Double-sealing flange assembly, pushing system and carrier rocket

Abstract

The embodiment of the invention provides a double-sealing flange assembly, a pushing system and a carrier rocket, the double-sealing flange assembly is used for pushing a high-pressure propellant in the carrier rocket, the double-sealing flange assembly further comprises a spring ring mounting groove (300) and a spring ring (3), the spring ring mounting groove (300) is provided with an upper flange end face (11) and a lower flange end face (21), the spring ring (3) is mounted in the spring ring mounting groove (300), and the spring ring (3) is connected with the spring ring mounting groove (300). When the upper channel and the lower channel are filled with high-pressure propellants, the spring plug ring (3) deforms under the pressure action of the high-pressure propellants, and self-tightening sealing between the spring plug ring (3) and the upper flange (1) and between the spring plug ring (3) and the lower flange (2) can be achieved. The device further comprises a graphite ring installation structure (400) and a graphite ring (4), the graphite ring installation structure (400) is provided with an upper flange end face (11) and a lower flange end face (21), and the graphite ring (4) can be installed in the graphite ring installation structure (400) in an attached mode. The flange structure and the sealing structure are simple, and the sealing efficiency is high.

Description

Technical Field

[0001] The invention relates to the field of launch vehicles, and in particular to a double-pass sealing flange component, a propulsion system and a launch vehicle. Background Art

[0002] Most of the mainstream launch vehicles in service in my country use low-temperature high-pressure propellants such as liquid oxygen-kerosene, liquid oxygen-methane, liquid hydrogen and liquid oxygen. The inside and outside of the launch vehicle flange are two different propellants, and the propellant temperature difference is large and the temperature range is wide. Once the flange sealing surface leaks, it will directly lead to system failure and launch failure, so the sealing reliability requirements are extremely high.

[0003] In the process of implementing the present invention, the applicant discovered that there are at least the following problems in the prior art:

[0004] The traditional single-channel sealing method has low reliability and cannot meet the sealing requirements of flange joint surfaces of low-temperature and high-pressure propellants such as liquid oxygen-kerosene, liquid oxygen-methane, liquid hydrogen and liquid oxygen of the current mainstream launch vehicles. Summary of the invention

[0005] The embodiments of the present invention provide a double-pass sealing flange assembly, a propulsion system and a launch vehicle, which can solve the technical problem in the prior art that "the traditional single-pass sealing method has low reliability and cannot adapt to the sealing requirements of the flange joint surfaces of high-pressure propellants such as liquid oxygen-kerosene, liquid oxygen-methane, liquid hydrogen and liquid oxygen of the current mainstream launch vehicles."

[0006] To achieve the above-mentioned purpose, in a first aspect, an embodiment of the present invention provides a double-pass sealing flange assembly, which is used for pushing high-pressure propellant in a launch vehicle, and comprises an upper flange arranged on an upper channel and a lower flange arranged on a lower channel, wherein the upper flange and the lower flange are both arranged vertically, and the upper flange end face of the upper flange and the lower flange end face of the lower flange can be connected to realize connecting the upper channel and the lower channel to form a leakage channel for high-pressure propellant from top to bottom, and the leakage channel is used to push the high-pressure propellant in the upper channel into the lower channel;

[0007] The double-pass sealing flange assembly further comprises a Vane ring installation groove and a Vane ring, wherein the Vane ring installation groove is provided with the upper flange end face and the lower flange end face, and the Vane ring is installed in the Vane ring installation groove, and when the upper channel and the lower channel are filled with high-pressure propellant, the Vane ring is deformed under the pressure of the high-pressure propellant to achieve a self-tightening seal with the upper flange and the lower flange;

[0008] The double-pass sealing flange assembly further comprises a graphite ring mounting structure and a graphite ring, wherein the graphite ring mounting structure is provided with the upper flange end face and the lower flange end face, and the graphite ring can be fittedly mounted in the graphite ring mounting structure;

[0009] The pan-seal ring mounting groove is arranged on the inner ring, the graphite ring mounting structure is arranged on the outer ring, and the distance between the inner ring and the central axis of the leakage channel is smaller than the distance between the outer ring and the central axis of the leakage channel.

