CA1337964C - Missile storage apparatus - Google Patents
Missile storage apparatusInfo
- Publication number
- CA1337964C CA1337964C CA000461401A CA461401A CA1337964C CA 1337964 C CA1337964 C CA 1337964C CA 000461401 A CA000461401 A CA 000461401A CA 461401 A CA461401 A CA 461401A CA 1337964 C CA1337964 C CA 1337964C
- Authority
- CA
- Canada
- Prior art keywords
- container
- missile
- exhaust gas
- quenching fluid
- launch
- 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 - Fee Related
Links
- 238000010791 quenching Methods 0.000 claims abstract description 31
- 230000000171 quenching effect Effects 0.000 claims abstract description 30
- 239000012530 fluid Substances 0.000 claims abstract description 17
- 239000012634 fragment Substances 0.000 claims abstract description 15
- 230000035515 penetration Effects 0.000 claims abstract description 11
- 230000001681 protective effect Effects 0.000 claims abstract description 8
- 239000007788 liquid Substances 0.000 claims description 13
- 239000012528 membrane Substances 0.000 claims description 10
- 229920005989 resin Polymers 0.000 claims description 5
- 239000011347 resin Substances 0.000 claims description 5
- 239000011159 matrix material Substances 0.000 claims description 4
- 239000000919 ceramic Substances 0.000 claims description 3
- 239000003822 epoxy resin Substances 0.000 claims description 2
- 229920000647 polyepoxide Polymers 0.000 claims description 2
- 229910010293 ceramic material Inorganic materials 0.000 claims 2
- 229920001187 thermosetting polymer Polymers 0.000 claims 2
- 239000011521 glass Substances 0.000 claims 1
- 238000004880 explosion Methods 0.000 abstract description 5
- 239000007789 gas Substances 0.000 description 10
- 238000010304 firing Methods 0.000 description 5
- 239000004411 aluminium Substances 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- -1 polyethylene Polymers 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 239000004698 Polyethylene Substances 0.000 description 1
- 239000004743 Polypropylene Substances 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000004794 expanded polystyrene Substances 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 231100001261 hazardous Toxicity 0.000 description 1
- 239000011796 hollow space material Substances 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 229920000573 polyethylene Polymers 0.000 description 1
- 229920001155 polypropylene Polymers 0.000 description 1
- 239000013535 sea water Substances 0.000 description 1
- 230000002459 sustained effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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
- F41F3/073—Silos for rockets, e.g. mounting or sealing rockets therein
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Protective apparatus for storing missiles on a ship, from which the missiles may be directly launched vertically, comprises a plurality of mutually adjacent, elongate protective containers (6, 7, 8, 9, 10, 11) mounted with their respective longitudinal axes vertical and each adapted to support vertically therein a missile (12, 13, 14) in a launch disposition. The upper end of each container has an opening through which the missile can pass during launch, the opening normally being closed by an openable closure (18, 19). The respective lower ends of the containers open, via respective exhaust gas valves, into a common plenum chamber (15) having an exhaust gas vent (16, 17) to atmosphere. Each container has an associated quenching fluid pipeline (23) provided with a quenching fluid valve (22), the valve (22) normally being closed but being automatically and instantaneously openable in response to penetration, by an externally originating projectile or fragment, of a wall of a container whereby pressurised quenching fluid flows into that container to douse or prevent fire or explosion.
Description
1337~64 Missile Storage Apparatus This invention relates to missile storage appartus and more particularly to apparatus for storing missiles on naval ships.
Missile propellants and warheads comprise combustible and/or explosive materials which are not particularly hazardous when handled and stored normally but which may be ignited by a substantial and/or sustained rise in temperature. The storage of missiles on ships is a long standing problem; the storage apparatus is clearly liable to "attack" either deliberately by an aimed projectile or incidentally by a fragment from, for example, a nearby explosion. Propellants and/or warheads may ignite when struck by such a projectile or fragment resulting in an explosion or fire.
