CN111735631A - Sealing device for spacecraft engine thrust chamber test - Google Patents
Sealing device for spacecraft engine thrust chamber test Download PDFInfo
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- CN111735631A CN111735631A CN202010754711.3A CN202010754711A CN111735631A CN 111735631 A CN111735631 A CN 111735631A CN 202010754711 A CN202010754711 A CN 202010754711A CN 111735631 A CN111735631 A CN 111735631A
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- sealing
- thrust chamber
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- base
- spacecraft engine
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/025—Details with respect to the testing of engines or engine parts
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Abstract
The invention provides a sealing device for a spacecraft engine thrust chamber test, which comprises: the limiting support frame comprises a limiting base and is used for fixing and limiting the thrust chamber; the positioning assembly is fixed on the limiting base and is used for abutting against the inner wall of a spray pipe of the thrust chamber; the driving mechanism is fixed in the middle of the inner side of the positioning assembly; the sealing disc comprises a sealing ring and is arranged at the top end of the driving mechanism; during testing, the outlet end of the thrust chamber is downwards fixed on the positioning assembly, and the driving mechanism provides external force to enable the sealing ring to be abutted against the inner wall of the throat part of the thrust chamber. The sealing device for the spacecraft engine thrust chamber test can avoid the thrust chamber from being crushed, and is simple in operation, convenient to disassemble and assemble, stable and reliable.
Description
Technical Field
The invention relates to the field of spacecraft engine thrust chamber sealing tests, in particular to a sealing device for a spacecraft engine thrust chamber test.
Background
The jet pipe of the thrust chamber of the liquid spacecraft engine is generally in an expanding-contracting-expanding Laval structure, a propellant is atomized through an injector and is combusted in a combustion chamber, and high-temperature and high-pressure fuel gas is converted into high-speed fuel gas to be sprayed out of the jet pipe, so that reactive thrust is generated. Before the hot test run of the thrust chamber, strict pressure test examination needs to be carried out on the thrust chamber overall to verify the sealing performance of the welding seams and the components of the thrust chamber. The pressure test is to inject water or compressed air with certain pressure into the closed cavity with sealing requirement, and after the pressure is stable, the inner and outer surfaces are checked to see whether leakage exists.
At present, a sealing device for a common spacecraft engine thrust chamber test provides a sealing ring to compress the inner wall of the thrust chamber, enough pretightening force is needed to ensure the sealing compression amount of the sealing ring, the wall surface of the thrust chamber is easily crushed, the sealing pressure is low, and the reliability is poor.
In view of this, it is urgently needed to design a sealing device for a spacecraft engine thrust chamber test, which is safe and reliable and can avoid the thrust chamber from being crushed.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a sealing device for a spacecraft engine thrust chamber test.
The invention provides a sealing device for a spacecraft engine thrust chamber test, which comprises: the limiting support frame comprises a limiting base and is used for fixing and limiting the thrust chamber; the positioning assembly is fixed on the limiting base and is used for abutting against the inner wall of a spray pipe of the thrust chamber; the driving mechanism is fixed in the middle of the inner side of the positioning assembly; the sealing disc comprises a sealing ring and is arranged at the top end of the driving mechanism; during testing, the outlet end of the thrust chamber is downwards fixed on the positioning assembly, and the driving mechanism provides external force to enable the sealing ring to be abutted against the inner wall of the throat part of the thrust chamber.
According to an aspect of the invention, the limit support frame further comprises: the limiting top cover is fixed at the top end of the thrust chamber; and the pull rod is arranged around the thrust chamber and connected between the limiting top cover and the limiting base.
According to one aspect of the invention, the positioning assembly comprises: the lower end of the hollow supporting bracket is connected with the limiting base, the upper end of the supporting bracket is a circular supporting plate, and the driving mechanism is installed in the hollow structure of the supporting bracket.
According to one aspect of the invention, the positioning assembly comprises: the hollow positioning bracket is fixed at the upper end of the supporting plate of the supporting bracket, the outer surface of the positioning bracket is matched with the shape of the inner wall of the spray pipe, and the driving mechanism is installed in the hollow structure of the positioning bracket.
According to one aspect of the invention, the positioning bracket is a non-metallic rigid material.
