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

Abstract

An embodiment of the present invention provides a propellant tank with a built-in pressurized tank, a pressurized tank, a rocket, and a pressurization method, which relates to the technical field of rocket pressurization. The propellant tank with a built-in pressurized tank includes: a propellant tank body, a pressurized tank body, and a support device; the support device is installed at the bottom inside the propellant tank body, the pressurized tank body is arranged inside the propellant tank body and installed at the top of the support device; the propellant tank body, the pressurized tank body, and the support device are coaxial. Using a single large-capacity pressurized tank to replace multiple series-connected small-capacity tanks, thereby solving the problem of structural instability caused by complex structures in the traditional technology, and the pressurized tank provided at the propellant inlet and outlet can also play a role in preventing collapse when the propellant flows towards the engine.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket pressurization, and particularly to a propellant tank with a built-in pressurized tank, a pressurized tank, a rocket, and a pressurization method. Background Art

[0002] For launch vehicles adopting the cold helium or liquid nitrogen heating pressurization scheme, it is necessary to heat the cryogenic gas in the engine and then enter the propellant tank for pressurization. The container for storing the pressurizing medium (such as cold helium, liquid nitrogen, etc.) is the pressurized tank. In order to ensure the pressurization capacity, most of the current models place the pressurized tank in the cryogenic propellant tank to maintain the low temperature of the pressurizing medium. Even so, the volume of the pressurized tank required for pressurization is still relatively large. The traditional structure mostly adopts the series connection method of several small-volume pressurized tanks to meet the pressurization requirements. The volume of each small pressurized tank generally does not exceed 70L, and several small-volume pressurized tanks are installed on the side wall of the propellant tank.

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

[0004] How to provide a single large-capacity pressurized tank in the propellant tank to solve the problems of low structural efficiency and reliability existing in the series connection structure of several small-volume pressurized tanks. 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, aiming to provide a single large-capacity pressurized tank in the propellant tank to solve the problems of low structural efficiency and reliability existing in the series connection structure of several small-volume pressurized tanks.

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

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

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

[0009] Further, a propellant inlet / outlet port is provided at the center of the bottom of the propellant tank body;

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

[0011] Further, a skin is provided on the propellant flow window of the support device; a filter screen is provided in the middle of the skin.

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

[0013] A first flange and a second flange are provided on the side wall of the propellant storage tank body;

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

[0015] The pressurization medium outflow port is connected with an outflow pipeline, and the outflow pipeline extends outside the propellant storage tank body through the second flange.

[0016] Further, the support device includes:

[0017] An upper connecting member for connecting the bottom of the support pressurized storage tank body, and the upper connecting member is annular;

[0018] A lower connecting member for connecting the inner bottom surface of the propellant storage tank body, and the lower connecting member is annular;

[0019] A plurality of support components for supporting and connecting between the upper connecting member and the lower connecting member, and the plurality of support components are evenly distributed along the circumferences of the upper connecting member and the lower connecting member;

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

[0021] Further, the skin is provided on the entire virtual conical side surface formed by the outer side surfaces of the plurality of support components, the skin is in multiple pieces, and the multiple pieces of skin are connected end to end in sequence;

[0022] The left end of each piece of skin is connected to the support component directly opposite to the left end, and the right end of each piece of skin is connected to the support component directly opposite to the right end; at least one support component is provided between the left end of each piece of skin and the support component directly opposite to the right end; on the support components directly opposite to the left end and the right end of each piece of skin, two rows of connection holes are arranged in parallel along the longitudinal direction of the support component; between the left end and the right end of each piece of skin and the support components directly opposite thereto, they are bolted based on the connection holes; no connection holes are provided on the support components directly opposite to the middle of each piece of skin, and there is no connection with the skin; the upper end of each piece of skin is bolted to the upper connecting member, and the lower end of each piece of skin is bolted to the lower connecting member.

