초록 ▼

The present invention relates to launching system, more particularly relates to mobile launching system for missiles. The mobile missile launch system comprising a vehicle (14) having a chassis structure adapted to carry the launch system; a mounting frame (16) comprising predetermined truss framewo

The present invention relates to launching system, more particularly relates to mobile launching system for missiles. The mobile missile launch system comprising a vehicle (14) having a chassis structure adapted to carry the launch system; a mounting frame (16) comprising predetermined truss framework mounted onto the chassis structure; plurality of sliding mechanisms mounted at rear end of the mounting frame (16); 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.

대표청구항 ▼

1. A mobile missile launch system, said system comprising: a vehicle having a chassis structure adapted to carry the launch system;a mounting frame comprising predetermined truss framework mounted onto the chassis structure;a plurality of sliding mechanisms mounted at a rear end of the mounting fram

1. A mobile missile launch system, said system comprising: a vehicle having a chassis structure adapted to carry the launch system;a mounting frame comprising predetermined truss framework mounted onto the chassis structure;a plurality of sliding mechanisms mounted at a rear end of the mounting frame comprising: a beam comprising a plurality of sliders on one surface of the beam and hinged to the mounting frame on another surface of the beam, a plurality of saddles mounted onto the beam and adapted to slide on the sliders, a tube having openings and being fixed to at least one of the plurality of saddles at one end of the tube and an end cap at an other end of the tube, and an actuator connected to the tube through a piston and a rod and hinged at one end on the beam, wherein actuation of said piston contacts the rod with end cap of the tube to slide the saddles on the sliders;a plurality of canisters mounted onto said beam and a plurality of missiles ensconced within the canisters;a plurality of containers enclosing said canisters and connected to the saddles for linear movement;a plurality of resting units abutting to rear ends of the canisters and adapted to move linearly to transfer reaction forces from said missiles to the ground;communication means placed within the launch system to communicate with a remotely located unit; andat least one locking mechanism and at least one holding device mounted at a front end of each container to arrest linear motion of the container during mobility in a horizontal position. 2. The system as claimed in claim 1, wherein the truss frame work of the mounting frame is configured as front frame work and rear truss frame work for varying loads of mountings on it; wherein the front is configured for mounting actuators of hydraulic actuator for articulation by piston movement, fire control section and power supply cabin, and the rear truss frame work is configured for mounting the beam and actuators for articulation. 3. The system as claimed in claim 1, wherein said system is fitted with a thermal conditioning unit to regulate temperature inside the canister and a plurality of accumulators connecting to actuators and adapted to store for articulation of the beam. 4. The system as claimed in claim 1, wherein the holding device comprises: a platform of predetermined shape having at least one bracket consisting of one or more apertures and at least one hole at centre;a detachable stub element integrated with the missile below tip surface and mounted inside the bracket of the platform, said stub comprising one or more stub holes to accommodate pins provided at a preformed shaped element and has at least one protruding element at centre, wherein said protruding element is mounted inside the hole of platform;a plurality of hydraulic cylinders having a shaft and mounted at predefined positions onto the platform on either side of the bracket; anda plurality of housing elements fitted to the preformed shaped element;wherein the shaft of each hydraulic cylinder is fitted with preformed shape of bearing. 5. The system as claimed in the claim 4, wherein the shaft of cylinder, the bearings, the housing element and the preformed shaped element form a ball and socket mechanism. 6. The system as claimed in the claim 4, wherein pins pass through the apertures in the bracket to get inserted in the holes of the stub element. 7. The system as claimed in claim 1, wherein the locking mechanism to arrest linear motion of the missile comprises: a rocker assembly of predetermined shape pivoted at a bracket of the system, said rocker assembly comprising an actuating segment at a lower side and a loading segment at upper side and a rocker segment disposed in between the actuating segment and the loading segment;an actuator assembly connected to a lower end of platform of the system for applying load to the rocker assembly; andloading elements engaged at an operative top end of the rocker assembly to arrest linear motion of the missile. 8. The system as claimed in claim 7, wherein the rocker assembly is tapered away from the rocker segment and leads to the actuating segment at said lower side and the loading segment at said upper side. 9. The system as claimed in claim 7, wherein said rocker assembly is pivoted with a medially placed pivoting arrangement; wherein the pivoting arrangement and the bracket have matching holes to superimpose onto each other; and the pivoting arrangement is secured by inserting a pin and circlip through the matching holes. 10. The system as claimed in the claim 7, wherein the actuator assembly comprises a plurality of pre-tensioned springs placed between arms of a clevis and a rear wall, and a hydraulic actuator having a piston with a boss at its operative end and the clevis with a plurality of the arms aligned with the piston. 11. The system as claimed in the claim 10, wherein the springs are Belleville springs and said piston is placed symmetrically in between the springs. 12. The system as claimed in the claim 7, wherein the loading elements comprises a loading socket and a loading pin aligned in a horizontal linear axis configuration with a nose cap projection for applying a point load onto the missile. 13. A method of launching a missile using the mobile missile launch system of claim 1, said method comprising: actuating the beam, by a further actuator, to move from a horizontal position to a vertical position;actuating the actuator of the sliding mechanism by releasing pressure, wherein said releasing of the pressure allows at least one of said resting units to touch ground; andlaunching of the missile using control switches, wherein thrust forces generated by the launch of the missile is transferred to the ground through said at least one resting unit. 14. The method as claimed in claim 13, wherein said method comprises retracting the piston upwards to release the at least one resting unit from the ground after launching.