EP0486334B1 - Vorrichtung zur Kühlung eines Raumes mit einem Einspritzventil - Google Patents

Vorrichtung zur Kühlung eines Raumes mit einem Einspritzventil Download PDF

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Publication number
EP0486334B1
EP0486334B1 EP19910402703 EP91402703A EP0486334B1 EP 0486334 B1 EP0486334 B1 EP 0486334B1 EP 19910402703 EP19910402703 EP 19910402703 EP 91402703 A EP91402703 A EP 91402703A EP 0486334 B1 EP0486334 B1 EP 0486334B1
Authority
EP
European Patent Office
Prior art keywords
valve
piston
chamber
deformable element
missile
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
EP19910402703
Other languages
English (en)
French (fr)
Other versions
EP0486334A1 (de
Inventor
Pierre-Jacques 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 EP0486334A1 publication Critical patent/EP0486334A1/de
Application granted granted Critical
Publication of EP0486334B1 publication Critical patent/EP0486334B1/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 cooling an enclosure, comprising a valve for injecting cooling fluid, in particular for an enclosure of a vertical missile launching system.
  • means are provided for cooling such or such part of the system, as a function of the operations which occur, whether they have been ordered or produced incidentally.
  • the firing of a missile begins with an ignition of the acceleration thruster of the missile to execute the exit phase.
  • the propellants are not recovered and are evacuated upwards by one or more gas evacuation conduits, after passage or not in a tranquilization chamber located below the missile containers.
  • a coolant for example water
  • An injection of fluid directly into the tank or gas evacuation duct may also be desirable when there is fear of re-ignition of the residual gases after a normal shot.
  • Vertical missile launching systems generally include pressure sensors capable of measuring locally or generally the pressure in an enclosure, for example in the stilling chamber. The measurements thus carried out are analyzed and processed in order to determine whether or not it is necessary to inject a cooling fluid generally consisting of water.
  • a command for an injection valve, of the pyrotechnic type is triggered by means of an electric pulse for example.
  • patent FR 2523547 discloses an assembly for handling and positioning safety in the work station in a well of a rocket or missile thruster.
  • Safety for cooling in the event of inadvertent ignition of the propellant is ensured by spraying water supplied by pipes connected to the well in which the propellant actuates a float.
  • This safety device does not react to a brutal overpressure, and could not adapt to the vertical launch of a missile.
  • the principle of valves or valves having a deformable element and sensitive to a determined pressure is known, and illustrated for example by patent US 4216799 in the application to a logic fluid device. These logic circuits are adapted to sequential fluid passage commands. They are not designed to operate at high flow rates necessary for the injection of water for cooling systems, in particular for safety or emergency.
  • the object of the present invention is to remedy the aforementioned drawbacks and to propose a cooling device controlled by an injection valve which is not of the pyrotechnic type, the actuation of the valve being produced by the sudden overpressure which is produced during '' ignition of a propellant.
  • An object of the present invention is a device for cooling an enclosure, in particular a vertical missile launching system, comprising a supply of coolant in the enclosure, the supply being regulated by an injection valve.
  • a valve control device characterized in that the control device extends from the enclosure to the injection valve, and in that the control device comprises at least one valve control member which cooperates with at least one deformable element partially delimiting the enclosure, so that, when the pressure prevailing in the enclosure reaches a predetermined value, the deformable element is deformed and actuates the control member in the direction of l opening of the injection valve in order to supply the enclosure with cooling fluid.
  • An advantage of the present invention lies in the fact that it allows very rapid and safe injection of coolant.
  • Figure 1 is a partial perspective view of a gas evacuation system of a vertical missile launcher.
  • Figure 2 is a schematic representation of a first embodiment according to the invention.
  • Figure 3 is a schematic representation of a second embodiment according to the invention.
  • Figure 4 is a schematic representation of a third embodiment according to the invention.
  • Figure 5 is a schematic representation of a fourth embodiment according to the invention.
  • a gas evacuation system of a vertical missile launcher fitted to a warship generally comprises (FIG. 1) a recovery tank 1 for the propellant gases produced by a missile 2 on board a container 3, said propellant gases being admitted in the tank 1 through orifices 3 ′ above which the missiles are mounted 2.
  • An evacuation chimney 4 communicates with the tank 1 and allows the gases contained in the tank 1 to escape to the atmosphere.
  • the chimney evacuation can be of the single rectangular type like that shown in FIG. 1 or of the multi-cylinder type.
  • a cooling fluid injection device 5, in this case water, is also provided and it is connected to the building's fire circuit by a pipe 6.
