WO2012059934A1

WO2012059934A1 - Hatch opening and closing mechanism for vertical ship launcher

Info

Publication number: WO2012059934A1
Application number: PCT/IN2011/000046
Authority: WO
Inventors: Guruprasad Siddalingappa; Shreedhar Arvind Katti; Prasad Goud Alasani; Sanjay Kumar; Purushotham Krishnamurthy; Lev Belyustin; Alexander Bobrov; Alexander Maksichev; Valeriy Melnikov; Vladimir Nikolaev; Oleg Smirnov; Mikhail Khomyakov
Original assignee: Brahmos Aerospace Private Limited
Priority date: 2010-11-01
Filing date: 2011-01-20
Publication date: 2012-05-10

Abstract

A hatch opening and closing mechanism (10) for vertical ship launcher is disclosed wherein a plurality of missiles are stored for launching in a plurality of compartments provided in a truss. Each compartment is provided with a hatch (16) which is openable by a hydraulically actuated swivelable latch. The operation of the hatch opening and closing mechanism (10) of the vertical missile launcher is simple, reliable and has better shock absorption capacity.

Description

TITLE : HATCH OPENING AND CLOSING MECHANISM FOR VERTICAL SHIP LAUNCHER

FIELD OF INVENTION

This invention relates to missilery in general and to launchers particularly. Particularly, this invention relates to vertical ship launchers. Still particularly, this invention relates shipboard vertical ship launcher. BACKGROUND OF THE INVENTION

A missile is a fuel propelled projectile, propulsion being engineered by the reaction of rearward discharged gases, liberated with great force when the fuel is combusted.

In many military applications, missiles ready for launching are stored in canisters. The missiles contained in a canister are mounted in a missile launcher. These launchers are capable of locating, holding and launching a plurality of missiles. The type of launcher is chosen depending upon desired capability. On shipboards and submarines, where 360 degree capability is a desired characteristic and where launchers are placed below a protective deck, canisterised missiles are placed ready for vertical launching and therefore vertical ship launchers are a preferred launcher.

A Vertical Ship Launcher is therefore a type of missile-firing system used typically aboard submarines and ships. The Vertical Ship Launchers have replaced Armored Box Launcher systems and the twin-arm missile launcher system that were previously used. The Vertical Ship Launcher is a scaled- down equivalent for launching cruise missiles such as the Tomahawk and surface-to-air missiles. The Vertical Ship Launchers allow both submarines and ships to have more weapons ready for firing at a given time than with other launching systems.

The Vertical Ship Launchers are either of the type which have the missile cells arranged in a grid with one lid per cell and are "hot launch" systems, i.e. the engine ignites within the cell during the launch, and thus requiring complex exhaust piping for flames and gas or of the type having both grid systems and a revolver design with more than one missile per lid, or "cold launch" system that ejects the missile from the launch tube before igniting the engine.

Each system has its own typical advantages. The hot-launch system utilizes the missile's own engine to propel the missile out of the launching system, and this reduces the weight, the size, maintenance requirement, and the initial production cost of the system. The cold-launch system, in contrast, needs power sources other than that of the missile's own to propel it out of the cell, so additional space, weight, maintenance and cost are added.

The advantage of the cold-launch system is in its safety: should the missile engine malfunction while the warhead is armed to detonate during firing, the hot-launch system would be doomed, but the cold-launch system can still eject the missile out of the cell and eliminate or reduce the threat. Sometimes, the Vertical Ship Launchers are designed with a slanted angle instead of being perpendicular so that when the malfunctioned missile is ejected, it would fall into the water instead of landing on the deck.

Another advantage of the cold-launch system is in its low life cycle cost of the launching tubes: since the engine starts within the tube in a hot-launch system during launches, the tubes of the hot-launch system can only sustain a limited number of launches, after which the tube must be replaced. A cold- launch system, in contrast, can last much longer because the tubes are not subject to the extreme heat blasts like that of the hot-launch system, because in the cold-launch system, the engine does not start until after the missile was ejected out of the tube.

A vertical launcher typically comprises a structural framework assembly mounted on the vessel, such as a combatant ship or a submarine and provided in a hold. The framework is typically in the form of a truss having a plurality of cells. Each cell is adapted to hold a missile held in a support structure including a launching tube or a canister.

Each cell of the missile launching system includes, at its missile firing end, a hatch cover member for protection purposes. The hatch cover provides a protective cover and acts as a seal for the missiles in the cells from the environment during storage, transportation and exploitation. The hatch cover is locked in closed position with the help of a locking mechanism. During launching of a missile, the respective hatch of the cell containing the fired missile is opened by the operation of the locking mechanism while hatches of all the other cells remain in closed condition. Whenever missile needs to be fired, the respective hatch is opened and the adjacent hatches are closed. During this firing, all closed hatches experience upward load. Hatch locking mechanism holds the closed hatch in closed position. When a missile is fired, the hatch of the other missiles in the missile launcher faces an upward thrust. Therefore, an efficient hatch locking mechanism is required to withstand the upward thrust experienced by hatches of the cells of the unfired missiles.

The vessel in which the launcher is installed is often subjected to severe movements or shocks, apart from the normal rolling and pitching of the vessel. A vessel which is struck may further be subjected to severe shocks. Missiles by their nature are sensitive pieces of equipment and often contain electronic circuitry that may not be able to withstand even moderate shocks. Also the firing of a missile causes severe recoil which must be compensated for. For all these reasons it is necessary to provide means to protect missiles from shock and vibration both in its rest state and ready to launch state and in its post launch state.

The MK41 (USA) is a hot launch missile (plume comes out and then launch occurs). It cannot be pressurized. The missile is ensconced in a canister for storing. The canister sustains both internal and external pressure. The missile has a booster which ignites the missile. Electrical connection is flexible via tubes. Exhaust gases have an exit way through a conduit rising out and up from the bottom of the canister. The weight of the canisterised missile in addition to certain 'x' factor is the minimum thrust to be developed for launch to actuate. The MK41 has only vertical shock absorbers. Hatch of the canister is manually operated. This set-up takes care of rolling or pitching upto 0.5G. The disadvantages are:

1) unable to sustain nearby explosions upwards of 150G - 160G;

2) unable to sustain in heavy battlefield environment.

