Flame-retardant missile protection box

Abstract

The utility model discloses a flame-retardant missile protection box, which comprises a box body, a missile cavity, a port, a box cover and the like, and is mainly characterized in that an elastic damping seat is arranged at the head part of the missile cavity in the box body, the elastic damping seat wraps the head part of a missile through a profiling groove, an elastic sealing seat is arranged at the tail part of the missile cavity, and the elastic sealing seat also wraps the tail part of the missile through a profiling groove. A gland in threaded connection is arranged in the port, and when the gland is screwed into the port through threads, the gland can axially push the elastic sealing seat, so that the elastic sealing seat is matched with the elastic damping seat to jointly form axial clamping damping support for the guided missile, and meanwhile, the outer peripheral surface of the front end of the elastic sealing seat is tightly attached to the inner peripheral surface of the port to form radial interference fit sealing; therefore, the improved structure not only has better sealing performance, but also can form integrated damping and buffering for the guided missile loaded in the guided missile cavity, and has the advantages of high operation efficiency, high space utilization rate and the like, and particularly, the box body is provided with multiple layers of box walls, so that battlefield environment adaptability functions such as flame retardance and shock resistance can be integrated.

Description

Technical Field

[0001] This utility model relates to a protective box, specifically a flame-retardant missile protective box. Background Technology

[0002] Existing missile protection boxes are mostly manufactured using rotational molding. This process offers advantages such as seamless construction, strong corrosion resistance, and flexible design. A typical structure includes the box body, missile cavity, ports, and a cover. During use, the missile must be pre-loaded into a special protective frame before being placed into the missile cavity. This structure has significant drawbacks:

[0003] 1. The existing container lacks an integrated shock absorption structure for the missile, and shock absorption at the missile's nose and tail must rely entirely on the protective frame. 2. For small missiles, there is redundancy in the dimensions between the protective frame and the missile cavity, which makes the loaded missile susceptible to shaking. Furthermore, when loading multiple small missiles, the protective frame must be installed individually, reducing operational efficiency and the space utilization within the missile cavity, resulting in a serious waste of transportation resources. 3. The existing container cover relies on a single sealing ring pressed against the container end face for sealing, which is prone to sealing failure in humid and explosive environments in the field. 4. The container structure does not integrate flame-retardant, shock-resistant, or other battlefield environment adaptability functions. Utility Model Content

[0004] The technical problem to be solved by this utility model is to overcome the defects of the prior art and provide a flame-retardant missile protection box with good sealing performance, integrated shock absorption and buffer for the loaded missile, improved operation efficiency and space utilization, and integrated flame-retardant, shockproof and other battlefield environment adaptability functions.

[0005] The technical problem of this utility model is solved by the following technical solution:

[0006] A flame-retardant missile protection box includes a box body, a missile cavity disposed within the box body, a port disposed at one end of the box body for loading the missile into the missile cavity, and a box cover. The head of the missile cavity is provided with an elastic shock-absorbing seat, which has a contoured groove for wrapping the missile head. The tail of the missile cavity is provided with an elastic sealing seat, which has a contoured groove for wrapping the missile tail. The port is provided with a threaded pressure cap, which is screwed into the port and axially pushes the elastic sealing seat, so that the elastic sealing seat and the elastic shock-absorbing seat together form an axial clamping and shock-absorbing support for the missile. At the same time, the outer peripheral surface of the front end of the elastic sealing seat is tightly pressed against the inner peripheral surface of the port to form a radial interference fit seal. The box cover can be detachably closed to the port and the pressure cap is sealed inside.

[0007] The box body has multiple layers of box walls, which, from the inside out, include a shock-absorbing layer that forms the inner wall of the missile cavity, a buffer layer that absorbs impact energy, and a flame-retardant layer with fire-resistant function. The shock-absorbing layer, buffer layer, and flame-retardant layer are bonded together by high-temperature hot pressing or adhesive bonding to form an integral box wall structure.

[0008] The flame-retardant layer is a high-density polyethylene layer with added flame-retardant materials, and the buffer layer is filled with PU material or PE foam material.

[0009] The outer peripheral surface of the front end of the elastic sealing seat and the inner peripheral surface of the port form a conical fit.

[0010] The elastic sealing seat has an annular flange at its rear end, which forms an embedded connection with the groove on the inner end face of the pressure cover. The elastic sealing seat has a stepped structure in the middle that protrudes radially and allows the pressure cover to be pushed axially.

