US3842711A - Arming device for rocket type projectile launching tube - Google Patents

Arming device for rocket type projectile launching tube Download PDF

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Publication number
US3842711A
US3842711A US00289365A US28936572A US3842711A US 3842711 A US3842711 A US 3842711A US 00289365 A US00289365 A US 00289365A US 28936572 A US28936572 A US 28936572A US 3842711 A US3842711 A US 3842711A
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US
United States
Prior art keywords
rocket
catch
launch tube
lobe
tube
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
US00289365A
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English (en)
Inventor
G Bodinaux
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
Application granted granted Critical
Publication of US3842711A publication Critical patent/US3842711A/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
    • F41F3/052—Means for securing the rocket in the launching apparatus
    • 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

Definitions

  • the purpose of the present invention is to furnish, as
  • an arming device of a new conception providing for a practically total safety as well as, for the first time, for the interchangeability or the possibility of reusing said device.
  • the object of the invention is a particularly designed arming device, which is compact, highly resistant, failsafe and interchangeable, respectively reusable.
  • Such an arming device for rocket type projectile launching tubes includes the combination of a firing device, a withholding/releasing device and a common support for said devices such that said arming device forms an interchangeable, respectively reusable unit.
  • this arming device is designed to constitute a unit, directly connectable to the rear end of a tube without addition of any complementary elements, said compact unit being in itself complete and in full working condition.
  • the withholding/releasing device of this invention comprises a multi-lobed pivoted catch element engageable with a rocket to be launched to secure the same in the launcher against forward motion, and a catch retaining means normally being resiliently biased towards the catch to prevent its rotation towards a rocket releasing position.
  • the catch retaining means furthermore is operatively connected to a rocket thrust gas pressure responsive actuator that retracts the retainer away from the catch when the rocket is ignited to release the catch for rotation towards the rocket release position.
  • the actuation of the catch retainer may be accomplished by rotary, translatory or combined mo-- tions.
  • the catch itself is formed so that a first lobe engages the rocket to be held in the launcher, a second lobe engages the retainer for locking the catch in its rocket securing position, and a third lobe engages the rocket as it is loaded in the launch tube in a camming relationship whereby the loading motion cocks the catch means about its pivot from its at rest position to its rocket securing position.
  • the catch furthermore includes an abutment engageable with a safety biasing means for constantly urging the catch means towards its rest position, or rocket release position, thereby placing the catch means in the ready position for loading another rocket after a firing sequence.
  • the safety biasing means also holds the catch in firm engagement with the retainer means while it is in its rocket securing position.
  • the firing device substantially comprises a contactor, one fixed contact of which being directly fixed on said common support, whilst its mobile contact is indirectly carried by said support, via its guiding means.
  • FICY 1 in an axial section of a launching tube equipped with an arming device according to the invention, a projectile being inserted within the tube,
  • FIG. 2 is an enlarged scale view of the part of the. arming device indicated at A on FIG. 1, this device being at rest;
  • FIG. 3 is a view similar to that of FIG. 2, the device being shown in active position;
  • FIG. 4 shows the device according to FIG. 3, upon departure of the projectile
  • FIG. 5 is a view according to arrow F5 of FIG. 2;
  • FIGS. 6, 7, 9 II are sections according to lines VI- VI, VIIVII and IX-IX to XIXI respectively of FIG. 2;
  • FIG. 8 is a section according to line VIII-VIII of FIG. 7
  • the arming device is intended to equip a launching tube 1 for a projectile 2, in this instance a 2inch rocket having nozzles 3 and foldable fins 4.
  • This projectile shows, in the vicinity of said nozzles 3, a peripheral groove 5 allowing to withhold the projectile within the tube up to the moment of firing, as described more in detail hereinafter.
  • the arming device according to the invention is mounted on a single support 6, partially engaged through an aperture feature in the wall of the tube 1 such as double slots provided to this effect in tube 1, and is connected to the latter by any adequate means, such as a screw 7.
  • a pivoting contact finger 8 is provided, said finger being urged by a spring 9 and being fed, when firing, by a conductor 10.
  • the rocket withholding-release device comprises a catch element 11, a rigid catch retaining finger element 20, and a rocket thrust gas pressure responsive release actuator 25.
  • the catch element 1 1 is shown in its at rest position in FIG. 2 and in its rocket securing position in FIG. 3.
  • Catch element 11 is seen to be supported for pivotal motion about a central axis on support member 6 and radially extends into the rocket launcher tube 1 from a pivot position outside the tube.
