Solid rocket adiabatic rubber flexible bonding mechanism and bonding method

Abstract

The application discloses a solid rocket adiabatic rubber flexible bonding mechanism and a bonding method, relates to the field of solid rockets, and comprises a core frame, the outer diameter of which is smaller than the inner diameter of a solid rocket shell body, and an adsorption assembly is arranged on the core frame and used for adsorbing adiabatic rubber to the circumferential surface of the core frame through negative pressure; a lifting mechanism is connected to one end of the core frame and used for driving the core frame to move vertically; and a rotating mechanism is connected to the lifting mechanism and used for driving the core frame to rotate. The adiabatic rubber is picked up by using a negative pressure method, the adiabatic rubber is placed by releasing the negative pressure, master-slave follow-up bonding is realized, the bubble arrangement in the bonding process is automatically realized, the bonding stability is good, the size control is good, the adiabatic rubber is not deformed, and the positioning precision is high.

Description

TECHNICAL FIELD

[0001] The application designs a flexible bonding mechanism and bonding method for the inner wall of a small solid rocket shell, and is especially suitable for bonding the inner wall of a small solid rocket cylindrical shell. BACKGROUND

[0002] A small solid rocket is a high-pressure jet power device, and the internal high-temperature and high-pressure gas pressure can reach more than 15 MPa and the temperature can reach more than 1000 DEG C during operation. In order to ensure that the metal shell does not disintegrate under high temperature and high pressure, a layer of heat insulation rubber with a thickness of 0.5 mm needs to be pasted on the inner wall. Due to the small bonding space of the small solid rocket, the heat insulation rubber has high flexibility, resulting in high bonding position precision requirement and great operation difficulty, and air bubbles are easily generated. At present, manual operation is basically used. The small solid rocket is usually a slender deep hole, and the bonding cannot be effectively observed, resulting in high skill requirement for personnel.

[0003] The Chinese patent CN113818972A entitled "A bonding structure and method for a solid rocket combustion chamber heat insulation layer" is composed of a metal shell, a rubber piece, an air bag, a sealing end cover, an air inlet pipe and an air exhaust pipe. The heat insulation layer is bonded to the inner wall of the metal shell by using a soft air bag inflation support method. This method has good size adaptability, but requires that the heat insulation material has high elasticity and has the condition of pre-shaping. The high heat insulation material used for small solid rockets cannot be directly used due to high preparation requirements. SUMMARY

[0004] The technical problem solved by the application is to overcome the shortcomings of the prior art and provide a flexible bonding mechanism for solid rocket heat insulation rubber, which can bond the heat insulation rubber to the inner wall of different types of solid rockets with high quality, especially solve the problem of bonding the heat insulation rubber to the inner wall of small solid rockets, and has good adaptability, universality and high reliability.

[0005] The technical solution of the application is:

[0006] A flexible bonding mechanism for solid rocket heat insulation rubber comprises:

[0007] A core frame with an outer diameter smaller than the inner diameter of the solid rocket shell is provided with an adsorption assembly for adsorbing the heat insulation rubber to the peripheral surface of the core frame by negative pressure;

[0008] A lifting mechanism is connected to one end of the core frame and used to drive the core frame to move vertically;

[0009] A rotating mechanism is connected to the lifting mechanism and used to drive the core frame to rotate.

[0010] The adsorption assembly comprises air holes, air flow channels and a negative pressure generator. The air holes are arranged on the peripheral surface of the core frame, the air flow channels are used to communicate with the air holes, and the air flow channels are communicated with the negative pressure generator.

[0011] The air holes are arranged in multiple rows along the axial direction of the core frame, and each row of air holes is communicated through an air flow channel, and each air flow channel is connected with a negative pressure generator.

[0012] One end of the core frame is connected with a rotating shaft, the rotating shaft is connected with a rotating mechanism, and the rotating shaft is externally sleeved with an air slip ring, and the air flow channel and the negative pressure generator are communicated through the air slip ring.

[0013] The circumferential surface of the core frame is provided with a silica gel layer.

[0014] One end of the core frame away from the lifting mechanism is connected with an end cover, the outer circumferential surface of the end cover is sleeved with a positioning body, the positioning body is in interference fit with the end cover, and the outer diameter of the positioning body is 87-93% of the outer diameter of the silica gel layer minus the thickness of the bonded rubber.

