Rocket combat cabin capable of absorbing impact
By designing a buffer device and a fast disassembly structure in the Rocket Battle Crystal, the problem of the existing Rocket Battle Cels under the impact of the device damage, and achieved higher impact resistance and simple maintenance process.
Patent Information
- Application Number
- CN202421284040.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-06
- Publication Date
- 2025-01-28
- Estimated Expiration
- 2034-06-06
AI Technical Summary
Existing rocket combat compartments are susceptible to shock during transportation and launch, resulting in damage to internal equipment in the warhead, increasing the risk of damage.
A rocket fighting cabin that includes the cabin, the bottom plate, the fixed column, the buffer spring, and the sealing component is designed. The combustion of the combat department is made by the buffer device to enhance the impact resistance and simplify the maintenance process through the rapid disassembly structure.
Effectively protect the internal sensitive equipment and electronic components inside the Battle Department, reduce the damage caused by the impact, improve the stability and reliability of the combat department, and simplify the maintenance and maintenance process.
Smart Images
Figure CN222418793U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of rockets, in particular to a rocket combat cabin capable of absorbing impacts. Background Art
[0002] The rocket combat cabin is an important component of the rocket. Most of them are directly fixed inside the rocket and are used to house the internal warhead and protect some precision devices inside the rocket.
[0003] Some existing rocket combat cabins directly fix the warhead inside the cabin, which will be subjected to various impacts and loads during rocket transportation and launch. Directly fixing the warhead inside the cabin may cause the warhead to be affected by greater impact, increasing the risk of damage to the internal equipment of the warhead. Therefore, a rocket combat cabin that can absorb impact is proposed to solve the above problem. Utility Model Content
[0004] In order to make up for the above shortcomings, the utility model provides a rocket combat cabin that can absorb impacts, aiming to improve the problem that some rocket combat cabins in the prior art directly fix the warhead inside their cabin, which will be subjected to various impacts and loads during rocket transportation and launch. Directly fixing the warhead inside the cabin may cause the warhead to be affected by greater impacts, increasing the risk of damage to the internal equipment of the warhead.
[0005] In order to achieve the above purpose, the utility model adopts the following technical solutions:
[0006] A rocket combat cabin capable of absorbing shocks, comprising a cabin, wherein the cabin is slidably connected to a bottom plate, the top of the bottom plate is fixedly connected to a warhead, a plurality of fixing columns are fixedly connected to the bottom end of the cabin, the outer sides of the plurality of fixing columns are sleeved with a buffer spring 1, the outer sides of the plurality of fixing columns are threadedly connected with a tightening ring 1, four sliding grooves are provided inside the cabin, the interior of the four sliding grooves are slidably connected with a sliding block, the outer side of the sliding block is fixedly connected with a fixing seat 1, the interior of the fixing seat 1 is slidably connected with two connecting columns, the outer sides of the two connecting columns are sleeved with a buffer spring 2, one end of the two connecting columns are fixedly connected to a limiting plate, the outer side of the warhead is fixedly connected with four fixing seats 2, the outer sides of the two connecting columns are threadedly connected with a tightening ring 2, and the interior of the cabin is slidably connected with a sealing component;
[0007] As a further description of the above technical solution:
[0008] The sealing assembly includes four card slots, a top cover, four placement slots, four card columns, four push springs, four push rings, a rotating disk and four pull rods. The four card slots are all opened inside the cabin body, the outer side of the top cover is slidably connected to the inside of the cabin body, a handle is rotatably connected inside the top end of the top cover, the four placement slots are all opened inside the top cover, the outer sides of the four card columns are slidably connected to the inside of the top cover, the four push springs are respectively arranged inside the four placement slots, the inner sides of the four push rings are respectively fixedly connected to the outer sides of the four card columns, the outer sides of the four rotating disks are rotatably connected to the inside of the top cover, and the outer sides of the four pull rods are respectively rotatably connected to the inside of the four card columns;
