Control cabin body part based on missile cabin body
By using missile cabin parts made of carbon fiber composite materials, combined with the rolling tube process and conductive paint layer, the problem of inaccurate docking of traditional missile barrels is solved, and the effect of light volume, high strength and accurate docking is achieved.
Patent Information
- Application Number
- CN202421643670.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-11
- Publication Date
- 2025-04-29
- Estimated Expiration
- 2034-07-11
AI Technical Summary
Traditional missile cylinders are made of metal materials, which are heavy in volume and are prone to position deviations when connected.
The cylinder made of carbon fiber composite material is formed by a rolling tube process and a conductive paint layer is sprayed on the surface of the cylinder. The front frame of the cylinder is inserted through the side of the installation, and the restriction bar and the restriction groove are used to achieve accurate docking to prevent position deviation.
The missile bay body is light in size and high in strength, and the position deviation during docking is avoided through precise docking technology.
Smart Images
Figure CN222812276U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of missile cabins, in particular to a control cabin component based on a missile cabin. Background Art
[0002] The missile carbon fiber cabin is used to install missile-borne components and is combined with other components to form a missile. It includes three cabins: the guidance cabin, the connection cabin and the control cabin. The control cabin is a structural component and an important part of the missile.
[0003] Traditional cylinders are made of metal materials, which are heavy and have no restrictions on the docking installation between the cylinder and the front frame, resulting in position deviation between the two after docking installation. Therefore, a control cabin component based on the missile cabin is proposed. Utility Model Content
[0004] 1. Technical issues to be resolved
[0005] In view of the deficiencies in the prior art, the utility model provides a control cabin component based on a missile cabin, which has the advantages of being light in size and not expensive to dock, thereby solving the above-mentioned problems.
[0006] (II) Technical solution
[0007] In order to achieve the above-mentioned purpose of light volume and inexpensive docking, the utility model provides the following technical solutions: a control cabin component based on a missile cabin, including a cylinder, a front frame is installed through the side of the cylinder, and four evenly distributed mounting parts are arranged on the surface of the cylinder, a notch A is opened on one side of the cylinder, a notch B is opened on the other side of the cylinder, a frame groove is opened on the inner wall of the cylinder, a frame ring is fixedly installed on the side of the front frame, a protrusion A is fixedly installed on one side of the front frame, and a protrusion B is fixedly installed on the other side of the front frame, limiting strips are fixedly installed on the surfaces of the protrusion A and the protrusion B, a limiting groove is opened on the inner wall of the frame groove, a bracket is fixedly installed on the surface of the protrusion A, and a mounting plate is fixedly installed on the surface of the protrusion B.
[0008] Preferably, the front frame is interlaced and connected with the cylinder body through a limiting strip and a limiting groove.
[0009] Preferably, the protrusion A and the notch A correspond to each other, and the protrusion A is inserted into the interior of the notch A.
[0010] Preferably, the protrusion B and the notch B correspond to each other, and the protrusion B is inserted into the interior of the notch B.
[0011] Preferably, the cylinder is integrally formed by rolling a carbon fiber cloth prepreg tube.
[0012] Preferably, a conductive paint layer is sprayed on the surface of the cylinder.
[0013] (III) Beneficial effects
[0014] Compared with the prior art, the utility model provides a control cabin component based on a missile cabin, which has the following beneficial effects:
[0015] 1. The control cabin part based on the missile cabin adopts carbon fiber composite material through the cylinder body and is formed by tube rolling process. It has light volume and high strength.
[0016] 2. The control cabin component based on the missile cabin adopts the limiting strip and the limiting groove to slide and intersect with the cylinder through the front frame to achieve precise docking, and the protrusion A is inserted into the inside of the notch A, and the protrusion B is inserted into the inside of the notch B to ensure the precise insertion between the cylinder and the front frame, thereby preventing position displacement during docking. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] Figure 1 This is a schematic diagram of the front exploded structure of the utility model;
[0018] Figure 2 It is a schematic diagram of the side exploded structure of the utility model;
[0019] Figure 3 This is another side exploded structural schematic diagram of the utility model.
[0020] In the figure: 1, cylinder; 2, front frame; 3, mounting portion; 4, notch A; 5, notch B; 6, frame groove; 7, frame ring; 8, protrusion A; 9, protrusion B; 10, limiting strip; 11, limiting groove; 12, bracket; 13, mounting plate. DETAILED DESCRIPTION
[0021] 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.
