Internal fixing structure of guided missile packaging box

Abstract

The utility model discloses an internal fixing structure of a guided missile packaging box, which relates to the field of guided missile fixing structures and comprises at least one fixing seat arranged in the packaging box, a locking ring is arranged on the fixing seat and comprises a first bearing groove and at least one second bearing groove, the locking ring comprises a first buckling ring and at least one second buckling ring, and the first buckling ring and the second buckling ring are arranged on the fixing seat. The first bearing groove and the first buckling ring are buckled to form a fixing cavity, the second bearing groove and the second buckling ring are buckled to form a fixing cavity, the fixing cavity is used for fixing a missile, one end of the first buckling ring is hinged to the fixing base, and the end, away from the first buckling ring, of the second buckling ring is detachably connected with the fixing base. According to the internal fixing structure of the guided missile packaging box, the multiple fixing cavities are formed between the locking ring and the fixing base, multiple guided missiles can be fixed at the same time, the assembling efficiency is improved, and the rapid assembling requirement of modern production can be met.

Description

Technical Field

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

[0002] With the rapid development of modern weapon systems, the safe transportation and efficient assembly of missiles have become important issues. The traditional missile packaging box design, due to the single fixing cavity structure between the locking ring and the fixing seat, requires each missile to be locked separately when fixing multiple missiles. This is not only time-consuming but also increases the complexity of assembly, resulting in low assembly efficiency and unable to meet the rapid assembly requirements of modern production. Utility Model Content

[0003] The purpose of the utility model is to provide an internal fixing structure of a missile packaging box. The internal fixing structure of the missile packaging box is provided with a plurality of fixing cavities between a locking ring and a fixing seat, so that a plurality of missiles can be fixed at the same time, thereby improving the assembly efficiency and meeting the rapid assembly requirements of modern production.

[0004] The above-mentioned optimized structure of the utility model is achieved through the following technical solutions: an internal fixing structure of a missile packaging box, comprising at least one fixing seat arranged in the packaging box, a locking ring being provided on the fixing seat, the fixing seat comprising a first supporting groove and at least one second supporting groove, the locking ring comprising a first buckling ring and at least one second buckling ring, the first supporting groove and the first buckling ring, the second supporting groove and the second buckling ring are buckled into a fixing cavity, the fixing cavity is used to fix the missile, one end of the first buckling ring is hinged to the fixing seat, and the second buckling ring is detachably connected to the fixing seat at one end away from the first buckling ring.

[0005] In some embodiments, the inner walls of the first supporting groove, the second supporting groove, the first buckling ring, and the second buckling ring are all provided with a felt layer.

[0006] In some embodiments, the locking ring includes a hinged arc plate, which is hinged to the fixed seat, and the hinged arc plate is connected to a rotating arc plate. The hinged arc plate and the rotating arc plate are spliced ​​into a first buckling ring, and at least one second buckling ring is connected to the end of the rotating arc plate away from the hinged arc plate.

[0007] In some embodiments, a connecting plate is horizontally connected between the rotating arc plate and the second buckling ring, at least two reinforcing plates are connected between the outer wall of the rotating arc plate and the outer wall of the second buckling ring, and the two reinforcing plates are vertically connected to the connecting plate.

[0008] In some embodiments, the two reinforcing plates are symmetrically arranged on the connecting plate.

[0009] In some embodiments, the hinged arc plate and the rotating arc plate are provided with at least one first hinge mechanism, the first hinge mechanism includes a cover plate, the cover plate is provided on the outer wall of the hinged arc plate close to the rotating arc plate, the cover plate is provided with a core shaft, the core shaft is provided with a bottom plate, and the bottom plate is fixed on the outer wall of the rotating arc plate close to the hinged arc plate.

[0010] In some embodiments, at least one second hinge mechanism is provided between the first buckling ring and the fixed seat, the second hinge mechanism includes a hinge seat fixed on the fixed seat, a rotating shaft is passed through the hinge seat, a bottom film is sleeved on the rotating shaft, and the bottom film is fixed on the outer wall of the first buckling ring at one end away from the second buckling ring.

[0011] In some embodiments, at least one fixing plate is provided at one end of the second buckling ring away from the first buckling ring, and a mounting hole is provided on the fixing plate.

