A device for controlling and adapting deformation during machining of the inner wall of a rocket thrust chamber.

Abstract

This invention provides a deformation control and adaptive device for the inner wall of a rocket thrust chamber, belonging to the field of rocket thrust chamber processing technology. It includes a rocket thrust chamber, an installation platform with an annular snap-fit ​​notch at the upper end, a regulating filling fixture vertically disposed on the installation platform, and a fastening assembly disposed on the installation platform and clamping the upper and lower ends of the regulating filling fixture. By filling the rocket thrust chamber with the regulating filling fixture, the deformation of the inner wall of the thrust chamber can be precisely controlled according to its specific shape and size. This ensures geometric accuracy during processing. The regulating filling fixture provides precise positioning support inside the rocket thrust chamber, ensuring that the geometric shape and dimensional accuracy of the rocket thrust chamber are controlled during processing.

Description

Technical Field

[0001] This invention belongs to the field of rocket thrust chamber processing technology, specifically a deformation control and adaptive device for the inner wall of a rocket thrust chamber. Background Technology

[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, high-pressure gas produced by the combustion of fuel and oxidizer into thrust. The working principle of the rocket thrust chamber involves a series of processes, including fuel and oxidizer atomization, mixing, heat transfer, and combustion. Fuel and oxidizer are atomized into fine particles through nozzles in the thrust chamber, then mix and undergo a chemical reaction in the combustion chamber, releasing a large amount of heat energy. This heat energy is transferred to the coolant through the thrust chamber walls, and the coolant then carries away the heat to prevent the thrust chamber from overheating. Finally, the high-temperature, high-pressure gas is accelerated and discharged through the nozzle, generating thrust.

[0003] Controlling the deformation during manufacturing of the inner wall of the rocket thrust engine is crucial for ensuring the performance and safety of the rocket engine. The inner wall of the thrust engine is subjected to extreme temperature and pressure conditions during rocket flight; even minor deformation can lead to engine failure or even catastrophic consequences. Therefore, strict control over the deformation during manufacturing of the inner wall of the thrust engine can guarantee the stability and reliability of the engine under various operating conditions.

[0004] Therefore, there is an urgent need for a device for controlling and adapting the deformation of the inner wall of a rocket thruster. Summary of the Invention

[0005] To address the aforementioned problems, this invention provides a device for controlling and adapting the deformation of the inner wall of a rocket thrust chamber.

[0006] The technical solution of the present invention is: a deformation control and adaptive device for the inner wall of a rocket thrust chamber, comprising a rocket thrust chamber, an installation platform with an annular snap-fit ​​notch at the upper end, an adjustment and filling fixture disposed on the installation platform in a vertical direction, and a fastening assembly disposed on the installation platform and clamping the upper and lower ends of the adjustment and filling fixture.

[0007] The annular snap-fit ​​notch has a through-hole at its center, extending through the bottom of the mounting platform. The adjusting filling fixture includes a first positioning block vertically positioned within the annular snap-fit ​​notch and matching the inner wall size of the larger opening of the rocket thrust chamber; a central mandrel vertically penetrating the first positioning block; and a second positioning block matching the inner wall size of the smaller opening of the rocket thrust chamber. The second positioning block has a vertical insertion groove at its center that matches the size of the central mandrel. The first and second positioning blocks are movably connected to each other. The larger opening end face of the first positioning block has a plurality of first adjustment holes evenly distributed. The larger opening end face of the second positioning block has a plurality of second adjustment holes evenly distributed. The first positioning block has a plurality of interleaved and interconnected filling channels inside. The larger opening end face of the first positioning block has a filling port communicating with one of the filling channels.

[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 connected relative to each other, the polyurethane gasket can increase the friction between the contact area of ​​the first positioning block and the second positioning block, thereby improving the reliability of the connection.

[0010] Furthermore, the fastening assembly includes a top clamping rod connected to the upper end of the mounting platform via an automatic lifting rod, a rotating nut located at the center of the end face with a larger opening on the second positioning block, and a center clamp located at the lower end of the mounting platform and sleeved with the outer wall of the central mandrel, wherein the center clamp coincides with the center of the through mounting opening.