[0011] The box contains at least two missile cavities arranged side by side, and the adjacent missile cavities are separated by an integrally formed fireproof groove. The outer structure of the fireproof groove is the same as the flame-retardant layer of the box.

[0012] The box body has connecting rods at both ends of the bottom for securing with straps.

[0013] The top surface of the box is provided with multiple embedded handle slots and stacking positioning slots, and the bottom surface of the box is provided with multiple support feet.

[0014] The two sides of the box are each provided with multiple indicator arrows to indicate the stacking direction of the boxes.

[0015] The lid and body of the box are provided with multiple fire-resistant quick-release locks, each of which includes a lock hook on the side of the box body and a lock ring on the side of the lid.

[0016] Compared with the prior art, the main difference in this invention is that an elastic damping seat is provided at the head of the missile cavity within the housing, and this elastic damping seat has a contoured groove that wraps around the missile head. An elastic sealing seat is provided at the tail of the missile cavity, and this elastic sealing seat has a contoured groove that wraps around the missile tail. A threaded cap is provided at the port where the missile is loaded into the missile cavity. When the cap is screwed into the port, it axially pushes against the elastic sealing seat, so that the elastic sealing seat and the elastic damping seat together form an axial clamping and damping support for the missile. Simultaneously, the outer circumferential surface of the front end of the elastic sealing seat is tightly pressed against the inner circumferential surface of the port to form a radial interference fit seal. Therefore, through the above structural improvements, the sealing performance of the port can be improved. It can also provide axial clamping and shock-absorbing support for the missile's nose and tail, forming an integrated shock absorption buffer for the missile loaded inside the missile cavity. This better protects the internal missile and avoids the risk of swaying after loading. In particular, this structure eliminates the need for a traditional protective frame, thus effectively improving operational efficiency and the utilization of space within the missile cavity, preventing the waste of transportation resources. At the same time, the lid can be detachably closed at the port and the pressure cap is sealed inside, which further enhances protection. In addition, the box wall is integrally formed by high-temperature hot pressing or adhesive bonding of shock-absorbing layers, buffer layers, and flame-retardant layers, enabling the box to integrate flame-retardant, shock-absorbing, and other battlefield environment adaptability functions. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of this utility model.

[0018] Figure 2 for Figure 1 Top view.

[0019] Figure 3 for Figure 2 Sectional view A-A.

[0020] Figure 4 for Figure 1 Enlarged B-B sectional view.

[0021] Figure 5 for Figure 1 One of the perspective stereoscopic views.

[0022] Figure 6 for Figure 1 Another perspective stereoscopic view.

[0023] Figure 7 This is an enlarged cross-sectional view of the resilient sealing seat.

[0024] Figure 8 This is an enlarged cross-sectional view of the gland.

[0025] Figure 9 Enlarged cross-sectional view of the sealing seat and gland installed inside the port.

[0026] Figure 10 This is a magnified cross-sectional view of the port. Detailed Implementation

[0027] The embodiments of this utility model will now be described in detail with reference to the accompanying drawings.

[0028] like Figures 1-10 As shown, 1. Box body, 10. Port, 101. Internal thread, 11. Connecting rod, 12. Support foot, 13. Indicator arrow, 14. Handle groove, 15. Stacking positioning groove, 16. Fireproof reinforcement groove, 17. Reinforcing groove, 18. Multi-layer box wall, 181. Shock-absorbing layer, 182. Buffer layer, 183. Flame-retardant layer, 19. Missile cavity, 2. Box cover, 21. Lock, 3. Missile, 4. Elastic shock-absorbing seat, 5. Elastic sealing seat, 51. Annular flange, 52. Stepped structure, 6. Pressure cap, 61. Groove, 62. External thread, 7. Contouring groove. The same labels in each figure represent the same components.

[0029] A flame-retardant missile protective box, such as Figure 1 As shown, this device can be used for the storage and preservation of small missiles, such as those approximately 20cm-60cm in length, 30mm-50mm in diameter, and weighing 1kg-5kg. Its structure includes a housing 1, a missile cavity 19 within the housing, a port 10 located at one end of the housing for loading the missile 3 into the missile cavity 19, and a housing cover 2. This embodiment uses... Figure 3 The left side of the view shown represents the front or head of the missile protection box, while the right side represents the rear or tail of the missile protection box.

[0030] The box 1 is rectangular in shape, with multiple embedded handle slots 14 and stacking positioning slots 15 on the top surface of the box, and multiple support feet 12 on the bottom surface of the box 1.