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

[0013] The internal fixing structure of this missile packaging box is provided with multiple supporting grooves on the fixing seat, and multiple corresponding buckling rings are provided on the locking ring, so as to form multiple fixing cavities. When the locking ring is fixed on the fixing seat, multiple missiles can be fixed at the same time, which improves the assembly efficiency and can meet the rapid assembly requirements of modern production; at the same time, the first buckle ring is hinged on the fixing seat, and the rotating arc plate is hinged on the hinged arc plate, which can reduce the linear space occupied by the locking ring when multiple missiles are placed on the fixing seat, thereby improving the convenience of operation and making the loading and unloading process simpler and faster. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a schematic cross-sectional diagram of the installation of the utility model in a packaging box;

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

[0016] In the figure: 1. fixed seat; 11. first supporting groove; 12. second supporting groove; 2. locking ring; 21. first buckling ring; 22. second buckling ring; 23. hinged arc plate; 24. rotating arc plate; 3. connecting plate; 4. reinforcing plate; 5. first hinge mechanism; 51. cover plate; 52. core shaft; 53. bottom plate; 6. second hinge mechanism; 61. hinge seat; 62. rotating shaft; 63. bottom plate; 7. fixed plate. DETAILED DESCRIPTION

[0017] 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.

[0018] refer to Figure 1-2 , a missile packaging box internal fixing structure, comprising at least one fixing seat 1 arranged in the packaging box, a locking ring 2 is arranged on the fixing seat 1, the fixing seat 1 comprises a first supporting groove 11, at least one second supporting groove 12, the locking ring 2 comprises a first buckling ring 21, at least one second buckling ring 22, the first supporting groove 11 and the first buckling ring 21, the second supporting groove 12 and the second buckling ring 22 are buckled to form a fixing cavity, the fixing cavity is used to fix the missile, one end of the first buckling ring 21 is hinged to the fixing seat 1, the first buckling ring 21 can be rotated to achieve the buckling and separation between the locking ring 2 and the fixing seat 1, the second buckling ring 22 is provided with at least one fixing plate 7 at one end away from the first buckling ring 21, the fixing plate 7 is provided with a mounting hole, bolts or screws can be used to pass through the mounting hole to fix the fixing plate 7 on the fixing seat 1, so as to realize the installation of the locking ring 2 and the fixing seat 1, and then realize the fixation of multiple missiles in the fixing cavity, improve the assembly efficiency, and meet the rapid assembly requirements of modern production.

[0019] In some embodiments, the inner walls of the first supporting groove 11, the second supporting groove 12, the first buckling ring 21, and the second buckling ring 22 are all provided with a felt layer. The felt layer can increase the friction between the missile and the fixing cavity, thereby enhancing the fixing effect of the missile in the fixing cavity, while providing additional buffering protection and reducing possible scratches or damages to the surface of the missile during transportation.

[0020] The locking ring 2 also includes a hinged arc plate 23 and a rotating arc plate 24. The hinged arc plate 23 and the rotating arc plate 24 are spliced ​​into a first buckling ring 21. The rotating arc plate 24 is connected to at least one second buckling ring 22 at one end away from the hinged arc plate 23. At least one second hinge mechanism 6 is provided between the hinged arc plate 23 and the fixed seat 1. The second hinge mechanism 6 includes a hinge seat 61, a rotating shaft 62 and a bottom film 63. The bottom of the hinge seat 61 is fixed on the fixed seat 1 and can be fixed by bolts. A rotating shaft 62 is penetrated through the top of the hinge seat 61. A bottom film 63 is sleeved on the rotating shaft 62. The bottom film 63 is fixed on the outer wall of the first buckling ring 21 at one end away from the second buckling ring 22. The rotation of the bottom film 63 on the rotating shaft 62 can realize the rotation of the first buckling ring 21 on the fixed seat 1.

[0021] The hinged arc plate 23 is connected to the rotating arc plate 24, and the hinged arc plate 23 and the rotating arc plate 24 are provided with at least one first hinge mechanism 5, and the first hinge mechanism 5 includes a cover plate 51, a core shaft 52 and a bottom plate 53. The cover plate 51 is arranged on the outer wall of the hinged arc plate 23 on the side close to the rotating arc plate 24, and the cover plate 51 is provided with a core shaft 52, and the core shaft 52 is provided with a bottom plate 53, and the bottom plate 53 is fixed on the outer wall of the rotating arc plate 24 on the side close to the hinged arc plate 23. The rotation of the bottom plate 53 on the core shaft 52 can realize the rotation of the rotating arc plate 24 on the hinged arc plate 23, so that when the locking ring 2 rotates away from the fixed seat 1, the rotating arc plate 24 continues to rotate to realize double rotation, so that the rotating arc plate 24 and the second buckling ring 22 connected thereto face downward, thereby reducing the linear occupied space after the locking ring 2 is rotated, which is convenient for the installation and disassembly of the missile.