Accordingly, it has hitherto been customary to store ships' missiles below the waterline, thereby providing some degree of protection, the missiles being moved up to the firing deck as and when desired. Typically, the firing deck supports a number of launch tubes into each of which a missile is loaded prior to firing whereupon vulnerability to "attack" by projectiles or fragments is immediately and substantially increased. In addition, the launch tubes confine the missiles which confinement could actually ~, 1~37961 exacerbate the effects of ignition caused by a projectile or fragment attack.
An object of the present invention is to provide protective apparatus for storing missiles or the like on ships from which apparatus the missiles may be directly launched vertically as and when desired.
According to the present invention there is provided apparatus comprising a plurality of mutually adjacent, elongate protective containers mounted with their respective longitudinal axes vertical and each adapted to support vertically therein a missile or the like in a launch disposition, the upper end of each container having an opening through which the missile can pass during launch, said opening normally being closed by an openable closure and the lower end of each container opening, via exhaust gas valve means, into a common plenum chamber having exhaust gas vent means to atmosphere, said containers having respective quenching fluid inlets and quenching fluid valve means associated therewith, said quenching fluid valve means normally being closed but each being automatically and substantially instantaneously openable in response to penetration, by an externally originating projectile or fragment, of a wall of its associated container thereby enabling quenching fluid to flow into that container through its quenching fluid inlet.
Preferred features and a preferred apparatus of the invention will now be described, by way of example only, with reference to the accompanying drawing which is a schematic cut-away perspective view of the apparatus loaded with vertical launch missiles.
1~37964 Referring to the drawing, the apparatus of the invention, designated generally by reference numeral 1, is shown rigidly mounted substantially between the upper deck 2 and a lower deck 3 of a warship. The apparatus 1 comprises two sets 4 and 5 of four elongate, vertically disposed containers, the six containers visible in the drawing being designated by reference numerals 6 to 11 respectively.
Each container 6 to 11 is in the form of an enclosure comprising four elongate wall sections that are arcuate in plan view and which may be strengthened by one or more external metal members. These sections, in the case of container 9, are designated 9~, gn~ 91~l and 9"" and are preferably formed of a fibre reinforced resin/ceramic/fibre reinforced resin laminate, adjacent sections being bonded together. A container made of such a laminate is generally able to contain fragments resulting from explosion of the motor(s) of the missile stored therein thereby minimising the chance of such a fragment reaching, and initiating ignition of, the motor(s) of a missile stored in an adjacent container of the apparatus. A preferred laminate comprises a loosely needled blanket of ceramic fibres (for example that available under the trade mark "FIBREFRAX~) sandwiched between layers of glass fibre mat embedded in an epoxy resin. Preferably, each section 9' etc is produced by longitudinally cutting a tube formed of said laminate. The four vertices of the hollow space formed by the sections accommodate the wings of the missile, three of which are designated by reference numerals 12, 13 and 14, mounted in each container in a vertical launch disposition. Integral with the laminate sections 9~, gn~ 9ll1 and 9nl' is a fragment or projectile penetrating detector means the nature and purpose of which are described more fully below.
1~37964 The respective lower ends of the containers 6 etc communicate , via respective one-way flap or other valves (not shown) with a plenum chamber 15 that is provided with an exhaust duct 16 having an open upper end 17. Each of the valves is normally closed but immediately (eg about 0.1 second) prior to firing of a missile, the valve associated with the container 6 etc containing the missile to be fired is opened and automatically closes preferably immediately after the missile has left its container. Closure may be effected by, for example, the action of a return spring, the rate of closure depending upon the rate of exhaust gas pressure decay within the container. Thus, each valve permits, during firing of a missile, exhaust gas from the missile to pass into the plenum chamber 15 whence it passes to atmosphere through the duct 16. On the other hand, such valve in its normal, closed, position serves to prevent exhaust gas from one missile entering, via the plenum chamber 15, a container housing another missile which could otherwise result in damage to or even accidental ignition of that other missile.
