Rocket thrust chamber inner wall machining deformation control and self-adaption device

Abstract

The invention provides a rocket thrust chamber inner wall machining deformation control and self-adaption device, and belongs to the technical field of rocket thrust chamber machining. Comprising a rocket thrust chamber, a mounting and placing platform with an annular clamping notch formed in the upper end, a regulating and filling tool arranged on the mounting and placing platform in the vertical direction, and a fastening assembly arranged on the mounting and placing platform and used for clamping the upper end and the lower end of the regulating and filling tool. The rocket thrust chamber is filled with the adjusting and controlling filling tool, customization can be conducted according to the specific shape and size of the rocket thrust chamber, deformation of the inner wall of the thrust chamber is accurately controlled by adjusting and controlling the pressure and shape of the filling tool, the geometric accuracy in the machining process is ensured, and the adjusting and controlling filling tool provides accurate positioning and supporting in the rocket thrust chamber; and it is ensured that the geometric shape and the size precision of the rocket thrust chamber are controlled in the machining process.

Description

Technical Field

[0001] The invention belongs to the technical field of rocket thrust chamber processing, and in particular is a rocket thrust chamber inner wall processing deformation control and self-adaptation device. Background Art

[0002] The rocket thrust chamber is one of the core components of a liquid rocket engine. Its main function is to convert the high-temperature and high-pressure gas produced by the combustion of the fuel and oxidizer into thrust. The working principle of the rocket thrust chamber involves a series of processes such as atomization, mixing, heat transfer and combustion of the fuel and oxidizer. The fuel and oxidizer are atomized into fine particles through the nozzle in the thrust chamber, and then mixed and chemically reacted in the combustion chamber, releasing a large amount of heat energy. This heat energy is transferred to the coolant through the thrust chamber wall, and the coolant then takes away the heat to prevent the thrust chamber from overheating. Finally, the high-temperature and high-pressure gas is accelerated and discharged through the nozzle to generate thrust.

[0003] Controlling the machining deformation of the inner wall of the rocket thrust chamber is crucial to ensuring the performance and safety of the rocket engine. The inner wall of the thrust chamber is subjected to extreme temperature and pressure conditions during the rocket flight. Any slight deformation may cause engine failure or even lead to catastrophic consequences. Therefore, strict control of the machining deformation of the inner wall of the thrust chamber can ensure the stability and reliability of the engine under various working conditions.

[0004] Therefore, there is an urgent need for a rocket thrust chamber inner wall machining deformation control and adaptive device. Summary of the invention

[0005] In view of the above-mentioned problems, the present invention provides a rocket thrust chamber inner wall machining deformation control and adaptive device.

[0006] The technical solution of the present invention is: a rocket thrust chamber inner wall processing deformation control and self-adaptation device, comprising a rocket thrust chamber, a mounting and placing platform with an annular clamping notch at the upper end, a regulating and filling tooling arranged on the mounting and placing platform along the vertical direction, and a fastening component arranged on the mounting and placing platform and clamping the upper and lower ends of the regulating and filling tooling;

[0007] A through installation opening that passes through the bottom end of the installation and placement platform is provided at the center of the annular clamping recess; the control and filling tooling includes a first positioning block that is vertically arranged in the annular clamping recess and matches the inner wall size of the larger end of the rocket thrust chamber opening, a central core shaft that vertically passes through the first positioning block, and a second positioning block that matches the inner wall size of the smaller end of the rocket thrust chamber opening, a plug-in vertical groove that matches the size of the central core shaft is provided at the center of the second positioning block, the first positioning block and the second positioning block are movably connected on opposite sides, a plurality of first adjustment holes are evenly arranged on the end face with the larger opening of the first positioning block, a plurality of second adjustment holes are evenly arranged on the end face with the larger opening of the second positioning block, a plurality of filling channels that are staggered and connected to each other are provided inside the first positioning block, and a filling port that is connected to one of the filling channels is provided on the end face with the larger opening of the first positioning block.

[0008] Furthermore, a polyurethane gasket is provided at the relative connection between the first positioning block and the second positioning block.

