Radial connection device for air-breathing hypersonic missile and engine

Abstract

The present application relates to a kind of radial connecting device of air-breathing hypersonic missile and engine, belong to the field of missile structure.The present application includes: elastic support device (2), adjusting screw (3), support mounting seat (5), locking mechanism;The locking mechanism includes: locking nut (4), locking screw (6);The elastic support device (2) includes: support leaf spring (7), heat sink leaf spring (8);The adjusting screw (3) is vertically inserted into support mounting seat (5), locking nut (4) is provided at the contact place of adjusting screw (3) outside support mounting seat (5), the locking nut (4) is around and is provided in adjusting screw (3) outside, can adapt to the circumferential and radial thermal deformation caused by engine when rocket cruise under the requirement of meeting support rigidity.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of missile structure, and particularly relates to a radial connecting device for air-breathing hypersonic missiles and engines. BACKGROUND

[0002] During the operation of the air-breathing hypersonic missile, the engine is subjected to long-time aerodynamic heating and combustion, resulting in large thermal deformation. The traditional rigid connection causes large thermal stress at the connection between the engine and the cabin body during the operation of the missile, and the connection structure is seriously damaged. In order to adapt to the large deformation, a new type of mechanical connecting device is designed for practical engineering flight test. SUMMARY

[0003] (I) Technical problem to be solved

[0004] The technical problem to be solved by the application is to provide a radial connecting device for air-breathing hypersonic missiles and engines, so as to solve the problem of large thermal stress at the connection between the engine and the cabin body in the prior art, which seriously damages the connection structure.

[0005] (II) Technical scheme

[0006] In order to solve the above technical problem, the application provides a radial connecting device for air-breathing hypersonic missiles and engines, which comprises: an elastic supporting device 2, an adjusting screw 3, a supporting mounting seat 5, and a locking mechanism.

[0007] The locking mechanism comprises: a locking nut 4 and a locking screw 6.

[0008] The elastic supporting device 2 comprises: a supporting leaf spring 7 and a heat sink leaf spring 8.

[0009] The adjusting screw 3 is vertically inserted into the supporting mounting seat 5, and a locking nut 4 is arranged at the position where the adjusting screw 3 contacts the outside of the supporting mounting seat 5, and the locking nut 4 is arranged around the outside of the adjusting screw 3.

[0010] The adjusting screw 3 is connected to one side of the supporting leaf spring 7 at the end of the supporting mounting seat 5, the other side of the supporting leaf spring 7 is a circular-arc-shaped supporting part, and the two ends of the supporting part are provided with holes.

[0011] A hole is formed in the side wall of the supporting mounting seat 5, and a locking screw 6 is arranged in the hole, the end of the locking screw 6 is connected to the part of the supporting mounting seat 5 inserted into the supporting mounting seat 5, and the radial locking of the supporting mounting seat 5 and the adjusting screw 3 is completed through the locking screw 6.

[0012] The heat sink leaf spring 8 is arranged in a circular-arc-shaped connecting part which is symmetrical to the supporting part, the connecting part is connected to the supporting part, a positioning socket is arranged in the connecting part, and the positioning socket is used to connect the cruise engine 1 in the circumferential direction.

[0013] Among them, the air-breathing hypersonic missile and engine radial connection device is provided with 4 groups, each group is the same structure, and the circumferential 4 points of the cruise engine 1 are uniformly supported, so that each point of the cruise engine 1 is uniformly stressed.

[0014] Among them, the adjusting screw 3 and the support plate spring 7 are provided with inward notches, and the outward protruding parts at the ends of the support plate spring 7 are clamped with the adjusting screw 3.

[0015] Among them, the connecting part and the supporting part are connected by the screws arranged on both sides.

[0016] Among them, the support plate spring 7 is made of titanium alloy.

[0017] Among them, the heat sink plate spring 8 is arranged at the support position of the support plate spring 7 and the cruise engine 1, which is used for absorbing the heat transmitted by the cruise engine 1 to the support plate spring 7, and reducing the temperature of the support plate spring 7.

[0018] Among them, the heat sink plate spring 8 is made of brass H62.

[0019] Among them, the support rigidity of the support plate spring 7 is adjusted by screwing the adjusting screw 3.

[0020] (Three) beneficial effects

[0021] The air-breathing hypersonic missile and engine radial connection device can adapt to the circumferential and radial thermal deformation caused by the engine during the cruise of the rocket. DRAWINGS

[0022] Fig. 1 It is a schematic diagram of the whole connection of the device of the present application;

[0023] Fig. 2 It is a schematic diagram of the structure of the device of the present application;

[0024] Fig. 3 It is a sectional view of the structure of the device of the present application. DETAILED DESCRIPTION

[0025] In order to make the purpose, content and advantages of the present application more clear, the specific embodiments of the present application are described in detail below in combination with the drawings and examples.

[0026] To solve the above technical problems, the present embodiment provides an air-breathing hypersonic missile and engine radial connection device, as shown in Figs. 1-3 The device comprises: an elastic support device 2, an adjusting screw 3, a support mounting seat 5 and a locking mechanism.

[0027] The locking mechanism comprises: a locking nut 4 and a locking screw 6

[0028] The elastic support device 2 comprises a support leaf spring 7 and a heat sink leaf spring 8.

