Guiding cabin body part based on missile cabin body

Abstract

The utility model relates to the technical field of missile cabins, and discloses a guided cabin part based on a missile cabin, which comprises a cylinder, a front frame is mounted at one end of the cylinder in a penetrating manner, and a rear frame is mounted at the other end of the cylinder in a penetrating manner; end bonding parts are arranged at the two ends of the inner wall of the cylinder body, a notch is formed in the end bonding part on the right side of the cylinder body, and a supporting lug bonding part is arranged on the surface of the cylinder body. According to the guided cabin body part based on the missile cabin body, the cabin body cylinder is made of a carbon fiber composite material and is formed through a pipe coiling technology, the inner diameter size precision is guaranteed through a mold, the outer diameter size precision is guaranteed through machining, five-axis machining is adopted for grooving and trepanning, a metal part and the cylinder are integrated through cold bonding, and the bonding precision is guaranteed through a bonding tool. And the bonding direction is determined according to the stress direction, the outwards-stressed parts are bonded from the inside, and the inwards-stressed parts are bonded from the outside, so that the advantages of light volume and strong impact resistance are achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of missile cabins, in particular to a guidance 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 cabins are all structural parts and are important components of the missile.

[0003] Traditional guidance cabins are made of metal materials, which are heavy, have insufficient load-bearing strength, and poor impact resistance, resulting in cracks in the cabin when used under various conditions such as transportation, mounting, launching, and flight of the missile. Utility Model Content

[0004] 1. Technical issues to be solved

[0005] In view of the deficiencies in the prior art, the utility model provides a guidance cabin component based on a missile cabin, which has the advantages of light volume and strong resistance, and solves the above-mentioned problems.

[0006] (II) Technical solution

[0007] In order to achieve the above-mentioned purpose of light volume and strong resistance, the utility model provides the following technical solutions: a guidance cabin component based on a missile cabin, comprising a cylinder, a front frame is inserted and installed at one end of the cylinder, and a rear frame is inserted and installed at the other end of the cylinder;

[0008] Both ends of the inner wall of the cylinder are provided with end bonding parts, a notch is provided on the end bonding part on the right side of the cylinder, and a support ear bonding part is provided on the surface of the cylinder.

[0009] Preferably, a convex ring A is fixedly mounted on the side surface of the front frame, a convex block is fixedly mounted on the surface of the front frame, and the front frame is bonded to the cylinder body via an end bonding portion.

[0010] Preferably, a convex ring B is fixedly mounted on the side surface of the rear frame, an extension plate is fixedly mounted on the side surface of the convex ring B, and the rear frame is bonded to the cylinder body via an end bonding portion.

[0011] Preferably, the lug bonding portion includes a lug bonding portion A and a lug bonding portion B, the surface of the lug bonding portion A is respectively fixedly mounted with a long lug and an oblique lug, and the surface of the lug bonding portion B is fixedly mounted with a short lug.

[0012] Preferably, the cylinder is made of carbon fiber and is formed by rolling a tube with carbon fiber cloth prepreg, and a conductive paint layer is provided on the inner and outer surfaces of the cylinder.

[0013] Preferably, the ear bonding portion A and the ear bonding portion B are both bonded to the inner wall of the cylinder by glue.

[0014] Preferably, the outer surface of the cylinder is bonded with the carbon fiber surface felt at the position of the lug bonding portion.

[0015] (III) Beneficial effects

[0016] Compared with the prior art, the utility model provides a guidance cabin component based on a missile cabin, which has the following beneficial effects:

[0017] 1. The guided cabin parts based on the missile cabin are made of carbon fiber composite materials and are formed by tube rolling technology. The inner diameter size accuracy is guaranteed by the mold, and the outer diameter size accuracy is guaranteed by machining. The grooving and hole opening are processed by five-axis machining. The metal parts and the cylinder are cold-bonded into one. The bonding accuracy is guaranteed by bonding tooling. The bonding direction is also determined according to the force direction. The parts subjected to outward force are bonded from the inside, and the parts subjected to inward force are bonded from the outside. Therefore, it has the advantages of light volume and strong resistance.

[0018] 2. The guidance cabin parts based on the missile cabin are sprayed with conductive paint on the inner and outer surfaces of the cylinder to ensure the conductivity of the cylinder and the electrical continuity of the entire missile. The installation interfaces such as the flange and support ears at the end of the cabin adopt metal structures to ensure the installation strength and accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the three-dimensional structure of the utility model;

[0020] Figure 2 This is a side view of the three-dimensional structure of the utility model;

[0021] Figure 3 This is a schematic diagram of the exploded structure of the front frame and the rear frame of the utility model;

[0022] Figure 4 This is a schematic diagram of the exploded structure of the utility model;

[0023] Figure 5 This is a schematic diagram of the side structure of the front frame of the utility model;

[0024] Figure 6 This is a schematic diagram of the top view of the front frame structure of the utility model;

[0025] Figure 7 This is a side view of the rear frame structure of the utility model;

[0026] Figure 8 It is a schematic diagram of the top view of the rear frame of the utility model.