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

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

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

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

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

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

[0029] The engine is also connected to the pressurized storage tank body through a pressurized storage tank pressurization pipeline penetrating into the propellant storage tank body;

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

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

[0032] In a fourth aspect, an embodiment of the present invention provides a pressurization method for a propellant storage tank of a launch vehicle. The pressurized storage tank body is arranged at the inner bottom of the propellant storage tank body, and the propellant flows into the engine through the propellant inlet / outlet port at the center of the bottom of the propellant storage tank body. The method includes:

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

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

[0035] The remaining part of the gas is pumped into the pressurized storage tank body through the pressurized storage tank pressurization pipeline to realize the pressurization of the pressurized storage tank.

[0036] The above technical solutions have the following beneficial effects:

[0037] Through the support device, a large-diameter or large-capacity pressurized tank can be installed at the bottom of the propellant tank. After installation, the center of gravity of the pressurized tank can coincide with the projection of the center of gravity of the propellant tank in the vertical direction, so that multiple small-capacity pressurized tanks arranged in series can be replaced, avoiding the structural instability problem caused by arranging multiple small-capacity pressurized tanks in series on the side wall of the propellant tank in the traditional technology. A single large-capacity pressurized tank can be used to replace multiple small-capacity tanks arranged in series, thereby solving the problem of low structural efficiency caused by complex structure in the traditional technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0039] Figure 1 is a schematic structural diagram of a propellant tank with an internal pressurized tank according to one embodiment of the present invention;

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

[0041] Figure 3 is a three-dimensional structural diagram of a hemispherical lower box body with a pressurized tank installed according to one embodiment of the present invention;

[0042] Figure 4 is a sectional view of a hemispherical lower box body with a pressurized tank installed according to one embodiment of the present invention;

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

[0044] Figure 6 is one embodiment of the present invention Figure 1 partial enlarged view A on;

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

[0046] The reference numerals are shown as:

[0047] 1. Propellant tank body; 11. Columnar upper tank body; 12. Hemispherical lower tank body; 13. Propellant inlet / outlet; 2. Pressurized tank body; 3. Support device; 31. Skin; 32. Filter screen; 36. Propellant flow window; 21. Pressurization port; 22. Pressurizing 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 implementation manners

[0048] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0049] The inventor found that the series connection method of multiple small-capacity pressurized tanks will increase the number of pressurized tanks, with low structural efficiency and reduced system reliability. To improve structural efficiency and system reliability, it is necessary to optimize multiple series-connected small-volume pressurized tanks into a large-diameter pressurized tank. Currently, there is no case to refer to for the installation of a large-diameter pressurized tank inside the tank. If the method of installing small-diameter tanks on the side wall is adopted, problems such as rocket eccentricity and severe stress at the support position of the side wall of the propellant tank will occur. When the propellant liquid level in the rocket approaches the bottom outlet, the liquid will generate friction with the tank wall and be affected by external disturbances, and the velocity at the center of the outlet will be higher than the flow velocity at the tank wall. This phenomenon is called slumping. To solve the problem of fluid slumping, traditional devices generally set an inverted cone anti-whirl device and a secondary turbulence cross cover at the outlet, but the traditional devices only solve the problem of liquid collapse and do not achieve the integrated design of a multi-functional structure. To ensure the quality of the propellant flowing into the engine, a filtering device needs to be set at the pipeline or the outlet of the propellant tank.

[0050] On the one hand, as Figure 1 、 Figure 2 、 Figure 3 and Figure 4 shown, an embodiment of the present invention provides a propellant tank with an internal pressurized tank, including: a propellant tank body 1, a pressurized tank body 2, and a support device 3;

[0051] The support device 3 is installed at the bottom inside the propellant tank body 1, and the pressurized tank body 2 is arranged inside 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 support device 3 are coaxial.