In a hot-launching apparatus, insulation is of paramount importance; if any damage occurs, none of the missiles will fire.

The KLUB (Russia) resides on a cradle at the base. Electrical connector is fitted to the canisterised missile after the missile and canister is manually loaded into the launcher.

The disadvantages are:

1) manual operation;

2) the cradle is suspended with 4 connections required between cradle and canister. The cradle is a complicated mechanism and may transfer some movements to the tube;

3) the cradle responds to the ship motions, hence renders no fixed stiffness to the canisterised missile.

Russian patent RU 2213924 discloses vertical ship launchers having an upper base connected to a truss framework of the launcher through detachable members for disengagement. A sleeve is installed in each compartment in the upper base of the launcher; the sleeve body at the lower end in the inside has an obturator in the form of an annular support for the transport launching packs. Installed in the lower base in each cell of the launcher in alignment with the mentioned sleeve is a second sleeve that is hinge-mounted on the body of the lower base by means of a shock-absorbing device. Mounted inside the second sleeve is a gripping device for fixing the transport launching packs against vertical displacements relative to the second sleeve and a mechanism for interconnection of the electrical connector of electrical communication of the ship fire control system with the transport launching packs. Installed outside the second sleeve are guide members provided to be engaged with the respective mating members of the lower base. Installed in the upper section of the truss framework around the edges of the latter are horizontally positioned supports for engagement with respective mating members of the ship for limiting the displacements of the truss framework caused by rolling and pitching of the ship.

Similarly, Russian Patent RU2213925 discloses a shipboard vertical ship launchers having an upper base connected to a truss framework of the launcher are interconnected through detachable members for disengagement with formation of the preset vertical clearance. A replaceable sleeve is installed in the upper base in each cell of the launcher. The sleeve body at the lower end in the inside has an obturator. A guide member is made on the sleeve for engagement with the respective mating member of the transport launching packs. Installed in the lower base in each cell of the launcher in alignment with the replaceable sleeve is a second sleeve that is hinge- mounted on the body of the lower base by means of a shock- absorbing device. A ring with a spherical bearing surface is installed on the second sleeve. Mounted inside the second sleeve are a gripping device and a mechanism for interconnection of the electrical connector of electrical communication of the ship fire control system with the transport launching packs. Installed in the upper section of the truss framework are supports for engagement with the mating members of the ship. Each cell of the launcher is provided with centering members. While both patents disclose art which is suitable in its own right there is a need for a vertical Ship Launcher that will overcome the disadvantage of the prior art.

OBJECT OF THE INVENTION

An object of the present invention is to provide a hatch opening and closing mechanism for vertical ship launcher which is reliable in operation.

Another object of the present invention is to provide a vertical ship launcher which is efficient in shock absorption.

Further another object of the present invention is to provide a vertical ship launcher that is safe in operation.

Still another object of the present invention is to provide a hatch opening and closing mechanism for vertical ship launcher which is simple in operation.

Yet another object of the present invention is to provide a hatch opening and closing mechanism for vertical ship launcher which helps in increasing the life of the hatch and as a result the life of the vertical ship launcher.

An added object of the present invention is to provide a hatch locking mechanism in order to facilitate in opening of the hatch during emergency launching of the missile. SUMMARY OF THE INVENTION

In accordance with the present invention there is provided a hatch locking and unlocking mechanism for a vertical ship launcher for storing and launching a plurality of missilesJsaid launcher comprising: a. a truss framework having an operatively top end and an operatively bottom end and defined by vertical members, transverse members, and diagonal members to provide a support structure fitted within a barbette of a ship;

b. a plurality of compartments defined within said truss framework;

c. a hatch for each of said compartments at the operative top end, said hatch provided on a top plate of the compartment; d. a flange plate disposed within each of said compartment and adapted to suspend a canister;

e. a shock absorbing system having a first shock absorbing system for absorbing longitudinal shock, a second shock absorbing system for absorbing lateral shock, and a third shock absorbing system for absorbing operatively bottom shock;

£ a swivelable latch having a hook formation, said latch adapted to be swiveled form a disengaged configuration to an engaged configuration in which said hook formation engage a flange of said top support structure;

g. a hydraulically actuated locking actuator adapted to actuate the latch in said engaging and disengaging configuration; said locking actuator having a coupling element extending from said locking actuator;

h. a plurality of connecting links interposed between the coupling element and the latch;

i. a coupling pin for coupling the links to the coupling element; j. a first connecting pin, a second connecting pin, a third connecting pin and a fourth connecting pin for connecting a link connecting bracket to the swivelable latch through the connecting links;

k. a latch bracket extending from said hatch and said latch connected to the latch bracket by a shear pin, the latch bracket engages said latch in the engaged position by means of a shear pin, said shear pin is adapted to shear when the load on the hatch exceeds a predetermined value to disengage the latch;

1. pivoting means lying wholly outside the compartment, for pivoting the hatch with respect to the opening of the compartment, said pivoting means comprising:

i. a fixed element secured to the base plate, said fixed element having plurality of splines;

ii. an angular displaceable element secured to the hatch element, said angular displaceable element having plurality of splines;

iii. the fixed and the angular displaceable elements together defining a hinge;

iv. a stepped spline shaft having plurality of splines, complementary to the splines of the fixed and the angular displaceable element respectively, said stepped spline shaft having reciprocating motion; and

a primary hydraulic actuator to actuate the stepped spline shaft for opening and closing the hatch element.

Typically, each compartment has a substantial square cross-section.

Typically, each canister has a substantial circular cross-section.

Typically, the truss framework is a space frame.