[0009] Note: Since the first positioning block and the second positioning block are relatively connected, the friction force of the contact area between the first positioning block and the second positioning block can be increased by the polyurethane gasket, thereby improving the connection reliability.

[0010] Furthermore, the fastening assembly includes a tightening rod on the upper end of the installation and placement platform through an automatic lifting rod, a rotating nut arranged at the center of the end face with a larger opening on the second positioning block, and a top collar arranged at the lower end of the installation and placement platform and sleeved on the outer wall of the central core shaft, and the top collar coincides with the center of the through installation opening.

[0011] Description: After the second positioning block is placed into the rocket thrust chamber through external equipment and connected to the smaller end of the opening of the second positioning block, in order to improve the compactness of the connection, the automatic lifting rod is started, and the extension of the automatic lifting rod drives the clamping rod to move downward and press the second positioning block downward. After clamping, the compression of the automatic lifting rod drives the clamping rod to move upward, and then, the upper end of the second positioning block is pressed and fixed by rotating the nut, and the bottom end of the first positioning block is fixed and installed by the top clamp, which greatly improves the overall mechanical strength and connection compactness of the control and filling tooling, helps to maintain the precise position and stability of the control and filling tooling, and enables the control and filling tooling to provide precise positioning support inside the rocket thrust chamber, ensuring that the geometric shape and dimensional accuracy of the rocket thrust chamber during the processing are controlled to avoid processing errors.

[0012] Furthermore, a top point is provided at the bottom end of the tightening rod, and a top groove matching the size of the top point is provided on the rotating nut.

[0013] Description: The extension of the automatic lifting rod drives the clamping rod to move downward, and when the second positioning block is pressed downward, the top end of the clamping rod is inserted into the top groove at the upper end of the rotating nut, which reduces the contact area and increases the downward pressing pressure, thereby further improving the compactness of the connection.

[0014] Furthermore, it also includes a temperature regulating tube arranged in the regulating and filling tooling, the temperature regulating tube includes a temperature regulating main tube arranged in the central core shaft along the length direction, a plurality of first temperature regulating branch tubes arranged in the first positioning block and connected with the temperature regulating main tube, a plurality of second temperature regulating branch tubes arranged in the second positioning block and connected with the temperature regulating main tube, and a rotating water inlet jacket arranged on the outer wall of the central core shaft and located at the lower end of the through-mounting port, the rotating water inlet jacket is connected with the temperature regulating main tube, and a water injection port is arranged on the outer wall of the rotating water inlet jacket, and the water injection port is connected with the external heating water tank.

[0015] Description: The hot water from the external heating water tank is introduced into the temperature regulating main pipe through the water injection port, and is evenly distributed to each of the first temperature regulating branch pipes and the second temperature regulating branch pipes through the temperature regulating main pipe. At the same time, the glue is injected into each filling channel through the filling port. Under the heating effect of the hot water, the colloid injected into the gap between the first positioning block and the rocket thrust chamber and the gap between the second positioning block and the rocket thrust chamber through each filling channel flows to various places, so that the colloid forms a uniform sealing layer. The above process makes it easier to fill small spaces and complex structures. Good fluidity enables the colloid to fully wet the contact surface, improve the density and bonding strength of the bonding interface, thereby optimizing the bonding effect and enhancing the sealing and durability between the rocket thrust chamber and the control filling tooling.

[0016] Furthermore, it also includes a circulating water injection component, which includes a constant temperature water tank for holding hot water, a forward circulating water pipe for connecting the water outlet of the constant temperature water tank and the water injection port, a circulating liquid outlet arranged on the outer wall of the central core shaft and located between the second positioning block and the rotating nut, and a reverse circulating water pipe for connecting the circulating liquid outlet and the water inlet of the constant temperature water tank.

