Propellant storage tank with built-in pressurization storage tank, pressurization storage tank, rocket and pressurization method

Abstract

The embodiment of the invention provides a propellant storage box with a built-in pressurization storage box, the pressurization storage box, a rocket and a pressurization method, and relates to the technical field of rocket pressurization, and the propellant storage box with the built-in pressurization storage box comprises a propellant storage box body, a pressurization storage box body and a supporting device; the supporting device is installed at the bottom in the propellant storage box body, and the pressurization storage box body is arranged in the propellant storage box body and installed at the top end of the supporting device. The propellant storage box body, the pressurization storage box body and the supporting device are coaxial. A single large-capacity pressurizing storage tank is used for replacing a plurality of small-capacity storage tanks connected in series, so that the problem that in the prior art, the structure is not stable due to the complex structure is solved, and the pressurizing storage tank arranged at the propellant inlet and outlet can also play a role in preventing collapse when propellants flow to an engine.

Description

Technical Field

[0001] The present invention relates to the field of rocket supercharging technology, and in particular to a propellant tank with a built-in supercharging tank, a supercharging tank, a rocket and a supercharging method. Background Art

[0002] For launch vehicles that use cold helium and liquid nitrogen heating and pressurization solutions, it is necessary to heat the cryogenic gas in the engine and then enter the propellant tank for pressurization. The container that stores the pressurization medium (cold helium, liquid nitrogen, etc.) is the pressurization tank. In order to ensure the pressurization capacity, most of the current models place the pressurization tank in the low-temperature propellant tank to maintain the low temperature of the pressurization medium. Even so, the volume of the pressurization tank required for pressurization is still large. Traditional structures often use several small-volume pressurization tanks in series to meet the pressurization requirements. The volume of each small pressurization tank generally does not exceed 70L, and several small-volume pressurization tanks are installed on the side walls of the propellant tank.

[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] How to provide a single large-capacity pressurized tank within the propellant tank to solve the problems of low structural efficiency and reliability existing in the structure of connecting several small-capacity pressurized tanks in series. Summary of the invention

[0005] Embodiments of the present invention provide a propellant tank with a built-in pressurized tank, a pressurized tank, a rocket and a pressurization method, and provide a single large-capacity pressurized tank in the propellant tank to solve the problems of low structural efficiency and low reliability of a structure in which several small-volume pressurized tanks are connected in series.

[0006] To achieve the above-mentioned purpose, in a first aspect, an embodiment of the present invention provides a propellant tank with a built-in pressurized tank, comprising: a propellant tank body, a pressurized tank body and a supporting device;

[0007] The support device is installed at the bottom of the propellant tank body, and the booster tank body is arranged in the propellant tank body and installed at the top of the support device;

[0008] The propellant tank body, the pressurized tank body and the supporting device are coaxial.

[0009] Furthermore, a propellant inlet and outlet is provided at the bottom center of the propellant tank body;

[0010] The vertical axis of the support device is coaxial with the center of the propellant inlet and outlet. The support device is installed on the inner bottom surface of the propellant tank body. Propellant flow windows are evenly arranged on the side of the support device. The propellant flow windows are connected to the propellant inlet and outlet so that the propellant in the propellant tank body can flow evenly through the propellant flow windows to reach the propellant inlet and outlet.

[0011] Furthermore, the propellant flow window of the supporting device is provided with a skin; and a filter net is provided in the middle of the skin.

[0012] Furthermore, a pressurization port is provided on the top of the pressurized storage tank body; a pressurized medium outlet is provided on the side of the pressurized storage tank body;

[0013] The side wall of the propellant tank body is provided with a first flange and a second flange;

[0014] The pressurization port is connected with a pressurization pipeline of the pressurization tank, and the pressurization pipeline of the pressurization tank passes through the first flange and extends to the outside of the propellant tank body;

[0015] The pressurized medium outlet is connected with an outlet pipeline, and the outlet pipeline passes through the second flange and extends to the outside of the propellant tank body.

[0016] Furthermore, the supporting device comprises:

[0017] An upper connecting piece used for connecting and supporting the bottom of the pressurized storage tank body, the upper connecting piece being in the shape of a circular ring;

[0018] A lower connecting piece used for connecting to the inner bottom surface of the propellant tank body, the lower connecting piece being in the shape of a circular ring;

[0019] Used to support multiple support components connected between the upper connecting member and the lower connecting member, wherein the multiple support components are evenly distributed along the circumference of the upper connecting member and the lower connecting member;

[0020] The diameter of the upper connecting piece is smaller than that of the lower connecting piece, and the upper connecting piece and the lower connecting piece are arranged coaxially and in parallel, and the axes of the upper connecting piece and the lower connecting piece vertically pass through the center of the propellant inlet and outlet.

