Low-friction buoyancy thrust adapter for rocket testing

Abstract

The present invention discloses a low-friction buoyancy thrust adapter for rocket testing, comprising a floating thrust plate and a support assembly for floatingly supporting the floating thrust plate. The support assembly comprises a single plunger cylinder, wherein the extended end face A of the piston rod of the single plunger cylinder contacts the plate surface A of the floating thrust plate through a lubricating fluid, and an end face sealing ring is provided between the end face A and the plate surface A. The present invention realizes the axial support load required during the test based on the single plunger cylinder; at the same time, the floating thrust plate and the piston rod are separated so as to be independent of each other, and then the floating thrust plate is independent of the outside of the oil chamber. Therefore, no matter how the floating thrust plate floats with the change of the engine center, the position change of the floating thrust plate has no effect on the space in the oil chamber. The space in the oil chamber is constant, so there is no need to configure a complex oil circuit, which reduces the processing cost of the thrust adapter and improves the convenience of subsequent maintenance. In addition, there is no instantaneous high pressure test condition that has extremely high sealing requirements.

Description

Technical Field

[0001] The invention relates to the field of rocket technology, in particular to a low-friction buoyancy thrust adapter for rocket testing. Background Art

[0002] Ground-based rocket engine ignition tests measure transient thrust, combustion chamber pressure, and other key parameters. As one of the primary methods for evaluating rocket engine performance and improving design, ground-based ignition tests are crucial for the inspection of rocket engine products and the development of new models. Existing engine thrust test benches utilize fixed mechanical structures for their support devices, resulting in high internal friction and reduced accuracy in testing engine parameters. Furthermore, after engine ignition, the engine casing expands due to heat, causing its center to shift upward, while the center of the support device remains unchanged. Consequently, a positional difference between the center of the rocket and the center of the support device occurs after ignition. This causes significant stress to accumulate at the mechanical connection between the rocket's head and the support device due to the engine's expansion and upward centering, while the center of the support device remains unchanged. This hinders engine thrust measurement. Furthermore, when the support device receives thrust from the engine, the flexible components are compressed and deformed, generating a return thrust on the engine. Excessive engine thrust can easily cause cracks in the flexible components, even posing a risk of explosion. This not only creates safety hazards but also further reduces the accuracy of engine parameter testing. In practice, this mechanical support structure is only suitable for engine thrust testing on small rockets, typically 500-ton rockets. Testing a 1,500-ton rocket requires three sets of flexible components, which not only increases the size of the support structure but also increases testing costs and increases test errors.

[0003] Based on the above-mentioned technical problems, the prior art CN210400854U discloses a buoyancy thrust adapter, one end of which is fixed to the thrust wall, and the other end of which forms a floating thrust plate that can float upward through fluid contact. The floating thrust plate contacts the end of the engine, so that after the subsequent engine ignition, when the rocket shell expands due to heat and the center moves upward, the floating thrust plate can be suspended and moved upward in the fluid. Then, during the entire test process, the floating thrust plate can be adaptively adjusted according to the actual center position of the engine, avoiding stress concentration due to misalignment at the connection between the rocket head and the support device, protecting the quality of the connection between them, reducing friction, and improving the test accuracy of various engine parameters.

[0004] However, in this type of buoyant thrust adapter, since one end of the floating thrust plate serves as a piston rod and is installed in the inner cavity of the connecting member serving as the cylinder, an annulus is formed between the circumferential surface of the piston rod and the circumferential surface of the inner cavity. As the floating thrust plate floats up and down in the radial direction and moves axially, the volume of the space between the piston rod and the inner cavity varies significantly. Due to the compressibility of the fluid, inlet and outlet oil passages must be provided on the connecting member to facilitate the replenishment or drainage of oil when the volume of the space between the piston rod and the inner cavity increases or decreases. This not only increases the number of inlet and outlet oil passages on the connecting member, increasing manufacturing and maintenance costs, but also increases the pressure of the fluid in the space between the piston rod and the inner cavity as the volume decreases, placing extremely high demands on the sealing performance of this space and increasing the sealing cost. Summary of the Invention

[0005] The purpose of the present invention is to provide a low-friction buoyancy thrust adapter for rocket testing, which solves the above-mentioned technical problems that the existing low-friction, center-adjustable floating thrust adapter requires complex oil circuits, high processing costs, troublesome maintenance and extremely high sealing requirements.

