Rapid dismounting and mounting structure in guided missile packaging box

Abstract

The utility model discloses a quick dismounting and mounting structure in a guided missile packaging box, which relates to the field of guided missile fixing structures, is used for connecting a locking ring and a fixing seat and comprises a fixing part, the fixing part penetrates through the locking ring, the fixing seat is provided with a fixing groove, a fixing block is arranged in the fixing groove, and a rotating cavity is arranged between the bottom of the fixing block and the bottom of the fixing groove. A limiting rod is arranged at the bottom of the fixing piece, a through hole is formed in the fixing block in a penetrating mode, a limiting groove is formed in the bottom of the fixing block, the limiting groove and the through hole are arranged in a crossed mode, the through hole and the limiting groove can be matched with the limiting rod in an inserted connection mode, and a rebounding piece is arranged on the fixing piece and arranged between the top of the fixing piece and the locking ring. According to the rapid dismounting and mounting structure in the guided missile packaging box, rapid mounting and dismounting of the guided missile locking ring can be achieved without tools, the mounting and dismounting speed is increased, accordingly, the production efficiency is improved, and meanwhile the position of a guided missile after mounting is convenient to adjust.

Description

Technical Field

[0001] The utility model relates to the field of missile fixing structures, in particular to a missile packaging box internal quick disassembly and assembly structure. Background Art

[0002] In the prior art, the fixation of missiles usually relies on the design of a locking ring, which is fixed on a fixing seat and uses the friction between the inner ring felt layer and the surface of the missile to achieve the stability of the missile. This design can meet the strength requirements required when the missile is fixed in the packaging box. However, the common fixing method of this locking ring requires the use of tools such as bolts or screws, which not only increases the complexity of installation, but also has low efficiency in mass production. In addition, once the missile is installed, if the position needs to be adjusted, this fixing method will also become very inconvenient because it is difficult to disassemble quickly. Utility Model Content

[0003] The purpose of the utility model is to provide a missile packaging box internal quick disassembly structure, the missile packaging box internal quick disassembly structure can realize the missile locking ring quick installation and disassembly without tools, improve the installation and disassembly speed, thereby improving production efficiency, and at the same time facilitate the adjustment of the missile position after installation.

[0004] The above-mentioned optimized structure of the utility model is realized through the following technical scheme: a quick disassembly and assembly structure inside a missile packaging box, used for connecting the locking ring and the fixing seat, including a fixing piece, the fixing piece passes through the locking ring, the fixing seat is provided with a fixing groove, a fixing block is provided in the fixing groove, a rotating cavity is provided between the bottom of the fixing block and the bottom of the fixing groove, a limiting rod is provided at the bottom of the fixing piece, a through hole is passed through the fixing block, a limiting groove is provided at the bottom of the fixing block, the limiting groove and the through hole are cross-arranged, the through hole and the limiting groove can be plugged and matched with the limiting rod, and a rebound piece is provided on the fixing piece, and the rebound piece is arranged between the top of the fixing piece and the locking ring.

[0005] In some embodiments, a limiting block is provided on the top of the fixing member, and the size of the limiting block is larger than the size of the through hole.

[0006] In some embodiments, the resilient member comprises a return spring, a resilient sheet is provided at the bottom of the return spring, and the top of the return spring is connected to the bottom of the limit block.

[0007] In some embodiments, the limiting groove is arranged perpendicular to the through hole.

[0008] In some embodiments, the limiting groove, the through hole and the limiting rod are all in a straight line shape.

[0009] In some embodiments, the limiting rod is coaxially fixed to the bottom of the fixing member.

[0010] In some embodiments, the fixing member is a square block, and arc blocks are provided on both sides of the square block.

[0011] In some embodiments, the through hole and the limiting rod are clearance-matched, and the limiting groove and the limiting rod are transitionally matched.