[0017] Description: When it is necessary to inject hot water into the thermostatic main pipe, the hot water pump in the constant temperature water storage tank is sucked to the forward circulation water pipe, and injected into the rotating water inlet sleeve through the forward circulation water pipe and the water injection port, and enters the thermostatic main pipe and each first thermostatic branch pipe and second thermostatic branch pipe through the rotating water inlet sleeve. Through the heating effect of hot water, the colloid injected into the gap between the first positioning block and the rocket thrust chamber and the second positioning block and the rocket thrust chamber through each filling channel flows to various places, and the injected hot water finally flows out through the circulation outlet and is discharged into the constant temperature water storage tank for recycling. The above process makes it easier to fill small spaces and complex structures. Good fluidity enables the colloid to fully wet the contact surface, improve the density and bonding strength of the bonding interface, thereby optimizing the bonding effect and enhancing the sealing and durability between the rocket thrust chamber and the control filling tooling.

[0018] Furthermore, a bubble mixing box is provided at the water outlet of the constant temperature water storage tank, and a mixing spiral tube is provided in the bubble mixing box, one end of which is connected to the constant temperature water storage tank and a water pump is provided at the connection. The side wall of the mixing spiral tube is connected to an air compressor through a ventilation pipe, and the other end of the mixing spiral tube is connected to the water inlet.

[0019] Description: When hot water is injected into the thermostatic main pipe, the hot water and bubbles are mixed in the mixing spiral pipe and injected into the rotating water inlet jacket and each of the first and second thermostatic branch pipes through the positive circulation water pipe and the water injection port. Due to the presence of bubbles, the bubbles will generate disturbances when moving in the liquid. This disturbance can break the laminar state of the liquid and increase the degree of turbulence, thereby increasing the kinetic energy of the water flow and the fluidity of the colloid, so that the colloid can be better filled into complex or small gaps to form a uniform sealing layer.

[0020] Furthermore, the mixing spiral pipe is composed of two spiral branches which surround each other, and the two spiral branches are connected by a connecting pipe, one of the spiral branches is connected to the constant temperature water tank, and the other spiral branch is connected to the air compressor.

[0021] Description: The hot water in the constant temperature water tank is sucked into the spiral branch pipe connected to it through a pump. At the same time, the external air is compressed into the spiral branch pipe connected to it through an air compressor. Since the two spiral branches are connected through a connecting pipe, the hot water and air are mixed at multiple points through multiple connecting pipes to form a uniform bubble water flow.

[0022] Furthermore, a constant temperature heater is provided in the constant temperature water storage tank.

[0023] Description: The water temperature can be conveniently controlled by a constant temperature heater to ensure that the water temperature is always within the required range, thereby ensuring the fluidity of the colloid injected into the gaps between the first positioning block and the rocket thrust chamber and the second positioning block and the rocket thrust chamber, making it easier to flow and fill in tiny gaps, helping the colloid to better penetrate and cover all surfaces, forming a uniform and bubble-free sealing layer.

[0024] Furthermore, a plurality of supporting legs are provided at the bottom end of the installation and placement platform, and a sliding wheel is provided at the bottom end of each of the supporting legs, and a brake assembly is provided at each of the sliding wheels.

[0025] Note: By setting support legs, the bottom of the installation platform is prevented from directly contacting the ground, thereby ensuring the service life of the installation platform. By setting sliding wheels at the bottom of each support leg, the overall movement of the device is facilitated, and the sliding wheels are fixed by the brake assembly to ensure the stability of the device during use.

[0026] Compared with the prior art, the beneficial effects of the present invention are:

