CN112855386A - Low-friction buoyancy thrust adapter for rocket test - Google Patents

Abstract

The invention discloses a low-friction buoyancy thrust adapter for a rocket test, which comprises a floating thrust plate and a supporting assembly for carrying out floating support on the floating thrust plate, wherein the supporting assembly comprises a single plunger cylinder, the end surface A of the extending end of a piston rod of the single plunger cylinder is contacted with the plate surface A of the floating thrust plate through lubricating fluid, and an end surface sealing ring is arranged between the end surface A and the plate surface A. The axial supporting load required by the axial direction during the test is realized based on the single plunger cylinder; meanwhile, the floating thrust plate and the piston rod are divided to be mutually independent, and then the floating thrust plate is independent of the outside of the oil cavity, so that no matter how the floating thrust plate floats along with the change of the center of the engine, the position change of the floating thrust plate does not influence the space in the oil cavity, the space in the oil cavity is fixed, a complex oil way does not need to be configured, the processing cost of the thrust adapter is reduced, the later maintenance convenience is improved, and the test condition with extremely high sealing requirement, namely instantaneous high pressure, does not exist.

Description

Low-friction buoyancy thrust adapter for rocket test

Technical Field

The invention relates to the technical field of rockets, in particular to a low-friction buoyancy thrust adapter for a rocket test.

Background

The ground ignition test of the rocket engine has the function of testing the transient thrust, the pressure of a combustion chamber and other important parameters of the rocket engine, is one of the main modes of performance identification and design improvement of the rocket engine, and has important significance for the inspection of rocket engine products and the development of new models. When the supporting device of the existing engine thrust test bed adopts a fixed mechanical structure, the internal friction is large, and the testing precision of various parameters of the engine is reduced; moreover, after the engine is ignited, the shell of the engine expands due to heat, the center of the shell moves upwards along with the expansion of the shell, and the center of the supporting device is inconvenient, so that the position difference is generated between the center of the rocket and the center of the supporting device after the rocket is ignited, and further, the mechanical connection part between the head of the rocket and the supporting device is lifted due to the expansion and the center of the engine, and the center of the supporting device is not changed, so that great stress is accumulated, and the measurement of the thrust of the engine is not facilitated. And after the supporting device receives the thrust from the engine, the flexible piece is pressed and deformed, a return thrust can be generated on the engine, the flexible piece is easy to crack due to overlarge thrust of the engine, and even has a cracking risk, so that not only can a potential safety hazard be generated, but also the precision of testing various parameters of the engine is further reduced. Meanwhile, in practical use, the supporting device with the mechanical structure is only suitable for engine thrust tests of small rockets, and is a conventional 500-ton rocket. When 1500 tons of rockets are tested, three groups of flexible parts are needed, so that the size of the supporting device is increased, the testing cost is increased, and the testing error is increased.

Based on the above technical problems, CN210400854U discloses a buoyancy-type thrust adapter, one end of which is fixed on a thrust wall, and the other end of which forms a floating thrust plate capable of floating upward by fluid contact, and contacts with the end of an engine through the floating thrust plate, so that after the subsequent engine is ignited, when a rocket case expands due to heating and moves up at the center, the floating thrust plate floats and moves up in the fluid. In the whole testing process, the floating thrust plate can be adjusted in a self-adaptive mode according to the actual central position of the engine, stress concentration caused by dislocation of a connecting part between the head of the rocket and the supporting device is avoided, the quality of the connecting part between the head of the rocket and the supporting device is protected, friction force is reduced, and the testing precision of various parameters of the engine is improved.

However, in this buoyancy-type thrust adapter, one end of the floating thrust plate is installed as a piston rod in the inner cavity of the connecting piece serving as the cylinder barrel, an annular space is formed between the circumferential surface of the piston rod and the circumferential surface of the inner cavity, and as the floating thrust plate floats up and down in the radial direction and moves axially, the change in the volume of the space between the piston rod and the inner cavity is large. The arrangement of an oil inlet and outlet way on the connecting piece is increased, and the manufacturing cost and the maintenance cost are increased; and when the volume of the space between the piston rod and the inner cavity is reduced, the pressure intensity of the fluid in the space is increased, so that the requirement on the sealing performance of the space is extremely high, and the sealing cost is high.