[0012] In summary, the utility model has the following beneficial effects:

[0013] The internal quick disassembly and assembly structure of the missile packaging box can realize the quick installation and disassembly of the missile locking ring without the aid of tools through the plug-in cooperation of the limit groove and the limit rod and under the rebound action of the rebound part, thereby improving the speed of missile installation and disassembly, and then improving the work efficiency on the production line, and facilitating the adjustment of the missile position after installation; at the same time, the quick installation and disassembly feature of the utility model can facilitate the adjustment and maintenance of the missile position after the missile is installed. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a schematic diagram of the use of the utility model in a packaging box;

[0015] Figure 2 It is an enlarged view of point A of the utility model;

[0016] Figure 3 It is a schematic cross-sectional view of the installation of the utility model between the locking ring and the fixing seat;

[0017] Figure 4 This is a three-dimensional diagram of the internal quick disassembly and assembly structure of a missile packaging box of the utility model;

[0018] Figure 5 This is a stereoscopic diagram from another perspective of the internal quick disassembly and assembly structure of a missile packaging box of the utility model.

[0019] In the figure: 1, locking ring; 2, fixing seat; 3, fixing piece; 31, limiting rod; 32, limiting block; 33, connecting rod; 4, fixing block; 41, through hole; 42, limiting groove; 5, rotating cavity; 6, rebound piece; 61, reset spring; 62, rebound sheet. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of them. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0021] refer to Figure 1-5 A quick disassembly and assembly structure inside a missile packaging box is used to connect the locking ring 1 and the fixing seat 2, including a fixing piece 3 that passes through the locking ring 1, a limiting block 32 is provided on the top of the fixing piece 3, a limiting rod 31 is provided on the bottom of the fixing piece 3, a connecting rod 33 is connected between the limiting block 32 and the limiting rod 31, and the connecting rod 33 passes through the locking ring 1; the fixing seat 2 is provided with a fixing groove, a fixing block 4 is provided in the fixing groove, a rotating cavity 5 is provided between the bottom of the fixing block 4 and the bottom of the fixing groove, a through hole 41 is passed through the fixing block 4, a limiting groove 42 is provided at the bottom of the fixing block 4, the limiting groove 42 and the through hole 41 are cross-arranged, the through hole 41 and the limiting groove 42 can be plugged and matched with the limiting rod 31, a rebound piece 6 is provided on the fixing piece 3, and the rebound piece 6 is arranged between the top of the fixing piece 3 and the locking ring 1, and the rebound piece 6 is arranged between the top of the fixing piece 3 and the locking ring 1. The elastic member 6 includes a reset spring 61 and a rebound sheet 62. The top of the reset spring 61 is connected to the bottom of the limit block 32, and the bottom of the reset spring 61 is connected to the rebound sheet 62. The rebound sheet 62 can increase the contact area between the reset spring 61 and the locking ring 1 when it is compressed and deformed, so that the locking ring 1 is subjected to more uniform force. The rebound member 6 can drive the fixing member 3 to reset, that is, after the limit rod 31 passes through the through hole 41, the limit rod 31 is rotated to be plugged and matched with the limit groove 42. The reset spring 61 resets and rebounds to drive the limit block 32 to rise, so that the limit rod 31 is placed on the upper part of the limit groove 42 without slipping, thereby achieving fixation between the fixing member 3 and the fixing block 4, thereby achieving the fixing effect of the locking ring 1 on the fixing seat 2. The whole process can be achieved without the aid of tools, thereby achieving rapid installation and disassembly of the missile.

[0022] In some embodiments, the limiting groove 42 is vertically arranged to the through hole 41 to facilitate the plug-in fit between the limiting rod 31 and the limiting groove 42 after rotation.

[0023] In some embodiments, the limit groove 42, the through hole 41 and the limit rod 31 can all be in a straight line shape, and the limit rod 31 is coaxially fixed at the bottom of the connecting rod 33, which can improve the force uniformity between the fixing member 3 and the fixing block 4 when the connecting rod 33 is plugged into the limit groove 42.

[0024] In some embodiments, the fixing member 3 may be a square block, and the size of the limit block 32 is larger than the size of the through hole 41. When the limit rod 31 passes through the through hole 41, the fixing member 3 can be prevented from passing through the through hole 41 as a whole, thereby avoiding failure of the fixing of the fixing member 3 to the fixing block 4. Arc blocks are provided on both sides of the square block, which can facilitate identification of the rotation angle of the limit rod 31 when the limit rod 31 is rotated, and facilitate the plug-in cooperation between the limit rod 31 and the limit groove 42.

