A MOBILE MISSILE LAUNCH SYSTEM AND METHOD THEREOF |
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申请号 | EP10707675.4 | 申请日 | 2010-01-11 | 公开(公告)号 | EP2414766B1 | 公开(公告)日 | 2013-10-09 |
申请人 | Director General, Defence Research & Development Organisation; | 发明人 | GURUPRASAD, Siddalingappa; KATTI, Shreedhar, Aravind; GOUD, Alasani Prasad; WAGHMARE, Vikas, Narayan; KUMAR, Sanjay; GUPTA, Atul; KHIRE, Ravindra, Sudhakar; SANTOSH, Tushar, Kant; GAUTAM, Bimal; RAM, Paras; | ||||
摘要 | |||||||
权利要求 | |||||||
说明书全文 | The present invention relates to launching system, more particularly relates to mobile launching system for missiles. Terrestrial Missile Launchers are launching mechanisms and platforms wherein missiles are fired from a fixed base. For this purposes, the missiles need to be transported from a warehouse or a silo to the launching base and effectively readied before deployment. In today's warfare, with increased enemy surveillance, such fixed launching bases can easily be remotely profiled, located and targeted by an enemy, thus fracturing an important aspect of attack. Its immobility is one of its biggest hindrances. Further, transportation of missiles from a silo to the launching base increases vulnerability to the enemy and provides them with an opportunity window to carry out destruction en-route. Destruction of missiles while being transported renders the launching platform useless and also causes a huge loss to the defenses. As technology progresses, with increases surveillance, reconnaissance, targeting, offensive, and defensive systems in place, modern day warfare has progressed from static, open-faced warfare to dynamic, stealth, guerilla warfare; the underlying idea being to provide least possible awareness to the enemy about operating or firing locations. This need introduces the need for vehicles and mobile units, some of which may be even remotely monitored. Typically, an Armoured Fighting Vehicle (AFV) is a terrestrial vehicle especially built and adapted for the purposes of combat and warfare. An AFV is protected with armour and armed with weapons for action on the battlefield. Alternatively known as military land vehicles, the AFVs are typically a family of trucks and tanks suited for action within a battlefield and adapted to traverse a variety of terrain from hard concrete and tar to sand to semi-soft ground to swampy marshy land with ease. However, they cannot be used for deploying and launching long range missiles. Smaller weapon systems can easily be fitted onto such vehicles to achieve short range target compatibility. Combat land vehicles with rocket launchers are disclosed in There is a need for improvement in missile carrying vehicles; to deploy missiles from said vehicle, to make it terrestrially mobile in order to skillfully improve ground coverage in war zones. There is also a need for a fast articulating launcher assembly which increases the military's ability to operate with agility without compromising on ground movement and thus decreasing the threat of being noticed. Such problems can be solved with the mobile missile launch system having the features of independent claim I, as well as with the method of launching a missile from said mobile missile launch system. The principal object of the invention is to provide a mobile missile system for carrying the missiles and firing said missiles from said mobile system itself. Another object of this invention is to provide a mobile missile system with a fast articulating and actuating system for readying the missiles for firing from said mobile system itself. Still another object of this invention is to provide a mobile missile system with a convenient missile deploying interface and capability. Yet another object of this invention is to provide a mobile missile system having an accurate missile deploying capability. Still another object of this invention is to provide a quick moving and agile mobile missile system. An additional object of this invention is to provide a mobile missile system which does not require an external power source either for its movement or for its missile deploying capability. Accordingly, the present invention provides for a mobile missile launch system (100), said system comprising: a vehicle (14) having a chassis structure (12) adapted to carry the launch system; a mounting frame (16) comprising predetermined truss framework mounted onto the chassis structure (12); plurality of sliding mechanisms mounted at rear end (19) of the mounting frame (16) comprising; a beam (22) comprising plurality of sliders (26) on one surface and is hinged to the mounting frame (16) on other surface, plurality of saddles (32, 34) mounted onto the beam (22) and are adapted to slide on the sliders (26), a tube (35) having an opening fixed to the saddle (32) at one end and an end cap (39) at other end, an actuator (31) connected to the tube (35) through a piston (29) and rod (37) and is hinged at one end on the beam (22), wherein said piston (29) actuation contacts the rod (37) with end cap (39) of the tube (35) to slide saddles (32, 34) on the sliders (26); plurality of canisters (43) mounted onto said beam (22) and plurality of missiles (II) ensconced within the canisters (43); plurality of containers (42) enclosing said canisters (43) and are connected to the saddles (32, 34) for linear movement; plurality of resting units (27) abutting to rear end of the canisters (43) and are adapted to move linearly to transfer reaction forces from said missiles (11) to ground (51); communication means/mast (56) placed within the launch system to communicate with remotely located unit; and at least one locking mechanism and at least one holding device mounted at front end of each container (42) to arrest linear motion of the container (42) during mobility in horizontal position, also provides for a method for holding a missile (11) securely comprising act of actuating hydraulic cylinders (8) for applying pressure onto housing elements (17) for moving protruding pins (13) of