According to one aspect of the invention, the drive mechanism is a cylinder drive mechanism.
According to an aspect of the invention, the drive mechanism further comprises: the cylinder body is cylindrical and is arranged in the hollow structure of the positioning bracket; and the cylinder sealing rings are arranged at the upper end and the lower end of the cylinder body, so that the cylinder body forms a closed cavity.
According to an aspect of the invention, the drive mechanism further comprises: and the piston shaft is arranged in the cylinder body, one end of the piston shaft is provided with an air inlet hole which is connected with an external air inlet pipe, and the other end of the piston shaft is connected with the sealing disc.
According to one aspect of the invention, the seal disk further comprises: the sealing gland is connected with the driving mechanism; the sealing base is fixed at the upper end of the positioning assembly, and the sealing gland can slide relative to the sealing base; the sealing ring is positioned between the sealing gland and the sealing base.
According to one aspect of the invention, the gland and the seal base each include a circular groove, the bottom end of the gland being snap-fitted within the seal base groove.
The sealing device for the spacecraft engine thrust chamber test can solve the problem of difficulty in pre-tightening operation by adopting the driving mechanism, the driving mechanism provides external force to enable the sealing ring to abut against the inner wall of the throat part of the thrust chamber through the mutual matching of the limiting support frame, the positioning assembly and the sealing disc, the thrust chamber is prevented from being crushed, and the sealing device for the spacecraft engine thrust chamber test is simple to operate, convenient to disassemble and assemble, stable and reliable.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description, serve to explain the principles of the invention.
FIG. 1 is a cross-sectional view of a spacecraft engine thrust room test seal assembly in accordance with one embodiment of the present invention;
FIG. 2 is a cross-sectional view of a spacecraft engine thrust room test seal assembly according to another embodiment of the present invention;
FIG. 3 is a perspective view of a spacecraft engine thrust room test seal assembly in accordance with one embodiment of the present invention;
FIG. 4 is a perspective view of a spacecraft engine thrust room test seal assembly according to another embodiment of the present invention;
FIG. 5 is a cross-sectional view of a spacecraft engine thrust room test fixture in accordance with one embodiment of the present invention;
FIG. 6 is a perspective view of a spacecraft engine thrust room test fixture in accordance with yet another embodiment of the present invention;
FIG. 7 is a cross-sectional view of a sealing tool for a spacecraft engine thrust room test according to one embodiment of the invention;
fig. 8 is a perspective view of a sealing tool for a spacecraft engine thrust room test according to still another embodiment of the invention.
Description of reference numerals:
100-limit support frame, 101-limit base, 102-limit top cover, 103-pull rod, 1031-upper pull rod, 1032-lower pull rod, 104-first pin shaft, 105-first nut, 106-spherical gasket, 107-second pin shaft, 200-positioning component, 201-support bracket, 202-support plate, 203-positioning bracket, 300-driving mechanism, 301-cylinder body, 302-cylinder sealing ring, 303-piston shaft, 400-sealing disc, 401-sealing ring, 402-sealing gland, 403-sealing base, 404-annular boss, 405-positioning hole and 406-connecting rod.
Detailed Description
Features and exemplary embodiments of various aspects of the present invention will be described in detail below, and in order to make objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention, for the purposes of illustrating the principles of the invention. Additionally, the components in the drawings are not necessarily to scale. For example, the dimensions of some of the elements or regions in the figures may be exaggerated relative to other elements or regions to help improve understanding of embodiments of the present invention.
The directional terms used in the following description are used in the illustrated directions, and do not limit the specific configurations of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise specified, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood as appropriate to those of ordinary skill in the art.
Furthermore, the terms "comprises," "comprising," "includes," "including," "has," "having" or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a structure or component comprising a list of elements does not include only those elements but may include other mechanical components not expressly listed or inherent to such structure or component. Without further limitation, an element defined by the phrase "comprising … …" does not exclude the presence of additional like elements in the article or device comprising the element.
Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be taken as limiting. Like terms refer to like elements throughout the description.
It will be apparent to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention.
