A missile folding lug structure driven by a traction shaft

Abstract

A missile folding lug structure driven by a traction shaft. Among them, the outer shell is formed by enclosing a left outer shell, a right outer shell and a middle outer shell. An outer shell groove for vertically placing the lug is arranged inside the outer shell. The lug is a standard lug, and a rotating shaft, a traction shaft and a small stop block are arranged under the pedestal of the lug, and the three are fixedly installed by screws. Rotating shaft installation through holes for installing the rotating shaft are symmetrically arranged on both sides of the outer shell groove. A fixed stop block is arranged on the upper part of the inner side of the middle outer shell. Through holes for installing a driving power source and a limiter are reserved on the middle outer shell. At the same time, an opening for placing the traction shaft is opened inside the outer shell on the same side as the through hole, and the opening is communicated with the through hole to form an air guide chamber. The limiter is fixedly connected to the driving power source, and the end of the limiter is fixedly connected to a spring. The invention effectively reduces the air resistance, is beneficial to the high-speed flight of the missile, and reduces the effective radar cross-sectional area, 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 in particular to a missile folding lug structure driven by a traction shaft. Background Art

[0002] Missile lugs are a relatively common type of rack adapter component. 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, and thus affecting the missile flight performance 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 missile folding lug structure driven by a traction shaft to solve the problems in the above background art.

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

[0005] A missile folding lug structure driven by a traction shaft includes a lug, a rotating shaft, a fixed stop, a driving power source, a stopper, a spring, a traction shaft and a housing. Among them, the housing is surrounded by a left housing, a right housing and a middle housing. An outer housing groove for vertically placing the lug is provided inside the housing. The lug is a standard lug. A rotating shaft, a traction shaft and a small stop are arranged under the pedestal of the lug, and the three are fixedly installed by screws. Circular rotating shaft installation through holes are symmetrically arranged on both sides of the outer housing groove for installing the rotating shaft of the lug. A fixed stop is arranged on the upper part of the inner side of the middle housing at the rear end of the rotating shaft. A through hole is reserved on the middle housing for installing the driving power source and the stopper. At the same time, an opening is formed in the housing on the same side as the through hole for placing and working the traction shaft, and the opening is connected to the square through hole to form an air guide chamber. The driving power source is used to generate high-pressure gas. 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 traction shaft to drive the rotating shaft to rotate. The stopper is fixedly connected to the driving power source, and the end of the stopper is fixedly connected to the spring. 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 and can be used to mount the missile.

[0006] In the present invention, a sealing gasket is provided on the right housing.

[0007] In the present invention, the stopper is a square slider.

[0008] In the present invention, the through hole is a square through hole.

[0009] In the present invention, the driving power source is a gas generator.

[0010] In the present invention, when it is implemented, the above-mentioned various components are first processed and prepared as required. When assembling, first assemble and fix the small stopper, the rotating shaft and the traction shaft on the lifting ear, and then install and fix the rotating shaft in the two circular rotating shaft installation through holes of the outer shell groove, install the fixed stopper on the inner side of the middle outer shell located at the rear end of the rotating shaft, use slotted headless screws to fix the left outer shell, the right outer shell and the middle outer shell, and then install the gas generator, the limiter and the spring into one body, install them into the reserved square through hole, use slotted headless screws to fix the sealing gasket to the right outer shell, and then put the lifting ear vertically, so that the limiter extends out of the locking lifting ear to complete the installation;

[0011] 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 an energy storage state. After the limiter is displaced a certain distance, the air guide chamber exposes an opening. The existence of the air guide chamber causes the airflow of high-pressure gas to change from radial to lateral, and then acts on the traction shaft along the pipeline. The traction shaft is impacted and drives the rotating shaft to rotate counterclockwise, and then the high-pressure gas flows out from the opening, 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, it can only stay at the end of the opening to prevent the lifting ear from rotating; when the traction shaft is about to contact the end of the opening, the obstruction of the small block on the limiter is released, and the limiter extends out of the square through hole under the push of the spring, constraining the lifting ear to move clockwise. After the traction shaft contacts the end of the opening, the rotating shaft stops rotating, and at this point, the lifting ear is locked and the contraction is completed; the gas generator is used to change the direction of the high-pressure gas flow through the existence of the air guide chamber, thereby driving the rotating shaft to rotate, so as to achieve the locking of the lifting ear.

