Radial connecting device for air-breathing hypersonic missile body and air inlet channel

By designing a suction type hypersonic missile connection device including cabin, sleeve, large gasket, disc spring and bolt, the problem of excessive thermal stress at the connection between the missile air inlet and cabin is solved, and the problem of excessive thermal stress at the connection between the missile air inlet and cabin is achieved. The adaptability compensation for missile thermal deformation and the stability of the connection structure are improved.

CN222211426UActive Publication Date: 2024-12-20XIAN MODERN CONTROL TECH RES INST
View PDF 0 Cites 0 Cited by

Patent Information

Application Number
CN202322893531.5
Authority / Receiving Office
CN · China
Patent Type
Utility models(China)
Current Assignee / Owner
Filing Date
2023-10-27
Publication Date
2024-12-20
Estimated Expiration
2033-10-27

AI Technical Summary

Technical Problem

The connection between the air inlet and the cabin of the hypersonic missile is too high due to long-term aerodynamic heating, resulting in excessive thermal stress, resulting in failure of the connection structure.

Method used

Design a radial connection device for suction hypersonic missile body and air intake passage, including cabin, sleeve, large gasket, disc spring and bolts, to adapt to the missile through the preload force and number of disc springs. Thermal deformation in each direction ensures the stability of the connecting structure.

Benefits of technology

Effectively compensate for the thermal deformation during the missile's operation, enhance the stability of the connection between the intake duct and the cabin, and avoid the failure of the connection structure.

✦ Generated by Eureka AI based on patent content.

Smart Images

  • Figure CN222211426U_ABST
    Figure CN222211426U_ABST
Patent Text Reader

Abstract

The utility model relates to a radial connecting device for a missile body and an air inlet channel of an air-breathing hypersonic missile, and belongs to the field of missiles. The device comprises a cabin body (1), a sleeve (2), a large gasket (3), a disc spring (4), a bolt (5) and an air inlet channel (6), the air inlet channel (6) is arranged at the bottom, the cabin body (1) is arranged above the air inlet channel (6), the sleeve (2) is arranged above the cabin body (1), holes are coaxially formed in the air inlet channel (6), the cabin body (1) and the sleeve (2) in the vertical direction, threaded structures are arranged on the inner side walls of the holes, the large gasket (3) is arranged at the joint of the top of the bolt (5) and the sleeve (2), and the disc spring (4) is arranged in the sleeve (2). The bolt (5) compresses the disc spring (4) through the large gasket (3), the bolt (5) penetrates through the cabin body (1) and is in threaded connection with the air inlet channel (6), and thermal deformation in three directions caused when the guided missile works can be adapted and compensated by connecting the device.
Need to check novelty before this filing date? Find Prior Art

Description

Technical Field

[0001] The utility model belongs to the field of missile structures, and in particular relates to a radial connection device between an air-breathing hypersonic missile body and an air inlet. Background Art

[0002] When a hypersonic missile is working, the air inlet deforms greatly due to long-term aerodynamic heating. The traditional rigid connection causes large thermal stress at the connection between the air inlet and the cabin during the missile working process, which may cause failure of the connection structure in severe cases. In order to adapt to the large deformation, a new type of mechanical connection device is designed, which has been successfully applied in actual engineering flight tests. Utility Model Content

[0003] 1. Technical issues to be resolved

[0004] The technical problem to be solved by the utility model is how to provide a radial connection device between the body and the air inlet of an air-breathing hypersonic missile, so as to solve the problem in the prior art that the thermal stress at the connection between the air inlet and the cabin body is large, resulting in failure of the connection structure.

[0005] (II) Technical solution

[0006] In order to solve the above technical problems, the utility model proposes a radial connection device between an air-breathing hypersonic missile body and an air inlet, comprising: a cabin 1, a sleeve 2, a large gasket 3, a disc spring 4, a bolt 5, and an air inlet 6;

[0007] The air inlet 6 is arranged at the bottom, a cabin 1 is arranged above the air inlet 6, and a sleeve 2 is arranged above the cabin 1;

[0008] The air inlet 6, the cabin 1 and the sleeve 2 are coaxially opened in the vertical direction, and a threaded structure is provided on the inner wall of the hole. A large gasket 3 is provided at the connection between the top of the bolt 5 and the sleeve 2, and the disc spring 4 is arranged in the sleeve 2. The bolt 5 is pressed against the disc spring 4 through the large gasket 3, and the bolt 5 passes through the cabin 1 and is threadedly connected to the air inlet 6.