FIG. 1 is a cross-sectional view of a spacecraft engine thrust room test seal assembly in accordance with one embodiment of the present invention; FIG. 2 is a cross-sectional view of a spacecraft engine thrust room test seal assembly according to another embodiment of the present invention; FIG. 3 is a perspective view of a spacecraft engine thrust room test seal assembly in accordance with one embodiment of the present invention; FIG. 4 is a perspective view of a spacecraft engine thrust room test seal assembly according to another embodiment of the present invention; FIG. 5 is a cross-sectional view of a spacecraft engine thrust room test fixture in accordance with one embodiment of the present invention; FIG. 6 is a perspective view of a spacecraft engine thrust room test fixture in accordance with yet another embodiment of the present invention; FIG. 7 is a cross-sectional view of a sealing tool for a spacecraft engine thrust room test according to one embodiment of the invention; fig. 8 is a perspective view of a sealing tool for a spacecraft engine thrust room test according to still another embodiment of the invention.
As shown in fig. 1, the present invention provides a sealing device for a spacecraft engine thrust room test, comprising: the limiting support frame 100 comprises a limiting base 101, and the limiting support frame 100 is used for fixing and limiting the thrust chamber T; the positioning assembly 200 is fixed on the limiting base 101, and the positioning assembly 200 is used for abutting against the inner wall of the spray pipe A of the thrust chamber T; the driving mechanism 300 is fixed in the middle of the inner side of the positioning assembly 200; a seal disc 400 including a seal ring 401, the seal disc 400 being disposed at a top end of the drive mechanism 300; during the test, the outlet end of the thrust chamber T is fixed downward on the positioning assembly 200, and the driving mechanism 300 provides external force to make the sealing ring 401 abut against the inner wall of the throat of the thrust chamber T.
Specifically, according to the sealing device for the liquid spacecraft engine thrust chamber test provided by the embodiment of the invention, the outlet end of the nozzle A of the thrust chamber T is vertically fixed on the positioning assembly 200 downwards, and the positioning assembly 200 is attached to the inner wall surface of the nozzle A through the self weight of the thrust chamber T. Then, since the positioning assembly 200 is fixed on the limit base 101, the thrust chamber T is fixed up and down by the limit support frame 100. Since the driving mechanism 300 is fixed at the center of the positioning assembly 200, and the positioning assembly 200 is fixed by the position-limiting supporting frame 100 by means of the thrust chamber T, the driving mechanism 300 has a firm and reliable supporting force. In the test process, the driving mechanism 300 provides an external force to compress the sealing ring 401, and the sealing ring 401 deforms to abut against the inner wall of the throat of the thrust chamber T.
In one embodiment, the retainer base 101 is a circular plate sized to fit the outlet of the nozzle A of the thrust chamber T. In another embodiment, the retainer base 101 is a protrusion extending from the center to the periphery, and the outer edge of the protrusion matches with the nozzle A of the thrust chamber T. According to one embodiment of the present invention, the restraining base 101 is formed to extend from the periphery of the lower end of the support bracket 201 to form four protrusions. In this embodiment, the limiting base 101 is a protrusion extending from the center to the periphery, and the limiting base 101 is a protrusion extending from the periphery of the lower end of the supporting bracket 201 to form four protrusions, and the outer edge of the protrusion matches with the nozzle a of the thrust chamber T.
It should be noted that, in general, the thrust chamber T includes the nozzle a, the combustion chamber B, and the head C, and the sealing device for the thrust chamber test of the spacecraft engine in this embodiment seals the throat portion of the nozzle a, and the combustion chamber B can form a closed space, so that the sealing test of the combustion chamber B of the thrust chamber T of the liquid spacecraft engine can be performed. Liquid or gas is injected into the thrust chamber T to implement initial pressure building, and the inner cavity is pressurized according to the pressure requirement of the pressure-resistant test of the thrust chamber to complete the test examination of the sealing property. Along with the increase of the pressure intensity of the combustion chamber B, the deformation amount can be increased by the pressure acting on the sealing ring 401, the sealing effect is better when the chamber pressure intensity of the combustion chamber B is larger, and the defects that the traditional method depends on pretightening force to maintain bulging of the sealing ring 401, the sealing pressure is low, the operation is difficult, the wall surface of the thrust chamber T is easily crushed and the like are overcome.