[0027] When the rocket thrust chamber wall processing deformation control and adaptive device of the present invention is in use, it can be customized according to the specific shape and size of the rocket thrust chamber by filling the rocket thrust chamber with a regulating and filling tooling, and the deformation of the thrust chamber wall can be accurately controlled by regulating the pressure and shape of the filling tooling to ensure the geometric accuracy during the processing. The regulating and filling tooling is composed of a first positioning block, a second positioning block and a central core shaft. When the second positioning block is placed in the rocket thrust chamber by an external device and connected to the smaller end of the second positioning block opening, the extension action of the automatic lifting rod drives the tightening rod to move downward and press the second positioning block downward. After being pressed, the compression action of the automatic lifting rod drives the tightening rod to move upward, and then the upper end of the second positioning block is pressed and fixed by the rotating nut, and the bottom end of the first positioning block is fixed and installed by the top clamp. The overall mechanical strength and connection compactness of the control and filling tooling are greatly improved, which is helpful to maintain the precise position and stability of the control and filling tooling, so that the control and filling tooling can provide precise positioning support inside the rocket thrust chamber, ensuring that the geometric shape and dimensional accuracy of the rocket thrust chamber during the processing are controlled; through the heating effect of hot water, the colloid injected into the gap between the first positioning block and the rocket thrust chamber and the second positioning block and the rocket thrust chamber through each filling channel flows to various places, and the injected hot water finally flows out through the circulating liquid outlet and is discharged into the constant temperature water storage tank for recycling. The above process makes it easier to fill small spaces and complex structures. Good fluidity enables the colloid to fully wet the contact surface, improve the density and bonding strength of the bonding interface, thereby optimizing the bonding effect and enhancing the sealing and durability between the rocket thrust chamber and the control and filling tooling. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of the overall external structure of the present invention;

[0029] Figure 2 It is a schematic diagram of the installation structure of the temperature regulating tube of the present invention in the first positioning block and the second positioning block;

[0030] Figure 3 It is a schematic diagram of the installation structure of the filling channel of the present invention in the first positioning block and the second positioning block;

[0031] Figure 4 It is a partial structural schematic diagram of the second positioning block of the present invention;

[0032] Figure 5 It is a partial structural schematic diagram of the first positioning block of the present invention;

[0033] Figure 6 It is a schematic diagram of the internal structure of the bubble mixing box of the present invention;

[0034] Among them, 1-rocket thrust chamber, 2-installation platform, 20-annular clamping recess, 21-through installation port, 22-support leg, 23-sliding wheel, 24-brake assembly, 3-regulating filling tooling, 30-first positioning block, 300-first adjustment hole, 301-filling channel, 31-center core shaft, 310-second adjustment hole, 302-filling port, 32-second positioning block, 320-plug-in vertical slot, 33-polyurethane gasket, 4-fastening assembly, 40-automatic lifting rod, 41-tightening rod, 410-top, 4 2-rotating nut, 420-top groove, 43-top jacket, 5-temperature regulating pipe, 50-temperature regulating main pipe, 51-first temperature regulating branch pipe, 52-second temperature regulating branch pipe, 53-rotating water inlet jacket, 530-water injection port, 6-circulating water injection assembly, 60-constant temperature water storage tank, 600-constant temperature heater, 61-forward circulating water pipe, 62-circulating liquid outlet, 63-reverse circulating water pipe, 64-bubble mixing box, 640-water pump, 641-mixing spiral pipe, 642-spiral branch pipe, 643-connecting pipe, 65-air compressor. DETAILED DESCRIPTION

[0035] In order to further understand the content of the present invention, the present invention is described in detail below through examples.

[0036] Example 1

[0037] like Figure 1As shown, a rocket thrust chamber inner wall processing deformation control and self-adaptation device comprises a rocket thrust chamber 1, a mounting and placing platform 2 with an annular clamping notch 20 at the upper end, a regulating and filling tool 3 arranged on the mounting and placing platform 2 along the vertical direction, a fastening component 4 arranged on the mounting and placing platform 1 and clamping the upper and lower ends of the regulating and filling tool 3, and a temperature regulating tube 5 arranged in the regulating and filling tool 3;

[0038] A through installation opening 21 penetrating through the bottom end of the installation placement platform 2 is provided at the center of the annular clamping recess 20; the regulating and filling tooling 3 includes a first positioning block 30 arranged in the annular clamping recess 20 along the vertical direction and matching the inner wall size of the larger opening end of the rocket thrust chamber 1, a central core shaft 31 penetrating the first positioning block 30 along the vertical direction, and a second positioning block 32 matching the inner wall size of the smaller opening end of the rocket thrust chamber 1, a plug-in vertical groove 320 matching the size of the central core shaft 31 is provided at the center of the second positioning block 32, the first positioning block 30 and the second positioning block 32 are movably connected on opposite sides, 6 first adjustment holes 300 are evenly arranged on the end face with the larger opening of the first positioning block 30, and 6 second adjustment holes 310 are evenly arranged on the end face with the larger opening of the second positioning block 32, and 4 filling channels 301 which are staggered and connected to each other are provided inside the first positioning block 30, and a filling port 302 connected to one of the filling channels 301 is provided on the end face with the larger opening of the first positioning block 30;