[0022] See also Figure 1-3A control cabin component based on a missile cabin comprises a cylinder 1, which is integrally formed by rolling a carbon fiber cloth prepreg tube, and the surface of the cylinder 1 is sprayed with a conductive paint layer. Pure silver paint with excellent conductive properties is selected as the conductive paint, and the brand is NX101. A front frame 2 is inserted and installed on the side of the cylinder 1, and four evenly distributed mounting parts 3 are arranged on the surface of the cylinder 1. A notch A4 is opened on one side of the cylinder 1, and a notch B5 is opened on the other side of the cylinder 1. A frame groove 6 is opened on the inner wall of the cylinder 1.
[0023] See also Figure 1-3 A frame ring 7 is fixedly mounted on the side of the front frame 2, a protrusion A8 is fixedly mounted on one side of the front frame 2, the protrusion A8 corresponds to the notch A4, and the protrusion A8 is inserted into the inside of the notch A4. A protrusion B9 is fixedly mounted on the other side of the front frame 2, the protrusion B9 corresponds to the notch B5, and the protrusion B9 is inserted into the inside of the notch B5.
[0024] See also Figure 1-3 The surfaces of the protrusions A8 and B9 are fixedly mounted with limiting strips 10, and the inner wall of the frame groove 6 is provided with limiting grooves 11. The cross-sections of the limiting strips 10 and the limiting grooves 11 are semicircular, and the front frame 2 is connected to the cylinder 1 through the limiting strips 10 and the limiting grooves 11. The surface of the protrusion A8 is fixedly mounted with a bracket 12 for connecting an external device; the surface of the protrusion B9 is fixedly mounted with a mounting plate 13 for connecting an external device.
[0025] Working principle: When in use, a layer of glue is applied to the surface of the frame groove 6 in advance, and then the front frame 2 is inserted into the outer wall of the frame groove 6, and the two are bonded together with glue. At the same time, the front frame 2 uses the limiting strip 10 and the limiting groove 11 to slide and insert with the cylinder 1 to achieve precise docking, and the protrusion A8 is inserted into the inside of the notch A4, and the protrusion B9 is inserted into the inside of the notch B5, ensuring the precise insertion between the cylinder 1 and the front frame 2, thereby preventing position displacement during docking.
[0026] The cylinder 1 is made of carbon fiber composite material and formed by a tube rolling process, and has a light volume and high strength.
[0027] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A control cabin component based on a missile cabin, comprising a cylinder (1), a front frame (2) being inserted and installed on the side of the cylinder (1), characterized in that: The surface of the cylinder (1) is provided with four evenly distributed mounting portions (3); a notch A (4) is provided on one side of the cylinder (1); a notch B (5) is provided on the other side of the cylinder (1); a frame groove (6) is provided on the inner wall of the cylinder (1); a frame ring (7) is fixedly mounted on the side of the front frame (2); a protrusion A (8) is fixedly mounted on one side of the front frame (2); a protrusion B (9) is fixedly mounted on the other side of the front frame (2); limiting strips (10) are fixedly mounted on the surfaces of the protrusion A (8) and the protrusion B (9); a limiting groove (11) is provided on the inner wall of the frame groove (6); a bracket (12) is fixedly mounted on the surface of the protrusion A (8); and a mounting plate (13) is fixedly mounted on the surface of the protrusion B (9).
2. A control cabin component based on a missile cabin according to claim 1, characterized in that: The front frame (2) is connected to the cylinder (1) through a limiting strip (10) and a limiting groove (11).
3. The control cabin component based on a missile cabin according to claim 1, characterized in that: The protrusion A (8) corresponds to the notch A (4), and the protrusion A (8) is inserted into the interior of the notch A (4).
4. The control cabin component based on a missile cabin according to claim 1, characterized in that: The protrusion B (9) corresponds to the notch B (5), and the protrusion B (9) is inserted into the interior of the notch B (5).
5. The control cabin component based on a missile cabin according to claim 1, characterized in that: The cylinder (1) is integrally formed by rolling a carbon fiber cloth prepreg tube.
6. The control cabin component based on a missile cabin according to claim 1, characterized in that: The surface of the cylinder (1) is sprayed with a conductive paint layer.