Typically, the vertical ship further comprises a baffle means for directing gases created at the time of launch from one canister to another canister in another compartment.

Typically, the first shock absorbing system is a top longitudinal shock absorbing system adapted to sustain longitudinal shocks to said canister.

Typically, the first longitudinal shock absorbing system is provided between said flange plate and said top plate of said truss framework and is defined by:

- a plurality of downward shock absorbing elements comprising a piston pin with a stub which abuts said flange plate interspersed radially around said canister; and - a plurality of upward shock absorbing elements comprising a cylinder secured to the operative upper face of the flange plate by a bolt and nut assembly interspersed radially around said canister.

Typically, the second lateral shock absorbing system is defined by a ring suspended by rods at their lower ends and placed circumferentially around said ring, said suspended rods fitted by lever arms projecting out of said truss framework at an operative upper end of said rod and substantially at the centre of said rod.

Typically, the third shock absorbing system is a bottom shock absorbing system provided underneath said missile to compensate for shocks in all directions.

Typically, the flange plate encircling said canister, disposed radially outwards from outer surface of said canister and located substantially at the top of said canister to support said canister in said compartment.

Typically, the baffle means is a substantially 'L' -shaped plate fixed between said flange plate and said cover adapted to prevent transfer of exhaust gases after missile is launched from one compartment to adjacent compartments. ' ■

Typically, the third shock absorbing system includes said means to electrically connect said canister to a power source. Typically, electrical connector means comprises a female portion adapted to engage with male portion located underneath said canister to provide the firing and electrical signals and connections.

Typically, each of the compartments placed at the corners of said truss framework has a flexible, substantially 'U'-shaped multilayer laminate sealing element interposed between top edge of said corner compartment and said vertical member of said truss framework adapted to prevent entry of gases and plume flame into said compartment after missile is launched and provide resilience and support to said canister with respect to said truss framework.

Typically, the substantially 'U'-shaped multilayer laminate sealing element comprises:

- a first layer of heat resistant material;

- a second layer selected from a group comprising neoprene rubber, acronitrile, or silicon underneath said first layer;

- a third layer of Kevlar fibre underneath said second layer; and

- a fourth layer of neoprene rubber underneath said third layer.

Typically, the locking actuator is provided with at least one disc spring. Typically, the shear pin is hollow.

Typically, the shear pin is provided with at least one notch. Typically, the coupling pin, said first connecting pin, said second connecting pin, said third connecting pin and said fourth connecting pin are solid.

Typically, the link connecting bracket cooperates with the hatch.

Typically, the first connecting pin, said second connecting pin, said third connecting pin and said fourth connecting pin are linearly aligned in the engaged configuration of the latch.

Typically, the hydraulic operation of the locking actuator is achieved with the help of a hydraulic system, said hydraulic system comprising at least one flow control valve, at least one shut off valve, at least one shuttle valve and at least one counter balance valve.

Typically, the hydraulic system is operated by oil.

Typically, the hatch cooperate with the top support structure through a seal, said seal is retained in position by means of a retainer plate.

Typically, the fixed and angular displaceable elements are provided along the edge of the hatch element.

Typically, the hatch has rectangular shape.

Typically, the fixed and angular displaceable elements are provided along one side of the hatch element. Typically, the hatch has a locking means to lock the hatch element to the side wall of the compartment

Typically, the locking means comprises a secondary hydraulic actuator, link and a latch.

Typically, the secondary hydraulic actuator is connected to primary hydraulic actuator by means of a connecting pipe and a rotary joint characterized in that the primary hydraulic actuator is adapted to be actuated only when the latch is in an operative unlocked position.

Typically, the hatch includes a cap plate for capping the pivoting means.

Typically, the angular displaceable element can be displaceable over an angle greater than 90°.

Typically, the vertical ship launcher comprises a means to electrically connect said canister to a power source at its operatively bottom end.

BRIEF DESCRIPTION OF THE ACCOMPANYING DRAWINGS:

Other aspects of the invention will become apparent by consideration of the accompanying drawing and their description stated below, which is merely illustrative of a preferred embodiment of the invention and does not limit in any way the nature and scope of the invention. Figure 1 is a perspective view of a vertical ship launcher in accordance with the present invention illustrating the truss framework and a canister containing a missile;

Figure 2 is a top view of a top plate of the vertical ship launcher with a plurality of openings in accordance with the present invention;

Figure 3 is a schematic view of a canister illustrating the various parts of the vertical ship launcher and locations of shock absorbing means;

Figure 4 is a detailed schematic view of the canister mounted in the truss framework of the vertical ship launcher showing the details of a shock absorbing means;

Figure 5 is a front view of the truss framework of figure 1 positioned within the barbette of a ship;

Figure 6 is a front view of the truss framework along with the shock absorbing means;

Figure 7 is a front upper view of the canister along with sectional views of a shock absorbing means;

Figure 8 is a detailed schematic illustration of the canister, the truss framework and the shock absorbing means;

Figure 9 shows the details of the location of the vertical axis shock absorbing means for the launcher of figure 1; Figure 10 shows the connecting details of the operative horizontal axis shock absorbing means of figure 9;

Figure 11 is a schematic view of the operative horizontal axis shock and vibration absorbing means for the launcher of figure 1;

Figure 12 is another schematic view of the operative horizontal axis shock and vibration absorbing means for the launcher of figure 1;

Figure 13 shows the plan schematic details of the operative horizontal axis shock and vibration absorbing means of figure 9;

Figure 14 is a detailed front view of the canister connected to the truss framework of figure 1;

Figure 15 illustrates a hatch locking mechanism for a missile launching system;

Figure 16 illustrates the kinematic scheme diagram of the hatch locking mechanism of figure 15 in locked condition;

Figure 17 illustrates the kinematic scheme diagram of the hatch locking mechanism of figure 15 in unlocked condition; Figure 18 illustrates a sectional view of the hatch locking mechanism of figure 15 in locked condition and another hatch locking mechanism in unlocked condition;