[0011] Explanation: After the second positioning block is placed into the rocket thrust chamber and connected to the smaller opening end of the second positioning block using external equipment, the automatic lifting rod is activated to improve the connection tightness. The extension of the automatic lifting rod drives the top clamping rod to move downward and press the second positioning block down. After pressing, the compression of the automatic lifting rod drives the top clamping rod to move upward. 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 center clamp. This greatly improves the overall mechanical strength and connection tightness of the control and filling fixture, helps maintain the precise position and stability of the control and filling fixture, and provides precise positioning support inside the rocket thrust chamber. This ensures that the geometric shape and dimensional accuracy of the rocket thrust chamber are controlled during the processing, avoiding processing errors.

[0012] Furthermore, the bottom end of the clamping rod is provided with a center point, and the rotating nut is provided with a top groove that matches the size of the center point.

[0013] Explanation: When the automatic lifting rod extends and moves the top clamping rod downward, pressing down on the second positioning block, the tip of the bottom of the top clamping rod inserts into the top groove of the upper end of the rotating nut. By reducing the contact area, the downward pressing pressure is increased, further improving the connection tightness.

[0014] Furthermore, it also includes a temperature regulating pipe disposed within the regulating filling fixture. The temperature regulating pipe includes a main temperature regulating pipe disposed along the length direction within the central mandrel, a plurality of first temperature regulating branch pipes disposed within the first positioning block and connected to the main temperature regulating pipe, a plurality of second temperature regulating branch pipes disposed within the second positioning block and connected to the main temperature regulating pipe, and a rotating water inlet sleeve disposed on the outer wall of the central mandrel and located at the lower end of the through installation port. The rotating water inlet sleeve is connected to the main temperature regulating pipe, and the outer wall of the rotating water inlet sleeve is provided with a water inlet, which is connected to an external heating water tank.

[0015] Instructions: Hot water from the external heating tank is introduced into the main temperature control pipe through the water inlet, and then evenly distributed to each of the first and second temperature control sub-pipes. Simultaneously, adhesive is injected into each filling channel through the filling port. Under the heating effect of the hot water, the adhesive injected into the gaps between the first positioning block and the rocket thrust chamber, as well as between the second positioning block and the rocket thrust chamber, flows to all locations, forming a uniform sealing layer. This process makes it easier to fill small spaces and complex structures. The good fluidity allows the adhesive to fully wet the contact surfaces, improving 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 fixture.

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

[0017] Instructions: When hot water needs to be injected into the temperature regulating main pipe, the hot water pump in the constant temperature storage tank draws the hot water into the forward circulation pipe, and then injects it into the rotating water inlet jacket through the forward circulation pipe and the water inlet. The hot water then enters the temperature regulating main pipe and each of the first and second temperature regulating sub-pipes. The heating effect of the hot water causes the colloid injected through the filling channels into the gaps between the first positioning block and the rocket thrust chamber, as well as between the second positioning block and the rocket thrust chamber, to flow to all locations. The injected hot water finally flows out through the circulation outlet and is discharged back into the constant temperature storage tank for reuse. This process makes it easier to fill small spaces and complex structures. The good fluidity allows the colloid to fully wet the contact surfaces, improving the density and bonding strength of the adhesive interface, thereby optimizing the bonding effect and enhancing the sealing and durability between the rocket thrust chamber and the regulating filling tooling.

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

[0019] Explanation: When hot water is injected into the main temperature control pipe, the hot water and air bubbles are mixed in the mixing spiral tube and injected into the rotating water inlet jacket and each of the first and second temperature control sub-pipes through the forward circulation water pipe and water inlet. Due to the presence of air bubbles, the movement of air bubbles in the liquid will generate disturbance. This disturbance can break the laminar flow state of the liquid, increase the degree of turbulence, thereby increasing the kinetic energy of the water flow and improving the fluidity of the colloid, so that the colloid can better fill complex or small gaps and form a uniform sealing layer.

[0020] Furthermore, the hybrid spiral tube is composed of two spiral branches that surround each other, and the two spiral branches are connected by a connecting pipe. One spiral branch is connected to a constant temperature water storage tank, and the other spiral branch is connected to the air compressor.

[0021] Explanation: Hot water in the constant temperature water storage tank is pumped into the spiral branch pipe connected to it. At the same time, external air is compressed into the spiral branch pipe connected to it by an air compressor. Since the two spiral branch pipes are connected by 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, the constant temperature water storage tank is equipped with a constant temperature heater.