Disclosure of Invention

The invention aims to: the low-friction buoyancy thrust adapter for the rocket test solves the technical problems that an existing low-friction center-adjustable floating thrust adapter needs to be provided with a complex oil way, is high in machining cost, troublesome to maintain, extremely high in sealing requirement and the like.

The technical scheme adopted by the invention is as follows:

the low-friction buoyancy thrust adapter for the rocket test comprises a floating thrust plate and a supporting assembly for carrying out radial and axial floating supporting on the floating thrust plate, wherein the supporting assembly comprises a single plunger cylinder, one end face A, extending out of an oil cavity of a cylinder barrel of the single plunger cylinder, of a piston rod of the single plunger cylinder is in contact with one side plate face A of the floating thrust plate through lubricating fluid, and an end face sealing ring for preventing the lubricating fluid between the end face A and the plate face A from overflowing is arranged between the end face A and the plate face A.

Furthermore, an exhaust duct for communicating the space sealed by the inner ring of the end face sealing ring with the outside is arranged on the floating thrust plate, and a sealing plug for plugging the end part of the exhaust duct is arranged at one end of the exhaust duct communicated with the outside.

Furthermore, one end of the exhaust duct is communicated with the plate surface A, and the other end of the exhaust duct is communicated with the circumferential surface of the floating thrust plate.

Furthermore, a limiting block is arranged on the upper side of the side wall of the piston rod, and the upper side of the side wall of the limiting block, which is close to the floating thrust plate, protrudes outwards to form a limiting step which is opposite to the floating thrust plate in the radial direction.

Furthermore, the limiting block is of an arc-shaped strip structure, the circle center of the limiting block is located on the axis of the piston rod, the inner circumferential surface of the limiting block is attached to the outer circumferential surface of the piston rod, and the limiting block is installed on the piston rod through an upper bolt.

Furthermore, a supporting block is installed on the lower side of the side wall of the piston rod, and the upper side of the side wall of the supporting block close to the floating thrust plate protrudes outwards to form a supporting step which is opposite to the floating thrust plate in the radial direction.

Furthermore, the supporting block is of an arc-shaped strip structure, the circle center of the supporting block is located on the axis of the piston rod, the inner circumferential surface of the supporting block is attached to the outer circumferential surface of the piston rod, and the supporting block is installed on the piston rod through a lower bolt.

Furthermore, a dust cover sleeved on the extending end of the piston rod is arranged between the end face of the cylinder barrel close to the floating thrust plate and the plate face A, and two ends of the dust cover are respectively in contact with the end face of the cylinder barrel and the plate face A.

Further, the closed end of the cylinder barrel is provided with a spherical groove, a posture adjusting 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 adjusting assembly comprises a posture adjusting ball head, a posture adjusting gasket and a posture adjusting screw, one side of the posture adjusting ball head is a plane and is positioned outside the spherical groove, the other side of the posture adjusting ball head protrudes outwards to form a convex spherical surface which is attached to the concave spherical surface of the spherical groove, the rod part of the posture adjusting screw penetrates through the posture adjusting gasket and the posture adjusting ball head and then is in threaded connection with the closed end of the cylinder barrel, and the posture adjusting ball head is in clearance fit with the posture adjusting screw.

Further, the lubricating fluid is grease.

Due to the adoption of the technical scheme, the invention has the beneficial effects that:

1. the invention relates to a low-friction buoyancy thrust adapter for rocket tests, which is used for innovatively dividing a floating thrust plate and a piston rod, and realizing axial supporting load required by the axial direction during the test based on the matching of a single plunger cylinder and the piston rod; meanwhile, floating is realized by a floating thrust plate which is independent from the piston rod and is floated at the extending end of the piston rod by lubricating fluid so as to be matched with the center of the engine to move upwards, ensure that the structure height is matched with the structure change of the engine and keep low friction force; meanwhile, the floating is independent of the outside of the oil cavity, so that no matter how the floating thrust plate floats along with the change of the center of the engine, the position change of the floating thrust plate does not influence the space in the oil cavity, and the space in the oil cavity is constant, so that a complex oil way does not need to be configured, the processing cost of the thrust adapter is reduced, the later maintenance convenience is improved, and the test condition with extremely high sealing requirement, namely instantaneous high pressure, does not exist;

2. according to the low-friction buoyancy thrust adapter for the rocket test, gas between the end face A and the plate face A is exhausted through the exhaust duct, so that the gas between the end face A and the plate face A is reduced or even eliminated, the friction force between the end face A and the plate face A is reduced, and the acquisition of various parameters of an engine is facilitated;