[0021] Furthermore, the skin is arranged on the entire virtual cone side surface formed by the outer side surfaces of the plurality of support components, and the skin is composed of a plurality of pieces, and the plurality of pieces of skin are sequentially connected end to end;

[0022] The left end of each skin is connected to the supporting assembly facing the left end, and the right end of each skin is connected to the supporting assembly facing the right end; at least one supporting assembly is arranged between the supporting assemblies facing the left and right ends of each skin; on the supporting assemblies facing the left and right ends of each skin, two rows of connecting holes are arranged in parallel along the longitudinal direction of the supporting assemblies; the left and right ends of each skin are respectively connected to the supporting assemblies facing them through bolts based on the connecting holes; no connecting holes are arranged on the supporting assembly facing the middle part of each skin, and it is not connected to the skins; the upper end of each skin is bolted to the upper connecting piece, and the lower end of each skin is bolted to the lower connecting piece.

[0023] Furthermore, the cross section of the support component is T-shaped or I-shaped.

[0024] In a second aspect, an embodiment of the present invention provides a pressurized tank with a support, the pressurized tank with a support is used in a propellant tank with a built-in pressurized tank as in any of the above, comprising: a pressurized tank body and a support device;

[0025] The bottom of the pressurized tank body is connected to the upper part of the supporting device, and the projection of the center of gravity of the pressurized tank body in the vertical direction coincides with the vertical axis of the supporting device.

[0026] In a third aspect, an embodiment of the present invention provides a launch vehicle, comprising: an engine, and a propellant tank with a built-in pressurized tank as described above or a pressurized tank with a support as described above;

[0027] A propellant inlet and outlet is provided at the bottom center of the propellant tank body;

[0028] The engine is connected to the propellant inlet and outlet;

[0029] The engine is also connected to the boost tank body via a boost tank boost pipeline penetrating into the propellant tank body;

[0030] The engine is also connected to the pressurized tank body through an outflow pipeline penetrating into the propellant tank body;

[0031] The engine is also connected to the propellant tank body through a propellant tank pressurization line.

[0032] In a fourth aspect, an embodiment of the present invention provides a method for pressurizing a propellant tank for a launch vehicle, wherein a pressurized tank body is disposed at the inner bottom of the propellant tank body, and propellant flows into an engine through a propellant inlet and outlet at the center of the bottom of the propellant tank body, and the method comprises:

[0033] The pressurized medium in the pressurized tank is pumped into the engine through the outflow pipeline;

[0034] The engine heats the pressurized medium into high-temperature gas, and part of the heated gas is pumped into the propellant tank body through the propellant tank pressurization pipeline to achieve the pressurization of the propellant tank;

[0035] The remaining gas is pumped into the boost tank body through the boost tank boost pipeline to achieve the boost tank boost.

[0036] The above technical solution has the following beneficial effects:

[0037] By means of the supporting device, a large-diameter or large-capacity booster tank can be installed at the bottom of the propellant tank. The center of gravity of the installed booster tank can coincide with the projection of the center of gravity of the propellant tank in the vertical direction, thereby being able to replace a plurality of small-capacity booster tanks arranged in series, thereby avoiding the problem of structural instability caused by the traditional technology of setting a plurality of small-capacity booster tanks in series on the side wall of the propellant tank. A single large-capacity booster tank can be used to replace a plurality of small-capacity tanks in series, thereby solving the problem of low structural efficiency caused by the complex structure of the traditional technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] 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.

[0039] Figure 1 It is a structural schematic diagram of a propellant tank with a built-in pressurized tank according to one embodiment of the present invention;

[0040] Figure 2 It is a structural schematic diagram of a supporting device of a pressurized tank with support according to one embodiment of the present invention;

[0041] Figure 3 It is a schematic diagram of the three-dimensional structure of a hemispherical lower box body equipped with a pressurized storage tank according to one embodiment of the present invention;

[0042] Figure 4 It is a schematic cross-sectional view of a hemispherical lower box body equipped with a pressurized storage tank according to one embodiment of the present invention;

[0043] Figure 5 Schematic diagram of a skin according to one embodiment of the present invention

[0044] Figure 6 One of the embodiments of the present invention Figure 1 A partial enlarged view of the above;

[0045] Figure 7 The present invention is a flowchart of a method for pressurizing a propellant tank of a launch vehicle according to one embodiment of the present invention.

[0046] The reference numerals are as follows:

[0047] 1. Propellant tank body; 11. Columnar upper body; 12. Hemispherical lower body; 13. Propellant inlet and outlet; 2. Pressurized tank body; 3. Support device; 31. Skin; 32. Filter; 36. Propellant flow window; 21. Pressurization port; 22. Pressurized medium outlet; 14. First flange; 15. Second flange; 23. Pressurized tank pressurization pipeline; 24. Outlet pipeline; 33. Upper connector; 34. Lower connector; 35. Support assembly; 4. Engine. DETAILED DESCRIPTION

[0048] 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.