the housing elements (17) for inserting into stub holes (6) of the missile (11) for holding the missile (11) securely, wherein a detachable stub element (2) is integrated with the missile (11) below tip surface and is mounted inside the bracket (3) of the platform (20), and said stub element (2) comprising one or more stub holes (6) to accommodate the pins (13) provided at preformed shaped element (17a) and has at least one protruding element (4) at centre, wherein said protruding element (4) is mounted inside the hole (5) of platform (20), also provides for a method for arresting linear motion of missile (11) comprising an act of activating actuator assembly (200) by removal of hydraulic fluid, causing pre-tensioned springs (200a) to act against arms (200b) of clevis (200d)) due to the removal of hydraulic fluid, wherein piston (200e) is thrust forward onto said clevis (200d) and forwardly extended stub (200g), applying load on rocker assembly (101b) by the extended stub (200g) which is transferred as point load onto loading elements and nose cap projection (90) at operative top end of rocker assembly (101) to arrest linear motion of the missile (11), wherein the rocker assembly (101) is pivoted at bracket of the system comprises an actuating segment (101a) at lower side and a loading segment (101c) at upper side and a rocker segment (101b) disposed in between the actuating segment (101a) and the loading segment (101c), and also provides for a method of launching a missile (11), said method comprising acts of; actuating beam (22) by actuator (24) to move from its horizontal position to vertical position; actuating actuator (31) by releasing pressure, wherein said releasing of the pressure allows resting unit (27) to touch ground (51); and launching of the missile (11) using control switches, wherein thrust forces generated by the launch of the missile (11) is transferred to the ground (51) through resting unit (27). The invention will now be described in accordance with the accompanying drawings, in which:
The present invention is in relation to a mobile missile launch system (100), said system comprising: a vehicle (14) having a chassis structure (12) adapted to carry the launch system; a mounting frame (16) comprising predetermined truss framework mounted onto the chassis structure (12); plurality of sliding mechanisms mounted at rear end (19) of the mounting frame (16) comprising; a beam (22) comprising plurality of sliders (26) on one surface and is hinged to the mounting frame (16) on other surface, plurality of saddles (32, 34) mounted onto the beam (22) and are adapted to slide on the sliders (26), a tube (35) having an opening fixed to the saddle (32) at one end and an end cap (39) at other end, an actuator (31) connected to the tube (35) through a piston (29) and rod (37) and is hinged at one end on the beam (22), wherein said piston (29) actuation contacts the rod (37) with end cap (39) of the tube (35) to slide saddles (32, 34) on the sliders (26); plurality of canisters (43) mounted onto said beam (22) and plurality of missiles (11) ensconced within the canisters (43); plurality of containers (42) enclosing said canisters (43) and are connected to the saddles (32, 34) for linear movement; plurality of resting units (27) abutting to rear end of the canisters (43) and are adapted to move linearly to transfer reaction forces from said missiles (11) to ground (51); communication means (56) placed within the launch system to communicate with remotely located unit; and at least one locking mechanism and at least one holding device mounted at front end of each container (42) to arrest linear motion of the container (42) during mobility in horizontal position. In still another embodiment of the present invention the truss frame work of mounting frame (16) is configured as front frame work (18) and rear truss frame work (19) for varying loads of mountings on it. In yet another embodiment of the present invention the front (18) and rear truss frame work (19) are configured for mounting of actuators for articulation, fire control section and power supply cabin (52) and beam (22), actuators for articulation respectively. In yet another embodiment of the present invention said system is fitted with thermal conditioning unit (38) to regulate temperature inside the canister (43). In yet another embodiment of the present invention said system is fitted with plurality of accumulators (36) connecting to actuators and are adapted to store for articulation of the beam (22). In yet another embodiment of the present invention the actuator (31) is preferably a hydraulic actuator for actuating piston (29) movement. In yet another embodiment of the present invention the holding device for container (42) comprising platform (20) of predermined shape having at least one bracket (3) consisting of one or more apertures (7) and at least one hole (5) at centre; detachable stub element (2) is integrated with the missile (11) below tip surface and is mounted inside the bracket (3) of the platform (20), said stub (2) comprising one or more stub holes (6) to accommodate pins (13) provided at preformed shaped element and has at least one protruding element (4) at centre, wherein said protruding element (4) is mounted inside the hole (5) of platform (20); plurality of hydraulic cylinders (8) having shaft (9) and are mounted at predefined positions onto the platform (20) on either side of the bracket (3); and plurality of housing elements (17) fitted to preformed shaped element (17a); and the shaft (9) of each hydraulic cylinder (8) is fitted with preformed shape of bearing (15) as shown in In yet another embodiment of the present invention the shaft (9) of cylinder, the bearings (15), the housing element (17) and the preformed shaped element (17a) form a ball and socket mechanism. In yet another embodiment of the present invention the pins (13) pass through the apertures (7) in the bracket (3) to get inserted in the holes (6) of the stub element (2). The present disclosure