Figure 19 illustrates a locking actuator of the hatch locking mechanism of figure 15 in accordance with the present invention;

Figure 20 illustrates a seal of the hatch locking mechanism of figure 15;

Figure 21 illustrates a schematic diagram of a hydraulic system for the operation of the hatch locking mechanism in accordance with the present invention;

Figure 22 illustrates a sectional view of a shear pin in accordance with the present invention;

Figure 23 illustrates the transfer force to the shear pin in the event of failure of the hydraulic system;

Figure 24 shows a hatch with a hatch mechanism actuator in accordance with this invention in open position;

Figure 25 is a sectional view along line AA in figure 24 illustrating the hatch mechanism actuator;

Figure 26 is the plan view of the hatch in accordance with this invention, showing partial cut away views of the hatch mechanism actuator; Figure 27 is sectional view showing along line BB in figure 26 illustrating the details of the hatch mechanism actuator;

Figure 28 illustrates the sectional views along line CC in figure 26 illustrating a latch in a locked position; and

Figure 29 illustrates the sectional views along line CC in figure 26 illustrating a latch in an unlocked position.

DETAILED DESCRIPTION

The invention will now be described with reference to the accompanying drawings which do not limit the scope and ambit of the invention. The description provided is purely by way of example and illustration.

Referring to the drawings, there is provided a vertical ship launcher as shown in the drawings. The drawings are merely exemplary and do not in anyway limit the ambit and the scope of the invention.

The vertical ship launcher comprises a truss framework (10) consisting of compartments, as shown in figure 1. Each compartment of the truss framework (10) has box-section vertical members (11), transverse members (12), and diagonal members (13), typically welded together to provide a support structure. Typically four or more such vertical members (11) constitute a compartment within which is ensconced a canister (16) holding a missile [not shown in figure]. The box-sections of the vertical members (11), the transverse members (12) and the diagonal members (13) increase the compressive strength of the truss framework (10) at the time of launching of the missile. At the operative upper end of the vertical members (11) of a compartment there is provided a top plate (18), shown in figure 2, with a plurality of openings (15) to be located above each of the compartments of the truss framework (10). The canister (16) which is typically cylindrical in shape is provided with a nose cap (20). The canister (16) is suspended from the plate (18) such that the nose cap (20) at the end of the canister (16) projects from the openings (15) provided on the top plate (18). The nose cap (20) is connected to a basic stub flange (22), as shown in figure 3, on the cylindrical body of the canister (16) by means of canister shear pins (24), shown in figure 4. At the end of the canister having the nose cap (20), a flange plate (26) is provided which extends circumferentially from the canister body (16). The flange plate (26) may extend from the canister (16) or from the stub flange (22) of the canister (16) to which the flange plate (26) is fitted. The nose cap (20) extends operatively upwards from the flange plate (26).

A barbette (29), illustrated in figure 5, is in the form of a bore which traverses through the multiple decks present in the ship, typically rising from the bottom deck (23), passing through the intermediate decks (25), and finally rising through the upper deck (27). The Vertical Ship Launcher comprising the truss framework (10) is fitted within the barbette (29). The Vertical Ship Launcher is fitted at the bottom of the barbette (29) and spaced apart from the walls of the barbette (29).

Figure 6 illustrates the truss framework (10) having the vertical members (1 1), the transverse members (12) and the diagonal members (13) along with a plurality of shock absorbing means (200, 300 and 400) to hold the canister (16). The shock absorbing means (200) are located at the operative top end of the truss framework (10). The shock absorbing means (200) is typically a Longitudinal Shock Absorbing System (SAS) and is fitted at the top of the barbette (29), between the top plate (18) and the flange plate (26). The shock absorbing means (200) comprises spring loaded motion restrictors (28 and 30), particularly shown in figure 7 and figure 8. Typically, if a shock originates at the bottom of the vessel, the shock wave travels through the structure to the top and dampens through its travel through the structure before reaching the shock absorbing means (200). In order to combat lateral shocks taking place at the bottom of a ship or vessel, the entire truss framework (10) of the launcher acts as a cantilever beam. The shock absorbing means (200, 300 and 400) essentially are shock absorbing cylindrical structures that absorb/dampen movements of the canister (16) along the operative vertical axis. A first motion restrictor (28) resist movement in the vertical axis in an operative downward direction and a second motion restrictor (30) resist movement in the vertical axis in an operative upward direction. The first motion restrictor (28) and second motion restrictor (30) are typically made of springs.

In accordance with a preferred embodiment of the invention, the number of second motion restrictor (30) are half that of the first motion restrictor (28), as particularly seen in figure 9. Typically, four first motion restrictor (28) and eight second motion restrictor (30) are provided. The first motion restrictor (28) and the second motion restrictor (30) house disc or Belleville washers [not shown in the figure] in order to resist deformation. Typically, the bellville washers are stacked in an alternating direction resulting in lowering of the spring constant and increasing deflection capacity. The springs of the first motion restrictor (28) and the second motion restrictor (30) are pre-tensioned, typically from 0.75 times upto 1.5 times the mass of the canister (16). The second motion restrictor (30) not only have to compensate for the downward movement but also the weight of the canister (16) and the missile contained therein. Typically, the first motion restrictor (28) has a piston pin (32) which is partially housed in a spring containing cylinder (34). The piston pin (32) has a stub which abuts the flange plate (26). Typically eight such pins support the flange plate (26) from below and are symmetrically placed radially below the flange plate (26) as seen in figure 10. The first motion restrictor (28) does not resist movement of the canister (16) in the upward direction.