  • the catch retaining finger element 20 and the gas pressure response release actuator 25 are supported on the unitary support means 6, with the actuator 25 extending radially into the launch tube through the aperture feature therein.
  • the catch element 11 includes three lobes 12, 13 and 14, an abutment 16 and an override sloping surface 15 between the abutment l6 and lobe 14.
  • a safety finger element 17 resiliently biases catch element 11 by means of spring 19 in support 18 towards its at rest position, which, in FIG. 2, is in a clockwise direction.
  • the catch retaining finger 20 abuts slope 15.
  • This finger 20 is carried by one extremity of a rod 21 extending through a bore 22 of said support 6, this rod being urged towards catch 11 by a spring 23 extending between said finger 20 and a wall 24 traversed by said rod 21.
  • said rod 21 carries a rocket thrust gas pressure responsive pusher 25 projecting downwardly within tube 1 and having one surface 26 facing the front end of the tube.
  • This pusher 25 may move parallel to the axis of the tube 1, between two extreme positions delimited by the opposite walls 27 and 28 of a recess 29 in support 6.
  • the above described device functions as follows: the device being at rest or in the rocket release position (FIG. 2), a projectile 2 is inserted in the tube, from the front end of the latter.
  • the rear edge of the motor tube of projectile 1 pushes back lobe 13 of the catch 11 by a camming action.
  • the latter flips around its pivot towards its rocket securing direction, the slope l pushing back finger against its return spring 23 to cause retaining finger 20 to override lobe 14, whilst the abutment 16 pushes back the safety finger 17, against its return spring 19.
  • Lobe 12 penetrates into the peripheral groove 5 to secure the rocket against forward motion whilst the ignition or firing relay 30, provided at the extremity of fins 4, abuts against finger 8 (FIG. 1).
  • the arming device according to the invention may easily be recuperatcd and placed on a new tube. This operation is rendered particularly convenient due to the provision of the single support 6.
  • an arming device for a rocket launcher including a launch tube having an aperture feature in the tube wall, a rocket withholding-release means, and a rocket firing means spaced axially rearwardly on the launch tube with respect to said rocket withholding-release means; the improvement comprising a. a unitary support means for the rocket withholding-release means and the rocket firing means, said support means being removably secured to said launch tube in the area of the said aperture feature in the launch tube, said rocket withholding-release means and said firing means extending radially into the launch tube through the said aperture feature;
  • said rocket withholding-release means comprising a multi-lobed catch element pivotally mounted on said unitary support means for rotation about a central axis outside the rocket launch tube and radially extending into said tube for positively'engaging a rocket to be launched when said catch means is rotated in a first rocket securing direction, said catch means having a first lobe for positively engaging a rocket to be launched in said tube, and a second lobe;
  • a rocket thrust gas pressure responsive actuator element supported by said unitary support member and extending radially into said launch tube, said actuator element being subject to rocket thrust gas pressure and operably connected to said finger element for causing retraction thereof away from engagement with said catch means for thereby releasing said catch means for rotation in a rocket releasing direction upon firing of the rocket by said firing means.
  • An arming device for a rocket launcher comprismg:
  • a launch tube having a pair of apertures in its wall
  • a unitary support means releasably secured to said launch tube for supporting said firing and withholding-release means axially spaced from each other on said launch tube, said support means extending across said apertures to close said apertures, and said firing and withholding-release means extending radially through said apertures into said launch tube for engaging a rocket to be launched within said tube;
  • said rocket firing means comprising an electrical contact finger engageable with a firing relay of a rocket to be launched in said tube;
  • said withholding-release means comprising:
  • a pivoted catch element having an at-rest and a rocket securing position, and having circumferentially spaced thereabout first, second and third lobes, an abutment between the first and second lobes, and a sloping override surface between said abutment and said second lobe;
  • a catch retaining means comprising a rigid finger element resiliently biased towards said catch element and normally engaging the said sloping override surface of said catch element when said catch element is in its at-rest position and positively engage'able with said second lobe of said catch element when said catch element is rotated to its rocket securing position to prevent rotation of said catch element towards its at-rest position, the finger element sliding over said sloping override surface of said catch element when said catch element is rotated from its at-rest position to its rocket securing position;
  • a release actuator comprising means responsive to rocket thrust gas pressure connected to said finger element for retracting said finger element away from engagement with said second lobe of said catch means whenthe rocket to be launched is fired;

