A new type of connecting mechanism for projectile cabin sections

Abstract

The present invention relates to a novel connecting mechanism for a projectile cabin section, comprising: a first wedge block, a second wedge block, a front cabin and a rear cabin. Both the front cabin and the rear cabin are cylindrical structures. The front cabin includes a large-diameter section of the front cabin and a small-diameter section of the front cabin. The small-diameter section of the front cabin is docked with the small-diameter section of the rear cabin. Trapezoidal teeth are evenly distributed along the circumferential radial direction on the small-diameter section of the front cabin. A circumferential inclined plane is machined at the connection between the large-diameter section of the front cabin and the small-diameter section of the front cabin, and the height is the same as the height of the ring teeth. A positioning groove is opened at the top of the connection between the large-diameter section of the front cabin and the small-diameter section of the front cabin. The rear cabin includes a large-diameter section of the rear cabin and a small-diameter section of the rear cabin. Trapezoidal teeth are evenly distributed along the circumferential radial direction on the small-diameter section of the rear cabin. A rectangular groove is machined between two trapezoidal teeth on the large-diameter section of the rear cabin for installing the first wedge block and the second wedge block. Trapezoidal teeth are machined on the small-diameter section of the front cabin and the small-diameter section of the rear cabin to ensure that the trapezoidal teeth of the rear cabin can pass through the space between the trapezoidal teeth of the front cabin. The present invention effectively improves the waterproof performance and the load-bearing capacity of the product.

Description

Technical Field

[0001] The present invention relates to a novel connecting mechanism for missile body sections, belonging to the technical field of aerospace. Background Art

[0002] At present, some commonly used connecting mechanisms for sections are all socket forms. During the flight of the missile body, the reaction force caused by the vibration of the aircraft acts on the missile body, which will bring a strong impact to the missile body. This impact causes the socketed screws to bear shear stress, and may cause the screws to break. Summary of the Invention

[0003] The technical problem solved by the present invention is: overcoming the deficiencies of the prior art, and proposing a novel connecting mechanism for missile body sections to improve the waterproof performance and the bearing capacity of the product.

[0004] The technical solution adopted by the present invention is as follows:

[0005] A novel connecting mechanism for missile body sections includes: a first wedge block, a second wedge block, a front section and a rear section.

[0006] Both the front section and the rear section are cylindrical structures. The front section includes a large-diameter section of the front section and a small-diameter section of the front section. The small-diameter section of the front section is docked with the small-diameter section of the rear section; trapezoidal teeth are evenly distributed along the circumferential radial direction on the small-diameter section of the front section; a circumferential inclined surface is machined at the connection between the large-diameter section of the front section and the small-diameter section of the front section, and the height is the same as the height of the ring teeth;

[0007] A positioning groove is opened at the top of the connection between the large-diameter section of the front section and the small-diameter section of the front section;

[0008] The rear section includes a large-diameter section of the rear section and a small-diameter section of the rear section; trapezoidal teeth are evenly distributed along the circumferential radial direction on the small-diameter section of the rear section; a rectangular groove is machined between two trapezoidal teeth on the large-diameter section of the rear section for installing the first wedge block and the second wedge block;

[0009] A limiting protrusion is opened at the front end of the first wedge block, which is installed in cooperation with the positioning groove at the connection between the large-diameter section of the front section and the small-diameter section of the front section; a circumferential inclined surface is machined below the limiting protrusion, which is installed in cooperation with the circumferential inclined surface at the connection between the large-diameter section of the front section and the small-diameter section of the front section; the other three directions of the first wedge block are vertical planes, which are matched with the rectangular groove on the large-diameter section of the rear section;

[0010] Trapezoidal teeth are machined on the small-diameter section of the front section and the small-diameter section of the rear section to ensure that the trapezoidal teeth of the rear section can pass through the space between the trapezoidal teeth of the front section.

[0011] Further, trapezoidal teeth are evenly distributed along the circumferential radial direction on the small-diameter section of the front section, and the trapezoidal teeth are less than 45°.

[0012] Further, trapezoidal teeth are evenly distributed along the circumferential radial direction on the small-diameter section of the rear section, and the trapezoidal teeth are less than 45°.

[0013] Furthermore, a through hole is provided at the center of the bottom of the first wedge block, and it is connected to the threaded hole in the small-diameter section of the front cabin by screws.

[0014] Furthermore, the second wedge block has no limit protrusion, and the rest of the features are the same as those of the first wedge block.