[0039] like Figure 2 , 4 As shown in , 5, the temperature regulating tube 5 includes a temperature regulating main pipe 50 arranged in the central core shaft 31 along the length direction, five first temperature regulating branch pipes 51 arranged in the first positioning block 30 and connected to the temperature regulating main pipe 50, five second temperature regulating branch pipes 52 arranged in the second positioning block 32 and connected to the temperature regulating main pipe 50, and a rotating water inlet jacket 53 arranged on the outer wall of the central core shaft 31 and located at the lower end of the through-mounting opening 21, the rotating water inlet jacket 53 is connected to the temperature regulating main pipe 50, and a water injection port 530 is arranged on the outer wall of the rotating water inlet jacket 53, and the water injection port 530 is connected to the external heating water tank;

[0040] A polyurethane gasket 33 is provided at the relative connection between the first positioning block 30 and the second positioning block 32. Since the first positioning block 30 and the second positioning block 32 are relatively connected, the polyurethane gasket 33 can increase the friction force of the contact area between the first positioning block 30 and the second positioning block 32, thereby improving the connection reliability;

[0041] The fastening assembly 4 includes a tightening rod 41 connected to the upper end of the installation and placement platform 1 through an automatic lifting rod 40, a rotating nut 42 arranged at the center of the end face with a larger opening on the second positioning block 32, and a top clamping sleeve 43 arranged at the lower end of the installation and placement platform 2 and sleeved with the outer wall of the central core shaft 31. The top clamping sleeve 43 coincides with the center of the through-mounting opening 21. When the second positioning block 32 is placed in the rocket thrust chamber 1 through an external device and connected to the end with a smaller opening of the second positioning block 32, in order to improve the compactness of the connection, the automatic lifting rod 40 is started, and the tightening rod 41 is driven to move downward through the extension effect of the automatic lifting rod 40, and downward The second positioning block 32 is pressed. After being pressed, the compression action of the automatic lifting rod 40 drives the clamping rod 41 to move upward. Then, the upper end of the second positioning block 32 is pressed and fixed by the rotating nut 42, and the bottom end of the first positioning block 30 is fixed and installed by the top clamp 43, which greatly improves the overall mechanical strength and connection compactness of the regulating and filling tooling 3, helps to maintain the precise position and stability of the regulating and filling tooling 3, and enables the regulating and filling tooling 3 to provide precise positioning support inside the rocket thrust chamber 1, ensuring that the geometric shape and dimensional accuracy of the rocket thrust chamber 1 during the processing are controlled to avoid processing errors;

[0042] A top tip 410 is provided at the bottom end of the jacking rod 41, and a top groove 420 matching the size of the top tip 410 is provided on the rotating nut 42, wherein the automatic lifting rod 40 adopts the existing technology, and the jacking rod 41 is driven to move downward by the extension of the automatic lifting rod 40, and when the second positioning block 32 is pressed downward, the top tip 410 at the bottom end of the jacking rod 41 is inserted into the top groove 420 at the upper end of the rotating nut 42, and the contact area is reduced, the downward pressing pressure is increased, and the connection compactness is further improved;

[0043] Four supporting legs 22 are provided at the bottom of the installation and placement platform 2, and a sliding wheel 23 is provided at the bottom of each supporting leg 22, and a brake assembly 24 is provided at each sliding wheel 23, wherein the sliding wheel 23 and the brake assembly 24 adopt the existing technology, and the supporting legs 22 are provided to avoid the bottom of the installation and placement platform 2 from directly contacting the ground, thereby ensuring the service life of the installation and placement platform 2, and by providing a sliding wheel 23 at the bottom of each supporting leg 22, it is convenient to move the device as a whole, and the sliding wheel 23 is fixed by the brake assembly 24 to ensure the stability of the device during use.

