EP0481851A1 - Schliess- und Schutzvorrichtung für ein Gasauslasssystem eines senkrechten Abschussmoduls - Google Patents

Schliess- und Schutzvorrichtung für ein Gasauslasssystem eines senkrechten Abschussmoduls Download PDF

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Publication number
EP0481851A1
EP0481851A1 EP91402702A EP91402702A EP0481851A1 EP 0481851 A1 EP0481851 A1 EP 0481851A1 EP 91402702 A EP91402702 A EP 91402702A EP 91402702 A EP91402702 A EP 91402702A EP 0481851 A1 EP0481851 A1 EP 0481851A1
Authority
EP
European Patent Office
Prior art keywords
support
closing
pivot axis
closure
upper edge
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
EP91402702A
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English (en)
French (fr)
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EP0481851B1 (de
Inventor
Jacques-Pierre Truyman
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.)
Direction General pour lArmement DGA
Etat Francais
Original Assignee
Direction General pour lArmement DGA
Etat Francais
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 Direction General pour lArmement DGA, Etat Francais filed Critical Direction General pour lArmement DGA
Publication of EP0481851A1 publication Critical patent/EP0481851A1/de
Application granted granted Critical
Publication of EP0481851B1 publication Critical patent/EP0481851B1/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
    • F41F3/0413—Means for exhaust gas disposal, e.g. exhaust deflectors, gas evacuation systems

Definitions

  • the present invention relates to a device for closing and protecting a gas discharge system from a vertical launch module.
  • the vertical launch modules fitted to a surface building are generally embedded under the deck of the building and each include a system for evacuating the propellant gases produced during a normal missile launch or an inadvertent ignition, which evacuates propellant gases from the upper end or from the top of the module.
  • the gas evacuation system must be provided with a closing device which opens only in the event of an accidental ignition or a normal firing of a missile.
  • Single central chimney exhaust systems must be designed to prevent seawater, rain or other foreign objects from falling inside the chimney and either cause the chimney to fill up or build up concerns foreign objects, projectiles during the evacuation of gases.
  • the closing devices currently used consist of one or more resistant and motorized doors, each door being provided with a panel which is ejected during the evacuation of gas, following an inadvertent ignition.
  • each launch module requires its own door operator system which reduces the space available on the building.
  • the object of the present invention is a device for closing and protecting a gas evacuation system which is simple in its construction and which requires no motor means to operate the closing device.
  • the subject of the present invention is a closure and protection device which comprises at least one closure element mounted on a pivot axis passing through a support which is arranged around and near the upper end of the exhaust gas duct.
  • An advantage of the present invention lies in the fact that the closure element is opened by the sole pressure of the propellant gases.
  • the closing element is returned to the closed position by a return member and it is arranged in a protective element which makes it possible, on the one hand, to avoid the mounting of an ejectable part and non-recoverable likely to cause personal injury and material damage and, on the other hand, to ensure protection of the gas evacuation pipe or pipes, by preventing sea water or solid objects from entering the inside said evacuation conduits.
  • the passages 6 communicate with a plenum or plenum 7 which occupies most of the base 8 of the structure 1.
  • the device for discharging the missile propulsion gases consists, in the example shown in FIG. 1, of four separate conduits 9, preferably of cylindrical shape, which are arranged between the upper and lower plates 3 and 5, of on the one hand, and between the passages 6, on the other hand, so as to occupy the volume of the module delimited by the cells.
  • Each discharge pipe 9 is equipped with a closure and protection device 10, as shown in FIG. 1.
  • Each device 10 is mounted on the upper plate 3 of the vertical launch module and around the upper end 9 ′ of the evacuation duct which is associated with it.
  • the device 10 comprises a closure element constituted by a sleeve 11 whose upper edge 11 ′ is located above the free edge of the discharge duct 9, and two valves 12 pivotally mounted on an axis 13 passing through the body of the sleeve 11.
  • the pivot axis 13 is arranged in such a way that the valves 12, in the closed position, shown in dotted lines in FIG. 2, come to bear on the upper edge 11 ′ of the valve holder sleeve 11.
  • the valve holder sleeve 11 is fixed by its base 11 ⁇ to the upper plate 3, by any suitable means such as bolts 14 (FIGS. 4 and 6) .
  • a protective element 15 is arranged around the valve-carrying sleeve 11, and it is mounted and fixed on the latter by means of lugs or an internal crown applying to the base 11 ⁇ of the valve-carrying sleeve 11, and bolts 14, with the interposition of a seal 19 as shown in FIG. 6.
  • the protective element 15 which, in section, is elliptical has a free upper edge 15 ′ which is located above the upper edge 11 ′ of the valve holder 11.
  • Two discharge orifices 16 are formed at the base of the bodies of the protective element 15 and below the level of the valves 12. In this way, the valves 12 are protected from the action of seawater packets capable of sweeping the deck of the building, the seawater being discharged through the orifices 16.
  • the gases propulsion cannot escape laterally.
  • a return spring or any other equivalent means such as one or more torsion bars 17, mechanically return the valves to the closed position as soon as the pressure of the propulsion gases applying to the valves 12 is less than the spring setting or at the moment of torsion of the torsion bars.
  • the mechanical recall used is calculated so that it is not too large; otherwise the gas pressure necessary to open the valves 12 would be too high and would lead to a general increase. It should be noted that even with a relatively weak mechanical return, the valves 12 are not sensitive to seawater packets thanks to the presence of the protective element 15.
  • the nature of the materials used for the various constituent elements of the device according to the invention are chosen so as to resist the corroding actions of sea water and propellant gases, evacuating through the evacuation conduits .
  • each conduit 9 When a missile is fired or inadvertently ignited, the pressure of the propellant gases 18 prevailing in each conduit 9 causes the valves 12 to open, against the mechanical return, to bring them into the position where they are back to back, as shown in FIG. 2.
  • the propellant gases 18 are mainly evacuated upwards and into the atmosphere, thanks to the presence of the protective element which acts as a guide element for said propellants. A significant lateral evacuation could be detrimental for the missile fired.
  • the device according to the invention accommodates variations in the relative positions of the evacuation conduits 9 and of the upper plate 3 since it only fits on the evacuation conduits whatever their location in the plate. upper 3 of the vertical launch module.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Safety Valves (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Emergency Lowering Means (AREA)
  • Fire-Extinguishing By Fire Departments, And Fire-Extinguishing Equipment And Control Thereof (AREA)
EP19910402702 1990-10-18 1991-10-10 Schliess- und Schutzvorrichtung für ein Gasauslasssystem eines senkrechten Abschussmoduls Expired - Lifetime EP0481851B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9012877A FR2668254B1 (fr) 1990-10-18 1990-10-18 Dispositif de fermeture et de protection d'un systeme d'evacuation de gaz d'un module de lancement vertical.
FR9012877 1990-10-18

