US3721155A - Safety device for locking a missile on its launcher or in its container in either the transport or the launching position - Google Patents

Safety device for locking a missile on its launcher or in its container in either the transport or the launching position Download PDF

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Publication number
US3721155A
US3721155A US00116959A US3721155DA US3721155A US 3721155 A US3721155 A US 3721155A US 00116959 A US00116959 A US 00116959A US 3721155D A US3721155D A US 3721155DA US 3721155 A US3721155 A US 3721155A
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US
United States
Prior art keywords
missile
movable
short
circuit
locking
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Expired - Lifetime
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US00116959A
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English (en)
Inventor
E Stauff
M Maree
J Roze
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IND AEROSPATIALLE SOC NAT
SOC NAT IND AEROSPATIALLE FR
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IND AEROSPATIALLE SOC NAT
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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
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A19/00—Firing or trigger mechanisms; Cocking mechanisms
    • F41A19/58—Electric firing mechanisms
    • F41A19/69—Electric contacts or switches peculiar thereto

Definitions

  • ABSTRACT A safety device for locking a missile either in the transport position in its container, or in the firing position on its launcher, in which means maintains electric circuit for energizing the missile propellant igniters short-circuited as long as the missile is not in a condition to be fired, and actuating means with movable restraining means permitting to fetch the missile from an initial locking position to a final retracted position and latching said movable means in their final retracted position.
  • the present invention relates to a safety device for looking a missile on its launcher or in its container, irrespective of whether the missile is in the transport or launching position.
  • the locking system used to that end rnust rigorously interdict accidental igniting of the propulsion systems, and this not only until the firing command has been given but also until the restraining mechanism has completely retracted and been latched in its retracted position.
  • any locking system designed to provide the above safeguards must have the following features:
  • a safety latching device is characterized by the fact that it includes a mechanical restraining mechanism capable of occupying: either an initial locking position wherein it restrains the missile, breaks the electric circuit for energizing the missile propellant igniters, which circuit is additionally short-circuited; or, responsively to an actuating mechanism, a final retracted position wherein it is completely clear of the path of the missile, cancels the short circuit and closes the igniter energizing circuit, means being provided for latching the restraining mechanism in both its initial and final positions, the means for latching the restraining mechanism in its final retracted position being so devised as to allow the current for igniting the missile propulsion system to pass only if said restraining mechanism is effectively in its unlatched position, whereby safe operation is ensured, on the one hand by the fact that accidental firing due to an environmental magnetic field or unwanted energization of the igniters is prevented and, on the other, by the fact that the
  • FIG. 3 is a detail plan view of the end of the printed circuit providing the electrical circuitry, in the position it occupies when the mechanism is in its initial locking configuration;
  • FIG. 4 is a detail view corresponding to that of FIG. 3 but in which the end of the printed circuit is shown in the position it occupies when the mechanism is in its final retracted configuration;
  • FIGS. 5 and 6 are explanatory electrical diagrams showing the electrical connections which are made when the mechanism is in its locking and retracted positions respectively.
  • the locking device illustrated in the accompanying drawings basically includes a restraining mechanism which in the exemplary embodiment shown is formed by a cylindrical locking pin 1 made of high tensile steel and capable of sliding along its longitudinal axis xx through a housing generally designated by reference numeral 2 which is secured by any convenient means to a boss 3,, with which the missile container or launcher 3 is provided to that end.
  • the boss 3, is formed with a bore 4 through which the locking pin 1 extends in such manner that the head 1,, thereof be capable, when the pin is in its upper locking position shown in FIG. 1, of engaging into a lodging 5 provided for the purpose in missile 6.