[0049] The inventors found that the series connection of multiple small-capacity boost tanks would increase the number of boost tanks, resulting in low structural efficiency and reduced system reliability. In order to improve structural efficiency and system reliability, it is necessary to optimize multiple small-volume boost tanks in series into a large-diameter boost tank. At present, there is no case to refer to for the installation of a large-diameter boost tank in a tank. If a small-diameter tank is installed on the side wall, it will cause problems such as rocket eccentricity and severe stress on the support position of the side wall of the propellant tank. When the rocket propellant liquid level approaches the rear bottom outlet, the liquid will produce friction with the tank wall and will be disturbed by the outside world. The velocity at the center of the outlet will be higher than the flow velocity at the tank wall. This phenomenon is called collapse. In order to solve the problem of fluid collapse, traditional devices generally set an inverted cone anti-vortex device and a secondary spoiler cross cover at the outlet, but the traditional device is only to solve the problem of liquid collapse, and does not realize the integrated design of the multifunctional structure. In order to ensure the quality of the propellant flowing into the engine, a filtering device needs to be set at the pipeline or the propellant tank outlet.

[0050] On the one hand, if Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, an embodiment of the present invention provides a propellant tank with a built-in pressurized tank, comprising: a propellant tank body 1, a pressurized tank body 2 and a supporting device 3;

[0051] The support device 3 is installed at the bottom of the propellant tank body 1, and the booster tank body 2 is arranged in the propellant tank body 1 and installed at the top of the support device 3;

[0052] The propellant tank body 1, the pressurized tank body 2 and the supporting device 3 are coaxial.

[0053] In some embodiments, the pressurized tank body 2 is installed at the bottom of the inner side of the propellant tank body 1. Preferably, the pressurized tank body 2 is a structure symmetrical along the vertical axis, such as a spherical, cylindrical or ellipsoidal shape. Preferably, the propellant tank body 1 is a cryogenic propellant tank body, and the pressurized tank body 2 is used to store cryogenic nitrogen liquid. The propellant tank body 1 stores cryogenic propellants. The low temperature environment of the (cryogenic) propellant tank body 1 can be used to maintain the low temperature of the pressurized tank, thereby providing a stable low temperature environment for the cryogenic nitrogen liquid. The traditional method is to hang multiple gas cylinders on the side of the propellant tank body, and helium is stored in the gas cylinders. Compared with the same volume of gas and cryogenic nitrogen liquid, the weight of cryogenic nitrogen liquid is significantly heavier. Cryogenic nitrogen liquid is not suitable for the traditional method of hanging multiple gas cylinders in series on the side of the propellant tank body for storage. The embodiment of the present invention uses a single large-capacity pressurized tank body 2 instead of the traditional method of connecting multiple small-capacity gas cylinders in series. The vertical axes of the support device 3, the boost tank body 2, and the propellant tank body 1 coincide. Preferably, the support device 3, the boost tank body 2, and the propellant tank body 1 are all vertical axisymmetric structures to ensure stability. The support device 3 can install the (cryogenic) boost tank body 2 at a position that coincides with the projection of the center of gravity of the propellant tank body 1, so that the projections of the center of gravity of the low-temperature boost tank body 2 and the propellant tank body 1 can be symmetrically overlapped, so that no matter whether the diameter or capacity of the boost tank is large or small, the installation of the low-temperature boost tank body will not cause the propellant tank body or the rocket to have an eccentricity problem. The volume of the large-diameter low-temperature boost tank can be adjusted according to the boosting requirements, and the material of the low-temperature boost tank can be titanium alloy or aluminum alloy according to the boosting pressure. Preferably, the aluminum alloy materials of the boost tank body and the propellant tank body include but are not limited to any of the following models: 2A14, 2219 and 5A06.

[0054] The embodiments of the present invention have the following technical effects:

[0055] Through the low-temperature booster tank installation structure, a large-diameter or large-capacity booster tank can be installed at the bottom of the propellant tank. The center of gravity of the installed booster tank can coincide with the projection of the center of gravity of the propellant tank in the vertical direction, thereby being able to replace multiple small-capacity booster tanks arranged in series, avoiding the structural instability problem caused by the traditional technology of setting multiple small-capacity booster tanks in series on the side wall of the propellant tank. A single large-capacity booster tank can be used to replace multiple small-capacity tanks in series, thereby solving the problem of low structural efficiency caused by the complex structure of the traditional technology.

[0056] Furthermore, if Figure 1 As shown, a propellant inlet and outlet 13 is provided at the bottom center of the propellant tank body 1;

[0057] The vertical axis of the support device 3 is coaxial with the center of the propellant inlet and outlet 13. The support device 3 is installed on the inner bottom surface of the propellant tank body 1. Propellant flow windows 36 are evenly arranged on the side of the support device. The propellant flow windows 36 are connected to the propellant inlet and outlet 13 so that the propellant in the propellant tank body 1 can flow evenly through the propellant flow windows 36 to reach the propellant inlet and outlet 13.