[0010] In a second aspect, an embodiment of the present invention provides a high-pressure propellant pushing system for a launch vehicle, comprising an upper channel and a lower channel, wherein the upper channel pushes a first high-pressure propellant, and the lower channel contains a second high-pressure propellant, wherein the upper channel and the lower channel are sealed and connected via the aforementioned double-pass sealing flange assembly, so that the upper channel and the lower channel are connected to form a leakage channel for the high-pressure propellant, and the leakage channel is used to push the first high-pressure propellant in the upper channel into the lower channel.

[0011] In a third aspect, an embodiment of the present invention provides a launch vehicle, comprising a high-pressure propellant propulsion system of the aforementioned launch vehicle.

[0012] The above technical scheme has the following beneficial effects: the upper flange end face of the upper flange and the lower flange end face of the lower flange can be connected to realize the connection between the upper channel and the lower channel to form a leakage channel, and the leakage channel is used to push the high-pressure propellant in the upper channel into the lower channel; in the double-pass sealing flange assembly formed by the upper flange and the lower flange, a pan-seal ring is arranged on the inner ring as the main seal, which can be self-tightly sealed in the pan-seal ring mounting groove, and a graphite ring is arranged on the outer ring, which can be fitted in the graphite ring mounting structure as an auxiliary seal; the flange structure is simple, and the sealing structure is also simple, so the flange size under the same working condition is relatively small, and the manufacturing cost is low; if the pan-seal ring arranged on the inner ring fails, the sealing can also be achieved by the graphite ring on the outer ring that can be fitted in the graphite ring mounting structure, and the sealing efficiency is high, and the sealing reliability can be effectively improved compared with the traditional single-pass sealing. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0014] Figure 1 is a cross-sectional view of a double-pass sealing flange assembly according to an embodiment of the present invention;

[0015] Figure 2 is a cross-sectional view of the upper flange 1 of the embodiment of the invention;

[0016] Figure 3 is a cross-sectional view of the lower flange 2 of the embodiment of the invention;

[0017] Figure 4 2 is a cross-sectional view of a Variseal ring 3 according to an embodiment of the invention.

[0018] The reference numerals are:

[0019] 1. Upper flange; 2. Lower flange; 3. Universal plug ring; 4. Graphite ring; 5. Bolt; 6. Flat washer; 7. Spring washer; 8. Nut; 11. Upper flange end face; 21. Lower flange end face; 31. Spring energy storage ring; 32. Jacket; 300. Universal plug ring mounting groove; 400. Graphite ring mounting structure; 500. Fastening assembly; 310. Inner ring wall; 320. Upper top surface; 330. Outer ring wall; 340. Lower bottom surface; 410. Sealing tenon; 420. Sealing mortise. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0021] like Figure 1 As shown, in combination with an embodiment of the present invention, a double-pass sealing flange assembly is provided, and the double-pass sealing flange assembly is used for pushing high-pressure propellant in a launch vehicle. The double-pass sealing flange assembly includes an upper flange 1 arranged on an upper channel and a lower flange 2 arranged on a lower channel, and the upper flange 1 and the lower flange 2 are both arranged vertically, and the upper flange end face 11 of the upper flange 1 and the lower flange end face 21 of the lower flange 2 can be connected to realize connecting the upper channel and the lower channel to form a leakage channel for high-pressure propellant from top to bottom, and the leakage channel is used to push the high-pressure propellant in the upper channel into the lower channel; wherein, the high pressure of the high-pressure propellant refers to ≯20MPa (not more than 20MPa), and for a double-pass sealing flange or channel with a diameter of 600mm, 20MPa is a very high pressure, and a flange with this characteristic belongs to a large-caliber high-pressure sealing flange or channel.