[0006] The technical solution adopted in the present invention is as follows:

[0007] A low-friction buoyancy thrust adapter for rocket testing includes a floating thrust plate and a support assembly for radially and axially floating support thereof. The support assembly includes a single-plunger cylinder. An end face A of a piston rod of the single-plunger cylinder extends out of an oil chamber of the cylinder barrel of the single-plunger cylinder, and contacts a side plate face A of the floating thrust plate through a lubricating fluid. An end face sealing ring is provided between the end face A and the plate face A to prevent the lubricating fluid from overflowing therebetween.

[0008] Furthermore, an exhaust channel is provided on the floating thrust plate to connect the space sealed by the inner ring of the end face sealing ring with the outside world, and a sealing plug is provided at one end of the exhaust channel connected to the outside world to seal the end thereof.

[0009] Furthermore, one end of the exhaust channel is communicated with the plate surface A, and the other end thereof is communicated with the circumferential surface of the floating thrust plate.

[0010] Furthermore, a limiting block is installed on the upper side of the piston rod side wall, and the upper side of the limiting block close to the side wall of the floating thrust plate protrudes outward to form a limiting step radially opposite to the floating thrust plate.

[0011] Furthermore, the limit block is an arc-shaped strip structure, the center of which is located on the axis of the piston rod, the inner circumference of which is in contact with the outer circumference of the piston rod, and is installed on the piston rod through an upper bolt.

[0012] Furthermore, a support block is installed on the lower side of the piston rod side wall, and the upper side of the support block close to the side wall of the floating thrust plate protrudes outward to form a support step radially opposite to the floating thrust plate.

[0013] Furthermore, the support block is an arc-shaped strip structure, the center of which is located on the axis of the piston rod, the inner circumference of which is in contact with the outer circumference of the piston rod, and is installed on the piston rod through a lower bolt.

[0014] Furthermore, a dust cover sleeved on the extended end of the piston rod is provided between the end surface of the cylinder close to the floating thrust plate and the plate surface A, and both ends of the dust cover are in contact with the end surface of the cylinder and the plate surface A respectively.

[0015] Furthermore, a spherical groove is provided at the closed end of the cylinder, and a posture adjustment assembly is installed in the spherical groove. The center line of the spherical groove coincides with the axis of the single-plunger cylinder. The posture adjustment assembly includes a posture adjustment ball head, a posture adjustment washer and a posture adjustment screw. One side of the posture adjustment ball head is flat and is located outside the spherical groove, and the other side thereof bulges outward into a convex spherical surface that fits with the concave spherical surface of the spherical groove. The rod of the posture adjustment screw passes through the posture adjustment washer and the posture adjustment ball head and is threadedly connected to the closed end of the cylinder, and the posture adjustment ball head and the posture adjustment screw are clearance-matched.

[0016] Furthermore, the lubricating fluid is grease.

[0017] Due to the adoption of this technical solution, the beneficial effects of the present invention are:

[0018] 1. The low-friction buoyancy thrust adapter for rocket testing of the present invention separates the floating thrust plate from the piston rod. The present invention utilizes a single plunger cylinder and piston rod to achieve the required axial support load during testing. Furthermore, the floating thrust plate, which is independent of the piston rod and floats on the extended end of the piston rod by lubricating fluid, achieves buoyancy to match the upward shift of the engine center, ensuring that the structural height matches the structural changes of the engine while maintaining low friction. Furthermore, the buoyancy is independent of the exterior of the oil chamber. Therefore, regardless of how the floating thrust plate floats with changes in the engine center, its positional changes have no effect on the space within the oil chamber. The space within the oil chamber remains constant, eliminating the need for complex oil circuits. This reduces the processing cost of the thrust adapter and improves the convenience of subsequent maintenance. Furthermore, there is no need for transient high pressure test conditions that place extremely high demands on sealing.