  • the device comprises a closing-opening valve 7 which is mounted on the pipe 6, an injector 8 opening into the tank 1 which is shown partially in FIG. 2, and control means 9 for the valve 7
  • the control means 9 are constituted by a deformable metal membrane 10 disposed on a thermal protection 11 which, possibly, can cover all or part of the walls of the tank 1.
  • the membrane 10 and the thermal protection 11 are covered by a body 12 , at the upper part of which is an orifice 13 for the passage of a movable rod 14 provided with a head 15.
  • the body 12, the membrane 10 and the thermal protection 11 are fixed above an orifice 16 ′ formed in the upper wall 16 of the tank by any suitable means such as bolts 17.
  • the material of the body 12 may, for example, be of the same nature as the tank 1, in particular silicone resin.
  • the propulsion gases of the missile must, in order to be able to be evacuated outside the evacuation system, beforehand eject the mass of stationary air which is in the tank 1.
  • a significant overpressure is created in the tank.
  • Such an overpressure is used according to the invention as a driving force to deform the membrane 10 in the direction of the enlarged head 15.
  • the deformation of the membrane 10 causes, by contact on the head 15, a displacement of the rod 14 secured to the head 15, which rod 14 actuating an opening-closing drawer provided in the valve 7 so that the water is sprayed through the injector 8 inside the tank 1.
  • the spraying of water into the tank 1 causes the gases contained in the tank 1 to cool.
  • the device according to the invention operates in the same way when an accidental missile ignition occurs since in this case an overpressure is also caused in the tank 1 and the valve 7 is open, after deformation of the membrane 10. Another advantage is that the device according to the invention makes it possible to lighten the thermal protections of the tank 1 since at each phenomenon of overpressure the valve 7 opens and water is injected into the tank 1.
  • the water injection device comprises, in addition to the pipe 6, the water injector inside the tank 1 but not shown, control means 18 for valve 7 provided with its own delay, for example of the order of 5 seconds.
  • the control means 18 comprise a deformable metal membrane 10, a thermal protection 11, a holding body 12 which is integral with said membrane and thermal protection by means of a connecting piece 19.
  • the head of the rod is constituted by a piston 20 on which the end of a spring 21 bears, the other end of which bears on the body 12.
  • the valve 7 then has the possibility of returning to its initial position by the spring 21 and a slot 22 in which a stud 23 of the rod 14 moves.
  • the device has a structure similar to that of the device shown in Figure 3 and, in addition, has its own fixed delay stage, which allows the use of a simple hydraulic valve itself not having a delayed closure.
  • the delay stage consists of a chamber 24 filled with a fluid and delimited by the upper body 12, a bottom plate 25 and side pieces 26, the rod 14 passing through the bottom plate 25 and the body 12 so sealed by means of seals 27.
  • a piston 28 is mounted on the rod 14 and moves with the latter in the chamber 24 which is filled with oil, in a sealed manner. Ports 29 each provided with a valve 30 are formed in the piston 28.
  • the delay in closing the valve 7 is increased when the overpressure in the tank 1 is maintained, which is the case during an accidental ignition of a missile 2.
  • the organs which are identical to the embodiments of FIGS. 2 to 4 have the same references.
  • the upper end 31 of the rod 14 moves in a blind recess 32 formed in an end portion 33 of a floating plate 34 which is disposed in the chamber 24, above the second piston 28.
  • a second spring 35 is disposed between the body 12 and the floating plate 31 and a third spring 36 is disposed between the floating plate 34 and the second piston 28.
  • the floating plate 34 is provided with orifices 37 each equipped with a valve 38.
  • the floating plate 34 is, at rest, in a low position.
  • the deformation of the membrane 10 causes the piston 20 - rod 14 - piston 28 - end part 33 to move until a connection point 39 between the end part and a member 40 connected to the valve 7 occupies position I. In this position, only a small flow of water in the tank 1 is ensured by the valve 7.
  • the membrane returns to its initial position and the piston 20 also returns to its initial position with a delay, for example of a second, induced by the delay stage 28.
  • the action exerted by the return spring 36 on the turntable 34 ceases and the latter returns to the low rest position with a certain delay, for example after 5 seconds.
  • the duration of the deformation is a function the duration of combustion of the accelerator of the missile.
  • the piston 20 occupies a high position and the spring 36 pushes the floating plate 34 and consequently the end piece 33 which brings the connection point 39 to position II corresponding to a full opening of the valve 7 and therefore to a large flow of water in the tank 1.
  • the piston 20 returns to its initial position, for example in 1 or 2 seconds, but the floating plate which has moved a higher position returns to the lower rest position only after a longer time which depends in particular on the diameter of the orifices 37.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Safety Valves (AREA)
  • Multiple-Way Valves (AREA)
  • Lift Valve (AREA)