[0031] This implementation example Figure 5 The diagram shows six handle slots on each side of the top surface of the container. These six handle slots are evenly distributed along the length of the container, allowing personnel to be rationally distributed on both sides of the container based on its weight. The container can then be easily lifted using the handle slots on both sides. Figure 5 As shown in the example, the box can accommodate 6 people on each side. In extreme cases, when multiple people work together, a total of 12 people can lift the box together through the corresponding 12 handle slots.

[0032] The stacking positioning slot is a rectangular slot with an inverted trapezoidal cross-section, as shown in this embodiment. Figure 5The diagram shows that there are 6 sets of stacking positioning slots on the top surface of the box. These 6 sets of stacking positioning slots are equidistantly distributed along the length of the box. Each set has two stacking positioning slots, which are respectively set on both sides of the top surface of the box and arranged in a centrally symmetrical manner. Therefore, a total of 12 stacking positioning slots are designed on the top surface of the box.

[0033] Therefore, the bottom of the box needs to have 12 support feet to match the number of stacking positioning slots. These 12 support feet also need to correspond to the 12 stacking positioning slots, and the outline of each support foot should match the inner outline of the stacking positioning slot. The purpose of this design is to ensure that a single box can be placed stably on the ground by being supported by these 12 support feet. When two boxes are stacked, the 12 support feet on the bottom of one box can be fitted into the 12 stacking positioning slots on the top of the other box, thus ensuring the stability of the two boxes after stacking.

[0034] The box 1 has multiple indicator arrows 13 on both sides. These multiple indicator arrows are equidistant along the length of the box 1 and have the same direction. The purpose is to indicate the stacking direction of the box 1 so that users can accurately place or stack the box 1 and avoid safety hazards caused by inverted placement.

[0035] The box body is provided with connecting rods 11 at both ends of the bottom for securing with straps. For example, in this embodiment... Figure 6 As shown, connecting rods 11 are provided on both sides of the bottom of one end of the box. During transportation, the box 1 can be fastened to the carrier by passing straps through the connecting rods. Alternatively, multiple stacked boxes 1 can be connected and fastened to each other by passing straps through their respective connecting rods 11.

[0036] The enclosure 1 has multiple layers of enclosure walls 18. These multiple layers of enclosure walls, from the inside out, include a shock-absorbing layer 181 forming the inner wall of the missile cavity 19, a buffer layer 182 absorbing impact energy, and a flame-retardant layer 183 with fire-resistant function. The shock-absorbing layer 181, the buffer layer 182, and the flame-retardant layer 183 are bonded together by high-temperature hot pressing or adhesive bonding to form an integral enclosure wall structure. The flame-retardant layer 183 can be a high-density polyethylene layer with added flame-retardant materials, while the buffer layer 182 is filled with PU material or PE foam material, etc. Therefore, through the multi-layer structure design of the enclosure walls, the enclosure 1 can integrate battlefield environment adaptability functions such as flame retardancy and shock absorption.

[0037] The housing 1 is provided with at least two missile cavities 19 arranged side by side, for example in this embodiment. Figure 4The diagram shows two missile cavities arranged side by side. Each missile cavity 19 extends along the length of the housing 1. Adjacent missile cavities 19 are separated by an integrally formed fireproof groove 16. This fireproof groove is a triangular groove structure with a V-shaped cross-section, which is recessed inward from both the top and bottom surfaces of the housing. The fireproof grooves 16 on the top and bottom surfaces of the housing are exactly on the same vertical line.

[0038] Furthermore, there are six fireproof grooves in the middle of the top surface or the middle of the bottom surface of the enclosure. These six fireproof grooves are equidistantly distributed along the length of the enclosure, and the center lines of the six fireproof grooves coincide with the center line of the length of the enclosure, that is, the six fireproof grooves form a straight line. Then, there are reinforcing grooves at the beginning and end of the six fireproof grooves, as well as between each pair of adjacent fireproof grooves, so there are exactly seven reinforcing grooves. The center line of each reinforcing groove is perpendicular to the center line of each fireproof groove.

[0039] The outer structure of the stacking positioning groove 15, handle groove 14, reinforcing groove 17, fireproof reinforcing groove 16, and support foot 12 is the same as the flame-retardant layer 183 of the box body 1, and is integrally manufactured with the box body. Moreover, the fireproof reinforcing groove 16 and reinforcing groove 17 provided on the top and bottom surfaces of the box body are the same in position, number, and size, and serve the same function.