As shown in fig. 2, 3 and 4, according to an aspect of the present invention, the spacing support frame 100 further includes: the limiting top cover 102 is fixed at the top end of the thrust chamber T; and the pull rod 103 is arranged around the thrust chamber T and connected between the limiting top cover 102 and the limiting base 101.
Specifically, the limit top cover 102 in the limit support frame 100 is a circular plate, and is fixed on the head C of the thrust chamber T, and the limit top cover 102 and the limit base 101 are connected through the surrounding pull rods 103, so as to surround the thrust chamber T among the limit top cover 102, the limit base 101 and the pull rods 103. The limiting base 101 is fixed at the outlet position of a spray pipe A of the thrust chamber T, the limiting top cover 102 is fixed at the upper end of a head C of the thrust chamber T, and the whole thrust chamber T is fixed and limited through the pull rod 103. The limiting support frame 100 carries out limiting constraint on the upper and lower stressed parts of the thrust chamber T of the engine, truly simulates the stressed state of the thrust chamber T during working, can effectively check the sealing performance of the welding seam and each component of the thrust chamber T, and overcomes the defect of internal structure stress expansion caused by the self bearing of the thrust chamber T.
As shown in fig. 3 and 4, according to one embodiment of the present invention, there are four tie rods 103. Specifically, four pull rods 103 are distributed around the limiting support frame 100, and the four pull rods 103 are separated by 90 degrees and surround the limiting top cover 102 and the limiting base 101. The thrust chamber T is fixed between the limiting top cover 102 and the limiting base 101 through the four pull rods 103, limiting constraint is carried out on upper and lower stress components of the thrust chamber T of the engine, and the stress state of the thrust chamber T during working can be truly simulated.
As shown in fig. 5, according to an embodiment of the present invention, the check support frame 100 includes: the first pin shaft 104 is arranged at the first end of the pull rod 103 and connected with the limiting base 101; and the first nut 105 is arranged at the second end of the pull rod 103 and connected with the limit top cover 102.
Specifically, in an orientation in which the thrust chamber T is arranged with the opening facing downward, the first end of the tie rod 103 is at the lower end of the tie rod 103, and the second end of the tie rod 103 is at the upper end of the tie rod 103. In order to enable the pull rod 103 to be more stably fixed on the limiting top cover 102 and the limiting base 101, the first pin shaft 104 is arranged at the first end of the pull rod 103 and connected with the limiting base 101, and the pull rod 103 and the limiting base 101 can be movably adjusted when the installation is convenient. A first nut 105 is provided at the second end of the pull rod 103 and is connected to the limit cap 102, and the pull rod 103 is stably limited to the limit cap 102 by pre-tightening the first nut 105.
As shown in fig. 6, according to an embodiment of the present invention, the position limiting support frame 100 further includes: and the spherical washer 106 is arranged on the lower side of the first nut 105, and the spherical washer 106 is fixed on the limiting top cover 102.
Specifically, a spherical washer 106 is disposed between the first nut 105 and the pull rod 103, the spherical washer 106 is embedded in a through hole at a corresponding position of the limit cap 102, and in the present embodiment, the through holes are disposed corresponding to four angles on the limit cap 102 corresponding to four pull rods 103. When the pull rod 103 is positioned and installed, the spherical washer 106 can automatically align and bear force, and the limiting top cover 102 and the first nut 105 are uniformly stressed. As another embodiment of the present invention, the top limit cover 102 is further provided with a hanging ring, the hanging ring can be disposed at a position between the through holes corresponding to each two adjacent spherical washers 106, and the thrust chamber T pre-fixed on the top limit cover 102 is vertically hung onto the top limit base 101 through the hanging ring by an external force.
According to one embodiment of the present invention, the tie rod 103 includes: the upper bar 1031 and the lower bar 1032 are connected by a second pin 107, and the upper bar 1031 and the lower bar 1032 are connected by the second pin 107.
Specifically, in order to make the pull rod 103 fixed between the limit top cover 102 and the limit base 101 conveniently adjustable, the pull rod 103 is divided into an upper pull rod 1031 and a lower pull rod 1032, so that the pull rod 103 can be stored without occupying space after the sealing test is finished. The installation process of the limiting support frame 100 is that the limiting base 101 is fixed, the spacecraft engine thrust chamber T is placed on the limiting base 101 together with the limiting top cover 102, the lower link 1032 is connected with the limiting base 101 through the first pin 104, the upper link 1031 is connected with the lower link 1032 through the second pin 107, and finally the upper link 1031 and the spherical washer 106 on the limiting top cover 102 are screwed and fixed through the first nut 105.