3. the arrangement of the low-friction buoyancy thrust adapter attitude adjusting assembly for the rocket test is convenient for eliminating installation errors and ensuring the centrality and the like when the thrust adapter is installed, thereby being beneficial to subsequent tests;

4. compared with the prior art, the low-friction buoyancy thrust adapter for the rocket test is an integral piece of the single plunger cylinder, so that the strength of the single plunger cylinder can be improved on the premise of low cost, and the load borne by the single plunger cylinder can be improved; meanwhile, the assembly is not needed, the assembly step is omitted, and the manufacturing cost is reduced; in addition, the sealing ring and the dust ring are arranged on the circumferential surface of the oil cavity, and then the piston rod is directly inserted into the oil cavity, so that the assembly is simple, the assembly efficiency is high, the assembly process of the thrust adapter is greatly improved, and the original multiple assembly steps are simplified;

5. the low-friction buoyancy thrust adapter for the rocket test is in conventional floating arrangement in the field, and is supported in a floating mode by adopting lubricating oil. However, how to further reduce the floating friction of the floating thrust plate needs to break through the conventional means, and an unconventional conceivable lubricating fluid is used as the floating support fluid of the floating thrust plate, according to the following test, the friction coefficient of the lubricating grease is obviously less than that of the lubricating oil, and the lubricating grease is used for carrying out the fluid support of the floating thrust plate, so that the floating friction of the floating thrust plate can be further reduced, the acquisition of various parameters of the engine is facilitated, the acquisition accuracy is improved, and the interference caused by the friction is reduced.

Drawings

In order to more clearly illustrate the technical solution of the embodiment of the present invention, the drawings needed to be used in the embodiment will be briefly described below, and it should be understood that the proportional relationship of each component in the drawings in this specification does not represent the proportional relationship in the actual material selection design, and is only a schematic diagram of the structure or the position, in which:

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is an installation schematic diagram of a stop block;

FIG. 3 is a schematic view of the mounting of the support block;

FIG. 4 is a schematic structural diagram of a stopper;

fig. 5 is a schematic view of the fit between the piston rod and the cylinder barrel.

Reference numerals in the drawings indicate:

1-cylinder barrel, 2-piston rod, 3-limiting block, 301-limiting step, 4-dustproof cover, 5-floating thrust plate, 6-supporting block, 601-supporting step, 7-positioning sleeve, 8-posture adjusting top, 9-posture adjusting gasket, 10-posture adjusting screw, 11-spherical gasket, 12-conical gasket, 13-first rod seal, 14-second rod seal, 15-dustproof ring, 16-upper screw, 17-upper gasket, 18-outer end surface seal ring, 19-dustproof cover mounting bolt, 20-middle end surface seal ring, 21-inner auxiliary bolt, 22-inner auxiliary gasket, 23-inner end surface seal ring, 24-lower bolt, 25-lifting ring screw, 26-copper support, 27-sealing plug, 28-stay wire sensor, 29-outer auxiliary bolt, 30-exhaust duct, 31-spherical groove, 32-lower washer and 33-countersunk bolt hole.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the detailed description and specific examples, while indicating the preferred embodiment of the invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention.

The present invention will be described in detail with reference to fig. 1 to 5.

Example 1

As shown in fig. 1 to 3, the low-friction buoyancy thrust adapter for rocket tests comprises a floating thrust plate 5 and a supporting assembly for carrying out radial and axial floating supporting on the floating thrust plate, wherein the supporting assembly comprises a single plunger cylinder, one end face a of a piston rod 2 of the single plunger cylinder, which extends out of an oil cavity of a cylinder barrel 1 of the single plunger cylinder, is in contact with one side plate face a of the floating thrust plate 5 through lubricating fluid, and an end face sealing ring for preventing the lubricating fluid between the end face a and the plate face a from overflowing is arranged between the end face a and the plate face a. An oil film surface is formed between the end surface A and the plate surface A.

The end face sealing rings are preferably end face GREEN rings, and the number of the end face sealing rings is three, namely an inner end face sealing ring 23, a middle end face sealing ring 20 and an outer end face sealing ring 18 from inside to outside.

The lubricating fluid may be a lubricating fluid, grease, or the like.

