Propellant storage tank and application thereof in space launch vehicle
By designing the main body of the propellant tank and the common bottom separation layer, the problems of large weight, high manufacturing cost and complex process of common bottom propellant tanks have been solved, realizing lightweight, low cost and high efficiency in the preparation of propellant tanks, and improving the rocket's carrying capacity and stability.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-11-21
- Publication Date
- 2026-03-27
AI Technical Summary
Existing common-bottom propellant tanks suffer from problems such as large weight, high manufacturing cost, and complex manufacturing process.
The design adopts a tank body and a common bottom partition layer. The side of the common bottom partition layer is connected to the side wall of the tank body to separate the tank body in the horizontal direction. It is connected by a common bottom upper layer, a heat insulation layer and connecting components, which simplifies the manufacturing process.
It effectively reduces the weight of propellant tanks, simplifies the manufacturing process, reduces costs, improves space utilization and operational stability, enhances the rocket's payload capacity, and reduces launch costs.
Smart Images
Figure CN121738784A_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aerospace flight equipment technology, and in particular relates to a propellant tank and its application in a space launch vehicle. Background Technology
[0002] Propellant tanks are containers in rockets used to store liquid propellants. To improve the overall performance and launch efficiency of rockets, the common-bottom design, which combines the bottoms of two or more tanks into a single shared bottom, has become one of the key technologies in modern launch vehicle design. Designing an inter-tank section between propellant tanks such as liquid oxygen / liquid hydrogen, liquid oxygen / kerosene, and liquid oxygen / methane can effectively reduce the tank volume, improve space utilization, and enhance the overall rigidity and stability of the tank.
[0003] Existing common-bottom tank designs are often quite heavy. Adding a compartment to separate the two tanks directly increases the overall weight of the rocket and reduces its launch efficiency. At the same time, adding a common-bottom structure prolongs the processing cycle and increases costs, resulting in high manufacturing costs. Third, the manufacturing process of common-bottom tanks is complex, requiring advanced technologies such as integrated molding technology. This places high demands on production equipment and technical personnel, and the long production cycle leads to low production efficiency of the tanks.
[0004] Therefore, developing a propellant tank and its application in space launch vehicles to address the technical shortcomings of existing common-bottom propellant tanks, such as large weight, high manufacturing cost, and complex manufacturing process, has become an urgent problem for those skilled in the art. Summary of the Invention
[0005] Therefore, it is necessary to address the technical shortcomings of existing common-bottom propellant tanks, such as large weight, high manufacturing cost, and complex manufacturing process, and to provide a propellant tank and its application in space launch vehicles.
[0006] This application provides a propellant tank, which includes a tank body and a common-bottom partition layer. The side of the common-bottom partition layer is connected to the side wall of the tank body to horizontally separate the tank body.
[0007] In one embodiment, the formula for calculating the thickness d of the common-bottom separator layer is:
[0008] Where K is the shape factor or stress enhancement factor, i.e. a is the major axis of the ellipsoid of the main body of the storage tank, and b is the minor axis of the ellipsoid of the main body of the storage tank; D i —Inner diameter of the ellipsoid of the main body of the storage tank (mm); ρ — Design pressure of the main body of the tank (MPa); [σ] t —Allowable stress (MPa) of the main material of the tank; —The strength coefficient of the main weld of the storage tank is (0-1).
[0009] In one embodiment, the common-bottom separating layer includes a common-bottom upper layer and a heat insulation layer, wherein the heat insulation layer is disposed on the lower surface of the common-bottom upper layer.
[0010] In one embodiment, the common-bottom separator layer further includes a common-bottom underlayer disposed on the lower surface of the insulation layer.
[0011] In one embodiment, the insulation layer comprises any one or more of polyurethane foam, polyisocyanate foam, polyvinyl chloride foam, triaxial reinforced foam, and cork.
[0012] In one embodiment, the common bottom upper layer comprises a stainless steel plate, and the common bottom lower layer comprises a stainless steel plate.
[0013] In one embodiment, the thickness of the common bottom upper layer is greater than that of the common bottom lower layer.
[0014] In one embodiment, the propellant tank further includes a connecting assembly connected to the side wall of the tank body and the upper surface of the common-bottom partition layer, respectively.
[0015] In one embodiment, the connection assembly includes a fork-shaped ring and / or a π-shaped connector.
[0016] This application also provides an application of any of the above-described propellant tanks in a space launch vehicle.