[0015] The end cover is connected with the core frame through threads; the core frame and the end cover are made of aluminum alloy; and the gap between the core frame and the end cover is less than 0.2 mm.

[0016] The hardness of the positioning body is 30±5 HA higher than that of the silica gel layer; and the hardness of the silica gel layer is 10±5 HA.

[0017] The positioning body is made of polyurethane.

[0018] A flexible bonding method for solid rocket heat-insulating rubber, which uses the flexible bonding mechanism for solid rocket heat-insulating rubber, comprises the following steps of:

[0019] The heat-insulating rubber is placed on the surface of the core frame, and the adsorption assembly adsorbs the heat-insulating rubber to the surface of the core frame through negative pressure;

[0020] The solid rocket shell is moved to be sleeved on the outer surface of the core frame, the core frame is driven to rotate to the target position of the heat-insulating rubber through the rotating mechanism, and then the core frame is moved to the specified position of the inner wall of the solid rocket shell through the lifting mechanism;

[0021] The solid rocket shell is rotated, the core frame is synchronously rotated with the solid rocket shell, and the negative pressure of the adsorption assembly is removed row by row, so that the heat-insulating rubber is transferred to the inner wall of the solid rocket shell.

[0022] (1) The present application designs a novel small solid rocket inner wall heat-insulating rubber flexible bonding mechanism, uses a negative pressure method to pick up the heat-insulating rubber, and places the heat-insulating rubber by removing the negative pressure, so that the master-slave dynamic bonding is controlled, the work is reliable, and air bubbles can be effectively removed;

[0023] (2) The present application adopts a cylindrical suction disc (i.e. multiple suction holes on the outer cylindrical surface of the core frame, so that the core frame forms a cylindrical suction disc) and a multi-row suction hole multi-path control structure, which can be compatible with multiple diameters of small solid rockets at one time, and has good universality.

[0024] (3) The present invention adopts a low-hardness silicone layer coating structure, which reduces the requirements for equipment dimensional accuracy, realizes automatic de-bubbling during the bonding process, and has good bonding stability.

[0025] (4) The present invention adopts end positioning structures with different hardness, which can effectively position the heat insulation rubber during the bonding process, control the size well, prevent deformation and have high positioning accuracy. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the structural outline in an embodiment of the present invention;

[0027] Figure 2 This is a schematic diagram illustrating the working principle in an embodiment of the present invention;

[0028] Figure 3 This is a schematic diagram of the gas flow direction in an embodiment of the present invention;

[0029] Figure 4 This is an overall structural diagram of the flexible bonding mechanism for the solid rocket insulation rubber in an embodiment of the present invention.

[0030] Explanation of reference numerals in the attached drawings: 1. Core frame; 2. End cap; 3. Silicone layer; 4. Positioning body; 5. Air vent; 6. Airflow channel; 7. Insulating rubber; 8. Solid rocket shell; 9. Lifting mechanism; 10. Rotating mechanism. Detailed Implementation

[0031] The present application will now be described in further detail with reference to the accompanying drawings and specific embodiments:

[0032] This application discloses a flexible bonding mechanism for solid rocket insulation rubber, such as... Figure 1 As shown, it includes a core frame 1, an adsorption assembly disposed on the core frame 1, a lifting mechanism for driving the core frame 1 to move vertically, and a rotating mechanism for driving the core frame 1 to rotate.

[0033] like Figure 1 and Figure 3 As shown, the outer cylindrical surface of the core frame 1 is covered with a silicone layer 3. The end of the core frame 1 away from the lifting mechanism is connected to a head 2. The head 2 is connected and fixed to the core frame 1 through a threaded hole. The outer cylindrical surface of the head 2 is covered with a positioning body 4. The positioning body 4 is interference-fitted with the head 2. The outer diameter of the positioning body 4 is the outer diameter of the silicone layer 3 minus 90% of the thickness of the adhesive rubber.

