A folding lug structure for a missile

Abstract

A folding lug structure for a missile, wherein an installation groove for vertically placing the lug is provided inside the outer shell, the lug is a standard lug, a rotating shaft is provided under the lug pedestal, and a shaft protrusion and a small stopper are provided on the rotating shaft; rotating shaft installation through holes are symmetrically arranged on both sides of the installation groove, and an arc-shaped groove for placing the shaft protrusion is provided inside one of the rotating shaft installation through holes; a fixed stopper is provided on the upper part of the inner side of the outer shell at the rear end of the rotating shaft, and a through hole for installing a driving power source and a limiter is opened on the installation groove on the side where the arc-shaped groove is provided, and the through hole communicates with the arc-shaped groove to form an air guide chamber; the limiter is fixedly connected to the driving power source, the end of the limiter is fixedly connected to a spring, and an exhaust port for releasing high-pressure gas is provided on the arc-shaped groove. The invention effectively reduces the air resistance, is beneficial to the high-speed flight of the missile, and the effective radar cross-sectional area is reduced, thereby improving the anti-radar performance; the lug structure is separated from the missile body, which is convenient for manufacturing.

Description

Technical Field

[0001] The present invention relates to the technical field of missile parts, and particularly to a folding lug structure for a missile. Background Art

[0002] Missile lugs are relatively common rack adapter components. Two longitudinally arranged lugs are provided on airborne missiles. The lugs are locked on the rack, and the missile will be ejected from the rack first during launch and then fly autonomously. Currently, missile lugs all adopt standard fixed lugs specified by the national military standard. However, after the missile is launched, the lugs are fixed to the missile, resulting in protrusions on the missile, increasing the missile resistance, thereby affecting the flight performance of the missile and shortening the missile range. At the same time, the protruding lugs will increase the radar cross-section and affect the stealth performance of the missile. To increase the missile range and reduce the radar reflection area, the lugs need to be retracted after the missile is launched. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a folding lug structure for a missile to solve the problems in the above background art.

[0004] The technical problem solved by the present invention is achieved by the following technical solutions:

[0005] A folding lug structure for a missile, comprising a lug, a rotating shaft, a fixed stop, a stopper, a spring, a driving power source and a housing. Among them, the housing is a semi-closed structure, and an installation groove for vertically placing the lug is provided inside the housing. The lug is a standard lug specified by the national standard. A rotating shaft is provided under the circular pedestal of the lug, and a shaft protrusion and a small stop are provided on the rotating shaft, and the three are fixedly installed by screws. Rotating shaft installation through holes are symmetrically provided on both sides of the installation groove for installing the rotating shaft of the lug, and an arc-shaped groove for placing the shaft protrusion is provided inside one of the rotating shaft installation through holes. A fixed stop is provided on the upper inner side of the housing at the rear end of the rotating shaft, and a through hole for installing the driving power source and the stopper is opened on the installation groove on the side where the arc-shaped groove is provided. The through hole communicates with the arc-shaped groove to form a gas guide chamber. The driving power source is used to generate high-pressure gas, and the existence of the gas guide chamber is used to change the airflow direction of the high-pressure gas. The high-pressure gas acts on the shaft protrusion to drive the rotating shaft to rotate. The stopper is fixedly connected to the driving power source, the end of the stopper is fixedly connected to the spring, and at the same time, an exhaust port for releasing the high-pressure gas is provided on the arc-shaped groove. The stopper and the fixed stop are used to restrict the other eight degrees of freedom of the rotating shaft except for rotating along the axis where the center of the rotating shaft is located. Thus, the lug is completely fixed to mount the missile.

[0006] In the present invention, the housing is surrounded by a left housing, a right housing and two middle housings.

[0007] In the present invention, the fixed stop is provided on the upper inner side of the middle housing at the rear end of the rotating shaft.

[0008] In the present invention, a sealing gasket is provided on the right outer shell.

[0009] In the present invention, the limiter is a square slider.