The upper end of each of the containers 6 etc is normally closed by an inner "fly through" membrane and an outer protective lid. In the drawing, outer lid members 18, 19 serve to close off the two sets of containers 4 and 5 respectively. Each lid member 18, 19 is pivotably mounted and is movable between a closed and an open n launch~
position. In the drawing, the lid member 18 is shown in its closed position whilst the lid member 19 is shown in its open, "launch" position. Regarding the open lid member 19, it will be seen that its upper surface 20 abuts part of the open end 17 of the exhaust duct 16 and serves to deflect exhaust gas from missile 13 (shown as being launched) away from the initial flight path of the missile. This ensures that the exhaust gas, which issues from the duct 16 at a very high velocity, will not in any way affect the direction of flight of the missile as it is being launched. However, a separate deflecting member may be provided to fulfil this function. Each lid 18, 19 is provided with four blow out panels, one of which is designated 21, one positioned above the upper end of each container. These panels serve to relieve excess gas pressure within the container in the event of accidental ignition of a missile during storage when the lid member 18 or 19 is shut.
Each "fly through" membrane, one of which is designated 19', comprises expanded polystyrene sheet material having lines of weakness and which, during launch, will merely be penetrated by the missile. The membranes serve to prevent sea water, for example, entering the containers when the lid members 18 or 19 are open. Further, as it is intended that the missiles will be loaded into their respective containers in a factory and then be transported to the ship in question, it is desirable for the containers to be sealed against the ingress of moisture and other matter during transport and storage. The membranes 19' etc also serve that purpose and, for the same reason, the base of each container 6 etc, between the one way valve and the bottom of the missile, is provided with a membrane (not shown), for example of an aluminium/chlorosulphonated polyethylene/aluminium laminate, which membrane, during launch, will be destroyed by the exhaust gas. During transport and storage, the containers 6 etc may be slightly pressurised, for example by nitrogen, to help prevent ingress of moisture. Further, during transport and storage, the ends of each container 6 etc may be provided with protective end caps made, for example, of the afore-mentioned laminate, the caps being removed prior to loading of the containers, for example by crane, into position on the ship.
133796~
As already indicated, the walls of each missile container incorporate over substantially their entire area a detector (not shown) that is capable of detecting penetration thereof by a fragment or projectile. The detector associated with each container may be such as to detect penetration immediately after it has occurred but detection preferably occurs actually during the course of penetration. Any suitable type of detector may be employed but preferably it is in the form of a number of closely spaced (eg 2mm) electrically conductive wires, for example of copper, embedded in a sheet matrix of, for example, polypropylene. The sheet matrix may conveniently be laminated to either of the resin layers of the wall sections 9' etc of the containers. The wires are incorporated in an electrical circuit and, when a wire is broken or, alternatively, when two adjacent wires are shorted together by a fragment or projectile during passage thereof through the detector, the circuit provides an electrical signal that opens, via control circuitry, a fluid flow control valve (reference numeral 22 in the case of container 9) located in a quenching liquid pipe line (reference numeral 23 in the case of container 9) to which quenching liquid is supplied under pump pressure from a reservoir. The valve normally is closed and prevents the pressurised quenching liquid from entering its associated container. However, when the valve opens in response to said signal, quenching liquid, typically water, flows rapidly into the affected container and serves to prevent or quench an ensuing fire or explosion.
Each container is provided with a quenching liquid inlet at its upper end. The inlet associated with container 9 is designated by reference numeral 24 and is positioned such that quenching liquid entering the container will first t3373~
douse the most dangerous part of the missile, namely the war-head. One or more further inlets may, however, be provided at any desired location.