  • the missile is accordingly restrained along two mutually perpendicular axes which are horizontal in the case of FIG.
  • Housing 2 is formed in its middle part with an annular flange 7 which bounds two separate compartments, to wit an upper compartment 2; containing electrical contacts to which more detailed reference will be made hereinafter, and a lower compartment 2 through which locking pin 1 is guided and which is accordingly formed with a cylindrical abutment 8 capable of sliding within compartment 2, after the fashion of a piston through a cylinder, as will be explained in greater detail hereinafter.
  • locking pin 1 is provided over its middle portion with a sleeve 9 made of insulating material which is an exact fit through annular flange 7, and abutment 8 is provided with a seal 8,,.
  • a fluid-tight chamber is thus formed which communicates through an orifice 11 with a gas generator which is preferably a pyrotechnic system generally designated by reference numeral 12 and to which further reference will be made hereinbelow.
  • Pin 1 is restrained in the locking position of FIG. 1 by a shear-pin 13 which is inserted both through the wall of compartment 2, and into piston 8.
  • a flexible printed-circuit 16 which provides the overall electric circuitry and which shortcircuits the missile igniters for as long as the missile remains locked by pin 1, in the manner to be described in greater detail hereinbelow.
  • Insulating sleeve 9 carries on its upper end contacts 17 which, as will be explained later, close the feed circuits when pin 1 descends into the retracted position.
  • FIG. 3 on which are shown the inputs e e and e, and the outputs s s and s the igniters are short-circuited by the end 16 A of flexible printed-circuit 16.
  • This end 16, is retained between the lower base of housing compartment 2, and a cover 18 secured by any convenient means.
  • the cover 18 is formed with a central hole 19 for receiving the lower end of locking-pin 1 when the same is in its bottom position, and with a lodging 20 made of hard insulating material and forming, as will be explained in greater detail hereinafter, a stamping die which is caused to cut off the end 16,, of the printed circuit responsively to piston 8 (likewise made of insulating material) as the locking-pin l descends.
  • the pin 1 is in the locking position and restrains the missile 6 on its launcher or container 3 by virtue of the mechanical restraint exerted by its head 1,, in lodging 5;
  • the pin 1 is itself latched in the locking position by the mechanical restraint exerted by shear-pin 13;
  • the flexible printed-circuit 16 is itself effective in short-circuiting the circuit leading to the igniters, thereby providing an additional safeguard against accidental energization, and protection against electro-magnetic effects.
  • pin 1 is restrained in the retracted position by the spring contacts 15 bearing against a shoulder 9,, formed on insulating sleeve 9 and projecting outwardly in relation to contacts 17.
  • This non-return device for pin 1 provided by the contacts themselves, can be further improved by damping any tendency of the pin to rebound when it is arrested, for example by means of a lead plate (not shown).
  • the missile would be in the released configuration and would have to be handled with care, abandoned or destroyed, but in any event could not be launched under conditions representing a hazard for the operator.
  • a safety device for locking a missile having an electrically ignited propulsion system comprising, in combination:
  • an electric circuit for energizing the missile propellant igniters including short-circuiting means for maintaining said energizing circuit short-circuited for as long as the missile is not in a condition to be fired,
  • a Safety locking device as claimed in claim 1 posluonl 1 further characterized by actuating means for moving said movable restraining said first latch means being a sheappin means from its initial position to its final position; 6 A Safet lockin device as claime'd in claim 5 first latch means to positively lock said movable y g further characterized by restraining means in its initial locking position for Said actuatin means bein rotechnic means as long as said actuating means has not operated; 2O 7 A Safety i g ig claimed in Claim 1 and f h h t db second latch means to positively lock said movable 6 mac enze y said second latch means being movable contacts 7 restraining means in its final retracted position i h 2.
  • a safety locking device as claimed in claim 1, Much form Swtc further characterized by

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US00116959A 1970-02-23 1971-02-19 Safety device for locking a missile on its launcher or in its container in either the transport or the launching position Expired - Lifetime US3721155A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7006411A FR2080080A5 (US07714131-20100511-C00038.png) 1970-02-23 1970-02-23

Publications (1)