[0040] The head of the missile cavity 19 is provided with an elastic shock-absorbing seat 4, which has a contoured groove that wraps around the missile head. The tail of the missile cavity 19 is provided with an elastic sealing seat 5, which has a contoured groove 7 that wraps around the missile tail. Both the elastic shock-absorbing seat 4 and the elastic sealing seat 5 are made of rubber or silicone.

[0041] The port is equipped with a threaded cap 6, which is connected to the inner thread 101 of the port through the external thread 62 on the outer circumferential surface. In this embodiment, a trapezoidal thread connection is selected to form an anti-loosening mechanism. The cap 6 is screwed into the port through the thread and pushes the elastic sealing seat 5 axially, so that the elastic sealing seat 5 and the elastic damping seat 4 together form a clamping and damping support for the missile 3 in the axial direction. At the same time, the outer circumferential surface of the front end of the elastic sealing seat 5 is tightly attached to the inner circumferential surface of the port to form a radial interference fit seal.

[0042] In this embodiment, the outer peripheral surface of the front end of the elastic sealing seat 5 forms a conical fit with the inner peripheral surface of the port. A cone angle of 30° to 45° is preferred. Therefore, the tighter the gland 6 is screwed into the port, the greater the sealing performance. Then, the gland 6 is screwed into the port to its extreme position, as shown in the example... Figure 10 The axial length of the internal thread 101 on the inner circumferential surface of the port 10 shown is limited.

[0043] Therefore, through the above structural improvements, the sealing performance of port 10 can be improved, and axial clamping and shock-absorbing support can be formed for the missile head and tail. In other words, an integrated shock-absorbing buffer can be formed for the missile 3 loaded in the missile cavity 19, thereby better protecting the internal missile and avoiding the risk of shaking of the missile 3 after loading. In particular, this structure also eliminates the traditional protective frame, thus effectively improving the operational efficiency and the space utilization rate inside the missile cavity, and preventing the waste of transportation resources.

[0044] The elastic sealing seat 5 has an annular flange 51 at its rear end. The annular flange forms an embedded connection with the groove 61 on the inner end face of the pressure cover 6. The purpose is to allow the pressure cover 6 to better push the elastic sealing seat 5 axially. The elastic sealing seat has a stepped structure 52 in the middle that protrudes radially and allows the pressure cover 6 to push axially. It can better guide the pushing force of the pressure cover 6 to act completely on the elastic sealing seat 5.

[0045] The lid 2 can be detachably closed to the port 10 and the pressure cap 6 is sealed inside, thereby further enhancing protection. Of course, since the port 10 has already been sealed by the elastic sealing seat 5 pushed by the pressure cap 6, the lid 2 only needs to close the port 10. At this time, the material characteristics of the lid 2 and the box body 1 can also provide a certain sealing performance, thereby better ensuring the sealing of the box body in the field, wet and explosive vibration environment.

[0046] The detachable structure of the lid 2 is provided with multiple fireproof quick-release locks 21 between the lid 2 and the box body 1. For example, it needs to comply with the GJB5792-2006 military quick-release lock specification. There are many types of quick-release locks 21. The quick-release lock 2 involved in this embodiment includes a locking hook on the side of the box body and a locking ring on the side of the lid. That is, when the locking ring is connected to the locking hook, the lid can be closed on the box body and the port 10 is sealed. When the locking ring is disengaged from the locking hook, the lid can be easily removed from the box body to expose the pressure cap 6 inside the port 10.

[0047] The operation process of this utility model is as follows: When the new missile protection box is put into use, the elastic shock absorber 1 is first fitted onto the missile head through the contour groove. Then, the missile head, together with the elastic shock absorber 1, is inserted into the missile cavity 19 through the open port 10 until the missile head pushes the elastic shock absorber 4 to the head of the missile cavity 19. Then, the elastic sealing seat 5 is inserted through the port 10, and the tail of the missile is inserted into the contour groove 7 of the elastic sealing seat 5. Then, the pressure cover 6 is threaded into the port 10. As the pressure cover 6 is screwed into the port 10, it pushes the elastic sealing seat 5 axially, so that the elastic sealing seat 5 and the elastic shock absorber 4 together form an axial clamping and shock-absorbing support for the missile 3. At the same time, the outer peripheral surface of the front end of the elastic sealing seat 5 is tightly attached to the inner peripheral surface of the port 10 through the conical surface, thereby forming a radial interference fit seal. Finally, the box cover 2 can be closed to the port 10 by using multiple fireproof quick-release locks 21, thereby also sealing the pressure cover 6 inside.