[0022] The double-pass sealing flange assembly further comprises a Variseal ring installation groove 300 and a Variseal ring 3. The Variseal ring installation groove 300 is provided with the upper flange end face 11 and the lower flange end face 21. The Variseal ring 3 is installed in the Variseal ring installation groove 300. When the upper channel and the lower channel are filled with high-pressure propellant, the Variseal ring 3 is deformed under the pressure of the high-pressure propellant to achieve a self-tightening seal with the upper flange 1 and the lower flange 2.

[0023] The double-pass sealing flange assembly further includes a graphite ring mounting structure 400 and a graphite ring 4. The graphite ring mounting structure 400 is provided with the upper flange end face 11 and the lower flange end face 21. The graphite ring 4 can be fittedly mounted in the graphite ring mounting structure 400.

[0024] The pan-seal ring installation groove 300 is arranged on the inner ring, the graphite ring installation structure 400 is arranged on the outer ring, and the distance between the inner ring and the central axis of the leakage channel is smaller than the distance between the outer ring and the central axis of the leakage channel.

[0025] In the embodiment of the present invention, the upper flange end face 11 of the upper flange 1 and the lower flange end face 21 of the lower flange 2 can be connected to realize the connection between the upper channel and the lower channel to form a leakage channel, and the leakage channel is used to push the high-pressure propellant in the upper channel into the lower channel; in the double-pass sealing flange assembly formed by the upper flange 1 and the lower flange 2, the pan-seal ring 3 arranged on the inner ring is used as the main seal, which can be self-tightened in the pan-seal ring mounting groove, and the graphite ring 4 is arranged on the outer ring, and the graphite ring 4 can be fitted in the graphite ring mounting structure 400 as an auxiliary seal; the flange structure is simple, and the sealing structure is also simple, so the flange size under the same working condition is relatively small, and the manufacturing cost is low; if the radial pan-seal ring 3 arranged on the inner ring fails, the sealing can also be achieved by the graphite ring 4 on the outer ring that can be fitted in the graphite ring mounting structure 400, and the sealing efficiency is high, and the sealing reliability can be effectively improved compared with the traditional single-pass sealing.

[0026] Preferably, if Figure 4 As shown, the Variseal ring 3 includes a spring energy storage ring 31 and a jacket 32. The opening direction of the jacket 32 ​​is consistent with the pushing direction of the high-pressure propellant. When the upper channel and the lower channel are filled with high-pressure propellant, the pressure of the high-pressure propellant is downward, pressing the jacket 32 ​​downward. The opening of the jacket 32 ​​is at the bottom. The pressure of the high-pressure propellant forces the opening of the jacket 32 ​​at the bottom to open, thereby realizing the self-tightening of the Variseal ring 3, which is superior to the traditional sealing combination of an O-ring and a graphite ring.

[0027] Preferably, if Figure 2 and Figure 3As shown, the stuffing box installation groove 300 includes an inner ring wall 310 and an upper top surface 320 belonging to the upper flange end face 11, an outer ring wall 330 and a lower bottom surface 340 belonging to the lower flange end face 21. The inner ring wall 310 is vertically arranged and coaxial with the upper flange 1. The upper top surface 320 is horizontally arranged and connected to the inner ring wall 310. The outer ring wall 330 is vertically arranged and coaxial with the lower flange 2. The lower bottom surface 340 is horizontally arranged and connected to the outer ring wall 330. The inner ring wall 310 and the outer ring wall 330 are arranged inside and outside relative to the axis of the leakage channel. The upper top surface 320 and the lower bottom surface 340 are arranged up and down relative to each other. The space formed by the inner ring wall 310, the outer ring wall 330, the upper top surface 320 and the lower bottom surface 340 is used to install the stuffing box 3. That is, the inner ring wall 310 and the upper top surface 320 are in an inverted L shape, the outer ring wall 330 and the lower bottom surface 340 are in a regular L shape, and the space formed by the inner ring wall 310, the outer ring wall 330, the upper top surface 320 and the lower bottom surface 340 is a frame shape similar to a square character.