[0023] Explanation: The constant temperature heater allows for convenient control of the water temperature, ensuring that the water temperature is always within the required range. This guarantees the fluidity of the colloid injected into the gaps between the first positioning block and the rocket thrust chamber, as well as between the second positioning block and the rocket thrust chamber. This makes it easier for the colloid to flow and fill into the tiny gaps, helping the colloid to better penetrate and cover all surfaces, forming a uniform and bubble-free sealing layer.

[0024] Furthermore, the bottom of the installation platform is provided with multiple support legs, and each support leg is provided with a sliding wheel at its bottom, and each sliding wheel is provided with a brake assembly.

[0025] Explanation: By setting support legs, the bottom of the installation platform is prevented from directly contacting the ground, thus 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. The sliding wheels are fixed by a braking 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] The deformation control and adaptive device for the inner wall of the rocket thrust chamber of this invention, when in use, allows for the precise control of the deformation of the inner wall of the thrust chamber by adjusting the pressure and shape of the filling fixture, which can be customized according to the specific shape and size of the rocket thrust chamber. This ensures geometric accuracy during the processing. The adjusting filling fixture consists of a first positioning block, a second positioning block, and a central mandrel. When the second positioning block is placed into the rocket thrust chamber and connected to the smaller opening end of the second positioning block by external equipment, the extension of the automatic lifting rod drives the tightening rod downward, pressing the second positioning block downward. After tightening, the compression of the automatic lifting rod drives the tightening rod upward. 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 fixedly installed by the center clamp. This significantly improves the overall mechanical strength and compactness of the control and filling tooling, helping to maintain its precise position and stability. It provides accurate positioning support within the rocket thrust chamber, ensuring the geometric shape and dimensional accuracy of the rocket thrust chamber are controlled during processing. The heating effect of hot water facilitates the flow of the colloid injected through the filling channels into the gaps between the first positioning block and the rocket thrust chamber, as well as between the second positioning block and the rocket thrust chamber. The injected hot water then flows out through the circulation outlet and is recycled back into the constant-temperature water tank. This process makes it easier to fill small spaces and complex structures. The good fluidity allows the colloid to fully wet the contact surfaces, improving the density and bonding strength of the adhesive interface, thereby optimizing the bonding effect and enhancing the sealing and durability between the rocket thrust chamber and the control and filling tooling. Attached Figure Description

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

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

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

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

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

[0033] Figure 6 This 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 snap-fit ​​notch, 21-through installation port, 22-support leg, 23-sliding wheel, 24-brake assembly, 3-adjustment filling fixture, 30-first positioning block, 300-first adjustment hole, 301-filling channel, 31-central spindle, 310-second adjustment hole, 302-filling port, 32-second positioning block, 320-insertion vertical groove, 33-polyurethane gasket, 4-fastening assembly, 40-automatic lifting rod, 41-tightening rod, 410-center, 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 sleeve, 530-Water inlet, 6-Circulating water injection assembly, 60-Constant temperature water storage tank, 600-Constant temperature heater, 61-Forward circulating water pipe, 62-Circulating 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 Implementation

[0035] To further understand the content of the present invention, the present invention will be described in detail below through embodiments.

[0036] Example 1

[0037] like Figure 1As shown, a rocket thrust chamber inner wall processing deformation control and adaptive device includes a rocket thrust chamber 1, an installation platform 2 with an annular snap-fit ​​notch 20 at the upper end, an adjustment filling fixture 3 set on the installation platform 2 in the vertical direction, a fastening assembly 4 set on the installation platform 1 and clamping the upper and lower ends of the adjustment filling fixture 3, and a temperature control pipe 5 set in the adjustment filling fixture 3.

[0038] The annular snap-fit ​​notch 20 has a through-mounting port 21 at its center, which penetrates the bottom of the mounting platform 2. The adjusting filling fixture 3 includes a first positioning block 30, which is vertically located in the annular snap-fit ​​notch 20 and matches the inner wall size of the larger opening of the rocket thrust chamber 1; a central spindle 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 of the rocket thrust chamber 1. The center of the second positioning block 32 has an insertion vertical groove 320 that matches the size of the central spindle 31. The opposite sides of the first positioning block 30 and the second positioning block 32 are movably connected. The larger opening end face of the first positioning block 30 has 6 first adjustment holes 300 evenly distributed. The larger opening end face of the second positioning block 32 has 6 second adjustment holes 310 evenly distributed. The interior of the first positioning block 30 has 4 interleaved and interconnected filling channels 301. The larger opening end face of the first positioning block 30 has a filling port 302 that communicates with one of the filling channels 301.