[0019] 2. The low-friction buoyancy thrust adapter for rocket testing of the present invention discharges the gas between the end surface A and the plate surface A through the exhaust duct, thereby reducing or even eliminating the gas between the end surface A and the plate surface A, thereby reducing the friction between the end surface A and the plate surface A, and facilitating the collection of various engine parameters;

[0020] 3. The provision of the attitude adjustment assembly for the low-friction buoyancy thrust adapter for rocket testing of the present invention facilitates the elimination of installation errors and ensures centering when installing the thrust adapter, thereby facilitating subsequent testing.

[0021] 4. Compared to the prior art, the low-friction buoyancy thrust adapter for rocket testing of the present invention utilizes a single plunger cylinder as a single integral component, which not only improves the strength of the single plunger cylinder and increases its load capacity at a low cost, but also requires no assembly, eliminating assembly steps and reducing manufacturing costs. Furthermore, the sealing ring and dust seal are installed on the circumferential surface of the oil chamber, and the piston rod is directly inserted into the oil chamber, making assembly simple and efficient. This significantly improves the thrust adapter assembly process and simplifies the previously numerous assembly steps.

[0022] 5. The low-friction buoyancy thrust adapter for rocket testing disclosed herein uses lubricating oil for floating support, as is common in the art. However, the following tests clearly demonstrate that the friction coefficient of grease is lower than that of lubricating oil. Using grease for fluid support of the floating thrust plate can further reduce the friction of the floating thrust plate, facilitating the acquisition of various engine parameters, improving data acquisition accuracy, and reducing interference caused by friction. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments. It should be understood that the proportional relationships of the various components in the drawings of this specification do not represent the proportional relationships in actual material selection and design, and are merely schematic diagrams of structures or positions, among which:

[0024] Figure 1 It is a structural schematic diagram of the present invention;

[0025] Figure 2 This is a schematic diagram of the installation of the limit block;

[0026] Figure 3 This is a schematic diagram of the installation of the support block;

[0027] Figure 4 It is a structural diagram of the limit block;

[0028] Figure 5 It is a schematic diagram of the cooperation between the piston rod and the cylinder.

[0029] Description of the reference numerals in the accompanying drawings:

[0030] 1-cylinder, 2-piston rod, 3-limit block, 301-limit step, 4-dust cover, 5-floating thrust plate, 6-support block, 601-support step, 7-positioning sleeve, 8-attitude adjustment ball head, 9-attitude adjustment washer, 10-attitude adjustment screw, 11-spherical washer, 12-conical washer, 13-first sealing ring, 14-second sealing ring, 15-dust ring, 16-upper bolt, 17-upper washer, 18-outer end face sealing ring, 19-dust cover mounting bolt, 20-middle end face sealing ring, 21-inner auxiliary bolt, 22-inner auxiliary washer, 23-inner end face sealing ring, 24-lower bolt, 25-lifting eye screw, 26-copper support, 27-sealing plug, 28-pull wire sensor, 29-outer auxiliary bolt, 30-exhaust duct, 31-spherical groove, 32-lower washer, 33-countersunk bolt hole. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention. That is, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments.

[0032] The following combination Figures 1 to 5 The present invention is described in detail.

[0033] Example 1

[0034] like Figures 1 to 3 As shown, the low-friction buoyancy thrust adapter for rocket testing of the present invention includes a floating thrust plate 5 and a support assembly that provides radial and axial floating support for the floating thrust plate 5. The support assembly includes a single-plunger cylinder. The piston rod 2 of the single-plunger cylinder extends out of the oil chamber of the cylinder barrel 1 of the single-plunger cylinder. The end face A of the single-plunger cylinder protrudes from the oil chamber of the cylinder barrel 1 of the single-plunger cylinder. The end face A of the floating thrust plate 5 contacts the plate surface A of the floating thrust plate 5 through the lubricating fluid. An end face sealing ring is provided between the end face A and the plate surface A to prevent the lubricating fluid from escaping therebetween. An oil film surface is formed between the end face A and the plate surface A.