[0029] The adjusting screw 3 is vertically inserted into the support mounting seat 5, and a locking nut 4 is arranged outside the support mounting seat 5 and in contact with the adjusting screw 3, and the locking nut 4 is arranged outside the adjusting screw 3.

[0030] The adjusting screw 3 is inserted into the end of the support mounting seat 5 and connected to one side of the support leaf spring 7, and the other side of the support leaf spring 7 is a circular arc structure support part, and the both ends of the support part are provided with holes.

[0031] Holes are arranged on the side wall of the support mounting seat 5, and a locking screw 6 is arranged in the hole, and the end of the locking screw 6 is connected to the inserted part of the support mounting seat 5, and the radial locking of the support mounting seat 5 and the adjusting screw 3 is completed through the locking screw 6.

[0032] The heat sink leaf spring 8 is arranged to be symmetrical to the support part, and the connecting part is connected to the support part, and a positioning socket is arranged in the middle of the connecting part, which is used to connect the cruise engine 1 in the circumferential direction.

[0033] The air-breathing hypersonic missile and the engine radial connection device are provided with four groups, each group has the same structure, and the cruise engine 1 is uniformly supported at four points in the circumferential direction, so that the cruise engine 1 is uniformly stressed at each point.

[0034] The adjusting screw 3 is provided with an inward notch at the connection with the support leaf spring 7, and the end of the support leaf spring 7 is provided with an outward protruding part which is engaged with the adjusting screw 3.

[0035] The connecting part and the support part are fixed by screws arranged on both sides.

[0036] The material of the support leaf spring 7 is selected from titanium alloy.

[0037] The heat sink leaf spring 8 is arranged between the support leaf spring 7 and the support of the cruise engine 1, which is used to absorb the heat transmitted from the cruise engine 1 to the support leaf spring 7, and reduce the temperature of the support leaf spring 7.

[0038] The material of the heat sink leaf spring 8 is selected from brass H62.

[0039] According to the radial support stiffness requirement of the cruise engine, the adjusting amount of the adjusting screw is calculated, the support stiffness is controlled by the torque of the adjusting screw (20N.m), and after installation, the support device is locked by the locking nut and the locking screw.

[0040] The above merely describes the preferred embodiments of the present application, and it should be pointed out that, for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present application, and these improvements and modifications should also be considered as the protection scope of the present application.

Claims

1. A radial connection device between an air-breathing hypersonic missile and an engine, characterized in that, include: Elastic support device (2), adjusting screw (3), support mounting base (5), locking mechanism; The locking mechanism includes: a locking nut (4) and a locking screw (6); The elastic support device (2) includes: a support leaf spring (7) and a heat sink leaf spring (8); The adjusting screw (3) is vertically inserted into the support mounting base (5). A locking nut (4) is provided at the contact point between the adjusting screw (3) and the support mounting base (5). The locking nut (4) is wrapped around the outside of the adjusting screw (3). The adjusting screw (3) is inserted into the end of the support mounting base (5) and connected to one side of the support leaf spring (7). The other side of the support leaf spring (7) is an arc-shaped support part, and the two ends of the support part have openings. The support mounting base (5) has a hole on its side wall, and a locking screw (6) is provided in the hole. The end of the locking screw (6) is connected to the part of the support mounting base (5) inserted into the support mounting base (5). The support mounting base (5) and the adjusting screw (3) are radially locked by the locking screw (6). The heat sink leaf spring (8) is configured as an arc-shaped connecting part symmetrical to the support part. The connecting part is connected to the support part, and a positioning socket is provided in the middle of the connecting part. The positioning socket is used to connect to the cruise engine (1) circumferentially.

2. The radial connection device between the air-breathing hypersonic missile and the engine as described in claim 1, characterized in that, The air-breathing hypersonic missile and the engine radial connection device are provided in 4 groups, each group has the same structure, and provides uniform support for the cruise engine (1) at 4 points in the circumference, so that the cruise engine (1) is subjected to uniform force at each point.

3. The radial connection device between the air-breathing hypersonic missile and the engine as described in claim 2, characterized in that, The adjusting screw (3) is provided with an inward notch at the connection point with the support leaf spring (7), and the adjusting screw (3) is engaged with the outward protrusion at the end of the support leaf spring (7).

4. The radial connection device between the air-breathing hypersonic missile and the engine as described in claim 3, characterized in that, The connection between the connecting part and the support part is fixed by screws provided on both sides.

5. The radial connection device between the air-breathing hypersonic missile and the engine as described in claim 4, characterized in that, The material of the supporting leaf spring (7) is titanium alloy.

6. The radial connection device between the air-breathing hypersonic missile and the engine as described in claim 5, characterized in that, By adding a heat sink spring (8) at the support spring (7) and cruise engine (1) support, the heat transferred from the cruise engine (1) to the support spring (7) is absorbed, thereby reducing the temperature of the support spring (7).

7. The radial connection device between the air-breathing hypersonic missile and the engine as described in claim 6, characterized in that, The heat sink leaf spring (8) is made of brass H62.

8. The radial connection device between the air-breathing hypersonic missile and the engine as described in claim 7, characterized in that, The support stiffness of the support leaf spring (7) is adjusted by turning the adjusting screw (3).

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