Claims (15)

  1. Kühlvorrichtung eines Schutzbehälters (1), insbesondere eines senkrechten Flugkörper-Startsystems (2), bestehend aus einer Versorgung (6, 7, 8) mit Kühlflüssigkeit im Schutzbehälter (1), wobei die Versorgung mittels eines Einspritzventils (7) geregelt ist, und aus einer Steuervorrichtung des Ventils (7), dadurch gekennzeichnet, daß sich das Steuersystem vom Schutzbehälter (1) bis zum Einspritzventil (7) erstreckt, und daß das Steuersystem zumindest ein Steuerorgan (14, 15; 14, 20) des Ventils (7) umfaßt, das mit zumindest einem verformbaren Element (19) zusammenwirkt, das den Schutzbehälter teilweise abgrenzt, sodaß, wenn der innerhalb des Schutzbehälters herrschende Druck einen bestimmten Wert erreicht, sich das verformbare Element (1) verformt und das Steuerorgan (14, 15; 14, 20) betätigt, um das Einspritzventil (7) zu öffnen, damit der Schutzbehälter (1) mit Kühlflüssigkeit versorgt wird.
  2. Vorrichtung nach Patentanspruch 1, dadurch gekennzeichnet, daß das Steuerorgan (9) aus einem Druckknopf (15) besteht, von dem ein Ende durch das verformbare Element (10) verschoben werden kann und dessen anderes Ende die Öffnung des Flüssigkeitseinspritzventils (7) steuert.
  3. Vorrichtung nach einem der Patentansprüche 1 oder 2, dadurch gekennzeichnet, daß das verformbare Element (10) über einer Öffnung (16′) eines Wandabschnitts (16) angeordnet ist, der einen Raum begrenzt, in dem der Steuerdruck des verformbaren Elements (10) herrscht.
  4. Vorrichtung nach einem der Patentansprüche 1 bis 3, dadurch gekennzeichnet, daß das verformbare Element (10) aus einer elastischen Membran besteht.
  5. Vorrichtung nach Patentanspruch 4, dadurch gekennzeichnet, daß die elastische Membran (10) aus Metall besteht.
  6. Vorrichtung nach einem der Patentansprüche 4 oder 5, dadurch gekennzeichnet, daß die elastische Membran (10) auf der Seite des besagten Raums auf ihrer Innenseite mit einem Wärmeschutz (11) verkleidet ist, wobei die besagte Membran (10) und der besagte Wärmeschutz (11) zwischen einem ersten Schutz- und Befestigungskörper (12) und dem besagten Wandabschnitt (16) angeordnet sind.
  7. Vorrichtung nach einem der vorgenannten Patentansprüche, dadurch gekennzeichnet, daß das Ventil (7) mit Verzögerungsmitteln ausgestattet ist, die das Ventil nach einer bestimmten Zeit schließen.
  8. Vorrichtung nach einem der vorgenannten Patentansprüche 2 bis 7, dadurch gekennzeichnet, daß der Druckknopf aus einem Kolben (20) besteht, der sich auf eine Außenseite der elastischen Membran (10) abstützt, wobei die Stange (14) des besagten Kolbens (20) die Öffnung des besagten Ventils (7) steuert, und daß Rückzugsmittel (21) zwischen dem besagten Kolben (20) und dem Schutz- und Befestigungskörper (12) angeordnet sind.
  9. Vorrichtung nach Patentanspruch 8, dadurch gekennzeichnet, daß die Kolbenstange (14) mit einem Ansatz (23) bestückt ist, der sich innerhalb einer Aussparung (22) bewegen kann, die in einer Schutzhülle der besagten Stange (14) vorgesehen ist.
  10. Vorrichtung nach Patentanspruch 8, dadurch gekennzeichnet, daß an der Kolbenstange (14) Verzögerungsmittel (28, 29, 30) zum Verschließen des Ventils (7) angeordnet sind, wobei die besagten Verzögerungsmittel aus einem zweiten Kolben (28) bestehen, der innerhalb einer mit Öl gefüllten und mit dem Schutz- und Befestigungskörper (12) ein Teil bildenden Kammer (24) angeordnet ist, wobei der besagte zweite Kolben (28) mindestens eine mit einer Verschlußklappe (30) versehenen Öffnung (30) aufweist.
  11. Vorrichtung nach Patentanspruch 10, dadurch gekennzeichnet, daß sie außerdem eine auf der Kolbenstange (14) schwimmend montierte Platte (34) sowie zweite elastische, vorher geeichte Mittel (36) aufweist, die zwischen der Platte (34) und dem zweiten Kolben (28) montiert sind, und dritte elastische, vorher geeichte Mittel (35), die zwischen der Platte (34) und dem Körper (12) angeordnet sind, wobei die Platte (34) zumindest eine mit einer Klappe (38) bestückten Durchlaßöffnung (37) aufweist.
  12. Vorrichtung nach Patentanspruch 11, dadurch gekennzeichnet, daß das dem Kolben (20) gegenüberliegende Ende (31) der Kolbenstange (14) in einem Grundloch (32) beweglich ist, das in einem mit der Platte (34) ein Teil bildenen Zwischenteil (33) vorgesehen ist, und deren anderes Ende das besagte Ventil (7) steuert.
  13. Vorrichtung nach einem der vorstehenden Patentansprüche, dadurch gekennzeichnet, daß der Verformungssteuerdruck des verformbaren Elements (10) der von den bei der Zündung eines Flugkörpers erzeugten Gase erzeugte Überdruck ist.
  14. Vorrichtung nach Patentanspruch 13, dadurch gekennzeichnet, daß es sich beim Steuerdruck um denjenigen handelt, der innerhalb eines Schutzbehälters (1) herrscht, der mit einer Abführungsleitung (4) der Gase eines senkrechten Startsystems von Flugkörpern verbunden ist.
  15. Vorrichtung nach einem der vorstehenden Patentansprüche, dadurch gekennzeichnet, daß es sich bei der Kühlflüssigkeit um Wasser handelt.
EP19910402703 1990-11-15 1991-10-10 Vorrichtung zur Kühlung eines Raumes mit einem Einspritzventil Expired - Lifetime EP0486334B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9014195 1990-11-15
FR9014195A FR2669411B1 (fr) 1990-11-15 1990-11-15 Dispositif de commande d'une vanne d'injection d'un fluide.