[0035] The end face sealing rings are preferably end face Gly rings, and there are three of them, which are, from inside to outside, the inner end face sealing ring 23, the middle end face sealing ring 20 and the outer end face sealing ring 18.

[0036] The lubricating fluid may be lubricating liquid, grease or other fluids.

[0037] When using this invention for rocket engine testing, the bottom of cylinder barrel 1 is fixed to the thrust wall, and its other end is connected to the engine's connection end via a thrust frame ball joint assembly. When the engine is ignited, the oil chamber of the single-plunger cylinder is supplied with oil via the large oil cylinder to match the engine's axial thrust. Simultaneously, as the engine's centerline moves upward due to thermal expansion, the floating thrust plate 5 adjusts synchronously with the engine's actual center position, ensuring the accuracy of testing various engine parameters.

[0038] Compared with the prior art, the present invention designs a buoyancy thrust adapter that separates the floating thrust plate and the piston rod. The present invention realizes the axial support load required during the test based on the cooperation of a single plunger cylinder and a piston rod; at the same time, the floating is achieved based on the floating thrust plate 5 that is independent of the piston rod and floats on the extended end of the piston rod by the lubricating fluid to match the upward movement of the center of the engine, ensuring that the structural height matches the structural changes of the engine and maintains low friction; at the same time, the floating is independent of the outside of the oil chamber, so that no matter how the floating thrust plate floats with the change of the engine center, the position change of the floating thrust plate has no effect on the space in the oil chamber. The space in the oil chamber is constant, so there is no need to configure a complex oil circuit, which reduces the processing cost of the thrust adapter, improves the convenience of later maintenance, and does not have instantaneous high pressure, a test condition that has extremely high sealing requirements.

[0039] At the same time, in the present invention, the floating plate and the piston rod are independent, so that the floating is achieved only based on the floating plate and the lubricating fluid between the floating plate and the piston rod, so there is no need to set up an oil chamber for the piston rod to float, thereby simplifying the single-plunger cylinder structure, and eliminating the need to use multiple parts to splice a steel body with an opening smaller than the oil chamber, thereby reducing manufacturing costs.

[0040] Example 2

[0041] This embodiment further illustrates the oil film surface based on the embodiment 1.

[0042] When applying lubricating fluid between the end face A and the plate surface A, it is not possible to ensure that the surface of the lubricating fluid is a flat plane. Therefore, when lubricating fluid is applied to the end face A and / or the plate surface A, and the floating thrust plate 5 is installed on one side of the end face A of the piston rod so that the end face A contacts the plate surface A on one side of the floating thrust plate 5 through the lubricating fluid, the contact surface between them is not a completely flat plane because the surface of the lubricating fluid is not a completely flat plane. Therefore, when the end face A and the plate surface A contact through the lubricating fluid, air is present between them. The air increases the friction between the end face A and the plate surface A, which is not conducive to the collection of various engine parameters. Therefore, the following structure is adopted:

[0043] like Figure 1As shown, the floating thrust plate 5 is provided with an exhaust channel 30 that connects the space sealed by the inner ring of the end face sealing ring with the outside world, and a sealing plug 27 that blocks the end of the exhaust channel 30 is provided at one end connected to the outside world.

[0044] Furthermore, one end of the exhaust channel 30 is communicated with the plate surface A, and the other end thereof is communicated with the circumferential surface of the floating thrust plate 5 .

[0045] The installation of the floating thrust plate 5 is as follows: S1. Apply lubricating fluid to the end face A and / or the plate surface A; S2. Set the floating thrust plate 5 on one side of the end face A, and the end face A is in contact with the plate surface A through the lubricating fluid; S3. Fix the floating thrust plate 5 and the single plunger cylinder, and supply oil to the single plunger cylinder to extend the piston rod outward, thereby increasing the axial extrusion force between the piston rod and the floating thrust plate 5, and then discharge the gas between the end face A and the plate surface A through the exhaust channel 30, thereby reducing or even eliminating the gas between the end face A and the plate surface A, and then reducing the friction between the end face A and the plate surface A, which facilitates the collection of various engine parameters; S4. Then, use the sealing plug 27 to seal the end of the exhaust channel 30 that is connected to the outside world.