As shown in fig. 2, according to one aspect of the present invention, a positioning assembly 200 includes: the lower end of the hollow supporting bracket 201 is connected with the limiting base 101, the upper end of the supporting bracket 201 is a circular supporting plate 202, and the driving mechanism 300 is installed in the hollow structure of the supporting bracket 201.
As one embodiment, the lower end of the supporting bracket 201 of the positioning assembly 200 is connected to the limiting base 101, the limiting base 101 in the above embodiment is a protrusion extending from the center to the periphery, the supporting bracket 201 is formed by extending upward along the protrusion, the supporting bracket 201 is composed of four orifice plates with widths gradually decreasing from bottom to top, the middle of the supporting bracket 201 is a hollow cylinder, and the four orifice plates are connected and distributed around the hollow cylinder. The circular ring shape backup pad 202 is connected to four orifice plate upper ends, and the interior circle of circular ring shape backup pad 202 matches with the circle of cylinder, and the excircle matches with four orifice plate top outward flange, and the excircle diameter of one of them embodiment circular ring shape backup pad 202 is greater than four orifice plate top outward flange diameters. Adopt support bracket 201 and backup pad 202, can avoid locating component 200 all to set to the form of laminating thrust room T spray tube A inner wall, increased locating component 200's support dynamics, reduce simultaneously to thrust room T spray tube A inner wall atress on a large scale, can also save material.
According to one aspect of the invention, the positioning assembly 200 comprises: and a hollow positioning bracket 203 fixed to the upper end of the support plate 202 of the support bracket 201, wherein the outer surface of the positioning bracket 203 conforms to the shape of the inner wall of the nozzle a, and the driving mechanism 300 is installed in the hollow structure of the positioning bracket 203.
Specifically, the positioning bracket 203 of the positioning assembly 200 is designed to have an outer surface shape matched with the inner wall of the nozzle a, the bottom surface of the positioning bracket 203 is the same as the annular support plate 202, a hollow cylindrical positioning bracket 203 is formed, the positioning bracket 203 is fixed on the annular support plate 202, and the driving mechanism 300 is installed in the hollow structure of the positioning bracket 203. The positioning bracket 203 can accurately position the thrust chamber T during installation, and the risk of scratching the wall surface of the thrust chamber T nozzle A is reduced.
In accordance with one aspect of the present invention, the positioning bracket 203 is a non-metallic rigid material. The positioning bracket 203 made of non-metal rigid material is adopted, the wall surface of the thrust chamber T spray pipe A is not abutted with the positioning surface of the positioning bracket in the whole course in the test, namely, the wall surface is not contacted with the supporting bracket 201 and the supporting plate 202 in the positioning assembly 200, and the risk of crushing after the wall surface of the thrust chamber T spray pipe A is abutted with the bearing surface and the positioning sealing surface in a pre-tightening manner is avoided.
According to one aspect of the invention, the drive mechanism 300 is a pneumatic cylinder drive mechanism. The driving mechanism 300 is in a cylinder driving mode, is simple to operate, safe and reliable, has controllable sealing compression amount, can be suitable for thrust chamber products with high sealing pressure and large throat diameters of the thrust chambers T, and overcomes the defects of the original manual pre-tightening mode and low sealing pressure.
As shown in fig. 7 and 8, according to an aspect of the present invention, the driving mechanism 300 further includes: a cylinder 301 which is cylindrical and is arranged in the hollow structure of the positioning bracket 203; and the piston shaft 303 is arranged in the cylinder body 301, one end of the piston shaft is provided with an air inlet hole 304 which is connected with an external air inlet pipe, and the other end of the piston shaft is connected with the sealing disc 400.
Specifically, the driving mechanism 300 includes a cylinder 301 and a piston shaft 303 disposed inside the cylinder 301, the cylinder 301 is embedded in the hollow structure of the positioning bracket 203, and the piston shaft 303 is mounted in the cylinder 301.