[0053] In some embodiments, the pressurized storage tank body 2 is installed at the inner bottom of the propellant storage tank body 1. Preferably, the pressurized storage tank body 2 has a vertically axisymmetric structure, such as a spherical shape, a cylindrical shape, an ellipsoidal shape, etc. Preferably, the propellant storage tank body 1 is a cryogenic propellant storage tank body. The pressurized storage tank body 2 is used to store cryogenic nitrogen liquid, and the cryogenic propellant is stored in the propellant storage tank body 1. The cryogenic environment of the (cryogenic) propellant storage tank body 1 can be utilized to maintain the low temperature of the pressurized storage tank, thereby providing a stable low-temperature environment for the cryogenic nitrogen liquid. In the traditional method, multiple gas cylinders are hung on the inner side surface of the propellant storage tank body, and helium gas is stored in the gas cylinders. Compared with the same volume of gas and cryogenic nitrogen liquid, the weight of the cryogenic nitrogen liquid is significantly heavier. The cryogenic nitrogen liquid is not suitable for being stored by hanging multiple gas cylinders in series on the inner side surface of the propellant storage tank body in the traditional way. In the embodiments of the present invention, a single large-capacity pressurized storage tank body 2 is used to replace the way of connecting multiple small-capacity gas cylinders in series in the traditional method. The vertical axes of the support device 3, the pressurized storage tank body 2, and the propellant storage tank body 1 coincide. Preferably, the support device 3, the pressurized storage tank body 2, and the propellant storage tank body 1 all have a vertically axisymmetric structure, so as to ensure stability. The support device 3 can install the (cryogenic) pressurized storage tank body 2 at a position that coincides with the center of gravity projection of the propellant storage tank body 1, so that the center of gravity of the cryogenic pressurized storage tank body 2 and the center of gravity projection of the propellant storage tank body 1 are symmetrically coincident. Thus, regardless of whether the diameter or capacity of the pressurized storage tank is large or small, the problem of eccentricity of the propellant storage tank body or the rocket caused by the installation of the cryogenic pressurized storage tank body will not occur. The volume of the large-diameter cryogenic pressurized storage tank can be adjusted according to the pressurization requirements, and the material of the cryogenic pressurized storage tank can be titanium alloy or aluminum alloy, etc. according to the magnitude of the pressurization pressure. Preferably, the aluminum alloy materials of the pressurized storage tank body and the propellant storage tank body include but are not limited to any one of the following models: 2A14, 2219, and 5A06.

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

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

[0056] Further, as Figure 1 shown, a propellant inlet / outlet port 13 is provided at the center of the bottom of the propellant storage tank body 1;

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

[0058] In the traditional method, when the rocket propellant liquid level approaches the propellant inlet / outlet port 13, the liquid will generate friction with the wall of the propellant tank body and be affected by external disturbances. The velocity at the center of the flow port will be higher than the flow velocity at the tank wall, resulting in a collapse phenomenon. In response to the collapse phenomenon in the traditional method, the vertical axes of the support device 3, the pressurized tank body 2, and the propellant tank body 1 in the embodiment of the present invention are coaxial. Usually, the propellant inlet / outlet port 13 is located at the center of the bottom of the propellant tank body 1, and the pressurized tank body 2 is located directly above the propellant inlet / outlet port 13. The side surface of the support device 3 is evenly provided with propellant flow windows 36, so that the pressurized tank body 2 can play a role in preventing collapse.

[0059] The embodiment of the present invention has the following technical effects: By coaxially arranging the support device 3 and the pressurized tank body 2 at the bottom of the propellant tank body 1, when the rocket propellant liquid level approaches the propellant inlet / outlet port 13, it can play a role in preventing collapse.