[0022] In some embodiments, a connecting plate 3 is horizontally connected between the rotating arc plate 24 and the second buckling ring 22, and at least two reinforcing plates 4 are connected between the outer wall of the rotating arc plate 24 and the outer wall of the second buckling ring 22. The two reinforcing plates 4 are vertically connected to the connecting plate 3 and are symmetrically arranged on the connecting plate 3, which can enhance the connection strength between the rotating arc plate 24 and the second buckling ring 22, thereby improving the fixing effect of multiple missiles at the same time.

[0023] The specific working principle is as follows:

[0024] Rotate the first buckling ring 21, and then rotate the rotating arc plate 24 to expose the first supporting groove 11 and the second supporting groove 12 on the fixing seat 1, place the missile on the first supporting groove 11 and the second supporting groove 12, rotate the rotating arc plate 24, and then rotate the first buckling ring 21 to make the first supporting groove 11 and the first buckling ring 21, and the second supporting groove 12 and the second buckling ring 22 buckle, and fix the fixing plate 7 to the fixing seat 1 by tools such as bolts or screws, so as to realize the simultaneous fixation of multiple missiles, thereby improving the assembly efficiency.

[0025] 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 missile packaging box internal fixing structure, comprising at least one fixing seat (1) arranged in the packaging box, wherein the fixing seat (1) is provided with a locking ring (2), characterized in that: The fixing seat (1) comprises a first supporting groove (11) and at least one second supporting groove (12); the locking ring (2) comprises a first buckling ring (21) and at least one second buckling ring (22); the first supporting groove (11) and the first buckling ring (21), the second supporting groove (12) and the second buckling ring (22) are buckled together to form a fixing cavity, the fixing cavity is used to fix the missile; one end of the first buckling ring (21) is hinged to the fixing seat (1), and one end of the second buckling ring (22) away from the first buckling ring (21) is detachably connected to the fixing seat (1).

2. The internal fixing structure of a missile packaging box according to claim 1, characterized in that: The inner walls of the first supporting groove (11), the second supporting groove (12), the first buckling ring (21), and the second buckling ring (22) are all provided with a felt layer.

3. The internal fixing structure of a missile packaging box according to claim 1, characterized in that: The locking ring (2) comprises a hinged arc plate (23), the hinged arc plate (23) being hinged to the fixing seat (1), the hinged arc plate (23) being connected to a rotating arc plate (24), the hinged arc plate (23) and the rotating arc plate (24) being spliced ​​to form a first buckling ring (21), and the rotating arc plate (24) having an end away from the hinged arc plate (23) being connected to at least one of the second buckling rings (22).

4. The internal fixing structure of a missile packaging box according to claim 3, characterized in that: A connecting plate (3) is horizontally connected between the rotating arc plate (24) and the second buckling ring (22), at least two reinforcing plates (4) are connected between the outer wall of the rotating arc plate (24) and the outer wall of the second buckling ring (22), and the two reinforcing plates (4) are vertically connected to the connecting plate (3).

5. The internal fixing structure of a missile packaging box according to claim 4, characterized in that: The two reinforcing plates (4) are symmetrically arranged on the connecting plate (3).

6. The internal fixing structure of a missile packaging box according to claim 3, characterized in that: The hinged arc plate (23) and the rotating arc plate (24) are provided with at least one first hinge mechanism (5), the first hinge mechanism (5) comprising a cover plate (51), the cover plate (51) being provided on an outer wall of the hinged arc plate (23) on a side close to the rotating arc plate (24), the cover plate (51) being provided with a core shaft (52), a bottom plate (53) being provided on the core shaft (52), the bottom plate (53) being fixed on an outer wall of the rotating arc plate (24) on a side close to the hinged arc plate (23).

7. The internal fixing structure of a missile packaging box according to claim 1, characterized in that: At least one second hinge mechanism (6) is provided between the first buckling ring (21) and the fixing seat (1), the second hinge mechanism (6) comprising a hinge seat (61) fixed on the fixing seat (1), a rotating shaft (62) passing through the hinge seat (61), a bottom film (63) sleeved on the rotating shaft (62), and the bottom film (63) fixed on the outer wall of an end of the first buckling ring (21) away from the second buckling ring (22).

8. The internal fixing structure of a missile packaging box according to claim 1, characterized in that: At least one fixing plate (7) is provided at one end of the second buckling ring (22) away from the first buckling ring (21), and a mounting hole is provided on the fixing plate (7).

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