US3780617A - Device for breaking a launching rack-to-missile umbilical cord - Google Patents

Device for breaking a launching rack-to-missile umbilical cord Download PDF

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Publication number
US3780617A
US3780617A US3780617DA US3780617A US 3780617 A US3780617 A US 3780617A US 3780617D A US3780617D A US 3780617DA US 3780617 A US3780617 A US 3780617A
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US
United States
Prior art keywords
disk
missile
cable
hole
launching
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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
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English (en)
Inventor
F Tabarie
A Bernard
Aubin G Saint
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Direction General de lArmement DGA
Original Assignee
Delegation Ministerielle pour lArmement
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Publication of US3780617A publication Critical patent/US3780617A/en
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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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T83/00—Cutting
    • Y10T83/404—By means to misalign aligned apertured tools
    • Y10T83/416—Rotary relative movement solely about a single pivot

Definitions

  • LAUNCH/N6 R'ACK ABSTRACT In a missile launching apparatus in which a missile is coupled to a launching rack by an umbilical cord which passes through an opening in the skin or fairing of the missile, there is provided a device for severing the umbilical cord.
  • This device includes a rotatable disk provided wth a hole which is offset relative to the axis of rotation of the disk and through which hole the cord passes.
  • a cable is provided connecting the disk with the launching rack so that upon launching, the disk is rotated through a fraction of a turn.
  • the disk is provided with a knife edge bordering part of the aforementioned hole for purposes of severing the umbilical cord.
  • the hole in the disk is provided in a half of the disk and the other half of the disk is at least substantially imperforate. This latter half of the disk operates to obturate the opening in the skin of the missile after the umbilical cord has been severed.
  • a safety pin is provided to lock the disk against rotation prior to launching of the missile and this pin is of a strength to be sheared when the disk is rotated by the aforesaid cable.
  • a switch which includes an actuator bearing against the disk and adapted to enter the aforesaid hole upon rotation of the disk in order to actuate the switch.
  • This invention relates to breaking devices for cutting launching rack-to-missile umbilical cords after the launching of missiles.
  • missiles such as torpedoes or rockets are connected with associated launching racks by means of multiwire cables through which data is transmitted to the missile up to the last moment prior to launching. This connection is broken only after the take-off of the missle.
  • Breakwire devices operated by pulling force are commonly used.
  • the cable includes a length of smaller cross-section which breaks under the pulling force which results upon launching.
  • the pulling force method leads to heavy stresses when a large number of wires are involved. Moreover, it is difficult to evaluate this pulling force precisely as a result of which the missile can be caused to deviate from the calculated trajectory.
  • Breaking devices using jettisonable connectors are also well known. However, this technique can lead to functional failures due to poor contacts, and hence there is a lack of reliability. Furthermore, the design of a jettisonable connector raises problems when disconnection is to take place in a high pressure area.
  • a device which disposes of the aforesaid disadvantages while allowing not only the breaking of the umbilical cord but also the blanking off of the cord passage through the missile fairing.
  • the invention moreover eliminates any problem due to electrical circuit continuity as no connectors are used which must be plugged into sockets.
  • the invention also avoids the need for weakened wire sections to enable breaking in response to a pulling force.
  • the reliability of missiles equipped in accordance with this invention is greatly improved.
  • an object of the invention is to provide a device allowing a cable to be separated flush with the skin of the associated missle.
  • connecting cord containing electrical wires which is the most commonly used from.
  • This case is not exhaustive because the device of this invention can also be used for breaking or blanking off any flexible connection between a missile and its launching rack (flexible conduit, for instance).
  • Such a cable or flexible conduit will be referred herein to as the umbilical cord.
  • a device for cutting, at the take-off of a missile, the launching rack-tomissile umbilical cord consists, for example, of a rotary disk provided with a hole offset in relation to the rotation axis, The umbilical cord conduit is routed through this hole.