One end of the piston shaft 303 is matched with the shape of the cylinder body 301, is arranged into a first cylinder with the same diameter as the cylinder body 301, and is clamped in the cylinder body 301, an air inlet hole 304 is arranged in the middle of the first cylinder and is connected with an air inlet pipe, the air inlet pipe penetrates through the cylinder body 301 and the hollow structure of the support bracket 201, and an outlet is formed in the lower end of the central cylinder of the support bracket 201 to extend the air inlet pipe to the outside. The other end of the piston shaft 303 is a second cylinder with a diameter smaller than that of the cylinder body 301, the second cylinder is connected with the sealing disc 400 through a pin shaft, and the piston shaft 303 can act on the sealing disc 400 to reciprocate by switching on and off the air inlet pipe. A circular hole having the same diameter as that of the second cylinder is reserved in the upper end surface of the cylinder 301 so that the piston shaft 303 can reciprocate in the circular hole.
According to an aspect of the invention, the driving mechanism 300 further comprises: and cylinder seals 302 provided at upper and lower ends of the cylinder 301 in contact with the piston shaft 303 such that the cylinder 301 and the piston shaft 303 form a closed chamber.
Specifically, a circle of first grooves are formed in the contact surface of the first cylinder of the piston shaft 303 and the inner wall of the cylinder body 301, and the cylinder sealing ring 302 is embedded in the first grooves and is used for being in close contact with the cylinder body 301. The second cylinder of piston shaft 303 sets up round second recess with the round hole contact surface of cylinder body 301 up end, and cylinder sealing washer 302 is embedded in the second recess and is used for with cylinder body 301 in close contact with. Two cylinder sealing rings 302 are arranged at the upper end and the lower end of the cylinder body, so that the cylinder body 301 and the piston shaft 303 form a closed cavity.
According to one aspect of the invention, the sealing disk 400 further comprises: a gland 402 connected to the drive mechanism 300; a sealing base 403 fixed on the upper end of the positioning assembly 200, and a sealing gland 402 capable of sliding relative to the sealing base 403; the seal ring 401 is located between the gland 402 and the seal base 403.
Specifically, the gland 402 and the seat 403 of the gland 400 are slidably engaged, and the gland 402 is engaged with the piston shaft 303 because the gland 400 is engaged with the drive mechanism 300, the support bracket 201, and the retainer base 101 to accurately position the axis and throat center line of the thrust chamber T.
The sealing base 403 is connected with the supporting base of the cylinder 301, and the sealing gland 402 and the sealing base 403 move relatively under the action of the driving mechanism 300, so that the sealing ring 401 expands and abuts against the inner wall of the throat of the thrust chamber T.
According to one aspect of the invention, the gland 402 and the seal base 403 each include a circular groove, with the bottom end of the gland 402 snapping into the groove of the seal base 403.
Specifically, the middle of the sealing gland 402 and the sealing base 403 is a coaxial circular groove, the diameter of the circular groove of the sealing gland 402 is smaller than that of the circular groove of the sealing base 403, and the diameter of the circular groove at the bottom end of the sealing gland 402 is the same as that of the circular groove of the sealing base 403, so that the bottom end of the sealing gland 402 is clamped in the groove of the sealing base 403 and can move up and down.
According to an embodiment of the present invention, an annular boss 404 extends from the upper end of the gland 402, and the annular boss 404 is matched with the upper end surface of the sealing base 403 to place the sealing ring 401.
In this embodiment, the upper port of the gland 402 extends to the periphery to form an annular boss 404, the width of the annular boss 404 is the same as the width of the side wall of the circular groove of the sealing base 403, and the sealing ring 401 is placed between the annular boss 404 and the upper end face of the sealing base 403. When the bottom end of the sealing gland 402 is clamped in the groove of the sealing base 403 to move downwards, the annular boss 404 approaches the upper end face of the sealing base 403, the sealing ring 401 is compressed to enable the sealing ring 401 to expand, the deformed sealing ring 401 can be tightly attached to the throat position of the thrust chamber T, a closed cavity is formed in the combustion chamber B of the thrust chamber T, and then a sealing test can be performed on the combustion chamber B.
According to an embodiment of the present invention, the surfaces of the annular bosses 404 opposite to the sealing base 403 are provided with mounting grooves, and the groove walls of the mounting grooves are arc-shaped surfaces.