Publications (2)

Publication Number Publication Date
EP0481851A1 true EP0481851A1 (de) 1992-04-22
EP0481851B1 EP0481851B1 (de) 1994-07-20

Family

ID=9401340

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19910402702 Expired - Lifetime EP0481851B1 (de) 1990-10-18 1991-10-10 Schliess- und Schutzvorrichtung für ein Gasauslasssystem eines senkrechten Abschussmoduls

Country Status (3)

Country Link
EP (1) EP0481851B1 (de)
ES (1) ES2061209T3 (de)
FR (1) FR2668254B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2930817A1 (fr) * 2008-04-30 2009-11-06 Dcns Sa Systeme d'obturation d'un conduit d'evacuation des gaz d'un lanceur de missiles

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4173919A (en) * 1977-12-12 1979-11-13 General Dynamics Corporation Two-way rocket plenum for combustion suppression
EP0366247A2 (de) * 1988-10-27 1990-05-02 British Aerospace Public Limited Company Aufprallgesteuerter Druckregler

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4173919A (en) * 1977-12-12 1979-11-13 General Dynamics Corporation Two-way rocket plenum for combustion suppression
EP0366247A2 (de) * 1988-10-27 1990-05-02 British Aerospace Public Limited Company Aufprallgesteuerter Druckregler

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
AVIATION WEEK AND SPACE TECHNOLOGY, vol. 114, 2 mars 1981, pages 40-50, New York, US; E.H. KOLCUM: "Vertical launching system scheduled for sea tests" *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2930817A1 (fr) * 2008-04-30 2009-11-06 Dcns Sa Systeme d'obturation d'un conduit d'evacuation des gaz d'un lanceur de missiles
WO2009138664A2 (fr) * 2008-04-30 2009-11-19 Dcns Système d'obturation d'un conduit d'évacuation des gaz d'un lanceur de missiles
WO2009138664A3 (fr) * 2008-04-30 2010-01-07 Dcns Système d'obturation d'un conduit d'évacuation des gaz d'un lanceur de missiles

Also Published As

Publication number Publication date
ES2061209T3 (es) 1994-12-01
EP0481851B1 (de) 1994-07-20
FR2668254A1 (fr) 1992-04-24
FR2668254B1 (fr) 1993-07-23

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