When the invention is used for rocket engine tests, the bottom of the cylinder barrel 1 is fixed on a thrust wall, and the other end of the cylinder barrel is connected with the connecting end of an engine through a thrust frame ball head assembly. The engine is ignited, and oil is supplied to an oil cavity of the single plunger cylinder through the large oil cylinder so as to match the axial thrust of the engine; meanwhile, when the central line of the engine moves upwards due to thermal expansion, the floating thrust plate 5 is synchronously adjusted along with the actual central position of the engine, so that the test precision of various parameters of the engine is ensured conveniently.

Compared with the prior art, the invention designs a brand-new buoyancy thrust adapter to creatively separate the floating thrust plate and the piston rod, and realizes the axial supporting load required by the axial direction during the test based on the matching of the single plunger cylinder and the piston rod; meanwhile, floating is realized by a floating thrust plate 5 which is independent from the piston rod and is floated at the extending end of the piston rod by lubricating fluid so as to be matched with the center of the engine to move upwards, ensure that the structure height is matched with the structure change of the engine and keep low friction force; meanwhile, the floating is independent of the outside of the oil cavity, so that no matter how the floating thrust plate floats along with the change of the center of the engine, the position change of the floating thrust plate does not influence the space in the oil cavity, the space in the oil cavity is constant, a complex oil way does not need to be configured, the processing cost of the thrust adapter is reduced, the later maintenance convenience is improved, and the test condition with extremely high sealing requirement, namely instantaneous high pressure, does not exist.

Meanwhile, in the invention, the floating plate and the piston rod are independent, so that floating is realized only based on the floating plate and the lubricating fluid between the floating plate and the piston rod, an oil cavity is not required to be arranged for floating of the piston rod, the structure of the single plunger cylinder is simplified, a steel body with an opening smaller than the oil cavity is not required to be spliced by multiple parts, and the manufacturing cost is reduced.

Example 2

In this example, the oil film surface is further described based on example 1.

When coating lubricating fluid between terminal surface A and face A, can't guarantee that the lubricating fluid surface is smooth plane, consequently at terminal surface A and/or face A coating lubricating fluid, install one side at the terminal surface A of piston rod with floating thrust plate 5 again, so that terminal surface A passes through lubricating fluid and when floating thrust plate 5's one side face A contact, the contact surface is incomplete smooth plane because of the lubricating fluid surface between it, consequently terminal surface A and face A pass through when lubricating fluid contacts, there is the air between it, the air can increase the frictional force between terminal surface A and the face A, be unfavorable for each parameter acquisition of engine, consequently adopt following structure:

as shown in fig. 1, the floating thrust plate 5 is provided with an exhaust duct 30 for communicating a space sealed by an inner ring of the end face seal ring with the outside, and a seal plug 27 for plugging an end portion of the exhaust duct 30 at one end communicating with the outside is provided.

Further, one end of the exhaust duct 30 communicates with the plate surface a, and the other end thereof communicates with the circumferential surface of the floating thrust plate 5.

The floating thrust plate 5 is mounted as follows: s1, coating lubricating fluid on the end face A and/or the plate face A; s2, arranging the floating thrust plate 5 on one side of the end surface A, wherein the end surface A is contacted with the plate surface A through lubricating fluid; s3, fixing the floating thrust plate 5 and the single plunger cylinder, and supplying oil to the single plunger cylinder to enable the piston rod to extend outwards, so that the axial extrusion force between the piston rod and the floating thrust plate 5 is increased, and then the gas between the end surface A and the plate surface A is discharged through the exhaust duct 30, so that the gas between the end surface A and the plate surface A is reduced or even eliminated, the friction force between the end surface A and the plate surface A is reduced, and the acquisition of various parameters of the engine is facilitated; s4, the end of the discharge port 30 communicating with the outside is then sealed by the seal plug 27.

Example 3

The floating restriction of the floating plate is specifically performed as follows:

as shown in fig. 1 and 2, a limit block 3 is mounted on the upper side of the side wall of the piston rod 2, and the upper side of the side wall of the limit block 3 close to the floating thrust plate 5 protrudes outward to form a limit step 301 which is radially opposite to the floating thrust plate 5.