[0039] like Figure 2 , 4 As shown in Figure 5, the temperature control pipe 5 includes a main temperature control pipe 50 disposed along the length direction within the central spindle 31, five first temperature control branch pipes 51 disposed within the first positioning block 30 and connected to the main temperature control pipe 50, five second temperature control branch pipes 52 disposed within the second positioning block 32 and connected to the main temperature control pipe 50, and a rotating water inlet sleeve 53 disposed on the outer wall of the central spindle 31 and located at the lower end of the through installation port 21. The rotating water inlet sleeve 53 is connected to the main temperature control pipe 50, and the outer wall of the rotating water inlet sleeve 53 is provided with a water inlet 530, which is connected to an 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 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 top clamping rod 41 connected to the upper end of the mounting platform 1 via an automatic lifting rod 40, a rotating nut 42 located at the center of the larger opening end face of the second positioning block 32, and a center clamping sleeve 43 located at the lower end of the mounting platform 2 and sleeved with the outer wall of the central spindle 31. The center clamping sleeve 43 coincides with the center of the through mounting opening 21. When the second positioning block 32 is placed into the rocket thrust chamber 1 by external equipment and connected to the smaller opening end of the second positioning block 32, the automatic lifting rod 40 is activated to improve the connection tightness. The extension action of the automatic lifting rod 40 drives the top clamping rod 41 to move downwards. The second positioning block 32 is pressed down. After pressing, the compression action of the automatic lifting rod 40 drives the top clamping rod 41 to move upward. Then, the upper end of the second positioning block 32 is pressed and fixed by rotating the nut 42, and the bottom end of the first positioning block 30 is fixedly installed by the top clamp 43. This greatly improves the overall mechanical strength and connection compactness of the regulating filling fixture 3, helps to maintain the precise position and stability of the regulating filling fixture 3, and enables the regulating filling fixture 3 to provide precise positioning support inside the rocket thrust chamber 1. This ensures that the geometric shape and dimensional accuracy of the rocket thrust chamber 1 are controlled during the processing, and avoids processing errors.

[0042] The bottom end of the clamping rod 41 is provided with a tip 410, and the rotating nut 42 is provided with a top groove 420 that matches the size of the tip 410. The automatic lifting rod 40 adopts existing technology. When the extension of the automatic lifting rod 40 drives the clamping rod 41 to move downward and presses the second positioning block 32 downward, the tip 410 at the bottom end of the clamping rod 41 is inserted into the top groove 420 at the upper end of the rotating nut 42. By reducing the contact area, the downward pressing pressure is increased, and the connection compactness is further improved.

[0043] The installation platform 2 has four support legs 22 at its bottom, and each support leg 22 has a sliding wheel 23 at its bottom. Each sliding wheel 23 is equipped with a brake assembly 24. The sliding wheel 23 and the brake assembly 24 adopt existing technology. By setting the support legs 22, the bottom of the installation platform 2 is prevented from directly contacting the ground, thus ensuring the service life of the installation platform 2. By setting the sliding wheel 23 at the bottom of each support leg 22, it is convenient to move the entire device. The brake assembly 24 fixes the sliding wheel 23, ensuring the stability of the device during use.

[0044] Example 2

[0045] This embodiment discloses a method for using a deformation control and adaptive device for the inner wall of a rocket thrust chamber, as described in Embodiment 1, including the following steps:

[0046] S1. The first positioning block 30 is installed on the inner wall of the rocket thrust chamber 1 by external equipment to form a prefabricated product. Then, the prefabricated product is placed in the annular snap-fit ​​notch 20 so that the central spindle 31 extends to the bottom of the installation platform 2 through the through installation port 21.

[0047] S2. The second positioning block 32 is hoisted to the upper end of the rocket thrust chamber 1 using external equipment, and its side with the smaller opening is connected to the upper end of the first positioning block 30. The automatic lifting rod 40 is activated, and the extension action of the automatic lifting rod 40 drives the top clamping rod 41 to move downward and press the second positioning block 32 downward. After pressing, the compression action of the automatic lifting rod 40 drives the top clamping rod 41 to move upward. Then, the upper end of the second positioning block 32 is pressed and fixed by rotating the nut 42, and the bottom end of the first positioning block 30 is fixed and installed by the top clamp 43.