[0060] Preferably, as Figure 1 、 Figure 3 and Figure 4 shown, the propellant tank body 1 includes a columnar upper tank body 11 and a hemispherical lower tank body 12; the lower end of the columnar upper tank body 11 is hermetically butted with the upper end of the hemispherical lower tank body 12 to form a complete cavity;

[0061] The center of the bottom of the hemispherical lower tank body 12 is provided with a propellant inlet / outlet port 13;

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

[0064] In some embodiments, the pressurized storage tank body 2 is installed at the inner bottom of the propellant storage tank body 1. The pressurized storage tank body 2 has a vertically axisymmetric structure, such as a spherical shape, a cylindrical shape, an ellipsoidal shape, etc. The pressurized storage tank body 2 is used to store cryogenic nitrogen liquid, and the propellant storage tank body 1 stores cryogenic propellant. The cryogenic environment of the (cryogenic) propellant storage tank body 1 can be utilized to maintain the low temperature of the pressurized storage tank, so as to provide a stable low-temperature environment for the cryogenic nitrogen liquid. In the traditional method, multiple gas cylinders are hung on the inner side surface of the propellant storage tank body, and helium gas is stored in the gas cylinders. Compared with the same volume of gas and cryogenic nitrogen liquid, the weight of the cryogenic nitrogen liquid is significantly heavier, and the cryogenic nitrogen liquid is not suitable for being stored by hanging multiple gas cylinders in series on the inner side surface of the propellant storage tank body in the traditional way. The embodiment of the present invention uses a single large-capacity pressurized storage tank body 2 to replace the traditional method of connecting multiple small-capacity gas cylinders in series. The vertical axes of the support device 3, the pressurized storage tank body 2, and the propellant storage tank body 1 coincide, and all three have a vertically axisymmetric structure, so as to ensure stability. In the traditional method, when the rocket propellant liquid level approaches the propellant inlet / outlet 13, the liquid will generate friction with the tank wall of the propellant tank body and be disturbed by the outside world. The velocity at the center of the flow port will be higher than the flow velocity at the tank wall, resulting in a collapse phenomenon. In response to the collapse phenomenon, the vertical axes of the support device 3 and the pressurized storage tank body 2 in the embodiment of the present invention are coaxial with the center of the propellant inlet / outlet 13, and the pressurized storage tank body 2 is located directly above the propellant inlet / outlet 13. The side surface of the support device 3 is evenly provided with propellant flow windows 36, so that the pressurized storage tank body 2 can play a role in preventing collapse. The support device 3 can install the (cryogenic) pressurized storage tank body 2 at a position that coincides with the center of gravity projection of the propellant storage tank body 1, so that the center of gravity projections of the cryogenic pressurized storage tank body 2 and the propellant storage tank body 1 are symmetrically coincident. Therefore, regardless of the diameter or capacity of the pressurized storage tank, the installation of the cryogenic pressurized storage tank body will not cause eccentricity problems in the propellant storage tank body or the rocket. The volume of the large-diameter cryogenic pressurized storage tank can be adjusted according to the pressurization requirements, and the material of the cryogenic pressurized storage tank can be titanium alloy, aluminum alloy, etc. according to the pressurization pressure. Preferably, the aluminum alloy materials of the pressurized storage tank body and the propellant storage tank body include, but are not limited to, any one of the following models: 2A14, 2219, and 5A06

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

[0066] Through the support device 3, a large-diameter or large-capacity pressurized tank can be installed at the bottom of the propellant tank. After installation, the center of gravity of the pressurized tank can coincide with the projection of the center of gravity of the (cryogenic) propellant tank in the vertical direction, thus replacing multiple small-capacity pressurized tanks arranged in series, avoiding the structural instability problem caused by arranging multiple small-capacity pressurized tanks in series on the side wall of the propellant tank in the traditional technology. A single large-capacity pressurized tank can be used to replace multiple small-capacity tanks arranged in series, thereby solving the problem of low structural efficiency caused by the complex structure in the traditional technology. Moreover, the pressurized tank provided with the propellant inlet and outlet can also play a role in preventing collapse when the propellant flows towards the engine.

[0067] Further, as Figure 2 , Figure 3 and Figure 5 shown, a skin 31 is provided at the propellant flow window 36 of the support device 3; a filter screen 32 is provided in the middle of the skin 31.