[0044] Example 2

[0045] This embodiment discloses a method for using a rocket thrust chamber inner wall machining deformation control and adaptive device of embodiment 1, comprising the following steps:

[0046] S1. The first positioning block 30 is installed on the inner wall of the rocket thrust chamber 1 by an external device to form a prefabricated product. Then, the prefabricated product is placed in the annular clamping recess 20 so that the central core shaft 31 extends through the through-mounting opening 21 to the bottom end of the mounting platform 2.

[0047] S2. The second positioning block 32 is hoisted to the upper end of the rocket thrust chamber 1 by an external device, and the side with a smaller opening is connected to the upper end of the first positioning block 30. The automatic lifting rod 40 is started, and the extension of the automatic lifting rod 40 drives the clamping rod 41 to move downward, and presses the second positioning block 32 downward. After being pressed, the compression of the automatic lifting rod 40 drives the clamping rod 41 to move upward, and then the upper end of the second positioning block 32 is pressed and fixed by the rotating nut 42, and the bottom end of the first positioning block 30 is fixed and installed by the top clamp 43.

[0048] S3. The hot water from the external heating water tank is introduced into the temperature regulating main pipe 50 through the water injection port 530, and is evenly distributed to each of the first temperature regulating branch pipes 51 and the second temperature regulating branch pipes 52 through the temperature regulating main pipe 50. At the same time, the glue is injected into each filling channel 301 through the filling port 302. Under the heating effect of the hot water, the glue injected into the gap between the first positioning block 30 and the rocket thrust chamber 1 and the gap between the second positioning block 32 and the rocket thrust chamber 1 through each filling channel 301 flows to all places, so that the glue forms a uniform sealing layer. Finally, the rocket thrust chamber 1 is processed.

[0049] Example 3

[0050] The difference between this embodiment and embodiment 1 is that:

[0051] like Figure 1 , 6 As shown, the circulating water injection assembly 6 is also included. The circulating water injection assembly 6 includes a constant temperature water storage tank 60 for holding hot water, a forward circulating water pipe 61 for connecting the water outlet of the constant temperature water storage tank 60 and the water injection port 530, a circulating liquid outlet 62 provided on the outer wall of the central core shaft 31 and located between the second positioning block 32 and the rotating nut 42, and a reverse circulating water pipe 63 for connecting the circulating liquid outlet 62 and the water inlet of the constant temperature water storage tank 60. The hot water is heated so that the hot water injected into the first positioning block 32 through each filling channel 301 is The colloid in the gap between the positioning block 30 and the rocket thrust chamber 1 and the gap between the second positioning block 32 and the rocket thrust chamber 1 flows to various places, and the injected hot water finally flows out through the circulating liquid outlet 62 and is discharged into the constant temperature water storage tank 60 for recycling. The above process makes it easier to fill small spaces and complex structures. Good fluidity enables the colloid to fully wet the contact surface, improve the density and bonding force of the bonding interface, thereby optimizing the bonding effect and enhancing the sealing and durability between the rocket thrust chamber 1 and the regulating and filling tooling 3;

[0052] A bubble mixing box 64 is provided at the water outlet of the constant temperature water storage tank 60. A mixing spiral tube 641 is provided in the bubble mixing box 64, one end of which is connected to the constant temperature water storage tank 60 and a water pump 640 is provided at the connection. The side wall of the mixing spiral tube 641 is connected to an air compressor 65 through a vent pipe. The other end of the mixing spiral tube 641 is connected to the water injection port 530. The water pump 640 and the air compressor 65 both adopt the existing technology. When hot water is injected into the thermostatic main pipe 50, the hot water and the bubbles are mixed in the mixing spiral tube 641, and injected into the rotating water inlet jacket 53 and each of the first thermostatic branch pipe 51 and the second thermostatic branch pipe 52 through the forward circulation water pipe 61 and the water injection port 530. Due to the presence of bubbles, the bubbles will generate disturbances when moving in the liquid. Such disturbances can break the laminar flow state of the liquid and increase the degree of turbulence, thereby increasing the kinetic energy of the water flow and the fluidity of the colloid, so that the colloid can be better filled into complex or small gaps to form a uniform sealing layer.