[0009] As a further description of the above technical solution:
[0010] The outer sides of the four clamping columns are respectively slidably connected to the insides of the four clamping slots, and the outer sides of the four clamping columns are respectively slidably connected to the insides of the four placement slots;
[0011] As a further description of the above technical solution:
[0012] The four push springs are respectively sleeved on the outer sides of the four clamping columns, and the outer sides of the four push springs are in contact with the outer sides of the four push rings;
[0013] As a further description of the above technical solution:
[0014] The outer sides of the four pushing rings are respectively slidably connected to the insides of the four pushing springs, and the top ends of the four pulling rods are rotatably connected to the bottom end of the rotating disk;
[0015] As a further description of the above technical solution:
[0016] The outer sides of the plurality of fixing columns are slidably connected to the inside of the bottom plate, and the bottom ends of the plurality of tightening rings are in contact with the top end of the bottom plate;
[0017] As a further description of the above technical solution:
[0018] The top ends of the plurality of buffer springs 1 are fixedly connected to the bottom end of the bottom plate, and the bottom ends of the plurality of buffer springs 1 are fixedly connected to the inner bottom end of the cabin;
[0019] As a further description of the above technical solution:
[0020] The interior of the cabin is fixedly connected to a limited seat, and both ends of the top and bottom of the outer side of the cabin are fixedly connected to fixing rings, and a plurality of fixing holes are opened inside the two fixing rings.
[0021] The utility model has the following beneficial effects:
[0022] 1. In the utility model, the buffer device can buffer the warhead in different directions through the cooperation of the fixed column, the buffer spring, the tightening ring and the bottom plate, thereby enhancing the overall impact resistance of the warhead, effectively protecting the sensitive equipment and electronic components inside the warhead, reducing the damage to the equipment caused by the impact, and improving the stability and reliability of the warhead.
[0023] 2. In the utility model, the quick disassembly of the warhead is achieved through the cooperation of structures such as the card slot, the card column, the push spring and the push ring, so that the maintenance and repair process of the warhead is simpler, the time required for maintenance is shortened, and the maintenance work efficiency is improved. BRIEF DESCRIPTION OF THE DRAWINGS
[0024] Figure 1 This is a three-dimensional schematic diagram of a rocket combat cabin capable of absorbing impact proposed by the utility model;
[0025] Figure 2 This is a schematic structural diagram of a bottom plate of a rocket combat cabin that can absorb impacts proposed by the utility model;
[0026] Figure 3 This is a schematic structural diagram of a rocket combat compartment warhead capable of absorbing impacts proposed by the utility model;
[0027] Figure 4 for Figure 2 The enlarged view of point A in the middle;
[0028] Figure 5 The utility model is a schematic structural diagram of a clamping column of a rocket combat compartment capable of absorbing impact.
[0029] Legend:
[0030] 1. Cabin; 2. Bottom plate; 3. Warhead; 4. Fixing column; 5. Buffer spring 1; 6. Tightening ring 1; 7. Sliding groove; 8. Sliding block; 9. Fixing seat 1; 10. Connecting column; 11. Buffer spring 2; 12. Limiting plate; 13. Fixing seat 2; 14. Tightening ring 2; 15. Slot; 16. Top cover; 17. Mounting groove; 18. Fixing column; 19. Push spring; 20. Push ring; 21. Rotating disk; 22. Pull rod; 23. Limiting seat; 24. Fixing ring; 25. Fixing hole; 26. Handle. DETAILED DESCRIPTION
[0031] 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 the embodiments. Based on the embodiments in 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.