[0068] In some embodiments, covering the propellant flow window 36 with the skin 31 with the filter screen 32 can effectively filter impurities in the propellant and prevent impurities from entering the engine, ensuring the working safety of the engine. A filter screen is provided on the support device 3, so that the support device 3 has both a support and a filtering function at the same time. After the support device 3 and the pressurized tank are combined and installed at the center of the bottom of the propellant tank, it can also have the function of preventing fluid collapse.

[0069] Further, as Figure 1 shown, a pressurization port 21 is provided at the top of the pressurized tank body 2; a pressurizing medium outlet 22 is provided on the side of the pressurized tank body 2;

[0070] A first flange 14 and a second flange 15 are provided on the side wall of the propellant tank body 1;

[0071] The pressurization port 21 is connected with a pressurized tank pressurization pipeline 23, and the pressurized tank pressurization pipeline 23 extends outside the propellant tank body 1 through the first flange 14;

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

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

[0074] Further, as Figure 2 shown, the support device 3 includes:

[0075] An upper connecting member 33 for connecting and supporting the bottom of the pressurized tank body 2, and the upper connecting member 33 is circular;

[0076] A lower connecting member 34 for connecting the inner bottom surface of the propellant tank body 1, and the lower connecting member 34 is circular;

[0077] A plurality of support components 35 for supporting and connecting between the upper connecting member 33 and the lower connecting member 34, and the plurality of support components 35 are evenly distributed along the circumferences of the upper connecting member 33 and the lower connecting member 34;

[0078] 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 arranged coaxially and parallelly, and the axes of the upper connecting member 33 and the lower connecting member 34 both vertically pass through the center of the propellant inlet and outlet 13;

[0079] Wherein, the form formed by the upper connecting member 33 and the lower connecting member 34 between adjacent support components 35 and adjacent support components 35 serves as the propellant flow window 36.

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

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

[0082] Furthermore, as Figure 2 and Figure 3 shown, the skin 31 is arranged on the entire virtual conical side surface formed by the outer side surfaces of a plurality of support assemblies 35. The skin 31 is in multiple pieces, and the multiple pieces of skin 31 are connected end to end in sequence;

[0083] The left end of each piece of skin 31 is connected to the support assembly 35 directly opposite to the left end, and the right end of each piece of skin 31 is connected to the support assembly 35 directly opposite to the right end; at least one support assembly 35 is arranged between the left end of each piece of skin 31 and the support assembly 35 directly opposite to the right end; on the support assembly 35 directly opposite to the left end and the right end of each piece of skin 31, two rows of connection holes are arranged in parallel along the longitudinal direction of the support assembly 35; the left end and the right end of each piece of skin 31 are respectively connected to the directly opposite support assembly 35 through bolts based on the connection holes; no connection holes are arranged on the support assembly 35 directly opposite to the middle of each piece of skin 31, and there is no connection with the skin 31; the upper end of each piece of skin 31 is bolted to the upper connecting member 33, and the lower end of each piece of skin 31 is bolted to the lower connecting member 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] Further, the cross-section of the support assembly 35 is T-shaped or multi-shaped. The support assembly 35 is generally a stringer, and its cross-sectional form can be adjusted according to the force magnitude of the booster tank, which is generally T-shaped, multi-shaped, etc. T-shaped or multi-shaped stringer structures can enhance the support ability of the support assembly.

[0086] Second, as Figure 3 As shown, an embodiment of the present invention provides a supported booster storage tank, which is used in a propellant storage tank of a built-in booster storage tank, such as the previous one, including: a booster storage tank box 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 a booster for a propellant storage tank of a carrier rocket, wherein the booster storage tank box 2 is arranged at the inner bottom of the propellant storage tank box 1, and the propellant flows into the engine 4 through the propellant inlet and outlet port 13 at the bottom center of the propellant storage tank box 1, including:

[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] Embodiments of the present invention provide a large diameter low-temperature booster storage tank and its supporting structure. The support structure includes a pressurized storage box, a (low-temperature) propellant storage box, a load-bearing structure (supporting assembly), an upper connecting plate (upper connecting member), a lower connecting plate (lower connecting member) and a filter device (skin provided with a filter mesh).