[0025] In some embodiments, the through hole 41 and the limiting rod 31 are clearance-matched, so that the limiting rod 31 can quickly pass through the through hole 41, and the limiting groove 42 and the limiting rod 31 are transitionally matched, so that the limiting rod 31 can move in the limiting groove 42. At the same time, the limiting groove 42 has a certain locking force on the limiting rod 31, thereby improving the locking effect of the locking ring 1 on the fixing seat 2.

[0026] In some embodiments, a felt layer is provided on the inner wall of the locking ring 1. The felt layer can be made of wool felt, which can increase the friction between the locking ring 1 and the missile and enhance the locking force. At the same time, it can protect the surface of the missile and avoid scratches on the surface of the missile.

[0027] The specific working principle is as follows:

[0028] When installation is required, the locking ring 1 is placed on the fixing seat 2, and after the limiting rod 31 passes through the through hole 41, the limiting rod 31 is placed in the rotating chamber 5, and the limiting rod 31 is rotated to make it plug and match with the limiting groove 42. The return spring 61 returns and rebounds to drive the limiting block 32 to rise, so that the top of the limiting rod 31 contacts the inner top wall of the limiting groove 42, and the limiting rod 31 does not slip off, so that the fixing part 3 and the fixing block 4 can be fixed, thereby realizing the fixing effect of the locking ring 1 on the fixing seat 2; when disassembly is required, it is only necessary to press the limiting block 32 to deform the return spring 61, and the limiting rod 31 moves into the rotating chamber 5 under the action of pressure, and rotate the limiting rod 31 to make the limiting rod 31 plug and match with the through hole 41, so as to release the fixation between the fixing part 3 and the fixing block 4, and realize the quick disassembly between the locking ring 1 and the fixing seat 2.

[0029] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A quick disassembly and assembly structure inside a missile packaging box, used to connect a locking ring (1) and a fixing seat (2), characterized in that: The invention comprises a fixing member (3), wherein the fixing member (3) is arranged through the locking ring (1), the fixing seat (2) is provided with a fixing groove, a fixing block (4) is arranged in the fixing groove, a rotating cavity (5) is arranged between the bottom of the fixing block (4) and the bottom of the fixing groove, a limiting rod (31) is arranged at the bottom of the fixing member (3), a through hole (41) is arranged through the fixing block (4), a limiting groove (42) is arranged at the bottom of the fixing block (4), the limiting groove (42) and the through hole (41) are arranged crosswise, the through hole (41) and the limiting groove (42) can be plugged and matched with the limiting rod (31), and a rebound member (6) is arranged on the fixing member (3), and the rebound member (6) is arranged between the top of the fixing member (3) and the locking ring (1).

2. The missile packaging box internal quick disassembly and assembly structure according to claim 1, characterized in that: A limiting block (32) is provided on the top of the fixing member (3), and the size of the limiting block (32) is larger than the size of the through hole (41).

3. The internal quick disassembly and assembly structure of a missile packaging box according to claim 2, characterized in that: The resilient member (6) comprises a resilient spring (61), a resilient sheet (62) is provided at the bottom of the resilient spring (61), and the top of the resilient spring (61) is connected to the bottom of the limiting block (32).

4. The missile packaging box internal quick disassembly and assembly structure according to claim 1, characterized in that: The limiting groove (42) is arranged perpendicularly to the through hole (41).

5. The missile packaging box internal quick disassembly and assembly structure according to claim 1, characterized in that: The limiting groove (42), the through hole (41) and the limiting rod (31) are all in a straight line shape.

6. The missile packaging box internal quick disassembly and assembly structure according to claim 5, characterized in that: The limiting rod (31) is coaxially fixed to the bottom of the fixing member (3).

7. The internal quick disassembly and assembly structure of a missile packaging box according to claim 2, characterized in that: The fixing member (3) is a square block, and arc blocks are provided on both sides of the square block.

8. The missile packaging box internal quick disassembly and assembly structure according to claim 1, characterized in that: The through hole (41) and the limiting rod (31) are clearance-matched, and the limiting groove (42) and the limiting rod (31) are transitionally matched.

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