[0058] In the traditional way, when the rocket propellant liquid surface approaches the propellant inlet and outlet flow port 13, the liquid will produce friction with the wall of the propellant tank body and be affected by external disturbances. The speed at the center of the flow port will be higher than the flow speed at the wall, and a collapse phenomenon will occur. In response to the collapse phenomenon in the traditional way, the vertical axes of the support device 3, the boost tank body 2 and the propellant tank body 1 of the embodiment of the present invention are coaxial. Under normal circumstances, the propellant inlet and outlet flow port 13 is located at the bottom center of the propellant tank body 1, and the boost tank body 2 is located directly above the propellant inlet and outlet flow port 13. Propellant flow windows 36 are evenly arranged on the sides of the support device 3, so that the boost tank body 2 can play an anti-collapse role.

[0059] The embodiment of the present invention has the following technical effects: by arranging the support device 3 and the booster tank body 2 coaxially at the bottom of the propellant tank body 1, it plays a role in preventing the rocket propellant liquid level from sinking when it approaches the propellant inlet and outlet 13.

[0060] Preferably, if Figure 1 , Figure 3 and Figure 4 As shown, the propellant tank body 1 comprises a columnar upper body 11 and a hemispherical lower body 12; the lower end of the columnar upper body 11 and the upper end of the hemispherical lower body 12 are sealed and butted together to form a complete cavity;

[0061] A propellant inlet and outlet 13 is provided at the bottom center of the hemispherical lower box 12;

[0062] The vertical axis of the support device 3 is coaxial with the center of the propellant inlet and outlet 13. The support device 3 is installed on the inner bottom surface of the hemispherical lower box 12. The side of the support device is evenly provided with propellant flow windows 36. The propellant flow windows 36 are connected with the propellant inlet and outlet 13, so that the propellant in the propellant tank box 1 can flow evenly through the propellant flow windows 36 to reach the propellant inlet and outlet 13.

[0063] The pressurized tank body 2 is arranged inside the propellant tank body 1, the bottom of the pressurized tank body 2 is connected to the upper part of the supporting device 3, and the vertical projection of the center of gravity of the pressurized tank body 2 coincides with the vertical axis of the supporting device 3.

[0064] In some embodiments, the boost tank body 2 is installed at the bottom of the inner side of the propellant tank body 1, and the boost tank body 2 is a structure symmetrical along the vertical axis, such as a spherical, cylindrical or ellipsoidal shape. The boost tank body 2 is used to store cryogenic nitrogen liquid. The propellant tank body 1 stores cryogenic propellant. The low temperature environment of the (cryogenic) propellant tank body 1 can be used to maintain the low temperature of the boost tank, thereby providing a stable low temperature environment for the cryogenic nitrogen liquid. The traditional method is to hang multiple gas cylinders on the side of the propellant tank body, and helium is stored in the gas cylinders. Compared with the same volume of gas and cryogenic nitrogen liquid, the weight of cryogenic nitrogen liquid is significantly heavier. Cryogenic nitrogen liquid is not suitable for the traditional method of hanging multiple gas cylinders in series on the side of the propellant tank body for storage. The embodiment of the present invention uses a single large-capacity boost tank body 2 instead of the traditional method of connecting multiple small-capacity gas cylinders in series. The vertical axes of the support device 3, the boost tank body 2, and the propellant tank body 1 coincide, and all three are vertical axisymmetric structures, thereby ensuring stability. In the traditional method, when the rocket propellant liquid surface approaches the propellant inlet and outlet flow port 13, the liquid will produce friction with the wall of the propellant tank body and be disturbed by the outside world, and the velocity at the center of the flow port will be higher than the flow velocity at the wall, resulting in collapse. In order to address the collapse phenomenon, the vertical axes of the support device 3 and the boost tank body 2 of the embodiment of the present invention are coaxial with the center of the propellant inlet and outlet flow port 13, the boost tank body 2 is located directly above the propellant inlet and outlet flow port 13, and the side of the support device 3 is evenly provided with propellant flow windows 36, so that the boost tank body 2 can play an anti-collapse role. The supporting device 3 can install the (cryogenic) pressurized tank body 2 at a position that coincides with the projection of the center of gravity of the propellant tank body 1, so that the projection of the center of gravity of the cryogenic pressurized tank body 2 and the propellant tank body 1 can be symmetrically overlapped. Therefore, no matter whether the diameter or capacity of the pressurized tank is large or small, the installation of the cryogenic pressurized tank body will not cause eccentricity problems in the propellant tank body or the rocket. The volume of the large-diameter cryogenic pressurized tank can be adjusted according to the pressurization requirements, and the material of the cryogenic pressurized tank can be titanium alloy or aluminum alloy according to the size of the pressurization pressure. Preferably, the aluminum alloy material of the pressurized tank body and the propellant tank body includes but is not limited to any of the following models: 2A14, 2219 and 5A06

[0065] The embodiments of the present invention have the following technical effects:

[0066] By means of the supporting device 3, a large diameter or large capacity boosting tank can be installed at the bottom of the propellant tank. The center of gravity of the installed boosting tank can coincide with the projection of the center of gravity of the (cryogenic) propellant tank in the vertical direction, thereby being able to replace a plurality of small capacity boosting tanks arranged in series, thus avoiding the structural instability problem caused by the traditional technology of arranging a plurality of small capacity boosting tanks in series on the side wall of the propellant tank. A single large capacity boosting tank can be used to replace a plurality of small capacity tanks in series, thereby solving the problem of low structural efficiency caused by the complex structure of the traditional technology, and the boosting tank arranged at the propellant inlet and outlet can also play an anti-collapse role when the propellant flows to the engine.

[0067] Furthermore, if Figure 2 , Figure 3 and Figure 5 As shown, the propellant flow window 36 of the supporting device 3 is provided with a skin 31 ; a filter net 32 ​​is provided in the middle of the skin 31 .

[0068] In some embodiments, the skin 31 with the filter 32 is covered on the propellant flow window 36, which can effectively filter the impurities in the propellant and prevent the impurities from entering the engine, ensuring the safe operation of the engine. The filter is arranged on the support device 3, so that the support device 3 has both supporting and filtering functions. When the support device 3 is combined with the boost tank and installed at the bottom center of the propellant tank, it can also prevent the fluid from collapsing.

[0069] Furthermore, if Figure 1 As shown, a pressurization port 21 is provided on the top of the pressurized tank body 2; a pressurized medium outlet 22 is provided on the side of the pressurized tank body 2;

[0070] The side wall of the propellant tank body 1 is provided with a first flange 14 and a second flange 15;

[0071] The boost port 21 is connected to a boost tank boost pipeline 23, and the boost tank boost pipeline 23 passes through the first flange 14 and extends to the outside of the propellant tank body 1;

[0072] The pressurized medium outlet 22 is connected to an outlet pipeline 24 , and the outlet pipeline 24 passes through the second flange 15 and extends to the outside of the propellant tank body 1 .

[0073] In some embodiments, since the boost tank body 2 is arranged inside the propellant tank body 1, there is a pipeline connection between the boost tank body 2 and the engine. To solve this problem, a hole is opened on the side of the propellant tank body 1 and a first flange 14 and a second flange 15 are arranged so that the boost tank boost pipeline 23 can pass through the first flange 14 to connect the boost port 21 of the boost tank body 2 and the engine 4, and the outflow pipeline 24 passes through the second flange 15 to connect the boost medium outlet 22 and the engine. A propellant tank boost flange is also arranged on the top of the propellant tank body 1 so that the propellant tank boost pipeline 16 connects the inside of the propellant tank body 1 with the engine through the propellant tank boost flange 17. The above flanges and the pipelines passing through the flanges are all sealed to prevent propellant leakage. The first flange 14 and the second flange 15 can be on the upper box or the lower box, preferably on the side of the hemispherical lower box. During flight or experiment, the pressurized medium (such as liquid nitrogen) in the boost tank is pumped into the engine 4 through the outlet pipe 24. The engine 4 heats the pressurized medium into high-temperature gas. Part of the heated gas is pumped into the propellant tank through the propellant tank boost pipe 16 to achieve the boosting function, and part of the gas is pumped into the boost tank through the boost tank boost pipe 23 to achieve the pressurization of the boost tank.

[0074] Furthermore, if Figure 2 As shown, the supporting device 3 comprises:

[0075] An upper connecting member 33 for connecting and supporting the bottom of the pressurized storage tank body 2, the upper connecting member 33 being in the shape of a circular ring;

[0076] A lower connecting piece 34 for connecting to the inner bottom surface of the propellant tank body 1, the lower connecting piece 34 being in a circular ring shape;

[0077] Used to support a plurality of support components 35 connected between the upper connecting member 33 and the lower connecting member 34, wherein the plurality of support components 35 are evenly distributed along the circumference of the upper connecting member 33 and the lower connecting member 34;

[0078] The diameter of the upper connecting member 33 is smaller than that of the lower connecting member 34, and the upper connecting member 33 and the lower connecting member 34 are arranged coaxially and in parallel, and the axes of the upper connecting member 33 and the lower connecting member 34 vertically pass through the center of the propellant inlet and outlet flow port 13;

[0079] The window formed by the adjacent support assemblies 35 , the upper connecting members 33 and the lower connecting members 34 between the adjacent support assemblies 35 serves as a propellant flow window 36 .