[0034] like Figure 1As shown, the core frame 1 is made of aluminum alloy, which has high strength and low density, and the end cover 2 is also made of aluminum alloy, which is connected with the core frame 1 through threads, and the gap between the core frame 1 and the end cover 2 should be less than 0.2 mm after being tightened. The hardness of the positioning body 4 is 30±5 HA higher than that of the silica gel layer 3. In this embodiment, the hardness of the silica gel layer 3 is generally 10±5 HA, and the thickness is 10 mm, and the hardness of the positioning body 4 is 45 HA, and the thickness is 30 mm. The positioning body 4 is made of polyurethane.

[0035] When the core frame 1 is used to paste the heat-insulating rubber 7 on the solid rocket shell 8, the heat-insulating rubber 7 is adsorbed to the circumference of the core frame 1, the outer cylindrical surface of the core frame 1 is attached to the inner wall of the solid rocket shell 8, and then the core frame 1 is driven to rotate synchronously with the rotation of the solid rocket shell 8, and the heat-insulating rubber 7 is gradually pasted into the solid rocket shell 8. When the core frame 1 extends into the solid rocket shell 8, the end cover 2 made of harder material is pressed against the bottom of the inner cavity of the solid rocket shell 8, thereby achieving effective positioning of the heat-insulating rubber 7 during the pasting process and ensuring that the end of the heat-insulating rubber 7 on the core frame 1 does not deform. The positioning body 4 with a certain flexibility and a hardness higher than that of the silica gel layer 3 by a certain degree enables the end of the heat-insulating rubber 7 to be pressed tightly by the positioning body 4 during the rotation of the solid rocket shell 8 and the core frame 1, and the end portion attached to the positioning body 4 and the middle portion attached to the silica gel layer 3 do not have a large deformation difference, so that the heat-insulating rubber 7 can be uniformly pressed into the solid rocket shell.

[0036] The adsorption assembly is used to adsorb the heat-insulating rubber 7 to the circumferential surface of the core frame 1 through negative pressure. The adsorption assembly includes air holes 5, air flow channels 6, and negative pressure generators. The air holes 5 are arranged on the circumferential surface of the core frame 1, and a plurality of rows of air holes 5 are arranged along the axial direction of the core frame 1. Each row of air holes 5 is connected through an air flow channel 6, and each air flow channel 6 is connected with a negative pressure generator. The air holes 5 on the silica gel layer 3 are aligned with the air holes 5 of the core frame 1. In this embodiment, as shown in Figure 3 The core frame 1 has 8 rows of air holes 5 arranged radially along the outer circle, each row has 36 air holes 5 with a diameter of 1 mm, and the inner radial air flow channel 6 with a diameter of 2 mm connects the whole row of air holes 5. The silica gel layer 3 also has air holes 5 with the same diameter corresponding to the air holes 5 of the core frame 1. The negative pressure is transmitted to the surface of the silica gel layer 3 through the air flow channel 6 and the air flow channel 6 formed by the air holes 5 to adsorb the heat-insulating rubber 7. The size of the air hole 5 and the negative pressure value are related to the thickness and elastic modulus of the heat-insulating rubber 7.

[0037] As shown in Figure 4As shown, one end of the core frame 1 is connected with a rotating shaft, the rotating shaft is connected with a rotating mechanism 10, in the embodiment, the rotating mechanism is a motor. The rotating shaft is provided with an air slip ring, the air flow channel 6 and the negative pressure generator are communicated through the air slip ring. The motor is started, the core frame 1 can be driven to rotate through the rotating shaft, at the same time, the air slip ring is arranged, so that the multiple air flow channels 6 and the negative pressure generator can not interfere with each other in the rotating process of the core frame 1. The end of the core frame 1 connected with the rotating shaft is connected with a lifting mechanism 9, the lifting mechanism can drive the core frame 1 and the rotating mechanism to move vertically. In the embodiment, the lifting mechanism is an axial movement module, the rotating mechanism is a servo motor with an encoder, and the core frame 1 is connected with an output shaft of the rotating mechanism.

[0038] The implementation principle of the application is:

[0039] As Figure 2 shown, the bonding method is that when the bonding mechanism works, the heat insulation rubber 7 is placed on the surface of the silica gel layer 3, the air flow channel 6 formed by the air holes 5 and the air flow channel 6 of the core frame 1 introduces the negative pressure to the interface between the silica gel layer 3 and the heat insulation rubber 7, and the heat insulation rubber 7 is adsorbed on the surface of the silica gel layer 3.