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US3721155A true US3721155A (en) 1973-03-20

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US00116959A Expired - Lifetime US3721155A (en) 1970-02-23 1971-02-19 Safety device for locking a missile on its launcher or in its container in either the transport or the launching position

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US (1) US3721155A (US07714131-20100511-C00038.png)
DE (1) DE2104609C3 (US07714131-20100511-C00038.png)
FR (1) FR2080080A5 (US07714131-20100511-C00038.png)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4095508A (en) * 1977-04-04 1978-06-20 The United States Of America As Represented By The Secretary Of The Army Capacitive discharge firing mechanism
US4271748A (en) * 1978-07-06 1981-06-09 Her Majesty The Queen In Right Of Canada, As Represented By The Minister Of National Defence Shorting and radiation protection device for rocket
US4416183A (en) * 1981-07-28 1983-11-22 Adams Robert W Rocket retention and ignition system
US4716808A (en) * 1985-11-12 1988-01-05 Mcdonnell Douglas Corporation Mechanical launch sequencer for a missile
EP1808664A1 (en) * 2006-01-13 2007-07-18 Saab AB IM-lock for weapons having preloaded projectiles
US20220009607A1 (en) * 2018-12-20 2022-01-13 Atlas Elektronik Gmbh Device and method for launching an underwater projectile from a watercraft

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2703803A1 (de) * 1977-01-29 1978-08-03 Wegmann & Co Schaltungsanordnung zur sicherung von elektrisch betaetigten waffensystemen
DE8525476U1 (de) * 1985-09-06 1985-10-17 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Elektrische Kupplung für Munition

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2751818A (en) * 1952-06-19 1956-06-26 Mitchell E Bonnett Latch mechanism for a rocket launcher
US2788712A (en) * 1954-07-09 1957-04-16 Bofors Ab Locking arrangement for singly and sequentially releasing ballistic missiles
US3331278A (en) * 1965-03-09 1967-07-18 Hi Shear Corp Separable fastener assembly

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2751818A (en) * 1952-06-19 1956-06-26 Mitchell E Bonnett Latch mechanism for a rocket launcher
US2788712A (en) * 1954-07-09 1957-04-16 Bofors Ab Locking arrangement for singly and sequentially releasing ballistic missiles
US3331278A (en) * 1965-03-09 1967-07-18 Hi Shear Corp Separable fastener assembly

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4095508A (en) * 1977-04-04 1978-06-20 The United States Of America As Represented By The Secretary Of The Army Capacitive discharge firing mechanism
US4271748A (en) * 1978-07-06 1981-06-09 Her Majesty The Queen In Right Of Canada, As Represented By The Minister Of National Defence Shorting and radiation protection device for rocket
US4416183A (en) * 1981-07-28 1983-11-22 Adams Robert W Rocket retention and ignition system
US4716808A (en) * 1985-11-12 1988-01-05 Mcdonnell Douglas Corporation Mechanical launch sequencer for a missile
EP1808664A1 (en) * 2006-01-13 2007-07-18 Saab AB IM-lock for weapons having preloaded projectiles
US20100251881A1 (en) * 2006-01-13 2010-10-07 Saab Ab IM-lock for weapons having preloaded projectiles
US7913607B2 (en) 2006-01-13 2011-03-29 Saab Ab IM-lock for weapons having preloaded projectiles
US20220009607A1 (en) * 2018-12-20 2022-01-13 Atlas Elektronik Gmbh Device and method for launching an underwater projectile from a watercraft
US12017741B2 (en) * 2018-12-20 2024-06-25 Atlas Elektronik Gmbh Device and method for launching an underwater projectile from a watercraft

Also Published As

Publication number Publication date
DE2104609B2 (de) 1974-01-10
FR2080080A5 (US07714131-20100511-C00038.png) 1971-11-12
DE2104609C3 (de) 1974-08-01
DE2104609A1 (de) 1971-09-09

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