[0028] When the upper channel and the lower channel are filled with high-pressure propellant, under the pressure of the high-pressure propellant, the opening of the jacket 32 expands, and the spring energy storage ring 31 is compressed, so that a self-tightening seal can be formed between the jacket 32, the spring energy storage ring 31 and the inner ring wall 310, the outer ring wall 330, the upper top surface 320 and the lower bottom surface 340. Moreover, the greater the medium pressure, the tighter the inner ring wall 310, the outer ring wall 330, the upper top surface 320 and the lower bottom surface 340 are pressed, so the greater the self-tightening force and the better the sealing effect.

[0029] Preferably, the diameter tolerance of the outer ring wall 330 is 0 to +0.08 mm; the diameter tolerance of the inner ring wall 310 is -0.08 to 0 mm. That is, the diameter tolerance of the outer ring wall 330 is a positive tolerance, and the diameter tolerance of the inner ring wall 310 is a negative tolerance of -0.08 to 0. Through these two tolerances, the compression rate of the stuffing box 3 can be ensured to be 20%-30%, which can ensure the sealing effect without applying an additional tightening torque.

[0030] Preferably, the spring energy storage ring 31 can be applied to the sealing environmental temperature in the range of -200°C to 300°C. The materials used for the spring energy storage ring 31 include one of the following: cobalt-based alloy steel wire, cobalt-based alloy steel strip, nickel-based alloy steel wire, nickel-based alloy steel strip, 301 austenitic stainless steel wire or 301 austenitic stainless steel strip.

[0031] The jacket 32 can be applied to the sealing environmental temperature in the range of -200°C to 300°C. The materials used for the jacket 32 include one of the following: modified polytetrafluoroethylene, ultra-high molecular weight polytetrafluoroethylene, reinforced polytetrafluoroethylene, graphite and glass fiber.

[0032] That is, the Pan Seal 3 can be used for sealing environment temperature in the atmosphere of -200℃~300℃, so that the double-pass sealing flange assembly of the entire embodiment can be used for the temperature range of -200℃~300℃, that is, it is suitable for large diameter (≯600mm diameter, wall thickness>1mm) pipelines and end face sealing conditions with a wide temperature range (-200℃~300℃). The sealing ring and flange structure can adapt to the sealing under low temperature contraction and high temperature expansion, even for different high-pressure propellants with large temperature difference and wide temperature range, such as liquid oxygen kerosene, liquid oxygen methane, liquid hydrogen and liquid oxygen. And it is better than the traditional O-ring and graphite ring sealing combination, because the traditional O-ring and graphite ring sealing combination can only adapt to the normal temperature propellant sealing in the temperature range of -60℃~50℃. Among them, the large diameter refers to a diameter of ≯600mm (not greater than 600mm), and the wall thickness must also meet >1mm. For a double-pass sealing flange or channel with a diameter of 600mm, 20MPa is a very high pressure. The flange with this characteristic belongs to a large-caliber high-pressure sealing flange or channel. Preferably, the configuration of the spring energy storage ring 31 includes one of the following: a V-type cantilever spring, an H-type helical spring, an S-type coil spring, a G-type grid spring, and an L-type symmetrical spring, which can be selected according to the pressure of the high-pressure propellant and the gap size between the pan-seal ring mounting groove 300 and the graphite ring mounting structure 400.

[0033] Preferably, the graphite ring installation structure 400 is a mortise and tenon structure, which includes a downwardly protruding sealing tenon 410 belonging to the upper flange end surface 11 and a downwardly recessed sealing tenon 420 belonging to the lower flange end surface 21, and the sealing tenon 410 can be vertically embedded in the sealing tenon 420 to form a mortise and tenon connection with the sealing tenon 420. The mortise and tenon structure is simple in form and easy to match, and the graphite ring 4 can be installed in a close fit.