[0015] Furthermore, trapezoidal teeth less than 45° are machined on the small-diameter sections of the front cabin and the rear cabin.

[0016] Furthermore, a U-shaped groove is machined on the circumference of the small-diameter section of the front cabin for installing a sealing ring.

[0017] Furthermore, four threaded holes are machined on the small-diameter section of the front cabin and are connected to the first wedge block and the second wedge block.

[0018] Furthermore, an initial scale line and a final scale line are machined on the outer surface of the large-diameter section of the front cabin; a positioning scale line is machined on the outer surface of the large-diameter section of the rear cabin.

[0019] Furthermore, when the cabin sections are docked, the positioning scale line of the rear cabin aligns with the initial scale line of its front cabin. After docking in place, rotate clockwise to align the scale line of the rear cabin with the final scale line of the front cabin; after the front cabin and the rear cabin are sleeved through the trapezoidal teeth, first install a first wedge block, and the limit protrusion at the front end of the first wedge block is installed in cooperation with the positioning groove of the large-diameter section of the front cabin; then install three second wedge blocks to connect the four wedge blocks to the front cabin; due to the circumferential inclined surface machined at the connection between the large-diameter section and the small-diameter section of the front cabin, when the four wedge blocks are tightened with the front cabin, it drives the inclined surfaces of the first wedge block and the second wedge block to move along the circumferential inclined surface at the connection between the large-diameter section and the small-diameter section of the front cabin. While the first wedge block and the second wedge block move radially, they also move towards the rear cabin direction, driving the rear cabin to move backward, so that the mating surfaces of the T-shaped teeth of the front cabin and the rear cabin are closely attached to achieve locking.

[0020] The beneficial effects of the present invention compared with the prior art are as follows:

[0021] (1) The present invention adopts the method of the mechanism itself bearing force instead of the traditional screw bearing force and wedge block locking method, effectively improving the bearing capacity of the product;

[0022] (2) On the basis of ensuring the original waterproof function of the sealing ring, the present invention adds a socket joint mating surface between the cabin sections to improve the waterproof performance;

[0023] (3) The present invention can adapt to the requirements of aerial bombs of any shape and size by changing the structure of the cabin body. This mechanism occupies a small volume, has little impact on other structures of the cabin body, and has high versatility. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic structural diagram of the present invention;

[0025] Figure 2It is a schematic diagram of the initial position for the rear cabin docking;

[0026] Figure 3 It is a schematic diagram of the completed rear cabin docking;

[0027] Figure 4 It is a schematic diagram of the invention's structural principle;

[0028] Figure 5 It is the front cabin structure diagram of the present invention;

[0029] Figure 6 It is the rear cabin structure diagram of the present invention;

[0030] Figure 7 It is the structural diagram of the wedge block of the present invention. Specific implementation manners

[0031] The present invention will be further elaborated below in conjunction with embodiments.

[0032] Figure 1-7 As shown, a new type of projectile cabin section connection mechanism includes: a first wedge block 1, a second wedge block 2, a front cabin 3, and a rear cabin 4.

[0033] Both the front cabin 3 and the rear cabin 4 are cylindrical structures. The front cabin 3 includes a large-diameter section of the front cabin and a small-diameter section of the front cabin. The small-diameter section of the front cabin is docked with the small-diameter section of the rear cabin; Trapezoidal teeth are evenly distributed along the circumferential radial direction on the small-diameter section of the front cabin; A U-shaped groove is machined on the circumference of the small-diameter section of the front cabin for installing a sealing ring; A circumferential inclined surface is machined at the connection between the large-diameter section of the front cabin and the small-diameter section of the front cabin, and the height is the same as the height of the ring teeth.

[0034] A positioning groove is opened at the top of the connection between the large-diameter section of the front cabin and the small-diameter section of the front cabin; Four threaded holes are machined on the small-diameter section of the front cabin and are connected to the first wedge block 1 and the second wedge block 2; Initial scale lines and end scale lines are machined on the outer surface of the large-diameter section of the front cabin.

[0035] The rear cabin 4 includes a large-diameter section of the rear cabin and a small-diameter section of the rear cabin; Trapezoidal teeth are evenly distributed along the circumferential radial direction on the small-diameter section of the rear cabin; A rectangular groove is machined between two trapezoidal teeth on the large-diameter section of the rear cabin for installing the first wedge block 1 and the second wedge block 2; A positioning scale line is machined on the outer surface of the large-diameter section of the rear cabin.

