Auxiliary missile fixing structure
By setting a fixed plate, slide rod and limit plate on the locking ring in the missile packaging box, combined with the adjustment device, the missile wing plate is locked, which solves the problems of displacement and safety hazards during missile transportation, and improves the fixing strength and stability.
Patent Information
- Application Number
- CN202421427351.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-21
- Publication Date
- 2025-03-18
- Estimated Expiration
- 2034-06-21
AI Technical Summary
Missiles are prone to vibration and displacement during long-distance transportation. The existing felt layer is insufficient friction, making it difficult to effectively fix the missile, which poses safety hazards.
A missile assisted fixing structure is designed, including a first fixing plate, a second fixing plate and a slide rod on the locking ring. The two limiting plates move up and down through the slide rod, and the distance adjustment between the limiting plates is realized through the adjustment device to lock the missile wing plate.
By enhancing the fixed strength and stability of the missile in the missile packaging box, it avoids the missile's displacement during transportation, reduces safety risks, and adapts to the locking of wing plates of different lengths to improve the use range.
Smart Images
Figure CN222629945U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of missile fixing, in particular to a missile auxiliary fixing structure. Background Art
[0002] A missile packaging box is a box used to package missiles for easy storage and transportation. A missile packaging box generally has a mounting seat inside the box, on which the missile is placed, and then the missile is locked on the mounting seat through a locking ring. A felt layer is usually provided on the inner ring of the locking ring to increase the friction between the missile and the locking ring, thereby fixing the missile.
[0003] However, during long-distance transportation of the missile, the missile will vibrate, and it is difficult to prevent the missile from moving on the mounting base only through the friction between the missile and the felt layer. At the same time, there are two wing panels on the top of the missile. The wing panels are protruding structures, and through holes are set at the locking ring corresponding to the wing panels, which will further reduce the friction between the missile and the felt layer, making the missile easy to move during transportation, posing certain safety hazards. Utility Model Content
[0004] The utility model aims to provide a missile auxiliary fixing structure, which can enhance the fixing strength of the missile in the missile packaging box and improve the stability of the missile installation, thereby avoiding the displacement of the missile during long-term transportation and reducing safety hazards.
[0005] The above-mentioned optimized structure of the utility model is realized through the following technical scheme: a missile auxiliary fixing structure, fixed on the locking ring in the missile packaging box, including a first fixing plate and a second fixing plate fixed on the locking ring, two sliding rods are penetrated between the first fixing plate and the second fixing plate, two limit plates are slidably provided on the two sliding rods, and an adjustment device is also provided between the first fixing plate and the second fixing plate, and the adjustment device is connected to the two limit plates.
[0006] In some embodiments, the locking ring includes a mounting groove, and the first fixing plate and the second fixing plate are respectively fixed to two side walls of the mounting groove.
[0007] In some embodiments, the adjusting device includes a rotating rod, one end of which passes through the first fixed plate, and the other end passes through the two limit plates, and is rotatably connected to the second fixed plate, and the rotating rod is screwed together with the two limit plates; the rotating rod passes through the first fixed plate and one end is connected to an adjusting block.
[0008] In some embodiments, the rotating rod is symmetrically provided with a first thread and a second thread, the first thread and the second thread are respectively screwed together with the limiting plate, and the spiral directions of the first thread and the second thread are opposite.
[0009] In some embodiments, a limit platform is provided between the first thread and the second thread.
[0010] In some embodiments, anti-slip sheets are provided on the sides of the two limiting plates close to each other.
[0011] In some embodiments, the anti-slip sheet is elastic rubber.
[0012] In some embodiments, a spring washer is sleeved on the rotating rod, and the spring washer is arranged between the adjusting block and the first fixing plate.
[0013] In summary, the utility model has the following beneficial effects:
[0014] This missile auxiliary fixing structure is provided with an adjustment device between the first fixing plate and the second fixing plate. Through the screw connection between the rotating rod and the two limiting plates, the rotation of the rotating rod can be converted into the movement of the two limiting plates, so that the two limiting plates are moved closer to or farther away from each other, thereby realizing the locking of the missile wing plate, enhancing the fixing strength of the missile in the missile packaging box, improving the stability of the missile installation, thereby avoiding the displacement of the missile during long-term transportation and reducing safety hazards; at the same time, the distance between the two limiting plates can be adjusted by rotating the rotating rod, thereby realizing the locking of wing plates of different lengths, thereby improving the scope of use of the auxiliary fixing structure. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] Figure 1 This is a schematic diagram of the installation of the utility model on a locking ring;
[0016] Figure 2 It is an enlarged view of point A of the present utility model.
[0017] In the figure: 1, locking ring; 11, mounting groove; 2, first fixing plate; 3, second fixing plate; 4, sliding rod; 5, limiting plate; 6, adjusting device; 61, rotating rod; 62, adjusting block; 63, spring washer. DETAILED DESCRIPTION
[0018] 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.