The second motion restrictor (30) are cylinders which have a bolt (36) secured by a nut (38) to the operative upper face of the flange plate (26). The bolt (36) offers no resistance to the downward movement of the canister (16) while providing resistance to the upward movement of the canister (16). In the event of the upward movement of the canister (16), the flange plate (26) is resisted by the compression of the spring deforming operatively upwards in the cylinder (34) of second motion restrictor (30). Thus, the upward and downward movement of the canister (16) in the relative vertical axis is damped or absorbed by the cylindrical shock absorbing means (28, and 30) operating in tandem.

The shock absorbing means (300), shown in figure 10, are located on the truss framework (10) at a predetermined distance from the shock absorbing means (400) located at the operative bottom end of the truss framework (10). Movement in the horizontal axis and angular deflection at the lower end of the canister (16) is absorbed or damped by the shock absorbing means (300) which is typically a lateral Shock Absorbing System (SAS). The shock absorbing means (300) comprises a ring (40) suspended by elongate resilient rods (42) fitted by lever arms (44) and (46) to the truss structure (10) of the compartment of the frame work, as shown in figure 11, figure 12 and figure 13. For the purposes of this specification, the operative lower section of the canister (16) is defined as the part of the canister (16) which is between the middle section of the canister (16) and the end of the canister (16).

The elongate rod (42), of the shock absorbing means (300) is fitted to the ring (40) at the operative lower end and to a lever arm (44) at the operative upper end, typically by ball and socket joints. The elongate rod (42) provides the required stiffness. The lever arms (44 and 46) are advantageously fitted to the resilient rods (42) by pivot joints (48). The inner diameter of the ring (40) is just greater than the outer diameter of the canister (16) which slides through the ring (40) with some clearance. This arrangement symmetrically resists lateral displacement and swinging of the canister (16) ensconced in the compartment. The entire assembly has 1° freedom of rotation.

The shock absorbing means (400) located at the base of the canister (16) absorbs shock in all 6 degrees of freedom. The shock absorbing means (400) is the electrical connecting means to the missile in the canister (16). The shock absorbing means (400) helps in absorbing the shocks from the base.

The truss framework (10) itself acts as a lateral shock absorbing system at the operative top end of said canister (16). The truss framework (10) works in tandem with the shock absorbing means (300) to absorb shock waves in lateral direction. The canister (16) is supported in the truss framework (10) by means of its flange plate (26) at the operative top end. Supporting of the canister (16) in the truss framework (10) by means of its flange plate (26) is identical to a cantilever type arrangement whereby the shocks travel from the bottom of the ship to the bottom of the truss framework (10) and through it to the top of the truss framework (10).

When the missile is launched, the canister (16) undergoes vertically downward motion which acts on the shock absorbing means (200). The downward elements sustain the forces of the canister (16) in the downward direction. The downward motion of the canister (16) continues till the flange plate (26) firmly rests on the top plate (18). As the canister (16) moves downward, the canister (16) gets accurate vertical guidance by the piston pins (32) of the second motion restrictor (30). This provides firm location and positioning to the canister (16) at the instance of launching. The arrangement for locking of shock absorbing means (200, 300 and 400) is hence, not necessitated.

Each compartment is closed on the top by a hatch (50) which is pivotally connected to the truss framework (10) of the compartment is unlocked with the help of a hatch locking mechanism (54) and the hatch (50) swings open in a controlled manner just prior to the launch of the missile with the help of a hatch mechanism actuator (76), shown in figure 24. Each compartment is also isolated from the hold of ship by means of a resilient and flexible seal (52) typically made of a synthetic rubber, Kevlar and metallized fabric composite which blocks the entry of the gases and plume flame into the hold after the missile is launched. A substantially 'L-shaped' seal (17), shown in figure 14, protects adjacent missiles ensconced within their respective canisters (16) by not allowing the exhaust gases to diffuse into the other compartments and directing the gases in the upward direction away from adjacently resident canisterised missiles.

The vertical ship launcher includes a Top Support Structure (TSS) (60), shown in figure 15, which defines a hollow. The truss framework (10) is aligned within the hollow of the TSS (60) for structural stability. A flexible sealing element connects the top of the frame and the bottom of the TSS (60). A substantially 'U-shaped' element (19), shown in figure 14, joining the top edge of the compartment of a missile launcher and the vertical member of the truss framework (10) is adapted to prevent entry of gases and plume flame into the missile launcher after missile is launched and is also adapted to provide resilience and support to the canister (16) with respect to the truss framework (10). The sealing element (19) is a multilayer laminate which comprises a first topmost layer of a heat resistant material, a second layer of neoprene rubber or of acronitrile or of silicon, a third layer of Kevlar fibre, and a fourth bottom layer of neoprene rubber or of acronitrile or of silicon. The multilayer laminate is flexible, is heat resistant, typically upto 2000 degrees Celcius. The laminate has aluminium coating or silver coating. This coating eliminates moisture, has antifungal and antimicrobial properties.

The vertical ship launcher invention envisages a multi-compartment launcher typically having a 2x4 array of launch compartments, each compartment containing a canister (16) housing a missile. Each compartment is controlled by a controller, which contains data and information that is specific to the type of guided missile contained in the launch compartments. Alternative embodiments of the vertical ship launcher comprise single launch compartments, a one-dimensional array of launch compartments, or a two-dimensional array of any number of launch compartments.