[0036] A limit protrusion is opened at the front end of the first wedge block 1 and is installed in cooperation with the positioning groove at the connection between the large-diameter section of the front cabin and the small-diameter section of the front cabin; A circumferential inclined surface is machined below the limit protrusion and is installed in cooperation with the circumferential inclined surface at the connection between the large-diameter section of the front cabin and the small-diameter section of the front cabin; The other three directions of the first wedge block 1 are vertical planes and are matched with the rectangular groove of the large-diameter section of the rear cabin.

[0037] The small-diameter section of the front cabin and the small-diameter section of the rear cabin are machined with trapezoidal teeth to ensure that the 4 trapezoidal teeth of the rear cabin can pass through the space between the 3 trapezoidal teeth of the front cabin; when docking the cabin sections, a sealing ring needs to be installed in the U-shaped groove of the small-diameter section of the front cabin, and the positioning scale line of the rear cabin 4 is aligned with the initial scale line of its front cabin 3. After docking in place, rotate in the clockwise direction to align the scale line of the rear cabin 4 with the last scale line of the front cabin; after the front cabin 3 and the rear cabin 4 are sleeved through the trapezoidal teeth, first install a first wedge block 1, and the front-end limit protrusion of the first wedge block 1 is installed in cooperation with the positioning groove of the large-diameter section of the front cabin; then install three second wedge blocks 2, and then connect the four wedge blocks to the front cabin through screws; due to the machining of the circumferential inclined surface at the connection between the large-diameter section and the small-diameter section of the front cabin, when the screws are tightened, it drives the inclined surfaces of the first wedge block 1 and the second wedge block 2 to move along the circumferential inclined surface at the connection between the large-diameter section and the small-diameter section of the front cabin. While the first wedge block 1 and the second wedge block 2 move radially, they also move towards the rear cabin direction, driving the rear cabin 4 to move backward, so that the mating surfaces of the T-shaped teeth of the front cabin 3 and the rear cabin 4 are closely attached, achieving the purpose of locking.

[0038] The small-diameter section of the front cabin is evenly distributed with trapezoidal teeth along the circumferential radial direction, and the trapezoidal teeth are less than 45°. The small-diameter section of the rear cabin is evenly distributed with trapezoidal teeth along the circumferential radial direction, and the trapezoidal teeth are less than 45°. The small-diameter section of the front cabin and the small-diameter section of the rear cabin are machined with trapezoidal teeth less than 45°.

[0039] A through hole is opened at the center bottom of the first wedge block 1 and is connected to the threaded hole of the small-diameter section of the front cabin through a screw. The second wedge block 2 has no limit protrusion, and the other features are the same as those of the first wedge block 1.

[0040] Due to the different shapes and the thicknesses of the cabin bodies of the aerial bombs, the first wedge block 1, the second wedge block 2, the front cabin 3 and the rear cabin 4 with different sizes can be customized according to different structural forms of the aerial bombs, and the number and positions of the screw holes are changed.

[0041] The present invention adopts the method of the mechanism itself bearing force instead of the traditional screw bearing force and wedge block locking method, effectively improving the bearing capacity of the product.

[0042] On the basis of ensuring the original waterproof function of the sealing ring, the present invention adds a socket joint mating surface between the cabin sections to improve the waterproof performance.

[0043] The present invention can adapt to the requirements of aerial bombs of any shape and size by changing the structure of the cabin body. This mechanism occupies a small volume, has little influence on other structures of the cabin body, and has high versatility.

[0044] The present invention has no special requirements for materials and processing methods and has high adaptability. By changing the corresponding structural dimensions, it can adapt to different models of aerial bombs, has extremely high versatility, and can meet different needs such as military and civilian.