[0053] The mixing spiral tube 641 is composed of two spiral branches 642 that surround each other, and the two spiral branches 642 are connected by a connecting tube 643, one of the spiral branches 642 is connected to the constant temperature water tank 60, and the other spiral branch 642 is connected to the air compressor 65. A constant temperature heater 600 is provided in the constant temperature water tank 60, wherein the constant temperature heater 600 adopts the existing technology to pump the hot water in the constant temperature water tank 60 into the spiral branch 642 connected thereto, and at the same time, the external air is compressed into the spiral branch 642 connected thereto by the air compressor 65. Since the two spiral branches 642 are connected by the connecting tube 643, the hot water and air are mixed at multiple points through multiple connecting tubes 643 to form a uniform bubble water flow.

[0054] Example 4

[0055] The difference between this embodiment and embodiment 2 is that:

[0056] In step S3, when hot water needs to be injected into the thermostatic main pipe 50, the hot water pump in the constant temperature water storage tank 60 is sucked to the forward circulation water pipe 61, and injected into the rotating water inlet jacket 53 through the forward circulation water pipe 61 and the water injection port 530, and enters the thermostatic main pipe 50 and each of the first thermostatic branch pipes 51 and the second thermostatic branch pipes 52 through the rotating water inlet jacket 53. Through the heating effect of the hot water, the colloid injected into the gap between the first positioning block 30 and the rocket thrust chamber 1 and the second positioning block 32 and the rocket thrust chamber 1 through each filling channel 301 flows to various places, and the injected hot water finally flows out through the circulation outlet 62 and is discharged into the constant temperature water storage tank 60 for recycling;

[0057] In step S3, when hot water is injected into the temperature-adjusting main pipe 50, the hot water in the constant temperature water tank 60 is sucked into the spiral branch pipe 642 connected thereto by a pump. At the same time, the external air is compressed into the spiral branch pipe 642 connected thereto by the air compressor 65. Since the two spiral branch pipes 642 are connected by a connecting pipe 643, the hot water and the air are mixed at multiple points through multiple connecting pipes 643, and are injected into the rotating water inlet jacket 53 and each of the first temperature-adjusting branch pipe 51 and the second temperature-adjusting branch pipe 52 through the forward circulating water pipe 61 and the water injection port 530. Due to the presence of bubbles, the bubbles will cause disturbances when moving in the liquid.

Claims

1. A rocket thrust chamber inner wall processing deformation control and adaptive device, It is characterized in that The invention comprises a rocket thrust chamber (1), a mounting and placing platform (2) with an annular clamping notch (20) at the upper end, a regulating and filling tool (3) arranged on the mounting and placing platform (2) in a vertical direction, and a fastening component (4) arranged on the mounting and placing platform (1) and clamping the upper and lower ends of the regulating and filling tool (3); A through installation opening (21) penetrating the bottom end of the installation placement platform (2) is provided at the center of the annular clamping recess (20); The regulating and filling tool (3) comprises a first positioning block (30) which is arranged in the annular clamping recess (20) along the vertical direction and matches the inner wall size of the larger opening end of the rocket thrust chamber (1), a central core shaft (31) which vertically penetrates the first positioning block (30), and a second positioning block (32) which matches the inner wall size of the smaller opening end of the rocket thrust chamber (1), wherein the center of the second positioning block (32) is provided with a plug-in vertical groove (320) which matches the size of the central core shaft (31), and the first positioning block (30) is provided with a central core shaft (31). ) is movably connected to the opposite side of the second positioning block (32); a plurality of first adjustment holes (300) are evenly arranged on the end surface with a larger opening on the first positioning block (30); a plurality of second adjustment holes (310) are evenly arranged on the end surface with a larger opening on the second positioning block (32); a plurality of filling channels (301) which are staggered and connected to each other are arranged inside the first positioning block (30); a filling port (302) which is in communication with one of the filling channels (301) is arranged on the end surface with a larger opening on the first positioning block (30).