A hatch locking mechanism (54), shown in figure 15, is provided for locking the hatch (50) to a flange (98) of the TSS (60) of the vertical ship launcher. The hatch locking mechanism (54) consists of a locking actuator (96) having a coupling element (11) and a latch (58) cooperating with the help of a plurality of connecting links (86a, 86b, 86c and 86d). The locking actuator (96) is connected with the help of the plurality of connecting links (86a, 86b, 86c and 86d) to the latch (58) with the help of a coupling pin (92) and a plurality of connecting pins (82a, 82b, 82c and 82d). The coupling element (11) is connected with the help of a coupling pin (92) to the connecting link (86a). The connecting link (86a) cooperates with the connecting link (86b) and the connecting link (86c) with the help of the connecting pin (82b). The connecting link (86b) cooperates with a link connecting bracket (100) by means of the connecting pin (82a). The link connecting bracket (100) cooperates with the hatch (50). The connecting link (86b) is connected to the connecting link (86c) with the help of the connecting pin (82b). The connecting link (86d) is connected to the connecting link (86c) with the help of the connecting pin (82c). The connecting link (86d) cooperates with the latch (58) with the help of the connecting pin (82d). The coupling pin (92) and the connecting pins (82a, 82b, 82c and 82d) are typically solid pins. The connecting link (86a) is aligned at an angle to the connecting links (86b, 86c and 86d). The latch (58) cooperates with the latch bracket (114) with the help of a shear pin (88). The latch (58) is provided with a hook formation (94) to communicate with a flange (98) of the top support structure (60) in an engaged configuration of the latch (58) when the hatch (50) is in closed condition. The latch (58) is adapted to swivel from the engaged configuration to a disengaged configuration in order to unlock the hatch (50) by the angular displacement of the connecting links (86a, 86b, 86c and 86d). The connecting pins (82a, 82b, 82c and 82d) are linearly aligned in the engaged configuration of the latch (58).

The locking actuator (96) enables in the angular displacement of the connecting links (86a, 86b, 86c and 86d) and the latch (58) about the coupling pin (92), the connecting pins (82b, 82c, 82d and 82e) and the shear pin (88) for causing the latch (58) to displace between an engaged configuration and a disengaged configuration. The displacement of the latch (58) between the engaged configuration and the disengaged configuration enables in locking and unlocking of the hatch (50) respectively. In the locked condition of the hatch (50), as shown in figure 16, the connecting pins (82a, 82b, 82c and 82d) lie in a straight line and the hook formation (94) of the latch (58) cooperates with the flange (98) of the top support structure (60). Figure 17 illustrates the position of the connecting links (86a, 86b, 86c and 86d), the latch (58), the connecting pins (82a, 82b, 82c and 82d) and the shear pin (88) in the unlocked condition of the hatch (50) wherein the hook formation (94) of the latch (58) is disengaged from the flange (98) of the top support structure (60). Due to the operation of hatch locking mechanism (54), the latch (58) is caused to disengage from flange (98) of the top support structure (60) of the missile launching system. Figure 18 illustrates the position of the links (86a, 86b, 86c, 86d and 86e) and a latch (58) and the connecting pins (82a, 82b, 82c and 82d) and the shear pin (88) in a closed condition for hatch (115a) and in an open condition for a hatch (115b).

The locking actuator (96), shown on figure 19, consists of at least one disc spring (116). The disc springs (116) are preloaded and help in exerting a constant force on the latch (58) which further helps in compressing the seal (1 10), shown in figure 20. The seal (1 10) is positioned around the periphery of the hatch (50) and is located between the hatch (50) and the top support structure (60). The seal (110) is held in position with the help of a retainer plate (112). The locking actuator (96) helps in compressing the seal (1 10) so as to prevent water to enter the missile launching system and hence damaging the missiles contained therein.

The hatch locking mechanism (54) and the hatch mechanism actuator (76) is operated by means of a hydraulic system (118), shown in figure 21. The hatch mechanism actuator (76) is used to facilitate in opening the hatch (50) after the operation of the locking mechanism (96) to unlock the hatch (50). During closing of the hatch (50), the hatch mechanism actuator (76) is operated first and then the locking actuator (96) is actuated. The hydraulic system (118) typically consists of at least one flow control valve (120a and 120b), at least one shut off valve (122a and 122b), at least one shuttle valve (124) and at least one counter balance valve (126a and 126b). The flow control valve (120a and 120b) helps in regulating the flow of operating fluid in the hydraulic system (118). The flow control valve (120a and 120b) responds to changes of the flow of the operating fluid. The flow control valves (120a and 120b) are operated with the help of signals provided by an operator for launching of a missile. The shut off valves (122a and 122b) are operated when the flow of the operating fluid is required to be stopped. The shuttle valve (124) acts as a two way valve. The shuttle valve (124) helps in passing a part of the operating fluid into the locking actuator (96). This causes the locking actuator (96) to operate the movement of the connecting links (86a, 86b, 86c and 86d) and the latch (58) about the coupling pin (92), the connecting pins (82a, 82b, 82c and 82d) and a shear pin (88). The operation of the locking mechanism (54) enables in disengaging the latch (58) from the top support structure (60). A part of the operating fluid flows through the counter balance valves (126a and 126b) to operate the hatch mechanism actuator (76). The operation of the hatch mechanism actuator (76) causes the hatch (50) to open about a hinge (62) by 95 degrees from the closed position of the hatch (50). The counter balance valves (126a and 126b) helps in creating a back pressure in order cause the hatch (50) to open smoothly from 95 degrees to 135 degrees and hence prevent the hatch (50) to fall abruptly under gravity acting on the weight of the hatch (50).

In accordance with another aspect of the present invention, there is provided an alternate method for opening the hatch (50) in the event of failure of the hydraulic system (1 18). Therefore, during emergency launching of the missile if the hatch (50) does not open, the missile will be launched inside the missile launching system with the hatch (50) in locked condition which will cause damage to the missile launching system. Therefore, in the event of the failure of the hydraulic system (1 18), the locking mechanism (54) has to allow for opening of the hatch (50). Hence, an alternate method of opening the hatch (50) is provided which is achieved with the help of the shear pin (88), shown in figure 22. The shear pin (88) is provided between the latch (58) and the latch bracket (114). The shear pin (88) is defined by a head portion (88a) and an elongate portion (88b).The shear pin (88) is typically hollow along the length of the shear pin (88). The shear pin (88) is provided with notches (128a and 128b) on the outer surface of the elongate portion (88b) of the shear pin (88). The diameter of the notches (128a and 128b) is typically in the range of 11 mm to 12 mm.