[0012] Beneficial effects: The locking method of the present invention is simple and reliable when working or retracting. After retraction, since there are no protrusions on the surface of the missile body, the air resistance is reduced, the range is increased, and it is beneficial to the high-speed flight of the missile. The effective radar reflection cross-sectional area is reduced, and it is not easy to capture the signal, which effectively improves the anti-radar performance. The ear structure is separated from the missile body, which is convenient for manufacturing. When in use, it only needs to be installed as a whole in the slot reserved for the missile, which is simple, convenient and saves manufacturing costs. At the same time, the gas generator is used as a power source to drive the ear to retract, which is more reliable and has higher adaptability than a motor or a spring. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a front cross-sectional view of the folding ear structure in the working state in the preferred embodiment of the present invention.

[0014] Figure 2This is a downward cross-sectional view of the folding lug structure in the working state in the preferred embodiment of the present invention.

[0015] Figure 3 This is a front cross-sectional view of the folding lug structure in the folded state in the preferred embodiment of the present invention.

[0016] Figure 4 This is a rear view of the folding lug structure in the folded state in the preferred embodiment of the present invention.

[0017] Figure 5 This is a schematic diagram of the connection of the rotating shaft, the traction shaft and the small stopper in the preferred embodiment of the present invention. Detailed implementation manners

[0018] In order to make the technical means, creative features, achieved purposes and effects of the present invention easy to understand, the present invention will be further described below with reference to specific illustrations.

[0019] See, for example, Figures 1 to 5The folding lifting ear structure of a missile driven by a traction shaft shown in the figure comprises a lifting ear 1, a small stopper 2, a rotating shaft 3, a fixed stopper 4, a gas generator 5, a limiter 6, a spring 7, an air guide chamber 8, a traction shaft 9, an intermediate shell 10, a slotted headless screw 11, a right shell 12, a sealing gasket 13 and a left shell 14, wherein the left shell 14, the right shell 12 and the intermediate shell 10 are surrounded and fixed by the headless slotted screw 11 to form a shell, which greatly facilitates manufacturing and installation, the sealing gasket 13 is arranged on the right shell 12, and a shell groove is arranged in the shell, It is used to place the lifting ear 1, which is a standard lifting ear specified by the national standard. A rotating shaft 3, a traction shaft 9 and a small stopper 2 are arranged under the circular base of the lifting ear 1, and the three are fixedly installed with slotted headless screws 11; circular rotating shaft installation through holes are symmetrically arranged on both sides of the shell groove, which are used to install the rotating shaft 3 of the lifting ear 1, and a fixed stopper 4 is arranged on the upper inner side of the intermediate shell 10 located at the rear end of the rotating shaft 3. A square through hole is reserved on the intermediate shell 10 for installing the gas generator 5 and the limiter 6, and an opening is opened in the shell on the same side as the square through hole. It is used for placing and working the traction shaft 9, and the opening is connected to the square through hole to form an air guide chamber 8; the limiter 6 is a square slider, which is fixedly connected to the gas generator 5, and the end of the limiter 6 is fixedly connected to the spring 7. The limiter 6 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 ear 1 is completely fixed and can be used to mount the missile; after the missile is launched, the gas generator 5 works, and the high-pressure gas does work to push the limiter 6 to contract, and the spring 7 is in a compressed state, releasing the rotation in the counterclockwise (or clockwise, depending on the direction) direction. Rotation constraint, after the limiter 6 contracts, the high-pressure gas pushes the traction shaft 9 through the air guide chamber 8 to drive the ear 1 to rotate counterclockwise. After the end of the traction shaft 9 contacts the inner wall at the end of the opening, the rotation stops. At the same time, the inner wall of the opening limits the counterclockwise rotation of the ear 1. At this time, under the action of the spring 7, the limiter 6 is pushed out and contacts the small stopper 2 on the ear 1 to limit the freedom of the ear 1 to rotate clockwise. At this point, the ear 1 is contracted and is tightened on the missile body. In addition, the structure of the small stopper 2 on the ear 1 can prevent the limiter 6 from extending prematurely and hindering the contraction of the ear 1.