[0080] In some embodiments, the pressurized tank body 2 is supported and connected by the upper connecting member 33, and the lower connecting member 34 is connected to the propellant tank body 1. A plurality of supporting assemblies 35 are used to support between the upper connecting member 33 and the lower connecting member 34. The supporting device 3 can play a role in stably supporting the (low temperature) pressurized tank body 2; preferably, the upper connecting member is specifically an upper connecting plate, and the lower connecting member is specifically a lower connecting plate. The pressurized tank body 2 is connected to the supporting assembly 35 through the upper connecting member 33. The pressurized tank body 2 and the upper connecting member 33 can be connected by screwing or other connection methods. The upper connecting member 33 and the supporting assembly 35 as a load-bearing structure can be connected by screwing, riveting or other connection methods. The upper connecting member 33 can be an integral or segmented welded or riveted structure. The support assembly 35 and the lower connecting member 34 are connected by screwing, riveting or other connection methods. The lower connecting member 34 and the bottom of the propellant tank body 1 are connected by welding or other connection methods. The lower connector can be an integral or segmented welded or riveted structure. Threaded connection can facilitate the disassembly of local components for maintenance and replacement; riveting can enhance the overall stability of the cryogenic booster tank installation structure, and will not loosen under conditions such as vibration. Welding the lower connector to the bottom of the inner side of the propellant tank body can provide a more stable connection for the cryogenic booster tank installation structure. The inner diameter of the upper connector 33 is smaller than the maximum diameter of the booster tank body 2 in the horizontal direction, so that the booster tank body can sit stably on the upper connector 33.

[0081] The embodiment of the present invention has the following technical effects: the supporting device 3 is divided into an upper connecting member, a lower connecting member and a supporting assembly, which is convenient for installation and replacement and maintenance of some components.

[0082] Furthermore, if Figure 2 and Figure 3 As shown, the skin 31 is arranged on the entire virtual cone side surface formed by the outer side surfaces of the plurality of support assemblies 35, and the skin 31 is composed of multiple pieces, and the multiple pieces of skin 31 are sequentially connected end to end;

[0083] The left end of each skin 31 is connected to the support assembly 35 facing the left end, and the right end of each skin 31 is connected to the support assembly 35 facing the right end; at least one support assembly 35 is arranged between the support assemblies 35 facing the left and right ends of each skin 31; on the support assemblies 35 facing the left and right ends of each skin 31, two rows of connecting holes are arranged in parallel along the longitudinal direction of the support assemblies 35; the left and right ends of each skin 31 are respectively connected to the facing support assemblies 35 through bolts based on the connecting holes; no connecting holes are arranged on the support assembly 35 facing the middle part of each skin 31, and it is not connected to the skin 31; the upper end of each skin 31 is bolted to the upper connecting piece 33, and the lower end of each skin 31 is bolted to the lower connecting piece 34.

[0084] In some embodiments, the skin 31 covers the outer side of the support assembly 35 and is connected by two rows of connection holes and bolts, which can ensure the close fit between the skin 31 and the support assembly 35, and ensure that the propellant can only flow out through the filter. No connection holes are set in the middle of each skin 31 facing the support assembly 35, so as to provide stronger support capacity. The skin can be a single piece or multiple pieces, and multiple pieces are not easy to deform during installation.

[0085] Furthermore, the cross section of the support assembly 35 is T-shaped or I-shaped. The support assembly 35 is generally a beam, and its cross-sectional form can be adjusted according to the force of the pressurized tank, and is generally T-shaped, I-shaped, etc. The T-shaped or I-shaped beam structure can enhance the support capacity of the support assembly.

[0086] Second, as Figure 3 As shown, an embodiment of the present invention provides a pressurized tank with support, and the pressurized tank with support is used in a propellant tank with a built-in pressurized tank as in any of the above, comprising: a pressurized tank body 2 and a support device 3;

[0087] The bottom of the pressurized tank body 2 is connected to the upper part of the supporting device 3 , and the projection of the center of gravity of the pressurized tank body 2 in the vertical direction coincides with the vertical axis of the supporting device 3 .

[0088] The embodiment of the pressurized tank with support can be understood based on the description of the pressurized tank body 2 and the support device 3 in the embodiment of the propellant tank with built-in pressurized tank, and will not be repeated here.

[0089] Thirdly, Figure 1 As shown, an embodiment of the present invention provides a launch vehicle, comprising: an engine, and a propellant tank with a built-in pressurized tank as in any of the above or a pressurized tank with support as in the above;

[0090] A propellant inlet and outlet 13 is provided at the bottom center of the propellant tank body 1;

[0091] The engine 4 is connected to the propellant inlet and outlet 13;

[0092] The engine 4 is also connected to the boost tank body 2 via a boost tank boost pipe 23 penetrating into the propellant tank body 1;

[0093] The engine 4 is also connected to the boost tank body 2 via an outflow pipe 24 penetrating into the propellant tank body 1;

[0094] The engine 4 is also connected to the propellant tank body 1 via a propellant tank pressurization pipeline 16 .

[0095] For the launch vehicle embodiment, it can be understood based on the description of the propellant tank embodiment with a built-in pressurized tank, and will not be repeated here.