Figure 23 illustrates the transfer a shear force to the shear pin (88) in the event of failure of the hydraulic system (118) in order to shear the shear pin (88) about the notches (128a and 128b). When a missile is fired in the event of failure of the hydraulic system (1 18), the hatch (50) remains in closed condition. However, the hatch (50) is designed to withstand a static breaking load or force (F), typically in the range of 7,000 kg to 10, 000 kg or an equivalent force of 68,670 N to 98,1000 N, caused by the fired missile in the upward direction. The load (F) is applied to the center of the hatch (50), as shown in figure 23. A reaction (F_r) of the load (F) acts on the latch (58) in a direction opposite to the load (F) which is in the downwards direction, that is, F_r = - F. As the connecting pins 82a, 82b, 82c and 82d are linearly aligned, the reaction force (F_r) on the latch (58) creates a force (Fl) along the connecting pins 82d, 82c, 82b and 82a. The force (Fl) is transferred to the hatch (50) while no force is transferred to the locking actuator (96) along the link (86a) and the coupling element (11). The force (F_r) acting on the latch (58) further creates a force Fx on the shear pin (88) and the force Fl acting on the hatch (50) creates a force Fy on the shear pin (88). The force Fx and the force Fy creates a resultant force R_xy. The resultant force R_xy creates a shearing force on the shear pin (88) which causes shearing of the shear pin (88) along the notches (128a and 128b). The shearing of the shear pin (88) disengages the hook formation (94) of the latch (58) form the flange (98) of the top support structure (60) and hence unlocks the hatch (50) and allows the missile to be fired from the missile launching system.

Figure 24 illustrates the hatch (50) in accordance with this invention, in open position. Figure 25 is a sectional view of the hatch mechanism actuator (76) along line AA in Figure 24. The hatch (50) is provided to cover the openings (15) provided in the top plate (18) provided above the compartments of the truss framework (10)' and a pivoting means lying wholly outside the TSS (60), for pivoting the hatch (50) with respect to the opening (15) of the TSS (60). The pivoting means comprises a fixed element (68) secured to the top plate (18) and a stepped spline shaft (64). The fixed element (68) is provided with a plurality of splines and an angularly displaceable element (66) secured to the hatch (50). The angularly displaceable element (66) is also provided with a plurality of splines. The fixed element (68) and the angularly displaceable element (66) are provided along one side of the hatch (50). The fixed element (68) and the angularly displaceable element (66) define a hinge (62). The stepped spline shaft (64) is provided with a plurality of splines, complementary to the splines of the fixed element (68) and the angular displaceable element (66). The stepped spline shaft (64) has a reciprocating motion which is actuated with the help of a hydraulic system (118). The reciprocating motion of the stepped spline shaft (64) enables in opening and closing the hatch (50). A cap plate (74) is provided as a protective covering to the pivoting means is also shown in the figure 25. The angularly displaceable element (66) can be displaceable over an angle greater than 95° and hence causes the hatch (50) to be displaced by 95°. Figure 26 illustrates the plan view of the hatch (50). The hatch locking mechanism (54) and the hatch mechanism actuator (76) are connected to the hydraulic system (118) by means of a connecting pipe (78) and rotary joint (80) as shown in figure 27. The hydraulic system (1 18) is adapted to be actuated on receive signals to lock or unlock the latch (58), as shown in figure 28 and figure 29 respectively.

TESTS CONDUCTED

Initial trials and tests show that the shock and vibration absorbing means of the present invention is adapted to absorb and dampen moderate to high intensity shocks and vibrations and isolate these shocks and vibrations thereby considerably mitigating any potential damage that may have otherwise been caused to the ensconced missile and its delicate structures.

Several tests were performed on the hatch locking mechanism to test the mechanism for static operational load, maximum load, endurance and dynamic load. The details of the tests on the hatch locking mechanism are as follows:

1. Static test for operational load:

A load of 7,000 kg was applied at the center of the hatch and released after sometime. The hatch locking mechanism worked satisfactorily after the test and met all design and functional requirements. 2. Static test for maximum load:

The shear pin was replaced by a pin of higher strength and a load of 10,000 kg was applied at the center of the hatch and released after sometime. After the test the hatch locking mechanism worked satisfactorily and met all design and functional requirements.

3. Endurance test:

A load of 7,000 kg was applied at the center of the hatch and released continuously. This loading and unloading was repeated for 120 cycles. After the test, the hatch locking mechanism worked satisfactorily and met all design and functional requirements.

4. Dynamic test:

The aim of the dynamic test is to study the response of locking mechanism to shock and vibration. Shock and vibration conditions are simulated by impact through a dropping mass. A dummy mass (50Kg, lOOKg, and 150Kg) was dropped freely from varying heights of 0.224 meter, 0.896 meter, 2.016 meter and 3.584 meter on the hatch. During these tests the locking mechanism remained closed. After the test, the mechanism worked satisfactorily and was found to meet all design and functional requirements. TECHNICAL ADVANTAGES AND ECONOMIC SIGNIFICANCE

The product as described herein above offers several advancements over similar products disclosed in the prior art. The operation of the vertical missile launcher of the present invention is simple and reliable. The vertical missile launcher provides for better shock absorption capacity. The use of the hatch locking mechanism helps in increasing the life of the missile launching system. The hydraulically operated hatch locking mechanism and the hatch opening and closing mechanism help in reducing the operational and the maintenance cost of the vertical missile launcher. The hatch locking and unlocking mechanism for a vertical missile launcher of the present invention helps in reducing maintenance of the missile launching system. The hatch locking mechanism helps in facilitating the opening of hatch during emergency launching.