[0046] Example 3

[0047] The floating restrictions of floating plates are implemented as follows:

[0048] like Figure 1 and Figure 2 As shown, a limiting block 3 is installed on the upper side of the side wall of the piston rod 2 , and the upper side of the side wall of the limiting block 3 close to the floating thrust plate 5 is convex to form a limiting step 301 radially opposite to the floating thrust plate 5 .

[0049] The minimum vertical distance between the limiting step 301 and the floating thrust plate 5 is the maximum distance that the floating thrust plate 5 can move vertically; the setting of the limiting step 301 limits the floating stroke of the floating thrust plate 5, preventing the floating thrust plate 5 from slipping off the end surface A of the piston rod, thereby ensuring the sealing between the end surface A and the plate surface A, and ensuring the smooth progress of the rocket engine test.

[0050] Further, if Figure 4 As shown, the limit block 3 is an arc-shaped strip structure, the center of which is located on the axis of the piston rod 2, and the inner circumference thereof is in contact with the outer circumference of the piston rod 2. The limit block 3 is mounted on the piston rod 2 via an upper bolt 16. The upper bolt 16 is preferably a countersunk bolt, such as Figure 2 As shown, an upper washer 17 is sleeved on the upper bolt 16 to prevent the upper bolt from loosening.

[0051] Example 4

[0052] The gravity support of the floating thrust plate 5 is specifically implemented as follows: Figure 1 and Figure 3 As shown, a support block 6 is installed on the lower side of the side wall of the piston rod 2 , and the upper side of the side wall of the support block 6 close to the floating thrust plate 5 is convex to form a support step 601 radially opposite to the floating thrust plate 5 .

[0053] Furthermore, the support block 6 is an arc-shaped strip structure, the center of which is located on the axis of the piston rod 2 , and the inner circumference thereof is in contact with the outer circumference of the piston rod 2 , and is mounted on the piston rod 2 via a lower bolt 24 .

[0054] The lower bolt 24 is preferably a countersunk bolt, such as Figure 3 As shown, a lower washer is sleeved on the lower bolt 24 to prevent the lower bolt 24 from loosening.

[0055] Example 5

[0056] In order to prevent dust from entering between the end face A and the plate surface A, a dust cover 4 is provided between the end face of the cylinder 1 close to the floating thrust plate 5 and the plate surface A, and is sleeved on the protruding end of the piston rod 2. The two ends of the dust cover 4 are in contact with the end face of the cylinder 1 and the plate surface A respectively.

[0057] The dust cover 4 covers the limit block 3 and the support block 6. The dust cover is preferably a bellows with both ends bulging outward to form an outward edge. The dust cover mounting bolts 19 pass through the outward edge and are connected to the cylinder or floating thrust plate.

[0058] Example 6

[0059] During the test, higher verticality, straightness and flatness can obtain better test parameters. During actual installation, a relatively fixed thrust wall is required to adjust the installation position of the thrust adapter actually assembled. Therefore, a spherical groove 31 is provided at the closed end of the cylinder 1, and a posture adjustment component is installed in the spherical groove 31. The center line of the spherical groove 31 coincides with the axis of the single plunger cylinder. The posture adjustment component includes a posture adjustment ball head 8, a posture adjustment washer 9 and a posture adjustment screw 10. One side of the posture adjustment ball head 8 is flat and located outside the spherical groove 31, and the other side thereof is convex to form a convex spherical surface that fits the concave spherical surface of the spherical groove 31. The rod of the posture adjustment screw 10 passes through the posture adjustment washer 9 and the posture adjustment ball head 8 and is threadedly connected to the closed end of the cylinder 1, and the posture adjustment ball head 8 and the posture adjustment screw 10 are clearance-matched.