In the event of penetration of one or more of the containers occurring, the quenching liquid pumped into the container(s) will, of course, descend to the bottom of the container(s) and may, if the aluminium laminate membrane referred to earlier becomes damaged, flow via the flap or like valve(s) into the plenum chamber 15. Since, in the particular embodiment shown in the drawing, it is intended that penetration and quenching of, say, a single container should nevertheless leave the remaining containers and their missiles serviceable, quenching liquid that accumulates in the plenum chamber 15 is pumped out via conduit 25 so as to leave the exhaust gas flow passageways free for the purpose of further launchings. Preferably, an additional, normally open, valve, such as a solenoid valve, may be associated with each inlet/quenching fluid valve and that, during quenching, will automatically stop the flow of liquid through the inlet after, say, a period of three minutes but that will re-open if there is a further rise of temperature within the container, and so on. This will prevent the supply of unnecessarily excessive amounts of quenching liquid to the container(s) in question.
The lower part, designated 26, of the apparatus represents a control and monitoring panel from which, inter alia, opening and closing of the lid members 18, 19, missile launching and manual override of the quenching liquid con-trol valves may be effected In this respect, items 27 and 28 represent interfaces between the missile computer equipment and the ships computer equipment and item 29 represents an aerial for sending/receiving signals to and from the missile during launch.
13379~
Trials have demonstrated that apparatus of the invention provides greatly improved safety in the event of a projectile or fragment attack compared with hitherto proposed vertical launch missile magazines.
Missile propellants and warheads comprise combustible and/or explosive materials which are not particularly hazardous when handled and stored normally but which may be ignited by a substantial and/or sustained rise in temperature. The storage of missiles on ships is a long standing problem; the storage apparatus is clearly liable to "attack" either deliberately by an aimed projectile or incidentally by a fragment from, for example, a nearby explosion. Propellants and/or warheads may ignite when struck by such a projectile or fragment resulting in an explosion or fire.
Accordingly, it has hitherto been customary to store ships' missiles below the waterline, thereby providing some degree of protection, the missiles being moved up to the firing deck as and when desired. Typically, the firing deck supports a number of launch tubes into each of which a missile is loaded prior to firing whereupon vulnerability to "attack" by projectiles or fragments is immediately and substantially increased. In addition, the launch tubes confine the missiles which confinement could actually ~, 1~37961 exacerbate the effects of ignition caused by a projectile or fragment attack.
An object of the present invention is to provide protective apparatus for storing missiles or the like on ships from which apparatus the missiles may be directly launched vertically as and when desired.
According to the present invention there is provided apparatus comprising a plurality of mutually adjacent, elongate protective containers mounted with their respective longitudinal axes vertical and each adapted to support vertically therein a missile or the like in a launch disposition, the upper end of each container having an opening through which the missile can pass during launch, said opening normally being closed by an openable closure and the lower end of each container opening, via exhaust gas valve means, into a common plenum chamber having exhaust gas vent means to atmosphere, said containers having respective quenching fluid inlets and quenching fluid valve means associated therewith, said quenching fluid valve means normally being closed but each being automatically and substantially instantaneously openable in response to penetration, by an externally originating projectile or fragment, of a wall of its associated container thereby enabling quenching fluid to flow into that container through its quenching fluid inlet.
Preferred features and a preferred apparatus of the invention will now be described, by way of example only, with reference to the accompanying drawing which is a schematic cut-away perspective view of the apparatus loaded with vertical launch missiles.
1~37964 Referring to the drawing, the apparatus of the invention, designated generally by reference numeral 1, is shown rigidly mounted substantially between the upper deck 2 and a lower deck 3 of a warship. The apparatus 1 comprises two sets 4 and 5 of four elongate, vertically disposed containers, the six containers visible in the drawing being designated by reference numerals 6 to 11 respectively.