[0010] In the present invention, the through hole is a square through hole.

[0011] In the present invention, the driving power source is a gas generator.

[0012] In the specific implementation of the present invention, first, each component is processed and prepared as required. During assembly, first assemble and fix the small stop block, the rotating shaft, and the axon on the lifting lug. Then, install and fix the rotating shaft in the two rotating shaft installation through holes of the installation groove. Install and fix the stop block on the upper inner side of the middle outer shell at the rear end of the rotating shaft. Fix the left outer shell, the right outer shell, and the middle outer shell. Then, install the gas generator, the limiter, and the spring as an integral body, and install them into the reserved through hole. Use a slotted socket head cap screw to fix the sealing gasket to the right outer shell. Then, place the lifting lug vertically, so that the limiter extends out to lock the lifting lug, and the installation is completed.

[0013] During launch, the missile leaves the pylon, and the gas generator works to generate high-pressure gas to push the limiter to contract, so as to release the constraint on the lifting lug. At this time, the spring is in an energy storage state. After the limiter displaces a certain distance, the air guide chamber exposes the opening. Due to the existence of the air guide chamber, the airflow of the high-pressure gas changes from radial to transverse, and then acts on the axon along the pipeline. The axon is impacted and drives the rotating shaft to rotate counterclockwise along the arc-shaped groove. When the axon is about to contact the end of the opening of the air guide chamber, the high-pressure gas flows out from the exhaust hole, and the spring on the limiter releases, pushing the limiter to extend out of the middle outer shell. Blocked by the small stop block, the limiter can only stay at the end of the opening of the air guide chamber to prevent hindering the rotation of the lifting lug. When the axon completely contacts the end of the opening of the air guide chamber, the block of the small stop block on the limiter is released, and the limiter extends out of the through hole under the push of the spring, restricting the lifting lug to rebound clockwise. At this time, the rotating shaft stops rotating. Thus, the lifting lug is locked and the contraction is completed. The gas generator is used to change the direction of the high-pressure gas airflow through the existence of the air guide chamber to push the rotating shaft to rotate and perform contraction, realizing the locking of the lifting lug.

[0014] Advantageous effects: The locking method of the present invention is simple and reliable during work or contraction. After contraction, since there are no protrusions on the surface of the missile, the air resistance is reduced, the range is increased, which is beneficial to the high-speed flight of the missile, and the effective radar cross-sectional area is reduced, making it not easy to capture signals, effectively improving the anti-radar performance; the structure of the lifting lug is separated from the missile body, which is convenient for manufacturing. During use, only the whole needs to be installed in the reserved slot of the missile, which is convenient and saves manufacturing costs; at the same time, the gas generator is used as the power source for driving the contraction of the lifting lug, which is more reliable than a motor or a spring and has higher adaptability. Description of the Drawings

[0015] Figure 1 This is the front cross-sectional view of the folding lug structure in the working state in the preferred embodiment of the present invention.

[0016] Figure 2 This is the isometric view of the folding lug structure in the working state in the preferred embodiment of the present invention.

[0017] Figure 3 This is the front cross-sectional view of the folding lug structure in the folded state in the preferred embodiment of the present invention.

[0018] Figure 4 This is the front cross-sectional view of the folding lug structure in the folded state in the preferred embodiment of the present invention.

[0019] Figure 5 This is the connection schematic diagram of the small block, lug, rotating shaft, and shaft protrusion in the preferred embodiment of the present invention. Detailed implementation manners

[0020] In order to make the technical means, creative features, achieved purposes, and functions of the present invention easy to understand, the present invention will be further described below with reference to specific illustrations.