The minimum distance between the limiting step 301 and the floating thrust plate 5 in the vertical direction is the maximum distance that the floating thrust plate 5 can move in the vertical direction; the arrangement of the limiting step 301 limits the floatable stroke of the floating thrust plate 5, and prevents the floating thrust plate 5 from slipping from the end surface A of the piston rod, so that the sealing performance between the end surface A and the surface A is ensured, and the rocket launcher is ensured to be tested smoothly.

Further, as shown in fig. 4, the limiting block 3 is an arc-shaped strip structure, the center of the arc-shaped strip structure is located on the axis of the piston rod 2, the inner circumferential surface of the arc-shaped strip structure is attached to the outer circumferential surface of the piston rod 2, and the arc-shaped strip structure is mounted on the piston rod 2 through an upper bolt 16. The upper bolt 16 is preferably a countersunk bolt, and as shown in fig. 2, an upper washer 17 is sleeved on the upper bolt 16 to prevent the upper bolt from loosening.

Example 4

The gravity support for the floating thrust plate 5 is embodied as follows: as shown in fig. 1 and 3, a support block 6 is installed at a lower side of a side wall of the piston rod 2, and an upper side of the side wall of the support block 6 adjacent to the floating thrust plate 5 is protruded to form a support step 601 radially opposite to the floating thrust plate 5.

Further, the supporting block 6 is an arc-shaped strip structure, the circle center of the supporting block is located on the axis of the piston rod 2, the inner circumferential surface of the supporting block is attached to the outer circumferential surface of the piston rod 2, and the supporting block is mounted on the piston rod 2 through a lower bolt 24.

The lower bolt 24 is preferably a countersunk bolt, and as shown in fig. 3, a lower washer is sleeved on the lower bolt 24 to prevent the lower bolt 24 from being loosened.

Example 5

In order to prevent dust from entering between the end face A and the plate face A, a dust cover 4 sleeved on the extending end of the piston rod 2 is arranged between the end face of the cylinder barrel 1 close to the floating thrust plate 5 and the plate face A, and two ends of the dust cover 4 are respectively contacted with the end face of the cylinder barrel 1 and the plate face A.

The dust cover 4 covers the limiting block 3 and the supporting block 6 in the inner part, the dust cover is preferably a corrugated pipe, two ends of the dust cover protrude outwards to form an outwards-turned edge, and a dust cover mounting bolt 19 penetrates through the outwards-turned edge and then is connected with the cylinder barrel or the floating thrust plate.

Example 6

As the test is carried out, better test parameters can be obtained due to higher verticality, straightness and planeness. During actual installation, the installation position of the actually assembled thrust adapter needs to be adjusted by a relatively fixed thrust wall, so that a spherical groove 31 is formed in the closed end of the cylinder barrel 1, a posture adjusting assembly is installed in the spherical groove 31, the center line of the spherical groove 31 is overlapped with the axis of the single-plunger cylinder, the posture adjusting assembly comprises a posture adjusting ball 8, a posture adjusting gasket 9 and a posture adjusting screw 10, one side of the posture adjusting ball 8 is a plane and is positioned outside the spherical groove 31, the other side of the posture adjusting ball protrudes outwards to form a convex spherical surface which is attached to the concave spherical surface of the spherical groove 31, the rod part of the posture adjusting screw 10 penetrates through the posture adjusting gasket 9 and the posture adjusting ball 8 and then is in threaded connection with the closed end of the cylinder barrel 1, and the posture adjusting ball 8 is in clearance fit with the posture adjusting screw 10.

When the arrangement of the posture adjusting assembly is convenient for installing the thrust adapter, installation errors are eliminated, the centrality is ensured, and the like, so that the subsequent test is facilitated.

Example 7

For ease of lifting, a plurality of eye screws 25 are preferably mounted on the outer circumferential surface of the cylinder tube 1. In order to collect the pressure information inside the oil chamber, a pressure measuring port is preferably arranged on the outer circumferential surface of the cylinder barrel 1, a pressure sensor is installed in the pressure measuring port, and the pressure sensor collects the pressure change of the oil chamber; and a displacement sensor is arranged between the floating thrust plate and the piston rod to detect the thickness of an oil film surface between the floating thrust plate and the piston rod. Meanwhile, in order to improve the convenience of the assembly of the present invention, it is preferable that the floating thrust plate 5 and the piston rod are fixedly coupled by an inner auxiliary bolt 21, and the floating thrust plate 5 and the cylinder are fixedly coupled by an outer auxiliary bolt 29. After the assembly, when the gas between the floating thrust plate and the piston rod needs to be discharged, the cylinder barrel is fixed, then the floating thrust plate 5 is fixed, then the inner auxiliary bolt 21 and the outer auxiliary bolt 29 are detached, then the oil cavity is supplied with oil, so that the matching surface between the piston rod and the floating thrust plate is extruded by the outward extension of the piston rod, and then the gas between the piston rod and the floating thrust plate is discharged.