Specifically, in order to prevent the sealing ring 401 from easily sliding out of the position where the annular boss 404 is opposite to the sealing base 403 in the stressed compression process, mounting grooves of arc-shaped groove walls are formed in the surfaces where the annular boss 404 is opposite to the sealing base 403, so that the arc-shaped mounting grooves can limit the sealing ring 401 to be in a set position without shifting.
According to one embodiment of the present invention, the groove of the sealing base 403 is located at a positioning hole 405, and the connecting rod 406 is connected to the piston shaft 303 through the positioning hole 405.
Specifically, since the gland 402 is connected to the piston shaft 303 through the connecting rod 406, a positioning hole 405 needs to be reserved in the sealing base 403 located between the gland 402 and the piston shaft 303, so that the connecting rod 406 can move the gland 402 up and down through the sealing base 403. The positioning hole 405 is located at the center of the circular groove of the sealing base 403, and the diameter of the positioning hole 405 is adapted to the connecting rod 406. As a mode of this embodiment, a circle of second groove is disposed on an inner side wall of the positioning hole 405, and the cylinder seal ring 302 is embedded in the second groove for tightly contacting with the cylinder body 301; a circle of first groove is formed in the periphery of a first cylinder of the piston shaft 303, and the cylinder sealing ring 302 is embedded in the first groove and used for being in close contact with the cylinder body 301.
According to an embodiment of the present invention, a groove is formed at the top end of the piston shaft 303, and the connecting rod 406 extends into the groove of the piston shaft 303, and the connecting rod 406 is connected with the piston shaft 303 through a pin.
Specifically, the top end of the second cylinder of the piston shaft 303 is provided with a recessed groove, the connecting rod 406 can extend into the groove of the piston shaft 303, a through hole is formed in the side wall of the groove and the corresponding position of the connecting rod 406, and a pin shaft penetrates through the through hole to connect the connecting rod 406 with the piston shaft 303.
The assembly test process of the sealing device for the spacecraft engine thrust chamber test comprises the following steps:
the hoisting ring is installed on the limiting top cover 102, then the head C of the thrust chamber T is connected with the limiting top cover 102 and the first nut 105, the thrust chamber T is vertically hoisted to the limiting base 101 through the hoisting ring, the outer profile of the positioning bracket 203 is attached to the inner wall surface of the expansion section of the spray pipe A of the thrust chamber T by means of self weight, and the sealing ring 401 is positioned at the central line of the throat part of the thrust chamber T.
The upper tie bar 1031 and the limit cap 102 are screwed and fixed by a spherical washer 106 and a first nut 105. Compressed air is introduced into an air inlet pipe of the driving mechanism 300 to drive the cylinder to compress the sealing ring 401 to expand, so that the sealing ring 401 is attached to the inner wall surface of the throat part of the thrust chamber T.
And (3) filling water or compressed air into the inner cavity of the thrust chamber T to implement initial pressure building, disconnecting a water source or an air source of the driving mechanism after the initial pressure is stable, and then pressurizing the inner cavity according to the pressure requirement of the pressure resistance test of the thrust chamber T to finish the tightness test examination. After the test is finished, the pressure of the thrust chamber T is relieved, then the first nut 105, the spherical washer 106 and the upper pull rod 1031 are disassembled, the thrust chamber T is vertically lifted to be separated from the positioning bracket 203, and then the limiting top cover 102 is disassembled.
The sealing device for the spacecraft engine thrust chamber test can be suitable for the area with the diameter of the T throat part of the thrust chamber generally being more than 30mm, and when the diameter of the T throat part of the thrust chamber is smaller, the driving mechanism can adopt a threaded pre-tightening connection mode to replace a compression sealing ring.
The sealing device for the spacecraft engine thrust chamber test has the technical effects that:
1) self-tightening sealing: pre-compressing the seal ring 401 to form an initial seal cavity and establishing a low cavity pressure; along with the increase of the chamber pressure, the deformation is increased by acting on the compression sealing ring 401 of the sealing gland 402, the larger the chamber pressure of the inner chamber is, the better the sealing effect is, and the defects that the traditional sealing ring expansion is maintained by relying on pretightening force, the sealing pressure is low, the operation is difficult, the wall surface of a thrust chamber is easily crushed and the like are overcome.