Publications (2)

Publication Number Publication Date
EP0486334A1 EP0486334A1 (de) 1992-05-20
EP0486334B1 true EP0486334B1 (de) 1995-04-12

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Application Number Title Priority Date Filing Date
EP19910402703 Expired - Lifetime EP0486334B1 (de) 1990-11-15 1991-10-10 Vorrichtung zur Kühlung eines Raumes mit einem Einspritzventil

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EP (1) EP0486334B1 (de)
ES (1) ES2072570T3 (de)
FR (1) FR2669411B1 (de)

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3521850A (en) * 1968-03-29 1970-07-28 Aro Corp Pressure differential sensor valve assembly
US4216799A (en) * 1978-12-07 1980-08-12 The Aro Corporation Sequential AND fluid logic device
IT7967880A0 (it) * 1979-04-26 1979-04-26 Fiat Ricerche Valvola temporizzatrice automatica specialmente per il controllo della rogazione dell acqua in impianti di irrigazione
US4373420A (en) * 1980-10-06 1983-02-15 General Dynamics, Pomona Division Combustion suppressor
US4480522A (en) * 1981-10-15 1984-11-06 General Dynamics, Pomona Division Rocket exhaust-gas deflector
FR2523547B1 (fr) * 1982-03-19 1988-11-25 Mothe Gerard Ensemble de manutention et de positionnement de securite en poste de travail en puits d'un propulseur fusee engin ou outillage
SE439193B (sv) * 1983-10-05 1985-06-03 Bengt Arne Persson Sjelvstengande ventilanordning

Also Published As

Publication number Publication date
ES2072570T3 (es) 1995-07-16
FR2669411A1 (fr) 1992-05-22
EP0486334A1 (de) 1992-05-20
FR2669411B1 (fr) 1993-02-05

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