Each container 6 to 11 is in the form of an enclosure comprising four elongate wall sections that are arcuate in plan view and which may be strengthened by one or more external metal members. These sections, in the case of container 9, are designated 9~, gn~ 91~l and 9"" and are preferably formed of a fibre reinforced resin/ceramic/fibre reinforced resin laminate, adjacent sections being bonded together. A container made of such a laminate is generally able to contain fragments resulting from explosion of the motor(s) of the missile stored therein thereby minimising the chance of such a fragment reaching, and initiating ignition of, the motor(s) of a missile stored in an adjacent container of the apparatus. A preferred laminate comprises a loosely needled blanket of ceramic fibres (for example that available under the trade mark "FIBREFRAX~) sandwiched between layers of glass fibre mat embedded in an epoxy resin. Preferably, each section 9' etc is produced by longitudinally cutting a tube formed of said laminate. The four vertices of the hollow space formed by the sections accommodate the wings of the missile, three of which are designated by reference numerals 12, 13 and 14, mounted in each container in a vertical launch disposition. Integral with the laminate sections 9~, gn~ 9ll1 and 9nl' is a fragment or projectile penetrating detector means the nature and purpose of which are described more fully below.
1~37964 The respective lower ends of the containers 6 etc communicate , via respective one-way flap or other valves (not shown) with a plenum chamber 15 that is provided with an exhaust duct 16 having an open upper end 17. Each of the valves is normally closed but immediately (eg about 0.1 second) prior to firing of a missile, the valve associated with the container 6 etc containing the missile to be fired is opened and automatically closes preferably immediately after the missile has left its container. Closure may be effected by, for example, the action of a return spring, the rate of closure depending upon the rate of exhaust gas pressure decay within the container. Thus, each valve permits, during firing of a missile, exhaust gas from the missile to pass into the plenum chamber 15 whence it passes to atmosphere through the duct 16. On the other hand, such valve in its normal, closed, position serves to prevent exhaust gas from one missile entering, via the plenum chamber 15, a container housing another missile which could otherwise result in damage to or even accidental ignition of that other missile.
The upper end of each of the containers 6 etc is normally closed by an inner "fly through" membrane and an outer protective lid. In the drawing, outer lid members 18, 19 serve to close off the two sets of containers 4 and 5 respectively. Each lid member 18, 19 is pivotably mounted and is movable between a closed and an open n launch~
position. In the drawing, the lid member 18 is shown in its closed position whilst the lid member 19 is shown in its open, "launch" position. Regarding the open lid member 19, it will be seen that its upper surface 20 abuts part of the open end 17 of the exhaust duct 16 and serves to deflect exhaust gas from missile 13 (shown as being launched) away from the initial flight path of the missile. This ensures that the exhaust gas, which issues from the duct 16 at a very high velocity, will not in any way affect the direction of flight of the missile as it is being launched. However, a separate deflecting member may be provided to fulfil this function. Each lid 18, 19 is provided with four blow out panels, one of which is designated 21, one positioned above the upper end of each container. These panels serve to relieve excess gas pressure within the container in the event of accidental ignition of a missile during storage when the lid member 18 or 19 is shut.
Each "fly through" membrane, one of which is designated 19', comprises expanded polystyrene sheet material having lines of weakness and which, during launch, will merely be penetrated by the missile. The membranes serve to prevent sea water, for example, entering the containers when the lid members 18 or 19 are open. Further, as it is intended that the missiles will be loaded into their respective containers in a factory and then be transported to the ship in question, it is desirable for the containers to be sealed against the ingress of moisture and other matter during transport and storage. The membranes 19' etc also serve that purpose and, for the same reason, the base of each container 6 etc, between the one way valve and the bottom of the missile, is provided with a membrane (not shown), for example of an aluminium/chlorosulphonated polyethylene/aluminium laminate, which membrane, during launch, will be destroyed by the exhaust gas. During transport and storage, the containers 6 etc may be slightly pressurised, for example by nitrogen, to help prevent ingress of moisture. Further, during transport and storage, the ends of each container 6 etc may be provided with protective end caps made, for example, of the afore-mentioned laminate, the caps being removed prior to loading of the containers, for example by crane, into position on the ship.