2) A driving mechanism: adopt cylinder drive principle to accomplish sealing washer 401 initial compression, simple structure, the simple operation, drive air supply pressure requires lowly, avoids the too big operation of being difficult to of original mechanical thread pretightning force when withstand voltage test pressure is high.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions, improvements, etc. within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides a spacecraft engine thrust room sealing device for experiment which characterized in that includes:
the limiting support frame comprises a limiting base and is used for fixing and limiting the thrust chamber;
the positioning assembly is fixed on the limiting base and is used for abutting against the inner wall of a spray pipe of the thrust chamber;
the driving mechanism is fixed in the middle of the inner side of the positioning assembly;
the sealing disc comprises a sealing ring and is arranged at the top end of the driving mechanism;
during testing, the outlet end of the thrust chamber is downwards fixed on the positioning assembly, and the driving mechanism provides external force to enable the sealing ring to be abutted against the inner wall of the throat part of the thrust chamber.
2. The spacecraft engine thrust chamber test sealing device of claim 1, wherein the limiting support frame further comprises:
the limiting top cover is fixed at the top end of the thrust chamber;
and the pull rod is arranged around the thrust chamber and connected between the limiting top cover and the limiting base.
3. The spacecraft engine thrust room test seal of claim 1, wherein said positioning assembly comprises:
the lower end of the hollow supporting bracket is connected with the limiting base, the upper end of the supporting bracket is a circular supporting plate, and the driving mechanism is installed in the hollow structure of the supporting bracket.
4. The spacecraft engine thrust room test seal of claim 3, wherein said positioning assembly comprises:
the hollow positioning bracket is fixed at the upper end of the supporting plate of the supporting bracket, the outer surface of the positioning bracket is matched with the shape of the inner wall of the spray pipe, and the driving mechanism is installed in the hollow structure of the positioning bracket.
5. The spacecraft engine thrust chamber test seal assembly of claim 4, wherein said positioning bracket is a non-metallic rigid material.
6. The spacecraft engine thrust chamber test seal of claim 4, wherein said drive mechanism is a cylinder drive mechanism.
7. The spacecraft engine thrust room test seal of claim 6, wherein said drive mechanism further comprises:
the cylinder body is cylindrical and is arranged in the hollow structure of the positioning bracket;
and the cylinder sealing rings are arranged at the upper end and the lower end of the cylinder body, so that the cylinder body forms a closed cavity.
8. The spacecraft engine thrust room test seal of claim 7, wherein said drive mechanism further comprises:
and the piston shaft is arranged in the cylinder body, one end of the piston shaft is provided with an air inlet hole which is connected with an external air inlet pipe, and the other end of the piston shaft is connected with the sealing disc.
9. The spacecraft engine thrust room test seal assembly of claim 1, wherein said seal disk further comprises:
the sealing gland is connected with the driving mechanism;
the sealing base is fixed at the upper end of the positioning assembly, and the sealing gland can slide relative to the sealing base;
the sealing ring is positioned between the sealing gland and the sealing base.
10. The spacecraft engine thrust room test seal of claim 9, wherein said gland and said seal base each include a circular groove, and a bottom end of said gland is snap-fit into said seal base groove.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010754711.3A CN111735631A (en) | 2020-07-31 | 2020-07-31 | Sealing device for spacecraft engine thrust chamber test |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010754711.3A CN111735631A (en) | 2020-07-31 | 2020-07-31 | Sealing device for spacecraft engine thrust chamber test |
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| CN112345234A (en) * | 2020-10-29 | 2021-02-09 | 清华大学 | Testing device capable of analyzing line diameter change of O-shaped ring for high-pressure sealing on line |
| CN112378586A (en) * | 2020-10-30 | 2021-02-19 | 中国科学院沈阳自动化研究所 | Full-automatic self-adaptive aligning and plugging mechanism for throat part of large-sized cavity workpiece |
| CN112855933A (en) * | 2020-12-30 | 2021-05-28 | 江苏深蓝航天有限公司 | Throat sealing device and method for thrust chamber of liquid rocket engine |
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Application publication date: 20201002 |