[0032] Reference Figure 1-Figure 3 and Figure 4 The utility model provides an embodiment: a rocket combat cabin capable of absorbing impact, comprising a cabin body 1, a bottom plate 2 is slidably connected inside the cabin body 1, the bottom plate 2 is designed to facilitate fixing of a warhead 3, the top of the bottom plate 2 is fixedly connected with the warhead 3, a plurality of fixing columns 4 are fixedly connected to the bottom end of the cabin body 1, the fixing columns 4 are designed to cooperate with a buffer spring 5 and a tightening ring 6 to provide preliminary buffering for the bottom plate 2 and the warhead 3, a buffer spring 5 is sleeved on the outer sides of the plurality of fixing columns 4, the buffer spring 5 is designed to facilitate buffering of the bottom plate 2, a plurality of fixing columns 4 are threadedly connected on the outer sides with a tightening ring 6, the tightening ring 6 is designed to facilitate fixing of the bottom plate 2.
[0033] Four sliding grooves 7 are provided inside the cabin 1, and sliding blocks 8 are slidably connected inside the four sliding grooves 7. The sliding grooves 7 are designed to facilitate the sliding of the sliding blocks 8 inside them. A fixed seat 9 is fixedly connected to the outside of the sliding block 8. The sliding block 8 is designed to facilitate the fixation of the fixed seat 9. The inside of the fixed seat 9 is slidably connected with two connecting columns 10. The connecting columns 10 are designed to cooperate with the limiting plates 12 to squeeze the buffer springs 11. The outsides of the two connecting columns 10 are sleeved with buffer springs 11. The buffer springs 11 are designed to provide further buffering while being squeezed.
[0034] One end of the two connecting columns 10 is fixedly connected with a limiting plate 12, and the limiting plate 12 is designed to cooperate with the connecting column 10 to squeeze the buffer spring 11. The outer side of the warhead 3 is fixedly connected with four fixing seats 13, and the fixing seats 13 are designed to cooperate with the tightening ring 14. The buffer spring 11 is squeezed through the connecting column 10 and the limiting plate 12. The outer sides of the two connecting columns 10 are threadedly connected with a tightening ring 14, and the tightening ring 14 is designed to fix the connecting column 10. The interior of the cabin 1 is slidably connected with a sealing assembly, and the outer sides of multiple fixing columns 4 are slidably connected to the interior of the bottom plate 2. The fixing columns 4 are designed to cooperate with the buffer spring 5 and the tightening ring 6 to provide preliminary buffering for the bottom plate 2 and the warhead 3.
[0035] The bottom ends of multiple tightening rings 6 are in contact with the top end of the bottom plate 2, and the tightening rings 6 are designed to facilitate the fixing of the bottom plate 2. The top ends of multiple buffer springs 5 are fixedly connected to the bottom end of the bottom plate 2, and the bottom ends of multiple buffer springs 5 are fixedly connected to the inner bottom end of the cabin body 1. The buffer springs 5 are designed to facilitate the buffering of the bottom plate 2. The interior of the cabin body 1 is fixedly connected with a limiting seat 23, and the limiting seat 23 is designed to limit the top cover 16. The outer top and bottom ends of the cabin body 1 are fixedly connected with fixing rings 24, and the fixing rings 24 are designed to cooperate with the fixing holes 25 to fix the cabin body 1. Multiple fixing holes 25 are opened inside the two fixing rings 24.
[0036] like Figure 1-Figure 2 and Figure 5 As shown, the sealing assembly includes four card slots 15, a top cover 16, four placement slots 17, four card columns 18, four push springs 19, four push rings 20, a rotating disk 21 and four pull rods 22. The four card slots 15 are all opened inside the cabin body 1. The card slots 15 are designed to cooperate with the card columns 18 to fix the top cover 16. The outer side of the top cover 16 is slidably connected to the inside of the cabin body 1. The top cover 16 is designed to seal the cabin body 1. A handle 26 is rotatably connected to the top of the top cover 16. The handle 26 is designed to facilitate lifting the top cover 16. The four placement slots 17 are all opened inside the top cover 16. The placement slots 17 are designed to facilitate the placement of the card columns 18, the push springs 19 and the push rings 20.