[0040] The solid rocket shell 8 is moved to be sleeved outside the core frame 1, the core frame 1 is driven to rotate to the target position of the heat insulation rubber 7 through the rotating mechanism, then the core frame 1 is moved through the lifting mechanism, until the core frame 1 and the silica gel layer 3 are integrally moved to the specified position of the inner wall of the solid rocket shell 8.

[0041] The solid rocket shell 8 is rotated, the core frame 1 and the silica gel layer 3 are synchronously rotated with the solid rocket shell 8, the air holes 5 of the silica gel layer 3 are removed from the negative pressure row by row, the heat insulation rubber 7 is transferred to the inner wall of the solid rocket shell 8, and at the same time, the silica gel layer 3 performs rolling on the heat insulation rubber 7, which is helpful for bubble removal.

[0042] The disclosed technology of the application is common knowledge of the person skilled in the art.

[0043] Although the application is disclosed with the above preferred embodiments, it is not intended to limit the application, and any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the application, therefore, the protection scope of the application should be subject to the scope defined by the claims of the application.

Claims

1. A flexible bonding mechanism for solid rocket insulation rubber, characterized in that, include: The core frame (1) has an outer diameter smaller than the inner diameter of the solid rocket shell (8) and is equipped with an adsorption assembly for adsorbing the heat insulation rubber (7) onto the circumferential surface of the core frame (1) by negative pressure. The lifting mechanism is connected to one end of the core frame (1) and is used to drive the core frame (1) to move vertically; A rotating mechanism, connected to a lifting mechanism, is used to drive the core frame (1) to rotate; The circumferential surface of the core frame (1) has a silicone layer (3); The end of the core frame (1) away from the lifting mechanism is connected to a head (2). The head (2) is fitted with a positioning body (4) on its outer periphery. The positioning body (4) is interference-fitted with the head (2). The outer diameter of the positioning body (4) is the outer diameter of the silicone layer (3) minus 87-93% of the thickness of the adhesive rubber. The end cap (2) is connected to the core frame (1) by threads; both the core frame (1) and the end cap (2) are made of aluminum alloy. The gap between the core frame (1) and the end cap (2) is less than 0.2 mm; The hardness of the positioning body (4) is 30±5HA higher than that of the silicone layer (3); the hardness of the silicone layer (3) is 10±5HA.

2. The flexible bonding mechanism for solid rocket insulation rubber according to claim 1, characterized in that: The adsorption assembly includes pores (5), airflow channels (6) and a negative pressure generator. The pores (5) are opened on the circumferential surface of the core frame (1). The airflow channels (6) are used to connect multiple pores (5) and are connected to the negative pressure generator.

3. The flexible bonding mechanism for solid rocket insulation rubber according to claim 2, characterized in that: The air holes (5) are arranged in multiple rows along the axial direction of the core frame (1). Each air hole (5) is connected through an airflow channel (6), and each airflow channel (6) is connected to a negative pressure generator.

4. The flexible bonding mechanism for solid rocket insulation rubber according to claim 2, characterized in that: One end of the core frame (1) is connected to a rotating shaft, which is connected to a rotating mechanism. A slip ring is provided on the outer sleeve of the rotating shaft, and the airflow channel (6) and the negative pressure generator are connected through the slip ring.

5. The flexible bonding mechanism for solid rocket insulation rubber according to claim 1, characterized in that: The positioning body (4) is made of polyurethane.

6. A flexible bonding method for solid rocket insulation rubber, characterized in that, The flexible bonding mechanism for solid rocket insulation rubber as described in any one of claims 1-5 includes: The heat insulation rubber sheet (7) is placed on the surface of the core frame (1), and the adsorption component will adsorb the heat insulation rubber sheet (7) onto the surface of the core frame (1) through negative pressure; The solid rocket shell (8) is moved to be fitted outside the core frame (1), and the core frame (1) is rotated by the rotating mechanism until the heat insulation rubber (7) is in the target position. Then the lifting mechanism moves the core frame (1) to the designated position on the inner wall of the solid rocket shell (8). The solid rocket shell (8) is rotated, and the solid rocket shell (8) drives the core frame (1) to rotate synchronously. At the same time, the negative pressure of the adsorption components is removed row by row, and the heat insulation rubber (7) is transferred to the inner wall of the solid rocket shell (8).

Images