[0060] The setting of the attitude adjustment component makes it easy to eliminate installation errors and ensure centering when installing the thrust adapter, which is beneficial to subsequent tests.

[0061] Example 7

[0062] To facilitate lifting, multiple eyebolts 25 are preferably installed on the outer circumference of the cylinder 1. To collect information on the internal pressure of the oil chamber, a pressure gauge is preferably provided on the outer circumference of the cylinder 1, with a pressure sensor installed in the gauge to collect pressure changes in the oil chamber. A displacement sensor is provided between the floating thrust plate and the piston rod to detect the thickness of the oil film between them. Furthermore, to enhance the assembly convenience of the present invention, an internal auxiliary bolt 21 is preferably used to connect and secure the floating thrust plate 5 to the piston rod, and an external auxiliary bolt 29 is preferably used to connect and secure the floating thrust plate 5 to the cylinder. After assembly, to vent the gas between the floating thrust plate and the piston rod, the cylinder is first secured, followed by the floating thrust plate 5. The internal and external auxiliary bolts 21 and 29 are then removed, and oil is then supplied to the oil chamber. This allows the piston rod to extend outward, squeezing the mating surface between it and the floating thrust plate, thereby venting the gas between them.

[0063] One side of the outer circumference of the cylinder 1 bulges outward to form an outward edge, and one side of the outer circumference of the floating thrust plate 5 bulges outward to form an outward edge. The end of the rod of the external auxiliary bolt 29 passes through the outward edge of the floating thrust plate 5 and is threadedly connected to the outward edge of the cylinder 1.

[0064] The outer circumferential surface of the piston rod is located on one side outside the oil chamber and bulges outward to form an outward edge. The end of the rod of the internal auxiliary bolt 21 passes through the plate body of the floating thrust plate 5 and is threadedly connected to the outward edge of the piston rod. The limit block and the support block are both installed on the outward edge of the piston rod.

[0065] Example 8

[0066] In the present invention, Figure 1 As shown, the single plunger cylinder has no cylinder head. The single plunger cylinder seals the oil chamber from the outside world through a sealing assembly between the outer circumference of the piston rod 2 and the inner circumference of the cylinder barrel 1. The sealing assembly includes a first sealing ring 13, a second sealing ring 14 and a dust ring 15 which are sequentially installed on the inner circumference of the cylinder barrel 1 from the cylinder bottom to the extended end of the piston rod. Figure 1 and Figure 5 shown.

[0067] Compared with the prior art, the single-plunger cylinder in the present invention is an integral part, which can improve the strength of the single-plunger cylinder and increase the load it can withstand at a low cost; at the same time, it does not need to be assembled itself, eliminating the assembly steps and reducing the manufacturing cost; and, the sealing ring and the dust ring are installed on the circumferential surface of the oil chamber, and the piston rod is directly inserted into the oil chamber, which is simple to assemble and has high assembly efficiency, greatly improving the assembly process of the thrust adapter and simplifying the original numerous assembly steps.

[0068] Furthermore, in order to improve assembly convenience and the coaxiality of the piston rod and the cylinder, copper supports 26 sleeved on the piston rod are provided on both sides of the first sealing ring 13 and the dust ring 15 between the second sealing ring 14.

[0069] Example 9

[0070] When designing a floating thrust adapter, conventional floating configurations in the field typically utilize lubricating oil for floating support. However, the following tests clearly demonstrate that the friction coefficient of grease is lower than that of oil. Using grease for fluid support of the floating thrust plate can further reduce the friction of the floating thrust plate, facilitating the collection of various engine parameters, improving data accuracy, and reducing interference caused by friction.

[0071] The experimental analysis of the friction force between the floating thrust plate 5 and the piston rod with different lubricating fluids is as follows:

[0072] AActual test conditions:

[0073] Ambient temperature: +10℃~+23℃;

[0074] Air humidity: around 92%;

[0075] Surface wind speed: light breeze;

[0076] Instantaneous wind speed: breeze.

