Disclosed is a jet vane thrust vector control (JV-TVC) system. A general system has many problems in design techniques considering actual operation environments, and does not have reliability in component assembly design. The JV-TVC system improves thrust vector control and high angle of attack mane
Disclosed is a jet vane thrust vector control (JV-TVC) system. A general system has many problems in design techniques considering actual operation environments, and does not have reliability in component assembly design. The JV-TVC system improves thrust vector control and high angle of attack maneuvering performance of a missile by allowing rotational angles of jet vanes to maximum ��30��, precisely controls the thrust vector of the missile by preventing damages of components for the designated flight time of the missile, and improves precision and reliability in the assembly process by modularization.
대표청구항▼
What is claimed is: 1. A jet vane thrust vector control system, comprising: a rocket motor having a motor case, and a case flange unit protruded from the rear end of the motor case in a ring shape; a nozzle assembly including a nozzle body having a flange unit assembled to the case flange unit and
What is claimed is: 1. A jet vane thrust vector control system, comprising: a rocket motor having a motor case, and a case flange unit protruded from the rear end of the motor case in a ring shape; a nozzle assembly including a nozzle body having a flange unit assembled to the case flange unit and a cylindrical unit extended from the flange unit in the backward direction, and a nozzle liner assembled to the inner circumferences of the cylindrical unit and the flange unit and extended longer than the cylindrical unit in the backward direction; a skin including a skin body having its front end inner circumference closely adhered to the outer circumference of the case flange unit, and being fixed by fastening a screw passing through a main wall to the case flange unit, and a mounting strip formed on the inner circumference of the skin body as a ring-shaped plate; an actuator assembly including an actuator body fixed to the front surface of the mounting strip of the skin, and a piston rod protruded from the actuator body in the backward direction and linearly reciprocated in the forward/backward direction; a shroud assembly including a cylindrical shroud body disposed at the rear end of the cylindrical body of the nozzle body, a shroud liner assembled to the inner circumference of the shroud body, and a plurality of bosses protruded from the outer circumference of the shroud body; a jet vane assembly including a jet vane shaft rotationally supported by the bosses, and a jet vane assembled to the inside end of the jet vane shaft; a jet vane support unit including a bearing housing inserted into the boss unit, a bearing inserted into the bearing housing, for supporting the jet vane shaft, and a jet vane shaft mounting strip for supporting the outside end of the jet vane shaft; and a crank assembly engaged with the piston rod of the actuator assembly, for rotating the jet vane shaft and the jet vane in the right/left direction. 2. The system of claim 1, wherein the inner circumference of the front end of the shroud body is closely adhered to the outer circumference of the cylindrical unit of the nozzle assembly and hermetically sealed by an O-ring, and the front section of the front end of the shroud liner maintains a predetermined interval from the cylindrical unit and the inner circumference thereof maintains a predetermined interval from the outer circumference of the rear end of the nozzle liner, for forming complicated paths for preventing inflow of flame gas. 3. The system of claim 2, wherein a hooking jaw on which the outer circumference of the front end of the shroud liner is hooked is formed at the front end of the shroud body. 4. The system of claim 1, wherein the bosses of the shroud body and the jet vane shaft mounting strip are fixed to the mounting strip of the skin by fixing screws passing through the actuator body and the mounting strip. 5. The system of claim 1, wherein the jet vane is formed in a rectangular shape having inner and outer circumferences parallel to the center axis of the skin body and having a streamlined section, and a plane unit being parallel to the Center axis of the skin body to correspond to the outer circumference of the jet vane and contacting the circumference on the basis of the center axis is formed in the position of the inner circumference of the shroud liner corresponding to the bosses. 6. The system of claim 5, wherein the jet vane shaft comprises a support unit supported by the bosses, a jet vane assembly unit incorporated with the inside end of the support unit, the jet vane being assembled to the jet vane assembly unit, and an engaged unit incorporated with the outside end of the support unit and engaged with the crank assembly. 7. The system of claim 6, wherein a vane shaft fastening groove is formed on the root periphery of the jet vane, the jet vane assembly unit is extended from the end of the inner circumference of the support unit to both sides to make a right angle with the axial line of the jet vane shaft, and a vane shaft through hole is extended from the center of the inside surface thereof on the same axis as the jet vane shaft, and fastened to the vane shaft fastening groove of the jet vane. 8. The system of any one of claims 5 to 7, wherein a heat shield plate is inserted between the jet vane assembly unit and the jet vane. 9. The system of claim 8, wherein a assembly groove into which the root periphery of the jet vane is inserted is formed on the assembly part of the inside surface of the heat shield plate with the jet vane to have the same streamlined section as the section of the jet vane. 10. The system of either claim 1 or 6, wherein the crank assembly comprises a crank arm having its one end fixed to the engaged unit of the jet vane shaft, and a connection pin for relatively rotatably connecting the other end of the crank arm to the front end of the piston rod of the actuator.
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이 특허에 인용된 특허 (6)
Reynolds Hugh M. (San Jose CA) Kawabata Curt M. (North Ogden UT), Advanced composite polar boss.
Berdoyes, Michel; Dumortier, Andr?; Biz, Philippe; Hervio, Antoine, Rocket engine nozzle that is steerable by means of a moving diverging portion on a cardan mount.
Dombrowski Daniel C. (Elkton MD) Frey Thomas J. (Wilmington DE) Nevrincean Andrew G. (Oxford PA), Solid propellant dual pulse rocket motor loaded case and ignition system and method of manufacture.
Isaac, Clinton R.; Naramore, Adam; Thrasher, Talbot P.; Lajczok, Michael D.; Bellotte, Joseph, Space storable, thrust-vectorable rocket motor nozzle and related methods.
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