[0103] The volume of the large diameter low-temperature supercharged storage tank required for embodiments of the present invention can be adjusted according to the supercharge requirements, and the storage tank material can be made of titanium alloy, aluminum alloy, etc. according to the supercharge pressure. The shape of the storage tank 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 connection form of the load bearing structure and the lower connecting plate is screw connection, riveting or other connection methods. The lower connecting plate and the bottom of the box are welded or other connection forms. 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] In the embodiment of the present invention, by optimizing multiple series-connected small-volume pressurized tanks into a large-diameter pressurized tank, the structural efficiency and system reliability are improved; the pressurized tank is placed at the rear bottom of the propellant tank and a load-bearing structure is provided, providing a scheme for installing a large-diameter pressurized tank inside the tank, solving the eccentricity problem caused by placing it on the side wall in the traditional scheme and the severe stress problem at the side wall support points; using the pressurized tank as an anti-collapse function, and by installing a filter (a skin provided with a filter mesh) on the support structure, an integrated design of the pressurized tank and its support, filtering, and anti-collapse structures is realized.

[0108] In the above detailed description, various features are combined in a single embodiment to simplify the present disclosure. This method of disclosure should not be construed as reflecting an intention that the embodiments of the claimed subject matter require more features than those clearly stated in each claim. On the contrary, as reflected in the appended claims, the present invention lies in a state with fewer features than all the features of the disclosed single embodiment. Therefore, the appended claims are hereby clearly incorporated into the detailed description, where each claim stands alone as a separate preferred embodiment of the present invention.

[0109] In order to enable any person skilled in the art to implement or use the present invention, the above-described disclosed embodiments are described. For those skilled in the art; various modification methods of these embodiments are obvious, and the general principles defined herein can also be applied to other embodiments without departing from the spirit and protection 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 describing the above embodiments, but those of ordinary skill in the art should recognize that each embodiment can be further combined and arranged. Therefore, the embodiments described herein are intended to cover all such changes, modifications, and variations that fall within the protection scope of the appended claims. In addition, with respect to the term "comprising" used in the specification or claims, the coverage of this word is similar to the term "including". In addition, any term "or" used in the claims or the specification is to mean "non-exclusive or".

[0111] The specific embodiments described above further elaborate on the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above description is only the specific embodiments of the present invention and is not used to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope 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); the pressurized tank body (2) is arranged inside 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 support device (3) are coaxial; A propellant inlet and outlet port (13) is provided at the bottom center of the propellant tank body (1); 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). 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).

2. The propellant tank with built-in pressurized tank as claimed in claim 1, characterized in that: The propellant flow window (36) of the support device (3) is provided with a skin (31); and a filter screen (32) is provided in the middle of the skin (31).

3. 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 tank pressurization pipeline (23), and the pressurization tank pressurization pipeline (23) 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).

4. 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) used 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).

5. The propellant tank with built-in pressurized tank as claimed in claim 4, 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), 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 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); two rows of connection holes are arranged in parallel along the longitudinal direction of the support assembly (35) on the support 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 connection holes; the support assembly (35) facing the middle of each skin (31) is not provided with a connection 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).

6. The propellant tank with built-in pressurized tank as claimed in claim 4, characterized in that: The cross section of the support component (35) is T-shaped or I-shaped.

7. 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 claimed in any one of claims 1 to 6, 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).

8. A launch vehicle, characterized in that: include: An engine, and a propellant tank with a built-in pressurized tank as claimed in any one of claims 1 to 6 or a pressurized tank with support as claimed in claim 7; A propellant inlet and outlet port (13) is provided at the bottom center of the propellant tank body (1); 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).

9. A method for pressurizing a propellant tank of a launch vehicle, wherein the propellant tank is a propellant tank with a built-in pressurized tank as claimed in any one of claims 1 to 6, 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), thereby achieving the boosting of the boost tank.

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