also contains a method for holding a missile (11) securely comprising act of actuating hydraulic cylinders (8) for applying pressure onto housing elements (17) for moving protruding pins (13) of the housing elements (17) for inserting into stub holes (6) of the missile (11) for holding the missile (11) securely, wherein a detachable stub element (2) is integrated with the missile (11) below tip surface and is mounted inside the bracket (3) of the platform (20), and said stub element (2) comprising one or more stub holes (6) to accommodate the pins (13) provided at preformed shaped element (17a) and has at least one protruding element (4) at centre, wherein said protruding element (4) is mounted inside the hole (5) of platform (20). In yet another embodiment of the present invention the locking mechanism to arrest linear motion of the missile (11) comprising a rocker assembly (101) of predetermined shape pivoted at bracket of the system, said rocker assembly (101) comprises an actuating segment (101a) at lower side and a loading segment (101c) at upper side and a rocker segment (101b) disposed in between the actuating segment (101a) and the loading segment (101c); an actuator assembly (200) connected to lower end of platform (70) of the system for applying load to the rocker assembly (101); and loading elements engaged at operative top end of the rocker assembly (101) to arrest linear motion of the missile (11) as shown in In yet another embodiment of the present invention the rocker assembly (101) is tapered away from the rocker segment (101b) and leads to the actuating segment (101a) at lower side and a the loading segment (101c) at upper side. In yet another embodiment of the present invention a medially placed pivoting arrangement enables the rocker assembly (101) to pivot about. In yet another embodiment of the present invention the pivoting arrangement and the bracket have matching holes to superimpose onto each other. In yet another embodiment of the present invention the pivoting arrangement is secured by inserting a pin and circlip through matching holes. In yet another embodiment of the present invention the actuator assembly (200) comprises plurality of pre-tensioned springs (200a) and a hydraulic actuator having a piston (200e) with a boss (200f) at its operative end. In yet another embodiment of the present invention the actuator assembly (200) comprises a clevis (200d) with plurality of arms (200b) aligned with the piston (200e). In yet another embodiment of the present invention the springs (200a) are placed between arms (200b) of the clevis (200d) and rear wall (200c) of the actuator assembly (200). In yet another embodiment of the present invention the piston (200e) is placed symmetrically in between the springs (200a). In yet another embodiment of the present invention the springs (200a) are preferably Belleville springs. In yet another embodiment of the present invention the loading elements comprises a loading socket (80) and a loading pin (90a) which is aligned in horizontal linear axis configuration with nose cap projection (90) of the missile (11). The present disclosure also contains a method for arresting linear motion of missile (11) comprising an act of activating actuator assembly (200) by removal of hydraulic fluid, causing pre-tensioned springs (200a) to act against arms (200b)) of clevis (200d) due to the removal of hydraulic fluid, wherein piston (200e) is thrust forward onto said clevis (200d) and forwardly extended stub (200g), applying load on rocker assembly (101) by the extended stub (200g) which is transferred as point load onto loading elements and nose cap projection (90) at operative top end of rocker assembly (101) to arrest linear motion of the missile (11), wherein the rocker assembly (101) is pivoted at bracket of the system comprises an actuating segment (101a) at lower side and a loading segment (101c) at upper side and a rocker segment (101b) disposed in between the actuating segment (101a) and the loading segment (101c). In an example, the load is applied onto the actuator segment (101a) by removing fluid from hydraulic actuator of the actuator assembly (200). In another example, removing the fluid makes pre-tensioned springs (200a) to exert pressure to move clevis (200d) in forward direction. In another example, the loading elements includes a loading socket (80) and a loading pin (90a) for applying point load on to the nose cap projection (90). The present invention is in relation to a method of launching a missile (11), said method comprising acts of; actuating beam (22) by actuator (24) to move from its horizontal position to vertical position; actuating actuator (31) by releasing pressure, wherein said releasing of the pressure allows resting unit (27) to touch ground; and launching of the missile (11) using control switches, wherein thrust forces generated by the launch of the missile is transferred to the ground (51) thorough the resting unit (27). In yet another embodiment of the present invention said method comprises act of retracting piston (29) upwards to release the ground resting unit (27) from the ground (51) after launching. Firstly, the launch beam (22) hydraulically actuates from its inoperative horizontal resting state to its operative vertical state i.e. to achieve the position as shown in In a typical cold launch scenario, a gas generator operates. This removes the missile (II) from the canister (43) until the shear pin [used for locking missile (11) to canister] breaks. Typically, the velocity achieved during this operation is about 20 m/s to 50 m/s. Further, a low thrust booster operates. This enables the missile (II) to eject out of the canister (43) and container (42), typically up to a height of 200 m to 250 m above the launching site. At this height, on-board computers operate in order to pitch the missile (11) in its operative target direction. Still further, a high thrust booster ignites in order to aid the missile (11) to traverse the prefed distance to reach the target. |