[0048] S3. Hot water from the external heating tank is introduced into the temperature regulating main pipe 50 through the water inlet 530, and then evenly distributed to each of the first temperature regulating branch pipes 51 and the second temperature regulating branch pipes 52. At the same time, adhesive is injected into each filling channel 301 through the filling port 302. Under the heating effect of the hot water, the adhesive 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 all places, so that the adhesive 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, it also includes a circulating water injection assembly 6, which includes a constant temperature water storage tank 60 for holding hot water, a forward circulating water pipe 61 for connecting the outlet and inlet 530 of the constant temperature water storage tank 60, a circulating outlet 62 located on the outer wall of the central spindle 31 and between the second positioning block 32 and the rotating nut 42, and a reverse circulating water pipe 63 for connecting the circulating outlet 62 and the inlet of the constant temperature water storage tank 60. Through the heating effect of hot water, the water is injected into the first constant temperature water storage tank 60 through each filling channel 301. The flow of the colloid in the gaps between the positioning block 30 and the rocket thrust chamber 1, and between the second positioning block 32 and the rocket thrust chamber 1, is distributed to all parts. The injected hot water finally flows out through the circulation outlet 62 and is discharged back into the constant temperature water storage tank 60 for recycling. The above process makes it easier to fill small spaces and complex structures. The good fluidity allows 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 control filling tooling 3.

[0052] A bubble mixing chamber 64 is provided at the outlet of the constant temperature water storage tank 60. Inside the bubble mixing chamber 64, there is a mixing spiral tube 641 connected to the constant temperature water storage tank 60 at one end and a water pump 640 at the connection point. An air compressor 65 is connected to the side wall of the mixing spiral tube 641 through a vent pipe. The other end of the mixing spiral tube 641 is connected to the water inlet 530. The water pump 640 and the air compressor 65 both adopt existing technology. When hot water is injected into the temperature regulating main pipe 50, the hot water and bubbles are mixed in the mixing spiral tube 641 and injected into the rotating water inlet sleeve 53 and each of the first temperature regulating branch pipes 51 and the second temperature regulating branch pipes 52 through the forward circulation water pipe 61 and the water inlet 530. Due to the presence of bubbles, the bubbles will generate disturbance when they move in the liquid. This disturbance can break the laminar flow state of the liquid, increase the degree of turbulence, thereby increasing the kinetic energy of the water flow and improving the fluidity of the colloid, so that the colloid can better fill the complex or small gaps and form a uniform sealing layer.

[0053] The mixing spiral tube 641 consists of two spiral branch tubes 642 that surround each other and are connected by a connecting pipe 643. One spiral branch tube 642 is connected to a constant temperature water storage tank 60, and the other spiral branch tube 642 is connected to an air compressor 65. The constant temperature water storage tank 60 is equipped with a constant temperature heater 600. The constant temperature heater 600 uses existing technology to pump hot water from the constant temperature water storage tank 60 into the spiral branch tube 642 connected to it. At the same time, the air compressor 65 compresses external air into the spiral branch tube 642 connected to it. Since the two spiral branch tubes 642 are connected by a connecting pipe 643, the hot water and air are mixed at multiple points through multiple connecting pipes 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 temperature regulating main pipe 50, the hot water pump in the constant temperature storage tank 60 is drawn into the forward circulation water pipe 61, and injected into the rotating water inlet sleeve 53 through the forward circulation water pipe 61 and the water inlet 530. The hot water then enters the temperature regulating main pipe 50 and each of the first temperature regulating branch pipes 51 and the second temperature regulating branch pipes 52 through the rotating water inlet sleeve 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. The injected hot water finally flows out through the circulation outlet 62 and is discharged back into the constant temperature storage tank 60 for recycling.