Claims

1. A hatch locking and unlocking mechanism for a vertical ship launcher for storing and launching a plurality of missiles,Qsaid launcher comprising: a. a truss framework having an operatively top end and an operatively bottom end and defined by vertical members, transverse members, and diagonal members to provide a support structure fitted within a barbette of a ship; b. a plurality of compartments defined within said truss framework;

c. a hatch for each of said compartments at the operative top end, said hatch provided on a top plate of the compartment;

d. a flange plate disposed within each of said compartment and adapted to suspend a canister;

f. a swivelable latch having a hook formation, said latch adapted to be swiveled form a disengaged configuration to an engaged configuration in which said hook formation engage a flange of said top support structure;

iii. the fixed and the angular displaceable elements together defining a hinge;

v. a primary hydraulic actuator to actuate the stepped spline shaft for opening and closing the hatch element.

2. The vertical ship launcher as claimed in claim 1, wherein each compartment has a substantial square cross-section.

3. The vertical ship launcher as claimed in claim 1 , wherein each canister has a substantial circular cross-section.

4. The vertical ship launcher as claimed in claim 1, wherein said truss framework is a space frame.

5. The vertical ship launcher as claimed in claim 1 , further comprising a baffle means for directing gases created at the time of launch from one canister to another canister in another compartment.

6. The vertical ship launcher as claimed in claim 1, wherein said first shock absorbing system is a top longitudinal shock absorbing system adapted to sustain longitudinal shocks to said canister.

7. The vertical ship launcher as claimed in claim 1, wherein said first longitudinal shock absorbing system is provided between said flange plate and said top plate of said truss framework and is defined by: - a plurality of downward shock absorbing elements comprising a piston pin with a stub which abuts said flange plate interspersed radially around said canister; and

- a plurality of upward shock absorbing elements comprising a cylinder secured to the operative upper face of the flange plate by a bolt and nut assembly interspersed radially around said canister.

8. The vertical ship launcher as claimed in claim 1, wherein said second lateral shock absorbing system is defined by a ring suspended by rods at their lower ends and placed circumferentially around said ring, said suspended rods fitted by lever arms projecting out of said truss framework at an operative upper end of said rod and substantially at the centre of said rod.

9. The vertical ship launcher as claimed in claim 1, wherein said third shock absorbing system is a bottom shock absorbing system provided underneath said missile to compensate for shocks in all directions.

10. The vertical ship launcher as claimed in claim 1, wherein said flange plate encircling said canister, disposed radially outwards from outer surface of said canister and located substantially at the top of said canister to support said canister in said compartment.

1 1. The vertical ship launcher as claimed in claim 5, wherein said baffle means is a substantially 'L' -shaped plate fixed between said flange plate and said cover adapted to prevent transfer of exhaust gases after missile is launched from one compartment to adjacent compartments.

12. The vertical ship launcher as claimed in claim 1, wherein said third shock absorbing system includes said means to electrically connect said canister to a power source.

13. The vertical ship launcher as claimed in claim 1, wherein said electrical connector means comprises a female portion adapted to engage with male portion located underneath said canister to provide the firing and electrical signals and connections.

14. The vertical ship launcher as claimed in claim 1, wherein each of said compartments placed at the corners of said truss framework has a flexible, substantially 'U'-shaped multilayer laminate sealing element interposed between top edge of said corner compartment and said vertical member of said truss framework adapted to prevent entry of gases and plume flame into said compartment after missile is launched and provide resilience and support to said canister with respect to said truss framework.

15. The vertical ship launcher as claimed in claim 14, wherein said substantially 'U'-shaped multilayer laminate sealing element comprises:

- a first layer of heat resistant material;

- a third layer of Kevlar fibre underneath said second layer; and

- a fourth layer of neoprene rubber underneath said third layer.

16. The vertical ship launcher as claimed in claim 1, wherein said locking actuator is provided with at least one disc spring.

17. The vertical ship launcher as claimed in claim 1, wherein said shear pin is hollow.

18. The vertical ship launcher as claimed in claim 1, wherein said shear pin is provided with at least one notch.

19. The vertical ship launcher as claimed in claim 1, wherein said coupling pin, said first connecting pin, said second connecting pin, said third connecting pin and said fourth connecting pin are solid.

20. The vertical ship launcher as claimed in claim 1, wherein said link connecting bracket cooperates with the hatch.

21. The vertical ship launcher as claimed in claim 1, wherein said first connecting pin, said second connecting pin, said third connecting pin and said fourth connecting pin are linearly aligned in the engaged configuration of the latch.

22. The vertical ship launcher as claimed in claim 1, wherein the hydraulic operation of the locking actuator is achieved with the help of a hydraulic system, said hydraulic system comprising at least one flow control valve, at least one shut off valve, at least one shuttle valve and at least one counter balance valve.

23. The vertical ship launcher as claimed in claim 22, wherein said hydraulic system is operated by oil.

24. The vertical ship launcher as claimed in claim 1, wherein said hatch cooperate with the top support structure through a seal, said seal is retained in position by means of a retainer plate.

25. The vertical ship launcher as claimed in claim 1, wherein said fixed and angular displaceable elements are provided along the edge of the hatch element.

26. The vertical ship launcher as claimed in claim 1, wherein said hatch has rectangular shape.

27. The vertical ship launcher as claimed in claim 26, wherein said fixed and angular displaceable elements are provided along one side of the hatch element.

28. The vertical ship launcher as claimed in claim 1, wherein said hatch has a locking means to lock the hatch element to the side wall of the compartment

29. The vertical ship launcher as claimed in claim 28, wherein said locking means comprises a secondary hydraulic actuator, link and a latch.

30. The vertical ship launcher as claimed in claim 29, wherein said secondary hydraulic actuator is connected to primary hydraulic actuator by means of a connecting pipe and a rotary joint characterized in that the primary hydraulic actuator is adapted to be actuated only when the latch is in an operative unlocked position.

31. The vertical ship launcher as claimed in claim 1 , wherein said hatch includes a cap plate for capping the pivoting means.

32. The vertical ship launcher as claimed in claim 1, wherein said angular displaceable element can be displaceable over an angle greater than 90°.

33. The vertical ship launcher as claimed in claim 1, further comprising a means to electrically connect said canister to a power source at its operatively bottom end.