[0034] Preferably, a fastening assembly 500 is also included, and the fastening assembly 500 includes a bolt 5, a flat washer 6, a spring washer 7 and a nut 8, the bolt 5 passes through the upper flange 1 and the lower flange 2, the head of the bolt 5 is located above the upper flange 1, the spring washer 7 and the flat washer 6 are located on the screw of the bolt 5 between the head of the bolt 5 and the upper flange 1, and the nut 8 is located on the screw of the bolt 5 below the lower flange 2; the fastening assembly 500 withstands a preset tightening torque. Because the Variseal ring 3 can be installed in a self-tightening manner, the graphite ring 4 is installed in the graphite ring installation structure 400 of the mortise and tenon structure. After the upper flange 1 and the lower flange 2 are assembled, when the upper flange 1 and the lower flange 2 are connected together by the fastening assembly 500, the tightening torque required for the fastening assembly 500 is only required to connect the upper flange 1 and the lower flange 2 together, and to force the sealing tenon 410 to press the graphite ring 4 to compress the graphite ring 4, so the fastening assembly 500 is subjected to a very small preset tightening torque, which is the same as the single-pass seal under the same working conditions. Therefore, under the same working conditions, the sizes of the upper flange 1 and the lower flange 2 will become smaller, and the pipe walls of the upper flange 1 and the lower flange 2 will also become thinner, and thin-walled flanges can be used, so the double-pass sealing flange assembly of the embodiment of the present application is suitable for thin-walled flanges. It is also superior to the traditional sealing combination of O-ring and graphite ring, because the tightening torque required for the traditional sealing combination of O-ring and graphite ring needs to be 1.5 to 1.8 times more than that of a single-pass seal, which will inevitably lead to a bulky sealing flange structure, high bolt strength requirements, a sharp increase in manufacturing costs, and low structural efficiency.

[0035] Preferably, the graphite ring 4 is compressed and installed in the graphite ring installation structure 400, and the compression rate of the graphite ring 4 compressed and installed in the graphite ring installation structure 400 is 20% to 30%, which can ensure the auxiliary sealing effect of the graphite ring 4;

[0036] By controlling the size of the graphite ring mounting structure 400 and the tightening torque of the fastening assembly 500 to 21 to 30 N·m, the compression rate of the graphite ring 4 can be guaranteed to be 20%-30%, thereby ensuring the sealing effect. Among them, the negative tolerance of the inner diameter of the sealing mortise 420 is -0.15 to -0.1mm, the positive tolerance of the outer diameter of the sealing mortise 420 is +0.1 to +0.15mm, the positive tolerance of the inner diameter of the sealing tenon 410 is +0.1 to +0.15mm, and the negative tolerance of the outer diameter of the sealing tenon 410 is -0.15 to -0.1mm.

[0037] The gap between the upper flange end face 11 between the graphite ring mounting structure 400 and the outer wall of the upper flange 1, and the gap between the lower flange end face 21 between the graphite ring mounting structure 400 and the outer wall of the lower flange 2 can be measured by a feeler gauge to determine the compression rate of the graphite ring 4 and ensure that the compression rate of the graphite ring 4 is 20% to 30%.

[0038] Preferably, a clearance fit is adopted between the upper flange end face 11 and the lower flange end face 21 between the Variseal ring mounting groove 300 and the graphite ring mounting structure 400; and the dimensions in the upper and lower directions are prepared so that the Variseal ring 3 can achieve self-tightening sealing in the Variseal ring mounting groove 300 and the graphite ring 4 can achieve auxiliary sealing in the graphite ring mounting structure 400.

[0039] A clearance fit is adopted between the upper flange end face 11 between the Pan-Seal ring installation groove 300 and the inner wall of the upper flange 1, and between the Pan-Seal ring installation groove 300 and the lower flange end face 21 between the inner wall of the lower flange 2, so as to prepare the dimensions in the upper and lower directions so that the Pan-Seal ring 3 can achieve sealing and self-tightening in the Pan-Seal ring installation groove 300.