  • One end of a tensioning cable is wound about fore, when the disk has rotated by half a turn, during which it cuts the umbilical cord, the disk covers the cut end of the umbilical cord and blanks off the passage hole.
  • the fairing surface continuity is almost restored after the passage has been blanked off.
  • the disk is blocked by a safety pin which is sheared by the disk rotation.
  • FIG. I is a lengthwise cross-sectional view of a device provided in accordance with the invention, prior to missile take-off;
  • FIG. 2 is a cross-sectional view taken along line lI-Il of FIG. I;
  • FIG. 3 is a cross-sectional view taken along line III- III of FIG. I.
  • FIG. 4 corresponds to FIG. I, but shows the structure after missile take-off.
  • element I is a multiwire umbilical cord connecting a missile 2 to a launching rack LR.
  • Missile 2 may be, for example, a torpedo, a surface-tosurface or surface-to-ground missile to be launched from a submarine or some other type of missile.
  • Part 4 is a detachable section of the missile fairing or skin which serves as a cover for the device.
  • Element 5 is a mount for the device and it is traversed by cable ll through a packing gland 6 sealed by a packing 7.
  • the device includes a disk 8 which is allowed to rotate about a rounded bearing surface 8a of mount 5.
  • Disk 8 includes a portion provided with a hole 9 through which cable I is routed.
  • the disk is generally parallel to the missile skin and preferably rotates about an axis perpendicular to the longitudinal axis of the missile.
  • the edge of hole 9 is bevelled to form a knife edge 10 along a given length of the rim.
  • a tensioning cable 11 has one end lllla would around the rim of disk 8 while the other cable end llllb is attached to the launching rack LR.
  • Cable 11 includes two strands forming a loop 13 (FIG. 4) which engages with a stud 12 (FIG. 2) protruding from the rim of disk 8.
  • the cable is wound on about one-half of the disk rim.
  • Hole 9 is located in the other half of disk 8. At the time of missile take-off, disk 8 rotates through half of a turn under the control of cable 11 and edge It) cuts cable ll.
  • the disk half or portion with no hole is situated on the left-hand side of FIG. 2.
  • the disk then covers the cut end of cable I and blanks off the cable passage opening in cover 4.
  • the device is provided with a bushing loaded by spring 16. This bushing is released upon rotation of disk 8 and applies packing 17 against the lower surface of disk 8. Thereby, the cut end of the cable is insulated from the exterior by means of the disk 8 which forms a cover.
  • the bushing 15, spring 16 and packing l7 assure the tightness of the cover.
  • FIG. 4 shows the end lb of the cable insulated from the exterior.
  • the device also includes an automatic contactor 18 which automatically closes contact 19 after missile take-off.
  • Push rod is pushed against the lower surface of disk 8 by spring 21. Once the disk has rotated, push rod 20 enters into hole 9 of disk 8 and closes contact 19.
  • the latter can automatically control any operation the starting of which must precisely coincide with missile take-off (starting of a time relay for instance).
  • FIG. 4 illustrates the section la of cable 1 remaining attached to the launching rack and cable end 1b which, after the cutting action, is covered by disk 8.
  • Bushing 15 is pushed back by spring 16 and applies packing 17 against the lower surface of disk 8.
  • FIG. 4 also shows the automatic contactor 18 in the position it occupies when push rod 20 is engaged in hole 9 and contact w is closed.
  • a device comprising a rotatable disk having an axis of rotation and provided with a hole offset relative to said axis and through which said cord passes, at least part of said hole being bordered by a knife edge, and a cable distinct from said cord and peripherally engaging a portion of said disk approximately equal to half a circle, said hole being situated out of said portion, the peripheral engagement of the cable with the disk enabling said cable to rotate said disk by half a turn responsive to movement of the missile relative to said rack, said cable being coupled between said disk and said rack.
  • a device as claimed in claim 1 comprising a switch including an actuator bearing against said disk for entering said hole upon rotation of said disk to actuate the switch.
  • a device as claimed in claim 1 comprising a displaceable bushing actuated by rotation of said disk, a spring loading said bushing, and a packing applied by the bushing around said cord when the latter is severed.
  • a device as claimed in claim 1 comprising a lug on said disk detachably engaged by said cable.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Storing, Repeated Paying-Out, And Re-Storing Of Elongated Articles (AREA)
  • Electric Cable Installation (AREA)
  • Re-Forming, After-Treatment, Cutting And Transporting Of Glass Products (AREA)
US3780617D 1971-04-02 1972-03-30 Device for breaking a launching rack-to-missile umbilical cord Expired - Lifetime US3780617A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7111641A FR2132937A5 (enExample) 1971-04-02 1971-04-02

Publications (1)