2. A rocket thrust chamber inner wall machining deformation control and adaptive device according to claim 1, It is characterized in that A polyurethane gasket (33) is provided at the relative connection between the first positioning block (30) and the second positioning block (32).

3. A rocket thrust chamber inner wall machining deformation control and adaptive device according to claim 1, It is characterized in that The fastening assembly (4) comprises a clamping rod (41) connected to the upper end of the mounting platform (1) through an automatic lifting rod (40), a rotating nut (42) arranged at the center of the end surface with a larger opening on the second positioning block (32), and a top clamping sleeve (43) arranged at the lower end of the mounting platform (2) and sleeved with the outer wall of the central core shaft (31), wherein the top clamping sleeve (43) coincides with the center of the through mounting opening (21).

4. A rocket thrust chamber inner wall machining deformation control and adaptive device according to claim 3, It is characterized in that The bottom end of the tightening rod (41) is provided with a top point (410), and the rotating nut (42) is provided with a top groove (420) matching the size of the top point (410).

5. A rocket thrust chamber inner wall machining deformation control and adaptive device according to claim 3, It is characterized in that The invention also comprises a temperature regulating tube (5) arranged in the regulating and filling tooling (3), wherein the temperature regulating tube (5) comprises a temperature regulating main tube (50) arranged in the central core shaft (31) along the length direction, a plurality of first temperature regulating branch tubes (51) arranged in the first positioning block (30) and connected to the temperature regulating main tube (50), a plurality of second temperature regulating branch tubes (52) arranged in the second positioning block (32) and connected to the temperature regulating main tube (50), and a rotating water inlet sleeve (53) arranged on the outer wall of the central core shaft (31) and located at the lower end of the through-mounting opening (21), wherein the rotating water inlet sleeve (53) is connected to the temperature regulating main tube (50), and a water injection port (530) is arranged on the outer wall of the rotating water inlet sleeve (53), and the water injection port (530) is connected to an external heating water tank.

6. A rocket thrust chamber inner wall machining deformation control and adaptive device according to claim 5, It is characterized in that The invention also comprises a circulating water injection assembly (6), wherein the circulating water injection assembly (6) comprises a constant temperature water storage tank (60) for storing hot water, a forward circulating water pipe (61) for connecting the water outlet of the constant temperature water storage tank (60) and the water injection port (530), a circulating liquid outlet (62) provided on the outer wall of the central core shaft (31) and located between the second positioning block (32) and the rotating nut (42), and a reverse circulating water pipe (63) for connecting the circulating liquid outlet (62) and the water inlet of the constant temperature water storage tank (60).

7. A rocket thrust chamber inner wall machining deformation control and adaptive device according to claim 6, It is characterized in that A bubble mixing box (64) is provided at the water outlet of the constant temperature water storage tank (60), and a mixing spiral tube (641) is provided in the bubble mixing box (64), one end of which is connected to the constant temperature water storage tank (60) and a water pump (640) is provided at the connection point. The side wall of the mixing spiral tube (641) is connected to an air compressor (65) via a ventilation pipe, and the other end of the mixing spiral tube (641) is connected to the water injection port (530).

8. A rocket thrust chamber inner wall machining deformation control and adaptive device according to claim 6, It is characterized in that The mixing spiral pipe (641) is composed of two spiral branch pipes (642) that surround each other, and the two spiral branch pipes (642) are connected through a connecting pipe (643), one of the spiral branch pipes (642) is connected to the constant temperature water storage tank (60), and the other spiral branch pipe (642) is connected to the air compressor (65).

9. A rocket thrust chamber inner wall machining deformation control and adaptive device according to claim 6, It is characterized in that A constant temperature heater (600) is provided in the constant temperature water storage tank (60).

10. A rocket thrust chamber inner wall machining deformation control and self-adaptation device according to claim 1, It is characterized in that A plurality of supporting legs (22) are provided at the bottom end of the installation and placement platform (2), and a sliding wheel (23) is provided at the bottom end of each supporting leg (22), and a brake assembly (24) is provided at each sliding wheel (23).

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