One side of the outer circumferential surface of the cylinder barrel 1 protrudes outwards to form an outwards-turned edge, one side of the outer circumferential surface of the floating thrust plate 5 protrudes outwards to form an outwards-turned edge, and the tail end of the rod part of the outer auxiliary bolt 29 penetrates through the outwards-turned edge of the floating thrust plate 5 and then is in threaded connection with the outwards-turned edge of the cylinder barrel 1.

The outer circumferential surface of the piston rod is positioned on one side outside the oil cavity and protrudes outwards to form an outwards turned edge, the tail end of the rod part of the inner auxiliary bolt 21 penetrates through the plate body of the floating thrust plate 5 and then is in threaded connection with the outwards turned edge of the piston rod, and the limiting block and the supporting block are both arranged on the outwards turned edge of the piston rod.

Example 8

In the invention, as shown in fig. 1, a single plunger cylinder has no cylinder cover, the single plunger cylinder performs sealing between an oil cavity and the outside through a sealing assembly between the outer circumferential surface of a piston rod 2 and the inner circumferential surface of a cylinder barrel 1, and the sealing assembly comprises a first sealing ring 13, a second sealing ring 14 and a dust ring 15 which are sequentially arranged on the inner circumferential surface of the cylinder barrel 1 from the cylinder bottom to the outer extending end of the piston rod, as shown in fig. 1 and 5.

Compared with the prior art, the single plunger cylinder is an integral part, so that the strength of the single plunger cylinder can be improved on the premise of low cost, and the load which can be borne by the single plunger cylinder can be improved; meanwhile, the assembly is not needed, the assembly step is omitted, and the manufacturing cost is reduced; and the sealing ring and the dust ring are arranged on the circumferential surface of the oil cavity, and then the piston rod is directly inserted into the oil cavity, so that the assembly is simple, the assembly efficiency is high, the assembly process of the thrust adapter is greatly improved, and the original various assembly steps are simplified.

Further, in order to improve the assembly convenience and the coaxiality of the piston rod and the cylinder barrel, copper supports 26 sleeved on the piston rod are arranged on the two sides of the first sealing ring 13 and between the second sealing rings 14 and the dust rings 15.

Example 9

When the floating thrust adapter is designed, the floating support is carried out by adopting lubricating oil based on the conventional floating arrangement in the field. However, how to further reduce the floating friction of the floating thrust plate needs to break through the conventional means, and an unconventional conceivable lubricating fluid is used as the floating support fluid of the floating thrust plate, according to the following test, the friction coefficient of the lubricating grease is obviously less than that of the lubricating oil, and the lubricating grease is used for carrying out the fluid support of the floating thrust plate, so that the floating friction of the floating thrust plate can be further reduced, the acquisition of various parameters of the engine is facilitated, the acquisition accuracy is improved, and the interference caused by the friction is reduced.

Experimental analysis of the friction forces for different lubrication fluids between the floating thrust plate 5 and the piston rod is as follows:

a actual test conditions:

ambient temperature: the temperature is between +10 ℃ and +23 ℃;

air humidity: about 92 percent;

ground wind speed: breeze;

instantaneous wind speed: breeze is slight.

B, lubricating fluid: grease and lubricating oil

C, test process:

(1) after the floating thrust plate 5 and the piston rod are assembled according to the assembly requirement, the assembled floating thrust plate and the piston rod are placed on a test platform, lubricating grease is smeared between the floating thrust plate and the test platform, and radial load is applied to the floating thrust plate, so that the obtained friction coefficients are as follows:

table 1 grease loading test data

(2) After being assembled according to the assembly requirement, the floating thrust plate 5 and the piston rod are placed on a test platform, lubricating oil is smeared between the floating thrust plate and the test platform, and radial load is applied to the floating thrust plate, so that the obtained friction coefficients are as follows:

TABLE 2 lubricating oil loading test data

Therefore, the friction coefficient of the lubricating grease is far smaller than that of the lubricating oil, the lubricating grease is adopted for fluid supporting of the floating thrust plate, the floating friction force of the floating thrust plate can be further reduced, various parameters of the engine can be conveniently acquired, the acquisition accuracy is improved, and the interference caused by the friction force is reduced.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.