[0021] See, for example, Figures 1 to 5The folding ear structure of a missile shown in the figure comprises an ear 1, a small stopper 2, a rotating shaft 3, a fixed stopper 4, a stopper 5, a spring 6, a gas generator 7, an air guide chamber 8, an axon 9, an arc groove 10, an exhaust hole 11, an intermediate shell 12, a slotted headless screw 13, a screw hole 14, a right shell 15, a sealing gasket 16 and a left shell 17, wherein the left shell 17, the right shell 15 and the two intermediate shells 12 are combined to form a shell by inserting the headless slotted screw 13 into the screw hole 14 to fix it, which greatly facilitates manufacturing and installation, and the sealing gasket 16 is arranged on the right shell 15, and the shell is a semi-enclosed structure, and a mounting groove is arranged in the shell , used to vertically place the lifting ear 1, the lifting ear 1 is a standard lifting ear specified by the national standard, a rotating shaft 3 is arranged under the circular base of the lifting ear 1, an axle 9 and a small stopper 2 are arranged on the rotating shaft 3, and the three are fixedly installed with slotted headless screws 13; the shell and the lifting ear 1 form a complete structure, which can be used by simply embedding it into the missile body; circular rotating shaft mounting through holes are symmetrically arranged on both sides of the mounting groove, which are used to install the rotating shaft 3 on the lifting ear 1, and an arc groove 10 is arranged inside one of the circular rotating shaft mounting through holes, which is used to place the axle 9 on the rotating shaft 3; a fixed stopper 4 is arranged on the upper inner side of the intermediate shell 12 located at the rear end of the rotating shaft 3, and an arc groove 10 is arranged on the inner side of the intermediate shell 12 A square through hole is provided on the mounting groove on one side of the groove 10, and a large space is provided inside for installing the gas generator 7 and the stopper 5. The square through hole is connected to the arc groove 10 to form an air guide chamber 8; the stopper 5 is a square slider, which is fixedly connected to the gas generator 7, and the end of the stopper 5 is fixedly connected to the spring 6. The stopper 5 and the fixed stopper 4 are used to constrain the other eight degrees of freedom of the rotating shaft 3 except the rotation along the axis where the center of the rotating shaft is located, so that the lifting lug 1 is completely fixed and can be used to mount the missile; after the missile is launched, the gas generator 7 works, and the high-pressure gas does work to push the stopper 5 to contract. At this time, the spring 6 is in a compressed state, and the counterclockwise (or clockwise, depending on the direction) release is released. The rotation constraint in the direction is that after the limiter 5 contracts, the high-pressure gas pushes the axle 9 through the air guide chamber 8 to drive the rotating shaft 3 to rotate counterclockwise. After the end of the axle 9 contacts the inner wall at the end of the arc groove 10, the rotation of the rotating shaft 3 stops, and the high-pressure gas is released through the exhaust port 11 arranged on the arc groove 10. At the same time, the inner wall of the arc groove 10 limits the counterclockwise rotation of the ear 1. At this time, under the action of the spring 6, the limiter 5 is pushed out and contacts with the small stopper 2 on the ear 1 to limit the freedom of the ear 1 to rotate clockwise. At this point, the contraction is completed, and the ear 1 is tightened on the projectile body; in addition, the structure of the small stopper 2 on the ear 1 can prevent the limiter 5 from extending prematurely and hindering the contraction of the ear 1.

[0022] In this embodiment, during the specific implementation, first, the above various components are processed and prepared as required. During the assembly, first, the small stopper 2, the rotating shaft 3, and the axon 9 are assembled and fixed on the lifting lug 1. Then, the rotating shaft 3 is installed and fixed in the two circular rotating shaft installation through holes of the installation groove. The fixed stopper 4 is installed and fixed inside the middle housing 12 at the rear end of the rotating shaft 3. The left housing 17, the right housing 15, and the middle housing 12 are fixed using the slotted headless screw 13. Then, the gas generator 7, the limiter 5, and the spring 6 are installed as a whole and placed into the reserved square through hole. The sealing gasket 16 is fixed to the right housing 15 using the slotted headless screw 13. Then, the lifting lug 1 is placed vertically, and the limiter 5 extends to lock the lifting lug 1, completing the installation.