[0096] Fourthly, Figure 7 As shown, an embodiment of the present invention provides a method for pressurizing a propellant tank for a launch vehicle, wherein a pressurized tank body 2 is arranged at the inner bottom of a propellant tank body 1, and propellant flows into an engine 4 through a propellant inlet and outlet 13 at the bottom center of the propellant tank body 1, comprising:

[0097] Step S71, the pressurized medium in the pressurized tank body 2 is pumped into the engine 4 through the outflow pipeline 24;

[0098] Step S72, the engine 4 heats the pressurized medium into high-temperature gas, and a portion of the heated gas is pumped into the propellant tank body 1 through the propellant tank pressurization pipeline 16 to achieve pressurization of the propellant tank;

[0099] Step S73, the remaining gas is pumped into the boost tank body 2 through the boost tank boost pipeline 23 to achieve the boost tank boost.

[0100] The embodiment of the pressurization method for the propellant tank of a launch vehicle can be understood by referring to the embodiment of the propellant tank with a built-in pressurization tank, which will not be described in detail here.

[0101] The above technical solution of the embodiment of the present invention is described in detail below in conjunction with specific application examples. For technical details not introduced during the implementation process, please refer to the relevant description in the previous text.

[0102] The embodiment of the present invention provides a large-diameter cryogenic pressurized tank and its supporting structure. The supporting structure includes a pressurized tank, a (cryogenic) propellant tank, a load-bearing structure (support assembly), an upper connecting plate (upper connecting member), a lower connecting plate (lower connecting member) and a filter device (a skin provided with a filter screen).

[0103] The volume of the large-diameter low-temperature boost tank required in the embodiment of the present invention can be adjusted according to the boost requirement. The tank material can be titanium alloy, aluminum alloy, etc. according to the boost pressure. The tank shape is generally spherical, ellipsoidal, etc.

[0104] The pressurized tank is connected to the load-bearing structure through the upper connecting plate. The pressurized tank and the upper connecting plate can be connected by screwing or other connection methods, and the upper connecting plate and the load-bearing structure can be connected by screwing, riveting or other connection methods. The upper connecting plate can be an integral or segmented welded or riveted structure. The load-bearing structure is generally a truss, and its cross-sectional form can be adjusted according to the force of the pressurized tank, and is generally T-shaped, cross-shaped, etc.

[0105] The load-bearing structure and the lower connecting plate are connected by screw connection, riveting or other connection methods. The lower connecting plate and the bottom of the box are connected by welding or other connection methods. The lower connecting plate can be an integrated or segmented welded or riveted structure.

[0106] The bottom of the propellant tank is generally ellipsoidal, and the materials are generally 2A14, 2219, 5A06 and other materials.

[0107] The embodiment of the present invention improves the structural efficiency and system reliability by optimizing multiple small-volume booster tanks connected in series into a large-diameter booster tank; the booster tank is placed at the rear bottom of the propellant tank and a load-bearing structure is provided, providing a solution for installing a large-diameter booster tank in the tank, solving the eccentricity problem caused by placing the booster tank on the side wall and the severe stress problem at the side wall support point caused by the traditional solution; the booster tank is used to perform an anti-collapse function, and a filter (a skin provided with a filter mesh) is installed on the support structure, thereby realizing an integrated design of the booster tank and its support, filtering and anti-collapse structure.

[0108] In the above detailed description, various features are grouped together in a single embodiment to simplify the disclosure. This method of disclosure should not be interpreted as reflecting an intention that the embodiments of the claimed subject matter require more features than are clearly stated in each claim. On the contrary, as reflected in the appended claims, the invention is in a state of having less than all the features of the disclosed individual embodiments. Therefore, the appended claims are hereby expressly incorporated into the detailed description, with each claim standing on its own as a separate preferred embodiment of the invention.

[0109] 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.

[0110] 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". In addition, any term "or" used in the specification of the claims is intended to mean "non-exclusive or".

[0111] 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 propellant tank with a built-in pressurized tank, characterized in that: include: A propellant tank body (1), a pressurized tank body (2) and a supporting device (3); The support device (3) is installed at the bottom of the propellant tank body (1), and the pressurized tank body (2) is arranged in the propellant tank body (1) and installed at the top end of the support device (3); The propellant tank body (1), the pressurized tank body (2), and the supporting device (3) are coaxial.

2. The propellant tank with built-in pressurized tank as claimed in claim 1, characterized in that: The bottom center of the propellant tank body (1) is provided with a propellant inlet and outlet port (13); The vertical axis of the support device (3) is coaxial with the center of the propellant inlet and outlet (13); the support device (3) is mounted on the inner bottom surface of the propellant tank body (1); and propellant flow windows (36) are evenly arranged on the side of the support device. The propellant flow windows (36) are connected to the propellant inlet and outlet (13) so that the propellant in the propellant tank body (1) can flow evenly through the propellant flow windows (36) to reach the propellant inlet and outlet (13).