133796~
As already indicated, the walls of each missile container incorporate over substantially their entire area a detector (not shown) that is capable of detecting penetration thereof by a fragment or projectile. The detector associated with each container may be such as to detect penetration immediately after it has occurred but detection preferably occurs actually during the course of penetration. Any suitable type of detector may be employed but preferably it is in the form of a number of closely spaced (eg 2mm) electrically conductive wires, for example of copper, embedded in a sheet matrix of, for example, polypropylene. The sheet matrix may conveniently be laminated to either of the resin layers of the wall sections 9' etc of the containers. The wires are incorporated in an electrical circuit and, when a wire is broken or, alternatively, when two adjacent wires are shorted together by a fragment or projectile during passage thereof through the detector, the circuit provides an electrical signal that opens, via control circuitry, a fluid flow control valve (reference numeral 22 in the case of container 9) located in a quenching liquid pipe line (reference numeral 23 in the case of container 9) to which quenching liquid is supplied under pump pressure from a reservoir. The valve normally is closed and prevents the pressurised quenching liquid from entering its associated container. However, when the valve opens in response to said signal, quenching liquid, typically water, flows rapidly into the affected container and serves to prevent or quench an ensuing fire or explosion.
Each container is provided with a quenching liquid inlet at its upper end. The inlet associated with container 9 is designated by reference numeral 24 and is positioned such that quenching liquid entering the container will first t3373~
douse the most dangerous part of the missile, namely the war-head. One or more further inlets may, however, be provided at any desired location.
In the event of penetration of one or more of the containers occurring, the quenching liquid pumped into the container(s) will, of course, descend to the bottom of the container(s) and may, if the aluminium laminate membrane referred to earlier becomes damaged, flow via the flap or like valve(s) into the plenum chamber 15. Since, in the particular embodiment shown in the drawing, it is intended that penetration and quenching of, say, a single container should nevertheless leave the remaining containers and their missiles serviceable, quenching liquid that accumulates in the plenum chamber 15 is pumped out via conduit 25 so as to leave the exhaust gas flow passageways free for the purpose of further launchings. Preferably, an additional, normally open, valve, such as a solenoid valve, may be associated with each inlet/quenching fluid valve and that, during quenching, will automatically stop the flow of liquid through the inlet after, say, a period of three minutes but that will re-open if there is a further rise of temperature within the container, and so on. This will prevent the supply of unnecessarily excessive amounts of quenching liquid to the container(s) in question.
The lower part, designated 26, of the apparatus represents a control and monitoring panel from which, inter alia, opening and closing of the lid members 18, 19, missile launching and manual override of the quenching liquid con-trol valves may be effected In this respect, items 27 and 28 represent interfaces between the missile computer equipment and the ships computer equipment and item 29 represents an aerial for sending/receiving signals to and from the missile during launch.
13379~
Trials have demonstrated that apparatus of the invention provides greatly improved safety in the event of a projectile or fragment attack compared with hitherto proposed vertical launch missile magazines.
Claims (11)
1. Protective apparatus for storing missiles or the like on ships from which apparatus the missiles may be directly launched, substantially vertically, characterised in that the apparatus comprises a plurality of mutually adjacent, elongate protective containers mounted with their respective longitudinal axes vertical and each adapted to support vertically therein a missile or the like in a launch disposition, the upper end of each container having an opening through which the missile can pass during launch, said opening normally being closed by an openable closure and the lower end of each container opening, via exhaust gas valve means, into a common plenum chamber having exhaust gas vent means to atmosphere, said containers having respective quenching fluid inlets and quenching fluid valve means associated therewith, said quenching fluid valve means normally being closed but each being automatically and substantially instantaneously openable in response to penetration, by an externally originating projectile or fragment, of a wall of its associated container thereby enabling quenching fluid to flow into that container through its quenching fluid inlet.
2. Apparatus according to claim 1 characterised in that the walls of each container comprise a laminate of a ceramic material sandwiched between layers of a fibre-reinforced thermosetting resin.