[0037] The outer sides of the four posts 18 are slidably connected to the inside of the top cover 16. The post 18 is designed to cooperate with the slot 15 to fix the top cover 16. The four push springs 19 are respectively arranged in the four placement slots 17. The push springs 19 are designed to facilitate pushing the push rings 20, thereby pushing the post 18. The insides of the four push rings 20 are respectively fixedly connected to the outer sides of the four posts 18. The push ring 20 is designed to push the post 18 under the push of the push springs 19. The outer sides of the four rotating disks 21 are rotatably connected to the inside of the top cover 16. The rotating disk 21 is designed to facilitate driving the four pulling rods 22, thereby driving the post 18. The outer sides of the four pulling rods 22 are respectively rotatably connected to the inside of the four posts 18. The pulling rods 22 are designed to drive the post 18 to leave the inside of the slot 15 under the drive of the rotating disk 21.
[0038] The outer sides of the four clamping columns 18 are respectively slidably connected to the inside of the four clamping slots 15, and the outer sides of the four clamping columns 18 are respectively slidably connected to the inside of the four placement slots 17. The clamping columns 18 are designed to cooperate with the clamping slots 15 to fix the top cover 16. The four push springs 19 are respectively sleeved on the outer sides of the four clamping columns 18. The outer sides of the four push springs 19 are in contact with the outer sides of the four push rings 20. The push springs 19 are designed to facilitate pushing the push rings 20, thereby pushing the clamping columns 18. The outer sides of the four push rings 20 are respectively slidably connected to the inside of the four push springs 19. The push rings 20 are designed to push the clamping columns 18 under the push of the push springs 19. The top ends of the four pull rods 22 are rotatably connected to the bottom end of the rotating disk 21. The pull rods 22 are designed to drive the clamping columns 18 to leave the inside of the clamping slots 15 under the drive of the rotating disk 21.
[0039] Working principle: the cabin 1 is fixed directly to the inside of the rocket by a fixing device through a fixing ring 24 and a fixing hole 25. When the rocket explodes, the buffer spring 5 will cooperate with the tightening ring 6 to perform preliminary buffering on the bottom plate 2 and the warhead 3 to cope with the impact force generated by the rocket during launch, and the warhead 3 will also squeeze the buffer spring 2 11 in different directions through the connecting column 10 and the limit plate 12 to achieve further buffering. The buffer device buffers the warhead 3 in different directions, which enhances the overall impact resistance of the warhead 3, can effectively protect the sensitive equipment and electronic components inside the warhead 3, reduce equipment damage caused by impact, and improve the stability and reliability of the warhead 3. When the warhead 3 needs to be repaired, the rotating disk 21 can be rotated to drive the pulling rod 22, and then the card column 18 can be pulled to allow the card column 18 to leave the inside of the card slot 15. At this time, the top cover 16 can be taken out from the inside of the cabin 1 through the handle 26, and then through By loosening the tightening ring 1 6 and the tightening ring 2 14, the warhead 3 can be taken out from the interior of the cabin 1. After the warhead 3 is inspected and repaired, the bottom plate 2 is first aligned, and the fixing column 4 is slid back into the interior of the bottom plate 2 and fixed by the tightening ring 1 6. Then, the connecting column 10 and the tightening ring 2 14 are matched to further fix the warhead 3. Finally, the top cover 16 is put back into the interior of the cabin 1 and aligned. However, in the meantime, the rotating disk 21 needs to be rotated again. The rotating disk 21 pulls the clamping column 18 through the pulling rod 22, so that the clamping column 18 is completely immersed in the interior of the top cover 16, and no longer hinders the top cover 16 from entering the interior of the cabin 1. When the top cover 16 is completely entered into the interior of the cabin 1 and aligned, release your hand, and the pushing spring 19 will push the pushing ring 20 to push the clamping column 18 to engage in the interior of the slot 15. By quickly disassembling the warhead 3, the maintenance and inspection process of the warhead 3 is simplified, the time required for maintenance is shortened, and the maintenance work efficiency is improved.