3. The propellant tank with built-in pressurized tank as claimed in claim 2, characterized in that: The propellant flow window (36) of the support device (3) is provided with a skin (31); and a filter net (32) is provided in the middle of the skin (31).

4. The propellant tank with built-in pressurized tank as claimed in claim 1, characterized in that: The top of the pressurized storage tank body (2) is provided with a pressurization port (21); the side of the pressurized storage tank body (2) is provided with a pressurized medium outlet (22); The side wall of the propellant tank body (1) is provided with a first flange (14) and a second flange (15); The pressurization port (21) is connected to a pressurization pipeline (23) of a pressurized tank, and the pressurization pipeline (23) of the pressurized tank passes through the first flange (14) and extends to the outside of the propellant tank body (1); The pressurized medium outlet (22) is connected to an outlet pipeline (24), and the outlet pipeline (24) passes through the second flange (15) and extends to the outside of the propellant tank body (1).

5. The propellant tank with built-in pressurized tank as claimed in claim 1, characterized in that: The supporting device (3) comprises: An upper connecting piece (33) for connecting and supporting the bottom of the pressurized storage tank body (2), wherein the upper connecting piece (33) is in the shape of a circular ring; A lower connecting piece (34) for connecting to the inner bottom surface of the propellant tank body (1), wherein the lower connecting piece (34) is in the shape of a circular ring; A plurality of support components (35) used for supporting and connecting between the upper connecting member (33) and the lower connecting member (34), wherein the plurality of support components (35) are evenly distributed along the circumference of the upper connecting member (33) and the lower connecting member (34); The diameter of the upper connecting member (33) is smaller than the diameter of the lower connecting member (34), and the upper connecting member (33) and the lower connecting member (34) are coaxially arranged in parallel, and the axes of the upper connecting member (33) and the lower connecting member (34) vertically pass through the center of the propellant inlet and outlet port (13).

6. The propellant tank with built-in pressurized tank as claimed in claim 5, characterized in that: The skin (31) is arranged on the entire virtual cone side surface formed by the outer side surfaces of the plurality of support components (35), and the skin (31) is composed of a plurality of pieces, and the plurality of pieces of skin (31) are sequentially connected end to end; The left end of each skin (31) is connected to the supporting assembly (35) facing the left end, and the right end of each skin (31) is connected to the supporting assembly (35) facing the right end; at least one supporting assembly (35) is arranged between the supporting assemblies (35) facing the left and right ends of each skin (31); two rows of connecting holes are arranged in parallel along the longitudinal direction of the supporting assembly (35) on the supporting assemblies (35) facing the left and right ends of each skin (31); the left and right ends of each skin (31) are respectively connected to the supporting assemblies (35) facing them by bolts based on the connecting holes; the supporting assembly (35) facing the middle part of each skin (31) is not provided with a connecting hole and is not connected to the skin (31); the upper end of each skin (31) is bolted to the upper connecting piece (33), and the lower end of each skin (31) is bolted to the lower connecting piece (34).

7. The propellant tank with built-in pressurized tank as claimed in claim 5, characterized in that: The cross section of the support component (35) is T-shaped or I-shaped.

8. A pressurized tank with support, characterized in that: The pressurized tank with support is used in a propellant tank with a built-in pressurized tank as described in any one of claims 1 to 7, comprising: a pressurized tank body (2) and a support device (3); The bottom of the pressurized tank body (2) is connected to the upper part of the support device (3), and the projection of the center of gravity of the pressurized tank body (2) in the vertical direction coincides with the vertical axis of the support device (3).

9. A launch vehicle, characterized in that: include: An engine, and a propellant tank with a built-in pressurized tank as described in any one of claims 1 to 7 or a supported pressurized tank as described in claim 8; The bottom center of the propellant tank body (1) is provided with a propellant inlet and outlet port (13); The engine (4) is connected to the propellant inlet and outlet (13); The engine (4) is also connected to the boost tank body (2) via a boost tank boost pipeline (23) penetrating into the propellant tank body (1); The engine (4) is also connected to the boost tank body (2) via an outflow pipeline (24) penetrating into the propellant tank body (1); The engine (4) is also connected to the propellant tank body (1) via a propellant tank pressurization pipeline (16).

10. A method for pressurizing a propellant tank of a launch vehicle, wherein: The pressurized tank body (2) is arranged at the inner bottom of the propellant tank body (1), and the propellant flows into the engine (4) through the propellant inlet and outlet (13) at the bottom center of the propellant tank body (1), and is characterized in that it includes: The pressurized medium in the pressurized tank body (2) is pumped into the engine (4) through an outflow pipeline (24); The engine (4) heats the pressurized medium into high-temperature gas, and a portion of the heated gas is pumped into the propellant tank body (1) through the propellant tank pressurization pipeline (16), thereby achieving pressurization of the propellant tank; The remaining gas is pumped into the boost tank body (2) through the boost tank boost pipeline (23) to achieve the boosting of the boost tank.

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