Claims (10)

1. Low friction buoyancy thrust adapter for rocket test, including floating thrust plate (5) and carry out radial and axial floating support's supporting component to it, its characterized in that: the supporting assembly comprises a single plunger cylinder, one end face A of a piston rod (2) of the single plunger cylinder, extending out of an oil cavity of a cylinder barrel (1) of the single plunger cylinder, is in contact with one side plate face A of the floating thrust plate (5) through lubricating fluid, and an end face sealing ring for preventing the lubricating fluid between the end face A and the plate face A from overflowing is arranged between the end face A and the plate face A.

2. A rocket test low-friction buoyancy thrust adapter according to claim 1, wherein: an exhaust duct (30) for communicating the space sealed by the inner ring of the end face sealing ring with the outside is arranged on the floating thrust plate (5), and a sealing plug (27) for plugging the end part of the exhaust duct (30) is arranged at one end communicated with the outside.

3. A rocket test low-friction buoyancy thrust adapter according to claim 2, wherein: one end of the exhaust duct (30) is communicated with the plate surface A, and the other end of the exhaust duct is communicated with the circumferential surface of the floating thrust plate (5).

4. A rocket test low-friction buoyancy thrust adapter according to claim 1, wherein: and the upper side of the side wall of the piston rod (2) is provided with a limiting block (3), and the upper side of the side wall of the limiting block (3) close to the floating thrust plate (5) is protruded outwards to form a limiting step (301) which is opposite to the floating thrust plate (5) in the radial direction.

5. A rocket test low-friction buoyancy thrust adapter according to claim 4, wherein: the limiting block (3) is of an arc-shaped strip structure, the circle center of the limiting block is located on the axis of the piston rod (2), the inner circumferential surface of the limiting block is attached to the outer circumferential surface of the piston rod (2), and the limiting block is installed on the piston rod (2) through an upper bolt (16).

6. A rocket test low-friction buoyancy thrust adapter according to claim 1, wherein: and a supporting block (6) is arranged on the lower side of the side wall of the piston rod (2), and the upper side of the side wall of the supporting block (6) close to the floating thrust plate (5) is protruded outwards to form a supporting step (601) which is opposite to the floating thrust plate (5) in the radial direction.

7. A rocket test low-friction buoyancy thrust adapter according to claim 1, wherein: the supporting block (6) is of an arc strip-shaped structure, the circle center of the supporting block is located on the axis of the piston rod (2), the inner circumferential surface of the supporting block is attached to the outer circumferential surface of the piston rod (2), and the supporting block is installed on the piston rod (2) through a lower bolt (24).

8. A low friction buoyancy thrust adapter for rocket tests according to any one of claims 1 to 7, wherein: and a dust cover (4) sleeved at the outward extending end of the piston rod (2) is arranged between the end surface of the cylinder barrel (1) close to the floating thrust plate (5) and the plate surface A, and two ends of the dust cover (4) are respectively contacted with the end surface of the cylinder barrel (1) and the plate surface A.

9. A low friction buoyancy thrust adapter for rocket tests according to any one of claims 1 to 7, wherein: the closed end of the cylinder barrel (1) is provided with a spherical groove (31), a posture adjusting component is installed in the spherical groove (31), the central line of the spherical groove (31) coincides with the axis of the single plunger cylinder, the posture adjusting component comprises a posture adjusting ball head (8), a posture adjusting gasket (9) and a posture adjusting screw (10), one side of the posture adjusting ball head (8) is a plane and is positioned on the outer side of the spherical groove (31), the other side of the posture adjusting ball head protrudes outwards to form a convex spherical surface which is attached to the concave spherical surface of the spherical groove (31), the rod part of the posture adjusting screw (10) penetrates through the posture adjusting gasket (9) and the posture adjusting ball head (8) and then is in threaded connection with the closed end of the cylinder barrel (1), and the posture adjusting ball head (8) is in clearance fit with the posture adjusting screw (10).

10. A low friction buoyancy thrust adapter for rocket tests according to any one of claims 1 to 7, wherein: the lubricating fluid is grease.

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