[0009] Among them, a connected part is set below the air inlet 6. When the connected part is aligned with the hole of the air inlet 6, the disc springs 4 are grouped into three groups, with the groups facing back to back, and a total of 8 groups are placed in the sleeve 2.

[0010] The setting height of the sleeve 2 is determined according to the number of disc springs 4 and the size of the preload force, and the number of disc springs 4 and the height of the sleeve 2 are adjusted according to the load size.

[0011] (III) Beneficial effects

[0012] The utility model provides a radial connection device between an air-breathing hypersonic missile body and an air inlet. The device can be connected to adapt to and compensate for thermal deformation in three directions caused by the missile when it is working. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a schematic diagram of the structure of the device of the utility model. DETAILED DESCRIPTION

[0014] In order to make the purpose, content and advantages of the utility model clearer, the specific implementation methods of the utility model are further described in detail below in conjunction with the drawings and embodiments.

[0015] In order to solve the above technical problems, the present embodiment provides a device for radially connecting the body and the air inlet of an air-breathing hypersonic missile, such as Figure 1 As shown, it includes: a cabin 1, a sleeve 2, a large gasket 3, a disc spring 4, a bolt 5, and an air inlet 6;

[0016] The air inlet 6 is arranged at the bottom, a cabin 1 is arranged above the air inlet 6, and a sleeve 2 is arranged above the cabin 1;

[0017] The air inlet 6, the cabin 1 and the sleeve 2 are coaxially opened in the vertical direction, and a threaded structure is provided on the inner wall of the hole. A large gasket 3 is provided at the connection between the top of the bolt 5 and the sleeve 2, and the disc spring 4 is arranged in the sleeve 2. The bolt 5 is pressed against the disc spring 4 through the large gasket 3, and the bolt 5 passes through the cabin 1 and is threadedly connected to the air inlet 6.

[0018] Among them, a connected part is set below the air inlet 6. When the connected part is aligned with the hole of the air inlet 6, the disc springs 4 are grouped into three groups, with the groups facing back to back, and a total of 8 groups are placed in the sleeve 2.

[0019] The specifications and quantity of disc springs are determined according to the radial force load. In this example, the disc springs are 25×12.2×1.5×2.05, 8 groups, and 3 pieces in each group.

[0020] The sleeve height is determined according to the number of disc springs and the preload force. In this example, the effective sleeve height is 39mm.

[0021] The compression of the disc spring is determined according to the load size. In this example, the compression is 1.2 mm.

[0022] The opening size of the connected part connected to the air intake duct is determined according to the thermal deformation in two directions, which is 21.5mm×14.5mm in this example.

[0023] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the protection scope of the present invention.

Claims

1. A radial connection device between a body and an air inlet of an air-breathing hypersonic missile, characterized in that: include: Cabin body (1), sleeve (2), large gasket (3), disc spring (4), bolt (5), air inlet (6); The air inlet (6) is arranged at the bottom, a cabin (1) is arranged above the air inlet (6), and a sleeve (2) is arranged above the cabin (1); The air inlet (6), the cabin (1) and the sleeve (2) are provided with coaxial openings in the vertical direction, and a threaded structure is provided on the inner wall of the hole. A large gasket (3) is provided at the connection between the top of the bolt (5) and the sleeve (2), and the disc spring (4) is arranged in the sleeve (2). The bolt (5) presses the disc spring (4) through the large gasket (3), and the bolt (5) passes through the cabin (1) and is threadedly connected to the air inlet (6).

2. The air-breathing hypersonic missile body and air inlet radial connection device according to claim 1, characterized in that: A connected part is arranged below the air inlet (6). When the connected part is aligned with the hole of the air inlet (6), three disc springs (4) are grouped together, with the groups facing back to back, and a total of eight groups are placed in the sleeve (2).