[0045] Although the present invention has been disclosed above in preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the methods and technical content disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and decorations made to the above embodiments based on the technical essence of the present invention without departing from the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A novel connecting mechanism for projectile cabin sections, characterized in that, Including: A first wedge block (1), a second wedge block (2), a front cabin (3) and a rear cabin (4), Both the front cabin (3) and the rear cabin (4) are cylindrical structures. The front cabin (3) includes a large-diameter section of the front cabin and a small-diameter section of the front cabin. The small-diameter section of the front cabin is docked with the small-diameter section of the rear cabin; Trapezoidal teeth are evenly distributed along the circumferential radial direction on the small-diameter section of the front cabin; A circumferential inclined surface is machined at the connection between the large-diameter section of the front cabin and the small-diameter section of the front cabin, and the height is the same as the height of the ring teeth; A positioning groove is opened at the top of the connection between the large-diameter section of the front cabin and the small-diameter section of the front cabin; The rear cabin (4) includes a large-diameter section of the rear cabin and a small-diameter section of the rear cabin; Trapezoidal teeth are evenly distributed along the circumferential radial direction on the small-diameter section of the rear cabin; A rectangular groove is machined between two trapezoidal teeth on the large-diameter section of the rear cabin for installing the first wedge block (1) and the second wedge block (2); A limit projection is opened at the front end of the first wedge block (1) and is installed in cooperation with the positioning groove at the connection between the large-diameter section of the front cabin and the small-diameter section of the front cabin; A circumferential inclined surface is machined below the limit projection and is installed in cooperation with the circumferential inclined surface at the connection between the large-diameter section of the front cabin and the small-diameter section of the front cabin; The other three directions of the first wedge block (1) are vertical planes and are matched with the rectangular groove of the large-diameter section of the rear cabin; Trapezoidal teeth are machined on the small-diameter sections of the front cabin and the rear cabin to ensure that the trapezoidal teeth of the rear cabin (4) can pass through the space between the trapezoidal teeth of the front cabin (3).

2. The novel connecting mechanism for projectile cabin sections according to claim 1, characterized in that, Trapezoidal teeth are evenly distributed along the circumferential radial direction on the small-diameter section of the front cabin, and the trapezoidal teeth are less than 45°.

3. The novel connecting mechanism for projectile cabin sections according to claim 1, characterized in that, Trapezoidal teeth are evenly distributed along the circumferential radial direction on the small-diameter section of the rear cabin, and the trapezoidal teeth are less than 45°.

4. The novel connecting mechanism for projectile cabin sections according to claim 1, characterized in that, A through hole is opened at the center bottom of the first wedge block (1) and is connected to the threaded hole of the small-diameter section of the front cabin by a screw.

5. The novel connecting mechanism for projectile cabin sections according to claim 1, characterized in that, The second wedge block (2) has no limit projection, and the other features are the same as those of the first wedge block (1).

6. The novel connecting mechanism for projectile cabin sections according to claim 1, characterized in that, Trapezoidal teeth less than 45° are machined on the small-diameter sections of the front cabin and the rear cabin.

7. The novel connecting mechanism for projectile cabin sections according to claim 1, characterized in that, A U-shaped groove is machined on the circumference of the small-diameter section of the front cabin for installing a sealing ring.

8. The novel connecting mechanism for projectile cabin sections according to claim 1, characterized in that, Four threaded holes are machined on the small-diameter section of the front cabin and are connected to the first wedge block (1) and the second wedge block (2).

9. The novel connecting mechanism for projectile cabin sections according to claim 1, characterized in that, An initial scale line and a final scale line are machined on the outer surface of the large-diameter section of the front cabin; A positioning scale line is machined on the outer surface of the large-diameter section of the rear cabin.

10. The novel connecting mechanism for projectile cabin sections according to claim 9, characterized in that, When the cabin sections are docked, the positioning scale line of the rear cabin (4) is aligned with the initial scale line of the front cabin (3). After docking in place, rotate clockwise to align the scale line of the rear cabin (4) with the final scale line of the front cabin; After the front cabin (3) and the rear cabin (4) are sleeved through trapezoidal teeth, first install a first wedge block (1), and the limit projection at the front end of the first wedge block (1) is installed in cooperation with the positioning groove of the large-diameter section of the front cabin; Then install three second wedge blocks (2) to connect the four wedge blocks to the front cabin; Since a circumferential inclined surface is machined at the connection between the large-diameter section of the front cabin and the small-diameter section of the front cabin, when the four wedge blocks are tightened with the front cabin, it drives the inclined surfaces of the first wedge block (1) and the second wedge block (2) to move along the circumferential inclined surface at the connection between the large-diameter section of the front cabin and the small-diameter section of the front cabin. While the first wedge block (1) and the second wedge block (2) move radially, they will also move towards the rear cabin direction, driving the rear cabin (4) to move backward, so that the mating surfaces of the trapezoidal teeth of the front cabin (3) and the rear cabin (4) are tightly attached to achieve locking.

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