[0020] In this embodiment, when it is implemented, the various components are first processed and prepared as required. When assembling, the small stopper 2, the rotating shaft 3 and the traction shaft 9 are first assembled and fixed on the lifting ear 1, and then the rotating shaft 3 is installed and fixed in the two circular rotating shaft installation through holes of the outer shell groove, and the fixed stopper 4 is installed on the inner side of the middle outer shell 10 located at the rear end of the rotating shaft 3. The left outer shell 14, the right outer shell 12 and the middle outer shell 10 are fixed with the slotted headless screws 11, and then the gas generator 5, the limiter 6 and the spring 7 are installed in one body and installed in the reserved square through hole. The sealing gasket 13 and the right outer shell 12 are fixed with the slotted headless screws 11, and then the lifting ear 1 is placed vertically so that the limiter 6 extends out of the locking lifting ear 1 to complete the installation;

[0021] When launching, the missile leaves the rack, and the gas generator 5 works to generate high-pressure gas to push the stopper 6 to contract, so as to release the constraint on the lifting ear 1. At this time, the spring 7 is in the energy storage state. After the stopper 6 is displaced a certain distance, the air guide chamber 8 exposes the opening. The existence of the air guide chamber 8 causes the airflow of the high-pressure gas to change from radial to lateral, and then acts on the traction shaft 9 along the pipeline. The traction shaft 9 is impacted to drive the rotating shaft 3 to rotate counterclockwise, and then the high-pressure gas flows out from the opening, and the spring 7 on the stopper 6 is released, pushing the stopper 6 to extend out of the middle shell 10. Under the obstruction of the small stopper 2, it can only stay at the end of the opening to prevent the lifting ear 1 from rotating; when the traction shaft 9 is about to contact the end of the opening, the small stopper 2 releases the obstruction of the stopper 6, and the stopper 6 extends out of the square through hole under the push of the spring 7, constraining the lifting ear 7 to move clockwise. After the traction shaft 9 contacts the end of the opening, the rotating shaft 3 stops rotating, and the lifting ear 1 is locked and the contraction is completed.

Claims

1. A missile folding lug structure driven by a traction shaft, comprising a lug, a rotating shaft, a fixed stop, a driving power source, a limiter, a spring, a traction shaft and a housing, characterized in that The shell is composed of a left shell, a right shell and an intermediate shell, the shell is provided with a shell groove for vertically placing a lifting ear, the lifting ear is a standard lifting ear, and a rotating shaft, a traction shaft and a small stopper are provided under the base of the lifting ear; the two sides of the shell groove are symmetrically provided with rotating shaft mounting through holes for installing the rotating shaft, and a fixed stopper is provided on the upper inner side of the intermediate shell at the rear end of the rotating shaft, and a through hole for installing a driving power source and a limiter is reserved on the intermediate shell, and an opening for placing the traction shaft is opened in the shell on the same side of the through hole, and the opening is connected with the through hole 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 traction shaft to drive the rotating shaft to rotate; the limiter is a square slider, the limiter is fixedly connected to the driving power source, and the end of the limiter is fixedly connected to the spring; When launching, the missile leaves the rack, and the gas generator works to produce 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 an energy storage state. After the limiter is displaced a certain distance, the air guide chamber reveals an opening. The existence of the air guide chamber causes the airflow of high-pressure gas to change from radial to lateral, and then acts on the traction shaft along the pipeline. The traction shaft is impacted by the high-pressure gas and drives the rotating shaft to rotate counterclockwise, and then the high-pressure gas flows out from the opening, and the spring on the limiter is released, pushing the limiter to extend out of the middle shell. Under the obstruction of the small stopper, it can only stay at the end of the opening to prevent the lifting ear from rotating; when the traction shaft is about to contact the end of the opening, the small stopper releases the obstruction of the limiter, and the limiter extends out of the square through hole under the push of the spring, constraining the lifting ear to move clockwise. After the traction shaft contacts the end of the opening, the rotating shaft stops rotating, and the lifting ear is locked and the contraction is completed.

2. The missile folding lug structure driven by a traction shaft according to claim 1, wherein, A sealing gasket is arranged on the right outer shell.

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