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

Claims

1. A device for controlling and adapting deformation during machining of the inner wall of a rocket thrust chamber, characterized in that, It includes a rocket thrust chamber (1), an installation platform (2) with an annular snap-fit ​​notch (20) at the upper end, a regulating filling fixture (3) set on the installation platform (2) in the vertical direction, and a fastening assembly (4) set on the installation platform (1) and clamping the upper and lower ends of the regulating filling fixture (3). The annular snap-fit ​​notch (20) is provided with a through-hole (21) at the center of the bottom of the mounting platform (2). The regulating filling fixture (3) includes a first positioning block (30) located vertically in the annular snap-fit ​​notch (20) and matching the inner wall size of the larger opening end of the rocket thrust chamber (1), a central spindle (31) penetrating the first positioning block (30) vertically, and a second positioning block (32) matching the inner wall size of the smaller opening end of the rocket thrust chamber (1). The center of the second positioning block (32) is provided with an insertion vertical groove (320) matching the size of the central spindle (31). The opposite sides of the first positioning block (30) and the second positioning block (32) are movably connected. The first positioning block (30) is provided with a plurality of interleaved and interconnected filling channels (301) inside. The larger opening end face of the first positioning block (30) is provided with a filling port (302) communicating with one of the filling channels (301). It also includes a temperature control tube (5) located in the control filling fixture (3). The temperature control tube (5) includes a temperature control main tube (50) located in the central spindle (31) along the length direction, a plurality of first temperature control branch tubes (51) located in the first positioning block (30) and connected to the temperature control main tube (50), a plurality of second temperature control branch tubes (52) located in the second positioning block (32) and connected to the temperature control main tube (50), and a rotating water inlet sleeve (53) located on the outer wall of the central spindle (31) and at the lower end of the through installation port (21). The rotating water inlet sleeve (53) is connected to the temperature control main tube (50), and the outer wall of the rotating water inlet sleeve (53) is provided with a water inlet (530). The water inlet (530) is connected to an external heating water tank.

2. The device for controlling and adapting deformation during machining of the inner wall of a rocket thrust chamber according to claim 1, 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. The device for controlling and adapting deformation during machining of the inner wall of a rocket thrust chamber according to claim 1, characterized in that, The fastening assembly (4) includes a top clamping rod (41) connected to the upper end of the installation platform (1) via an automatic lifting rod (40), a rotating nut (42) located at the center of the end face with a larger opening on the second positioning block (32), and a top clamp (43) located at the lower end of the installation platform (2) and sleeved with the outer wall of the central spindle (31). The top clamp (43) coincides with the center of the through installation port (21).

4. The device for controlling and adapting deformation during machining of the inner wall of a rocket thrust chamber according to claim 3, characterized in that, The bottom end of the clamping rod (41) is provided with a top point (410), and the rotating nut (42) is provided with a top groove (420) that matches the size of the top point (410).

5. The device for controlling and adapting deformation during machining of the inner wall of a rocket thrust chamber according to claim 3, characterized in that, It also includes a circulating water injection assembly (6), which includes a constant temperature water storage tank (60) for holding hot water, a forward circulating water pipe (61) for connecting the outlet of the constant temperature water storage tank (60) and the water injection port (530), a circulating liquid outlet (62) located on the outer wall of the central spindle (31) and 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 inlet of the constant temperature water storage tank (60).

6. The device for controlling and adapting deformation during machining of the inner wall of a rocket thrust chamber according to claim 5, characterized in that, The outlet of the constant temperature water storage tank (60) is provided with a bubble mixing box (64). The bubble mixing box (64) is provided with a mixing spiral tube (641) that is connected to the constant temperature water storage tank (60) at one end and a water pump (640) is provided at the connection. An air compressor (65) is connected to the side wall of the mixing spiral tube (641) through a vent pipe. The other end of the mixing spiral tube (641) is connected to the water inlet (530).

7. The device for controlling and adapting deformation during machining of the inner wall of a rocket thrust chamber according to claim 6, characterized in that, The hybrid spiral pipe (641) is composed of two spiral branches (642) that surround each other, and the two spiral branches (642) are connected by a connecting pipe (643). One spiral branch (642) is connected to the constant temperature water storage tank (60), and the other spiral branch (642) is connected to the air compressor (65).

8. The device for controlling and adapting deformation during machining of the inner wall of a rocket thrust chamber according to claim 5, characterized in that, The constant temperature water storage tank (60) is equipped with a constant temperature heater (600).

9. The device for controlling and adapting deformation during machining of the inner wall of a rocket thrust chamber according to claim 1, characterized in that, The installation platform (2) has multiple support legs (22) at its bottom, and each support leg (22) has a sliding wheel (23) at its bottom, and each sliding wheel (23) has a brake assembly (24).

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