[0027] In the figure: 1, cylinder; 2, front frame; 3, rear frame; 11, bonding part; 12, notch; 13, ear bonding part; 21, convex ring A; 22, convex block; 31, convex ring B; 32, extension plate; 131, ear bonding part A; 132, ear bonding part B; 133, long ear; 134, oblique ear; 135, short ear. DETAILED DESCRIPTION

[0028] 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.

[0029] See also Figure 1-8 A guided cabin component based on a missile cabin comprises a cylinder 1, the cylinder 1 is made of carbon fiber and is formed by rolling a carbon fiber cloth prepreg tube, and the single layer thickness of the carbon fiber cloth prepreg is 0.25 mm; the inner and outer surfaces of the cylinder 1 are both provided with a conductive paint layer to ensure that the resistance between any two points on the cabin surface should not exceed 50 mΩ, a front frame 2 is inserted and installed at one end of the cylinder 1, and a rear frame 3 is inserted and installed at the other end of the cylinder 1;

[0030] See also Figure 1-8 Both ends of the inner wall of the cylinder 1 are provided with end bonding parts 11, a notch 12 is opened on the end bonding part 11 on the right side of the cylinder 1, and a support ear bonding part 13 is provided on the surface of the cylinder 1. The outer surface of the cylinder 1 is bonded with carbon fiber surface felt at the position of the support ear bonding part 13.

[0031] See also Figure 1-8 A convex ring A21 is fixedly installed on the side of the front frame 2, a convex block 22 is fixedly installed on the surface of the front frame 2, and the front frame 2 is bonded to the cylinder 1 through the end bonding part 11.

[0032] See also Figure 1-8 A convex ring B31 is fixedly installed on the side of the rear frame 3, and an extension plate 32 is fixedly installed on the side of the convex ring B31. The rear frame 3 is bonded to the cylinder 1 through the end bonding part 11.

[0033] See also Figure 1-8 The ear bonding part 13 includes an ear bonding part A131 and an ear bonding part B132. The ear bonding part A131 and the ear bonding part B132 are both bonded to the inner wall of the cylinder 1 by glue. The surface of the ear bonding part A131 is fixedly installed with a long ear 133 and an oblique ear 134, and the surface of the ear bonding part B132 is fixedly installed with a short ear 135.

[0034] Working principle: When in use, the cabin cylinder 1 is made of carbon fiber composite materials and formed by the tube rolling process. The inner diameter size accuracy is guaranteed by the mold, and the outer diameter size accuracy is guaranteed by machining. The grooving and hole opening are processed by five-axis machining. The metal parts and the cylinder 1 are cold-bonded into one, and the bonding accuracy is guaranteed by bonding tooling. The bonding direction is also determined according to the force direction. The outward force is bonded from the inside, and the inward force is bonded from the outside. It has the advantages of light size and strong resistance.

[0035] Conductive paint is sprayed on the inner and outer surfaces of the cylinder 1 to ensure the conductivity of the cylinder 1 and the electrical continuity of the entire missile. The installation interfaces such as the flange and support ears at the end of the cabin adopt metal structures to ensure the installation strength and accuracy.

[0036] 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 guidance cabin component based on a missile cabin, comprising a cylinder (1), characterized in that: A front frame (2) is inserted and installed at one end of the cylinder (1), and a rear frame (3) is inserted and installed at the other end of the cylinder (1); End bonding portions (11) are provided at both ends of the inner wall of the cylinder (1), a notch (12) is provided on the end bonding portion (11) on the right side of the cylinder (1), and a lug bonding portion (13) is provided on the surface of the cylinder (1).

2. The guidance cabin component based on a missile cabin according to claim 1, characterized in that: A convex ring A (21) is fixedly mounted on the side of the front frame (2), a convex block (22) is fixedly mounted on the surface of the front frame (2), and the front frame (2) is bonded to the cylinder (1) via an end bonding portion (11).

3. The guidance cabin component based on a missile cabin according to claim 1, characterized in that: A convex ring B (31) is fixedly mounted on the side of the rear frame (3), and an extension plate (32) is fixedly mounted on the side of the convex ring B (31). The rear frame (3) is bonded to the cylinder (1) via an end bonding portion (11).

4. The guidance cabin component based on a missile cabin according to claim 1, characterized in that: The lug bonding portion (13) comprises a lug bonding portion A (131) and a lug bonding portion B (132), the surface of the lug bonding portion A (131) being respectively fixedly mounted with a long lug (133) and an oblique lug (134), and the surface of the lug bonding portion B (132) being fixedly mounted with a short lug (135).

5. The guidance cabin component based on a missile cabin according to claim 1, characterized in that: The cylinder (1) is made of carbon fiber and is formed by rolling a tube with carbon fiber cloth prepreg, and both the inner and outer surfaces of the cylinder (1) are provided with a conductive paint layer.

6. The guidance cabin component based on a missile cabin according to claim 4, characterized in that: The ear bonding portion A (131) and the ear bonding portion B (132) are both bonded to the inner wall of the cylinder (1) by glue.

7. The guidance cabin component based on a missile cabin according to claim 1, characterized in that: The outer surface of the cylinder (1) is bonded with carbon fiber surface felt at the position of the lug bonding portion (13).

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