[0048] When missile 3 needs to be removed, simply remove the cover 2, the pressure cap 6, and the elastic sealing seat 5 in sequence to remove missile 3 completely from missile cavity 19. At this time, the elastic shock absorber 4 of the missile head will remain directly in the head of missile cavity 19. For example, the missile head can be detached without being pulled out by the elastic shock absorber 4 through size design or the friction of the outer surface. Therefore, when missile 3 is reinstalled, there is no need to first install the elastic shock absorber 4 on the missile head. Simply push the missile head into missile cavity 19 until the missile head is reinstalled in the contour groove of the elastic shock absorber 4. This simplifies the operation steps and allows for reuse.

[0049] The basic principles and main features of this utility model have been described above. Those skilled in the art should understand that this utility model is not limited to the above embodiments. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the utility model as claimed. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. A flame-retardant missile protection box, comprising a box body (1), a missile cavity (19) disposed within the box body, a port (10) disposed at one end of the box body for loading a missile (3) into the missile cavity (19), and a box cover (2), characterized in that: The head of the missile cavity (19) is provided with an elastic damping seat (4), and the elastic damping seat is provided with a contoured groove that wraps around the head of the missile. The tail of the missile cavity (19) is provided with an elastic sealing seat (5), and the elastic sealing seat is provided with a contoured groove (7) that wraps around the tail of the missile. The port (10) is provided with a threaded cover (6), which is screwed into the port (10) and pushes the elastic sealing seat (5) axially, so that the elastic sealing seat (5) and the elastic damping seat (4) together form a clamping and damping support for the missile (3) in the axial direction. At the same time, the outer peripheral surface of the front end of the elastic sealing seat (5) is tightly attached to the inner peripheral surface of the port (10) to form a radial interference fit seal. The lid (2) is detachably closed to the port (10) and encloses the cover (6) inside.

2. A flame resistant missile shelter in accordance with claim 1, wherein The box body (1) has multiple layers of box walls (18), which, from the inside out, include a shock-absorbing layer (181) forming the inner wall of the missile cavity (19), a buffer layer (182) absorbing impact energy, and a flame-retardant layer (183) with fire-proof function. The shock-absorbing layer (181), the buffer layer (182), and the flame-retardant layer (183) are formed into an integral box wall structure by high-temperature hot pressing or adhesive bonding.

3. A flame resistant missile shelter according to claim 2, characterised in that The flame-retardant layer (183) is a high-density polyethylene layer with added flame-retardant materials, and the buffer layer (182) is filled with PU material or PE foam material.

4. A flame resistant missile shelter kit according to claim 1, wherein The outer peripheral surface of the front end of the elastic sealing seat (5) and the inner peripheral surface of the port (10) form a conical fit.

5. A flame resistant missile shelter kit according to claim 1 wherein The elastic sealing seat (5) has an annular flange (51) at its rear end. The annular flange forms an embedded connection with the groove (61) on the inner end face of the pressure cover (6). The elastic sealing seat (5) has a stepped structure (52) that protrudes radially and allows the pressure cover (6) to be pushed axially in the middle.

6. A flame resistant missile shelter kit according to claim 2, wherein The box (1) is provided with at least two missile cavities (19) arranged side by side. The adjacent missile cavities are separated by an integrally formed fireproof groove (16). The outer structure of the fireproof groove (16) is the same as the flame-retardant layer (183) of the box (1).

7. A flame resistant missile shelter kit according to claim 1 wherein The box body (1) has connecting rods (11) at both ends of the bottom for securing with straps.

8. A flame resistant missile shelter kit according to claim 1 wherein The top surface of the box (1) is provided with multiple embedded handle grooves (14) and stacking positioning grooves (15), and the bottom surface of the box (1) is provided with multiple support feet (12).

9. A flame resistant missile shelter kit according to claim 1 wherein The box (1) has multiple indicator arrows (13) on both sides to indicate the stacking direction of the boxes.

10. A flame resistant missile shelter kit according to claim 1 wherein The lid (2) and the body (1) are provided with multiple fireproof quick-release locks (21), each quick-release lock (21) including a lock hook on the side of the body and a lock ring on the side of the lid.

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