groove 50 by translating inside the associated inlet groove 51.
  • Each locking groove 50 terminates at the other end with a hole 52.
  • This hole may be a through hole as shown in the drawings. Figures 9 and 11 .
  • bayonet system with more or less grooves and lugs. It is possible to reverse the position of the lugs and grooves, that is to say to practice lugs in the cap, and grooves on the launcher connector.
  • the lugs may be part of the rocket connector and the cap may be in contact with the launcher connector.
  • the cap 42 forms an independent piece.
  • This independent part comprises a groove 53 for inserting the cap 42 on the cable 4.
  • the cap 54 is molded on the cable 4.
  • the invention applies to any type of ammunition intended to leave a launcher.
  • the cable is attached to the front of the ammunition on the ogival head. It is possible to apply the invention to other locations of the munition.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Details Of Connecting Devices For Male And Female Coupling (AREA)
  • Connector Housings Or Holding Contact Members (AREA)

Claims (6)

  1. Munition (4) zum Platzieren in einem Sitz einer Abschussvorrichtung (2) für militärische Munition, wobei die Abschussvorrichtung (2) für militärische Munition einen Abschussvorrichtungsverbinder umfasst, wobei die Munition Folgendes umfasst:
    - ein Kabel (4);
    - einen Munitionsverbinder (41), der einen Abschluss für das Kabel bildet, wobei der Munitionsverbinder zum Anschließen an den Abschussvorrichtungsverbinder ausgelegt ist, wobei die Munition dadurch gekennzeichnet ist, dass sie ferner Folgendes umfasst:
    - Elemente (42) eines Arretiersystems (42, 48), wobei das Arretiersystem so ausgestattet ist, dass es den Abschussvorrichtungs- und den Munitionsverbinder verbunden hält, nachdem die Munition die Abschussvorrichtung verlassen hat, wobei das Kabel einen Kabelabreißpunkt (49) hat, dadurch gekennzeichnet, dass der Abreißpunkt am Ausgang des Munitionsverbinders vorgesehen ist.
  2. Munition nach dem vorherigen Anspruch, dadurch gekennzeichnet, dass der Kabelabreißpunkt durch eine örtliche Schwächung des Kabels realisiert wird.
  3. Munition nach einem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass das Arretiersystem ein Bayonettsystem ist.
  4. Munition nach Anspruch 3, dadurch gekennzeichnet, dass die Elemente des Arretiersystems durch eine Kappe (42) gebildet werden.
  5. Munition nach Anspruch 4, dadurch gekennzeichnet, dass die Kappe durch einen unabhängigen Teil gebildet wird, der eine Nut zum Einführen der Kappe auf das Kabel umfasst.
  6. Munition nach Anspruch 4, dadurch gekennzeichnet, dass die Kappe von einem auf das Kabel aufgeformten Teil gebildet wird.
EP03753577.0A 2002-08-21 2003-07-08 VERSCHMUTZUNGSUNEMPFINDLICHE Munition Expired - Lifetime EP1532418B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
BE2002/0494A BE1015204A3 (fr) 2002-08-21 2002-08-21 Connectique entre un lanceur militaire et des munitions resistant a l'encrassage.
BE200200494 2002-08-21
PCT/EP2003/050295 WO2004018956A1 (fr) 2002-08-21 2003-07-08 Connectique entre un lanceur militaire et des munitions resistant a l'encrassage

Publications (2)

Publication Number Publication Date
EP1532418A1 EP1532418A1 (de) 2005-05-25
EP1532418B1 true EP1532418B1 (de) 2013-11-20

Family

ID=31892619

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03753577.0A Expired - Lifetime EP1532418B1 (de) 2002-08-21 2003-07-08 VERSCHMUTZUNGSUNEMPFINDLICHE Munition

Country Status (7)

Country Link
EP (1) EP1532418B1 (de)
KR (1) KR20050062770A (de)
AU (1) AU2003271746A1 (de)
BE (1) BE1015204A3 (de)
BR (1) BR0313642A (de)
WO (1) WO2004018956A1 (de)
ZA (1) ZA200501754B (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010020088B4 (de) 2010-05-10 2013-06-27 Thyssenkrupp Presta Aktiengesellschaft Verfahren und Vorrichtung zur Regelung eines steuerbaren Energieabsorbers

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2793492A (en) * 1944-11-24 1957-05-28 Bruce H Sage Rocket assembly
US2984811A (en) * 1957-02-06 1961-05-16 Bendix Corp Electrical connector
DE1276413B (de) * 1965-03-24 1968-08-29 Dynamit Nobel Ag Kabeltrennstelle in Feststoff-Raketen
US3644938A (en) * 1969-11-03 1972-02-22 Hughes Aircraft Co Umbilical connector
SE397407B (sv) * 1975-02-19 1977-10-31 Bofors Ab Avrivningskontaktdon

Also Published As

Publication number Publication date
WO2004018956A1 (fr) 2004-03-04
KR20050062770A (ko) 2005-06-27
AU2003271746A1 (en) 2004-03-11
ZA200501754B (en) 2005-09-13
BE1015204A3 (fr) 2004-11-09
BR0313642A (pt) 2005-07-12
EP1532418A1 (de) 2005-05-25

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