[0040] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.
Claims
1. A rocket combat module capable of absorbing shock, comprising a module body (1), characterized in that: The interior of the cabin (1) is slidably connected to a bottom plate (2), the top of the bottom plate (2) is fixedly connected to a warhead (3), the interior bottom of the cabin (1) is fixedly connected to a plurality of fixing columns (4), the outer sides of the plurality of fixing columns (4) are sleeved with a buffer spring (5), the outer sides of the plurality of fixing columns (4) are threadedly connected to a tightening ring (6), the interior of the cabin (1) is provided with four sliding grooves (7), the interiors of the four sliding grooves (7) are slidably connected to sliding blocks (8), the sliding blocks ( The outer side of the warhead (3) is fixedly connected with a fixing seat (9), the inner side of the fixing seat (9) is slidably connected with two connecting columns (10), the outer sides of the two connecting columns (10) are sleeved with buffer springs (11), one ends of the two connecting columns (10) are fixedly connected with a limiting plate (12), the outer side of the warhead (3) is fixedly connected with four fixing seats (13), the outer sides of the two connecting columns (10) are threadedly connected with tightening rings (14), and the inner side of the cabin (1) is slidably connected with a sealing component.
2. A rocket combat module capable of absorbing shock according to claim 1, characterized in that: The sealing assembly comprises four card slots (15), a top cover (16), four placement slots (17), four card columns (18), four push springs (19), four push rings (20), a rotating disk (21) and four pull rods (22); the four card slots (15) are all arranged inside the cabin body (1); the outer side of the top cover (16) is slidably connected to the inside of the cabin body (1); a handle (26) is rotatably connected to the top of the top cover (16); the four placement slots (17) are all arranged on the The inside of the top cover (16), the outer sides of the four clamping columns (18) are slidably connected to the inside of the top cover (16), the four pushing springs (19) are respectively arranged inside the four accommodating grooves (17), the insides of the four pushing rings (20) are respectively fixedly connected to the outer sides of the four clamping columns (18), the outer sides of the four rotating disks (21) are rotatably connected to the inside of the top cover (16), and the outer sides of the four pulling rods (22) are respectively rotatably connected to the inside of the four clamping columns (18).
3. A rocket combat module capable of absorbing shock according to claim 2, characterized in that: The outer sides of the four clamping columns (18) are respectively slidably connected to the inside of the four clamping grooves (15), and the outer sides of the four clamping columns (18) are respectively slidably connected to the inside of the four placement grooves (17).
4. A rocket combat module capable of absorbing shock according to claim 2, characterized in that: The four push springs (19) are respectively sleeved on the outer sides of the four clamping columns (18), and the outer sides of the four push springs (19) are in contact with the outer sides of the four push rings (20).
5. The rocket combat module capable of absorbing shock according to claim 2, characterized in that: The outer sides of the four pushing rings (20) are respectively slidably connected to the insides of the four pushing springs (19), and the top ends of the four pulling rods (22) are rotatably connected to the bottom end of the rotating disk (21).
6. The rocket combat module capable of absorbing shock according to claim 1, characterized in that: The outer sides of the plurality of fixing columns (4) are slidably connected to the inside of the base plate (2), and the bottom ends of the plurality of tightening rings (6) are in contact with the top end of the base plate (2).
7. The rocket combat module capable of absorbing shock according to claim 1, characterized in that: The top ends of the plurality of buffer springs (5) are fixedly connected to the bottom end of the bottom plate (2), and the bottom ends of the plurality of buffer springs (5) are fixedly connected to the inner bottom end of the cabin (1).
8. The rocket combat module capable of absorbing shock according to claim 1, characterized in that: The interior of the cabin body (1) is fixedly connected to a limit seat (23), and both ends of the top and bottom of the outer side of the cabin body (1) are fixedly connected to fixing rings (24), and a plurality of fixing holes (25) are provided inside the two fixing rings (24).