[0023] During the launch, when the missile leaves the pylon, the gas generator 7 operates to generate high-pressure gas to push the limiter 5 to contract, so as to release the restraint on the lifting lug 1. At this time, the spring 6 is in an energy storage state. After the limiter 5 displaces a certain distance, the air chamber 8 exposes the opening. Due to the existence of the air chamber 8, the airflow of the high-pressure gas changes from radial to transverse, and then acts on the axon 9 along the pipeline. The axon 9 is impacted and drives the rotating shaft 3 to rotate counterclockwise along the arc-shaped groove 10. When the axon 9 is about to contact the opening end of the air chamber 8, the high-pressure gas flows out from the exhaust hole 11, and the spring 6 on the limiter 5 is released, pushing the limiter 5 to extend out of the middle housing 12. Blocked by the small stopper 2, the limiter 5 can only stay at the opening end of the air chamber 8 to prevent hindering the rotation of the lifting lug 1. When the axon 9 completely contacts the opening end of the air chamber 8, the block of the small stopper 2 on the limiter 5 is released, and the limiter 5 extends out of the square through hole under the push of the spring 6 to restrain the lifting lug 7 from rebounding clockwise. At this time, the rotating shaft 3 stops rotating. Thus, the lifting lug 1 is locked, completing the contraction.

Claims

1. A folding lug structure for a missile, comprising a lug, a rotating shaft, a fixed stop block, a limiter, a spring, a driving power source and a housing, characterized in that, The shell is provided with a mounting groove for vertically placing the lifting ear, the lifting ear is a standard lifting ear, a rotating shaft is provided under the base of the lifting ear, and an axle and a small stopper are provided on the rotating shaft; rotating shaft mounting through holes for mounting the rotating shaft are symmetrically provided on both sides of the mounting groove, and an arc-shaped groove for placing the axle is provided inside one of the rotating shaft mounting through holes; a fixed stopper is provided on the upper inner side of the shell at the rear end of the rotating shaft, and a through hole for mounting a driving power source and a limiter is opened on the mounting groove on the side where the arc-shaped groove is provided, the through hole is connected with the arc-shaped groove to form an air guide chamber, the driving power source is a gas generator for generating high-pressure gas, and the existence of the air guide chamber is used to change the airflow direction of the high-pressure gas, and the high-pressure gas acts on the axle to drive the rotating shaft to rotate; the limiter is a square slider, the limiter is fixedly connected to the driving power source, the end of the limiter is fixedly connected to the spring, and at the same time, an exhaust port for releasing the high-pressure gas is provided on the arc-shaped groove; When launching, the missile leaves the rack, and the gas generator works to generate high-pressure gas to push the limiter to contract, so as to release the constraint on the lifting ear. At this time, the spring is in the energy storage state. After the limiter is displaced a certain distance, the air guide chamber reveals an opening. Due to the existence of the air guide chamber, the airflow of high-pressure gas changes from radial to lateral, and then acts on the axon along the pipeline. The axon is impacted and drives the rotating shaft to rotate counterclockwise along the arc groove. When the axon is about to contact the open end of the air guide chamber, the high-pressure gas flows out from the exhaust hole, and the spring on the limiter is released, pushing the limiter to extend out of the middle shell. Under the obstruction of the small block, the limiter can only stay at the open end of the air guide chamber to prevent the lifting ear from rotating. When the axon completely contacts the open end of the air guide chamber, the obstruction of the small block on the limiter is released, and the limiter extends out of the through hole under the push of the spring, constraining the lifting ear to rebound clockwise. At this time, the rotating shaft stops rotating, and the lifting ear is locked and the contraction is completed.

2. The folding lug structure of a missile according to claim 1, characterized in that, The shell is composed of a left shell, a right shell and two middle shells.

3. The folding lug structure of a missile according to claim 2, wherein, The fixed stopper is arranged on the upper inner side of the intermediate housing at the rear end of the rotating shaft.

4. A missile folding lug structure according to claim 2, characterized in that, A sealing gasket is arranged on the right outer shell.

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