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
US00289365A 1971-09-16 1972-09-15 Arming device for rocket type projectile launching tube Expired - Lifetime US3842711A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE772649A BE772649A (fr) 1971-09-16 1971-09-16 Mecanisme d'armement pour tube de lancement de projectile du type roquette.

Publications (1)

Publication Number Publication Date
US3842711A true US3842711A (en) 1974-10-22

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ID=3858635

Family Applications (1)

Application Number Title Priority Date Filing Date
US00289365A Expired - Lifetime US3842711A (en) 1971-09-16 1972-09-15 Arming device for rocket type projectile launching tube

Country Status (3)

Country Link
US (1) US3842711A (fa)
BE (1) BE772649A (fa)
FR (1) FR2155288A5 (fa)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3958490A (en) * 1974-12-19 1976-05-25 The United States Of America As Represented By The Secretary Of The Navy Self-cocking rocket launcher detent
US3983785A (en) * 1974-06-17 1976-10-05 General Dynamics Corporation Missile launcher arming device
US4132150A (en) * 1977-08-08 1979-01-02 The Unites States Of America As Represented By The Secretary Of The Army Blast actuated detent
US4584925A (en) * 1983-09-26 1986-04-29 Culotta Kenneth W Underwater rocket launcher and rocket propelled missile
US5056407A (en) * 1989-11-09 1991-10-15 Dynamit Nobel Ag Rocket retainer in a launching device
WO2006119027A1 (en) * 2005-05-03 2006-11-09 Lockheed Martin Corporation Apparatus comprising a passively-actuated snubber
US8887613B1 (en) * 2013-09-30 2014-11-18 The United States Of America As Represented By The Secretary Of The Army Pin retainer on a missile launch rail
US20250051009A1 (en) * 2023-08-07 2025-02-13 Agency For Defense Development Dual detent apparatus for rocket

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4550640A (en) * 1983-09-16 1985-11-05 Werkzeugmaschinenfabrik Oerlikon-Buehrle Ag Missile canister restraint device

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3983785A (en) * 1974-06-17 1976-10-05 General Dynamics Corporation Missile launcher arming device
US3958490A (en) * 1974-12-19 1976-05-25 The United States Of America As Represented By The Secretary Of The Navy Self-cocking rocket launcher detent
US4132150A (en) * 1977-08-08 1979-01-02 The Unites States Of America As Represented By The Secretary Of The Army Blast actuated detent
US4584925A (en) * 1983-09-26 1986-04-29 Culotta Kenneth W Underwater rocket launcher and rocket propelled missile
US5056407A (en) * 1989-11-09 1991-10-15 Dynamit Nobel Ag Rocket retainer in a launching device
WO2006119027A1 (en) * 2005-05-03 2006-11-09 Lockheed Martin Corporation Apparatus comprising a passively-actuated snubber
US20090255398A1 (en) * 2005-05-03 2009-10-15 Lockheed Martin Corporation Apparatus comprising a passively-actuated snubber
US7624669B2 (en) 2005-05-03 2009-12-01 Lockheed Martin Corporation Apparatus comprising a passively-actuated snubber
US8887613B1 (en) * 2013-09-30 2014-11-18 The United States Of America As Represented By The Secretary Of The Army Pin retainer on a missile launch rail
US20250051009A1 (en) * 2023-08-07 2025-02-13 Agency For Defense Development Dual detent apparatus for rocket
US12467716B2 (en) * 2023-08-07 2025-11-11 Agency For Defense Development Dual detent apparatus for rocket

Also Published As

Publication number Publication date
BE772649A (fr) 1972-03-16
FR2155288A5 (fa) 1973-05-18

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