[0040] In combination with an embodiment of the present invention, a high-pressure propellant pushing system for a launch vehicle is also provided, comprising an upper channel and a lower channel, wherein the upper channel pushes a first high-pressure propellant, and the lower channel contains a second high-pressure propellant, wherein the upper channel and the lower channel are sealed and connected via any one of the aforementioned double-pass sealing flange assemblies, so that the upper channel and the lower channel are connected to form a leakage channel for the high-pressure propellant, and the leakage channel is used to push the first high-pressure propellant in the upper channel into the lower channel.

[0041] In combination with an embodiment of the present invention, a launch vehicle is also provided, comprising the aforementioned high-pressure propellant propulsion system of the launch vehicle.

[0042] It should be appreciated that in the foregoing detailed description, various features are grouped together in a single embodiment to streamline the disclosure.

[0043] The disclosed embodiments are described above to enable any person skilled in the art to implement or use the present invention. Various modifications of these embodiments are obvious to those skilled in the art, and the general principles defined herein may also be applied to other embodiments without departing from the spirit and scope of the present disclosure. Therefore, the present disclosure is not limited to the embodiments given herein, but is consistent with the broadest scope of the principles and novel features disclosed in this application.

[0044] The above description includes examples of one or more embodiments. Of course, it is impossible to describe all possible combinations of components or methods for the purpose of describing the above embodiments, but it should be recognized by those skilled in the art that the various embodiments may be further combined and arranged. Therefore, the embodiments described herein are intended to cover all such changes, modifications and variations that fall within the scope of protection of the appended claims. In addition, with respect to the term "comprising" used in the specification or claims, the word is covered in a manner similar to the term "including", just as "including," is explained as a transitional word in the claims. In addition, any term "or" used in the specification of the claims is intended to mean "non-exclusive or".

[0045] The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc. 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 double-pass sealing flange assembly, characterized in that: The double-pass sealing flange assembly is used for pushing high-pressure propellant in a launch vehicle. The double-pass sealing flange assembly comprises an upper flange (1) arranged on an upper channel and a lower flange (2) arranged on a lower channel. The upper flange end surface (11) of the upper flange (1) and the lower flange end surface (21) of the lower flange (2) can be connected to connect the upper channel and the lower channel to form a leakage channel for high-pressure propellant from top to bottom. The leakage channel is used to push the high-pressure propellant in the upper channel into the lower channel. The double-pass sealing flange assembly further comprises a Variseal ring installation groove (300) and a Variseal ring (3), wherein the Variseal ring installation groove (300) is provided with the upper flange end face (11) and the lower flange end face (21), and the Variseal ring (3) is installed in the Variseal ring installation groove (300), and when the upper channel and the lower channel are filled with high-pressure propellant, the Variseal ring (3) is deformed under the pressure of the high-pressure propellant to achieve a self-tightening seal with the upper flange (1) and the lower flange (2); The double-pass sealing flange assembly further comprises a graphite ring mounting structure (400) and a graphite ring (4); the graphite ring mounting structure (400) is provided with the upper flange end surface (11) and the lower flange end surface (21); and the graphite ring (4) can be fitted in the graphite ring mounting structure (400); The pan-seal ring mounting groove (300) is arranged on the inner ring, the graphite ring mounting structure (400) is arranged on the outer ring, and the distance between the inner ring and the central axis of the leakage channel is smaller than the distance between the outer ring and the central axis of the leakage channel.

2. The double-pass sealing flange assembly according to claim 1, characterized in that: The pan-seal ring (3) comprises a spring energy storage ring (31) and a jacket (32), and the opening direction of the jacket (32) is consistent with the pushing direction of the high-pressure propellant.