Publication Number Publication Date
US3780617A true US3780617A (en) 1973-12-25

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ID=9074626

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Application Number Title Priority Date Filing Date
US3780617D Expired - Lifetime US3780617A (en) 1971-04-02 1972-03-30 Device for breaking a launching rack-to-missile umbilical cord

Country Status (7)

Country Link
US (1) US3780617A (enExample)
AU (1) AU3886072A (enExample)
DE (1) DE2214674A1 (enExample)
FR (1) FR2132937A5 (enExample)
GB (1) GB1359573A (enExample)
IT (1) IT947166B (enExample)
SE (1) SE393184B (enExample)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5551368A (en) * 1994-01-10 1996-09-03 L'etat Francais, Represente Par Le Delegue Ministeriel Pour L'armement Container for launching a lightweight torpedo from a surface craft
US5652404A (en) * 1994-04-27 1997-07-29 Arianespace Device for disconnecting a releasable connector
US5710388A (en) * 1995-08-16 1998-01-20 The Whitaker Corporation Umbilical cord for projectile launching device
US6679154B1 (en) 2002-11-25 2004-01-20 Lockheed Martin Corporation Passive dynamically disconnecting arm
RU2288423C1 (ru) * 2005-04-13 2006-11-27 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Управляемая ракета в транспортно-пусковом контейнере
RU2300071C1 (ru) * 2005-10-04 2007-05-27 Хаджи-Мурат Хасанович Байсиев Стопорное устройство ракетной пусковой установки
RU2302600C1 (ru) * 2005-12-27 2007-07-10 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Двухступенчатая ракета в пусковом контейнере
US20150153135A1 (en) * 2012-11-13 2015-06-04 Raytheon Company Umbilical cable disconnect
US11709035B2 (en) 2021-08-12 2023-07-25 Raytheon Company Translating harness with passive disconnect
US20240093964A1 (en) * 2022-09-13 2024-03-21 Raytheon Company Passive line separator

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2119999B1 (en) * 2008-05-13 2011-07-20 Whitehead Alenia Sistemi Subacquei S.p.A. Torpedo umbilical cord cutting device
RU209915U1 (ru) * 2021-10-19 2022-03-23 Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" Люк отрывного электроразъема

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2870676A (en) * 1952-06-06 1959-01-27 Radkowski Leo Shearing device for cables
US3167047A (en) * 1961-12-26 1965-01-26 Henry D Eug Control cable cutter

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2870676A (en) * 1952-06-06 1959-01-27 Radkowski Leo Shearing device for cables
US3167047A (en) * 1961-12-26 1965-01-26 Henry D Eug Control cable cutter

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5551368A (en) * 1994-01-10 1996-09-03 L'etat Francais, Represente Par Le Delegue Ministeriel Pour L'armement Container for launching a lightweight torpedo from a surface craft
US5652404A (en) * 1994-04-27 1997-07-29 Arianespace Device for disconnecting a releasable connector
US5710388A (en) * 1995-08-16 1998-01-20 The Whitaker Corporation Umbilical cord for projectile launching device
US6679154B1 (en) 2002-11-25 2004-01-20 Lockheed Martin Corporation Passive dynamically disconnecting arm
RU2288423C1 (ru) * 2005-04-13 2006-11-27 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Управляемая ракета в транспортно-пусковом контейнере
RU2300071C1 (ru) * 2005-10-04 2007-05-27 Хаджи-Мурат Хасанович Байсиев Стопорное устройство ракетной пусковой установки
RU2302600C1 (ru) * 2005-12-27 2007-07-10 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Двухступенчатая ракета в пусковом контейнере
US20150153135A1 (en) * 2012-11-13 2015-06-04 Raytheon Company Umbilical cable disconnect
US9074842B2 (en) * 2012-11-13 2015-07-07 Raytheon Company Umbilical cable disconnect
US11709035B2 (en) 2021-08-12 2023-07-25 Raytheon Company Translating harness with passive disconnect
US20240093964A1 (en) * 2022-09-13 2024-03-21 Raytheon Company Passive line separator
US12241718B2 (en) * 2022-09-13 2025-03-04 Raytheon Company Passive line separator

Also Published As

Publication number Publication date
SE393184B (sv) 1977-05-02
AU3886072A (en) 1973-08-16
GB1359573A (en) 1974-07-10
FR2132937A5 (enExample) 1972-11-24
DE2214674A1 (de) 1972-11-30
IT947166B (it) 1973-05-21

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