[0077] B Lubricating fluid: grease and oil

[0078] C test process:

[0079] (1) Assemble the floating thrust plate 5 and the piston rod according to the assembly requirements and place them on the test platform. Apply grease between them and apply radial load to the floating thrust plate. The friction coefficient obtained is as follows:

[0080] Table 1 Grease loading test data

[0081]

[0082] (2) After assembling the floating thrust plate 5 and the piston rod according to the assembly requirements, place them on the test platform, apply lubricating oil between them, and apply radial load to the floating thrust plate. The friction coefficient obtained is as follows:

[0083] Table 2 Lubricating oil loading test data

[0084]

[0085] From the above, it can be seen that the friction coefficient of grease is much smaller than that of lubricating oil. Using grease for fluid support of the floating thrust plate can further reduce the friction of the floating thrust plate, facilitate the collection of various engine parameters, improve the accuracy of the collection, and reduce the interference caused by friction.

[0086] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A low-friction buoyancy thrust adapter for rocket testing, comprising a floating thrust plate (5) and a support assembly for radially and axially floating support thereof, characterized in that: The support assembly includes a single plunger cylinder, wherein an end face A of a piston rod (2) of the single plunger cylinder extends out of an oil chamber of a cylinder barrel (1) of the single plunger cylinder and contacts a side plate face A of a floating thrust plate (5) through a lubricating fluid, and an end face sealing ring is provided between the end face A and the plate face A to prevent the lubricating fluid from overflowing therebetween; An exhaust duct (30) is provided on the floating thrust plate (5) to connect the space sealed by the inner ring of the end face sealing ring with the outside world, and a sealing plug (27) is provided at one end of the exhaust duct (30) connected with the outside world to block the end thereof; A limiting block (3) is installed on the upper side of the side wall of the piston rod (2), and the upper side of the side wall of the limiting block (3) close to the floating thrust plate (5) is convex to form a limiting step (301) radially opposite to the floating thrust plate (5).

2. The low-friction buoyancy thrust adapter for rocket testing according to claim 1, characterized in that: One end of the exhaust duct (30) is in communication with the plate surface A, and the other end thereof is in communication with the circumferential surface of the floating thrust plate (5).

3. The low-friction buoyancy thrust adapter for rocket testing according to claim 1, characterized in that: The limit block (3) is an arc-shaped strip structure, the center of which is located on the axis of the piston rod (2), and the inner circumference thereof is in contact with the outer circumference of the piston rod (2). The limit block (3) is mounted on the piston rod (2) via an upper bolt (16).

4. The low-friction buoyancy thrust adapter for rocket testing according to claim 1, characterized in that: A support block (6) is installed on the lower side of the side wall of the piston rod (2), and the upper side of the side wall of the support block (6) close to the floating thrust plate (5) is convex to form a support step (601) radially opposite to the floating thrust plate (5).

5. The low-friction buoyancy thrust adapter for rocket testing according to claim 4, characterized in that: The support block (6) is an arc-shaped strip structure, the center of which is located on the axis of the piston rod (2), and the inner circumference thereof is in contact with the outer circumference of the piston rod (2). The support block (6) is mounted on the piston rod (2) via a lower bolt (24).

6. The low-friction buoyancy thrust adapter for rocket testing according to any one of claims 1 to 5, characterized in that: A spherical groove (31) is provided at the closed end of the cylinder (1), and a posture adjustment component is installed in the spherical groove (31). The center line of the spherical groove (31) coincides with the axis of the single-piston cylinder. The posture adjustment component comprises a posture adjustment ball head (8), a posture adjustment washer (9) and a posture adjustment screw (10). One side of the posture adjustment ball head (8) is a plane and is located outside the spherical groove (31), and the other side thereof is convex to form a convex spherical surface that fits the concave spherical surface of the spherical groove (31). The rod of the posture adjustment screw (10) passes through the posture adjustment washer (9) and the posture adjustment ball head (8) and is then threadedly connected to the closed end of the cylinder (1), and the posture adjustment ball head (8) and the posture adjustment screw (10) are clearance-matched.

7. The low-friction buoyancy thrust adapter for rocket testing according to claim 1, characterized in that: The lubricating fluid is grease.

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