3. The double-pass sealing flange assembly according to claim 2, characterized in that: The pan-seal ring installation groove (300) comprises an inner annular wall (310) and an upper top surface (320) belonging to the upper flange end surface (11), an outer annular wall (330) and a lower bottom surface (340) belonging to the lower flange end surface (21), and the space formed by the inner annular wall (310), the outer annular wall (330), the upper top surface (320) and the lower bottom surface (340) is used to install the pan-seal ring (3); When the upper channel and the lower channel are filled with high-pressure propellant, under the pressure of the high-pressure propellant, the opening of the jacket (32) is widened and the spring energy storage ring (31) is compressed, so that the jacket (32), the spring energy storage ring (31) can form a self-tight seal with the inner annular wall (310), the outer annular wall (330), the upper top surface (320) and the lower bottom surface (340).

4. The double-pass sealing flange assembly according to claim 3, characterized in that: The diameter tolerance of the outer ring wall (330) is 0 to +0.08 mm; The diameter tolerance of the inner annular wall (310) is -0.08 to 0 mm.

5. The double-pass sealing flange assembly according to claim 2, characterized in that: The spring energy storage ring (31) can be used in a sealing environment temperature within an atmosphere of -200°C to 300°C. The material used in the spring energy storage ring (31) includes one of the following: cobalt-based alloy steel wire, cobalt-based alloy steel strip, nickel-based alloy steel wire, nickel-based alloy steel strip, 301 austenitic stainless steel wire or 301 austenitic stainless steel strip; The jacket (32) is applicable to a sealing environment temperature within an atmosphere of -200°C to 300°C. The jacket (32) is made of one of the following materials: modified polytetrafluoroethylene, ultra-high molecular weight polytetrafluoroethylene, reinforced polytetrafluoroethylene, graphite and glass fiber.

6. The double-pass sealing flange assembly according to claim 2, characterized in that: The configuration of the spring energy storage ring (31) includes one of the following: a V-shaped cantilever spring, an H-shaped helical spring, an S-shaped coil spring, a G-shaped grid spring and an L-shaped symmetrical spring.

7. The double-pass sealing flange assembly according to claim 1, characterized in that: include: The graphite ring installation structure (400) is a mortise and tenon structure, comprising a downwardly protruding sealing tenon (410) belonging to the upper flange end surface (11) and a downwardly recessed sealing tenon (420) belonging to the lower flange end surface (21), and the sealing tenon (410) can be vertically embedded in the sealing tenon (420) to form a mortise and tenon connection with the sealing tenon (420).

8. The double-pass sealing flange assembly according to claim 7, characterized in that: It also includes a fastening assembly (500), wherein the fastening assembly (500) passes through the upper flange (1) and the lower flange (2), and the fastening assembly (500) bears a preset tightening torque.

9. The double-pass sealing flange assembly according to claim 1, characterized in that: The graphite ring (4) is compressed and installed in the graphite ring installation structure (400), with a compression rate of 20% to 30%.

10. The double-pass sealing flange assembly according to claim 1, characterized in that: A clearance fit is adopted between the upper flange end surface (11) and the lower flange end surface (21) between the Van Seal ring installation groove (300) and the graphite ring installation structure (400); A clearance fit is adopted between the upper flange end surface (11) between the Variseal ring installation groove (300) and the inner wall of the upper flange (1), and between the lower flange end surface (21) between the Variseal ring installation groove (300) and the inner wall of the lower flange (2).

11. A high-pressure propellant delivery system for a launch vehicle, characterized in that: The invention comprises an upper channel and a lower channel, wherein the upper channel pushes a first high-pressure propellant, and the lower channel contains a second high-pressure propellant. The upper channel and the lower channel are sealed and connected by a double-pass sealing flange assembly as described in any one of claims 1 to 10, so that the upper channel and the lower channel are connected to form a leakage channel for the high-pressure propellant, and the leakage channel is used to push the first high-pressure propellant in the upper channel into the lower channel.

12. A launch vehicle, characterized in that: It comprises the double-pass sealing flange assembly as described in any one of claims 1 to 10, or the high-pressure propellant pushing system of a launch vehicle as described in claim 11.

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