3. Apparatus according to claim 2 characterised in that said layer of ceramic material comprises a loosely needled blanket of ceramic fibres and in that said fibre-reinforced thermosetting resin comprises a glass fibre-reinforced epoxy resin.
4. Apparatus according to claim 1 characterised in that each container is, in any horizontal section, quasi-rectangular, each of the four walls thereof in any such section being inwardly convex and outwardly concave.
5. Apparatus according to claim 1 characterised in that the said openable closure comprises a pivotally mounted lid that, in its fully open position, serves during launch of a missile to deflect exhaust gas issuing from said vent means away from the launch path of said missile.
6. Apparatus according to claim 1 characterised in that each of said exhaust gas valve means is normally closed and means are provided to open, immediately prior to launch of a missile, the exhaust gas valve means associated with the container from which such missile is desired to be launched, there being means to close the valve immediately after launch of the missile.
7. Apparatus according to claim 6 characterised in that each of said exhaust gas valve means is a flap valve biassed into its closed position by spring means.
8. Apparatus according to claim 1 characterised in that the walls of each container include detector means adapted to sense penetration of one or more of said walls by an externally origin-ating projectile or fragment, said quenching fluid valve means being openable in response to said detector means sensing the occurrence of such penetration.
9. Apparatus according to claim 8 wherein said detector means comprises a sheet matrix having embedded therein closely spaced, electrically, conductive wires, said wires being incorpor-ated in an electrical circuit operative to cause opening of said quenching fluid valve means in the event of penetration of said matrix by a projectile or fragment.
10. Apparatus according to claim 1 including means automatic-ally to shut off the flow of quenching liquid into a said container after a predetermined period of time has elapsed, said means being operative to enable further quenching liquid to flow into said container in the event of there being a subsequent temperature rise within said container.
11. Apparatus according to claim 1 wherein each container is provided with a first rupturable membrane inwardly of, and adjacent to, its openable closure and with a second rupturable membrane inwardly of, and adjacent to, its exhaust gas valve means said membranes, together with the container walls, serving to provide a moisture proof enclosure for the missile.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8323984 | 1983-09-07 | ||
| GBGB8323984.8A GB8323984D0 (en) | 1983-09-07 | 1983-09-07 | Missile storage apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1337964C true CA1337964C (en) | 1996-01-23 |
Family
ID=10548439
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000461401A Expired - Fee Related CA1337964C (en) | 1983-09-07 | 1984-08-21 | Missile storage apparatus |
Country Status (4)
| Country | Link |
|---|---|
| CA (1) | CA1337964C (en) |
| FR (1) | FR2718226B1 (en) |
| GB (1) | GB8323984D0 (en) |
| IT (1) | IT8422534A0 (en) |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3988961A (en) * | 1975-08-08 | 1976-11-02 | The United States Of America As Represented By The Secretary Of The Army | Integrated rocket shipping container and launcher |
| GB2051320B (en) * | 1979-05-22 | 1983-09-28 | Gen Dynamics Corp | Two-way rocket plenum for combustion suppression |
| US4296669A (en) * | 1979-05-25 | 1981-10-27 | The United States Of America As Represented By The Secretary Of The Army | Rocket tube launcher with cast-in place tube support bulkhead |
| US4306486A (en) * | 1979-10-02 | 1981-12-22 | The United States Of America As Represented By The Secretary Of The Army | Low cost multiple round launcher |
-
1983
- 1983-09-07 GB GBGB8323984.8A patent/GB8323984D0/en active Pending
-
1984
- 1984-08-21 CA CA000461401A patent/CA1337964C/en not_active Expired - Fee Related
- 1984-09-05 IT IT8422534A patent/IT8422534A0/en unknown
- 1984-09-06 FR FR8413717A patent/FR2718226B1/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| FR2718226A1 (en) | 1995-10-06 |
| GB8323984D0 (en) | 1995-04-05 |
| IT8422534A0 (en) | 1984-09-05 |
| FR2718226B1 (en) | 1996-06-28 |
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