[0019] refer to Figure 1-2 A missile auxiliary fixing structure is fixed on a locking ring 1 in a missile packaging box for use, comprising a first fixing plate 2 and a second fixing plate 3. The locking ring 1 is provided with a mounting groove 11, which can be located in the middle of the locking ring 1 to increase the force stability of the locking ring 1. The first fixing plate 2 and the second fixing plate 3 are respectively fixed on the two side walls of the mounting groove 11, and can be fixed by welding; two sliding rods 4 are penetrated between the first fixing plate 2 and the second fixing plate 3 to enhance the connection strength between the first fixing plate 2 and the second fixing plate 3, and the two sliding rods 4 is provided with two limit plates 5, the two limit plates 5 can slide on the two slide bars 4, an adjusting device 6 is also provided between the first fixing plate 2 and the second fixing plate 3, the adjusting device 6 is connected with the two limit plates 5, the distance between the two limit plates 5 can be adjusted by the adjusting device 6, and the two ends of the two wing plates are clamped by the two limit plates 5, so as to lock the missile wing plate, enhance the fixing strength of the missile in the missile packaging box, improve the stability of the missile installation, thereby avoiding the displacement phenomenon of the missile during long-term transportation and reducing safety hazards.
[0020] The adjusting device 6 includes a rotating rod 61 and an adjusting block 62. One end of the rotating rod 61 passes through the first fixed plate 2, and the other end passes through the two limit plates 5 and extends to the second fixed plate 3. It is embedded in the second fixed plate 3 and can be rotated on the second fixed plate 3. The rotating rod 61 is symmetrically provided with a first thread and a second thread, and a limit platform is provided between the first thread and the second thread. The first thread and the second thread are respectively screwed with the limit plate 5, so that the rotation of the rotating rod 61 can be converted into the movement of the limit plate 5. The spiral directions of the first thread and the second thread are opposite, so that the synchronous movement of the two limit plates 5 can be realized, which is convenient for adjusting the distance between the two limit plates 5; the rotating rod 61 passes through one end of the first fixed plate 2 and is connected to the adjusting block 62. The adjusting block 62 is provided with an adjusting groove at the end away from the rotating rod 61. The adjusting groove can be square or regular hexagonal, and the adjusting block 62 can be adjusted using tools.
[0021] In some embodiments, the two limiting plates 5 are provided with anti-skid sheets on the side close to each other. The anti-skid sheets can be elastic rubber, which can protect the missile wing. At the same time, the elastic deformation of the anti-skid sheets can increase the locking force between the missile wing and the limiting plates 5, thereby improving the installation stability of the missile in the missile packaging box.
[0022] In some embodiments, a spring washer 63 is sleeved on the rotating rod 61 . The spring washer 63 is disposed between the adjustment block 62 and the first fixed plate 2 , which can reduce the vibration between the adjustment block 62 and the first fixed plate 2 and protect the adjustment device 6 .
[0023] 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.
[0024] The specific working principle is as follows:
[0025] Place the missile on the mounting seat, cover the locking ring 1 to lock the missile, and place the missile's wing plate in the mounting groove 11. Use a tool to rotate the adjustment block 62 to drive the rotating rod 61 to rotate, so that the two limit plates 5 screwed thereto are close to each other until they are tightly fitted at both ends of the wing plate, thereby locking the wing plate and improving the fixing strength of the missile in the missile packaging box. Use a tool to rotate the adjustment block 62 in the opposite direction to move the two limit plates 5 away from each other, so that the wing plate can be locked.
[0026] 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 auxiliary fixing structure, fixed on a locking ring (1) in a missile packaging box, characterized in that: It comprises a first fixing plate (2) and a second fixing plate (3) fixed on the locking ring (1); two sliding rods (4) are provided between the first fixing plate (2) and the second fixing plate (3); two limit plates (5) are slidably provided on the two sliding rods (4); an adjusting device (6) is also provided between the first fixing plate (2) and the second fixing plate (3); the adjusting device (6) is connected to the two limit plates (5).
2. A missile auxiliary fixing structure according to claim 1, characterized in that: The locking ring (1) comprises a mounting groove (11), and the first fixing plate (2) and the second fixing plate (3) are respectively fixedly disposed on two side walls of the mounting groove (11).
3. A missile auxiliary fixing structure according to claim 1, characterized in that: The adjusting device (6) comprises a rotating rod (61), one end of which passes through the first fixing plate (2), and the other end of which passes through the two limiting plates (5) and is rotatably connected to the second fixing plate (3), and the rotating rod (61) is threadedly engaged with the two limiting plates (5); one end of the rotating rod (61) passes through the first fixing plate (2) and is connected to an adjusting block (62).
4. A missile auxiliary fixing structure according to claim 3, characterized in that: The rotating rod (61) is symmetrically provided with a first thread and a second thread, the first thread and the second thread are respectively threadedly engaged with the limiting plate (5), and the spiral directions of the first thread and the second thread are opposite.
5. A missile auxiliary fixing structure according to claim 4, characterized in that: A limiting platform is provided between the first thread and the second thread.
6. A missile auxiliary fixing structure according to claim 1, characterized in that: The two limit plates (5) are provided with anti-slip sheets on the sides close to each other.
7. A missile auxiliary fixing structure according to claim 6, characterized in that: The anti-slip sheet is made of elastic rubber.
8. The missile auxiliary fixing structure according to claim 3, characterized in that: A spring washer (63) is sleeved on the rotating rod (61), and the spring washer (63) is arranged between the adjusting block (62) and the first fixing plate (2).