[0017] In summary, this application provides a propellant tank comprising: a tank body and a common-bottom partition layer, wherein the side of the common-bottom partition layer is connected to the side wall of the tank body for horizontally separating the tank body. This application also provides an application of the above-mentioned propellant tank in a space launch vehicle. In the technical solution provided by this application, the common-bottom partition layer replaces the inter-tank section structure, effectively reducing the overall weight of the propellant tank; during fabrication, only the common-bottom partition layer needs to be connected to the side wall of the tank body, making the fabrication process simple and inexpensive; it solves the technical defects of existing common-bottom propellant tanks, such as large weight, high fabrication cost, and complex fabrication process. Attached Figure Description
[0018] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.
[0019] Figure 1 A schematic diagram of the structure of a propellant tank provided in the embodiments of this application; Figure 2 This application provides a schematic cross-sectional view of a common-bottom partition layer in a propellant tank. The tank consists of a main body 1, a common bottom partition layer 2, a common bottom upper layer 21, a heat insulation layer 22, a common bottom lower layer 23, and a connecting component 3. Detailed Implementation
[0020] This application provides a propellant tank and its application in a space launch vehicle, which addresses the technical shortcomings of existing common-bottom propellant tanks, such as large weight, high manufacturing cost, and complex manufacturing process.
[0021] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.
[0022] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.
[0023] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.
[0024] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.
[0025] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.
[0026] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.
[0027] Please see Figure 1 This application provides a propellant tank, including: a tank body 1 and a common bottom partition layer 2, the side of the common bottom partition layer 2 being connected to the side wall of the tank body 1, for horizontally partitioning the tank body 1.
[0028] In the technical solution provided in this application embodiment, the propellant tank uses a common bottom partition layer 2 to separate the tank body 1, thereby achieving the separation of the propellant tank. It can be used for the storage of cryogenic propellants such as liquid oxygen / liquid hydrogen, liquid oxygen / kerosene, and liquid oxygen / methane.
[0029] Compared with the existing technology that involves designing an inter-tank section in the middle of the propellant tank for separation, the common-bottom partition layer 2 structure of this application has the following advantages: First, the weight of the common-bottom partition layer 2 is significantly reduced. In existing common-bottom tank structures, the two tanks storing different fuels are separated by adding a compartment. Compared with the prior art, the technical solution provided in this application does not require an additional compartment for separation, simplifying the structure and effectively reducing the weight of the common-bottom partition layer 2. At the same time, since the weight of the common-bottom tank structure provided in this application is effectively reduced, the pressure difference between the upper and lower halves of the propellant tank after the common-bottom partition layer 2 is separated can offset their respective internal pressure loads. At this time, the maximum pressure value that the bottom of the tank body 1 needs to withstand is reduced, and correspondingly, the bottom thickness of the tank body 1 can be reduced, and the mass of the tank body 1 is also reduced accordingly.
[0030] When applied to the propulsion system of a rocket, the rocket's payload capacity can be significantly improved. In space launches, every kilogram reduction in structural weight can significantly increase the carrying capacity and reduce launch costs. Calculations show that the propellant tank provided in this application can significantly reduce the overall launch cost when applied to rocket launches.
[0031] Secondly, the design of the common bottom partition layer 2 can effectively improve space utilization. The common bottom partition layer 2 is set inside the tank body 1, which can make full use of the space inside the tank, reduce the length of the propellant tank, thereby further shortening the length of the rocket body and reducing the weight of the rocket body, making the overall design of the rocket body more compact.
[0032] Third, the operational stability and reliability of the propellant tank have been effectively improved. Since the propellant tank of this application eliminates the inter-tank section design, it saves the structural mass of the inter-tank section. At the same time, the shortening of the rocket length has optimized the slenderness ratio and reduced the "elasticity", making the rocket flight more stable.
[0033] Fourth, structural simplification can further reduce the number of parts and dead corners inside the main body of the propellant tank, reduce the amount of unusable propellant, further help reduce the weight of the rocket, and at the same time enable it to carry more payloads into space.
[0034] Fifth, the common bottom partition layer 2 is located inside the main body of the propellant tank 1, and will not form a protrusion on the outside of the propellant tank, thus optimizing the aerodynamic shape of the propellant tank and reducing flight drag.
[0035] To further optimize the technical solution, while effectively ensuring that the common-bottom separator 2 can separate propellants of different compositions in the propellant tank, and taking into account the design requirement of weight reduction through the common-bottom separator 2, the calculation formula for the thickness d of the common-bottom separator 2 in the technical solution provided in this application embodiment is as follows:
[0036] Where K is the shape factor or stress enhancement factor, i.e. a is the major axis of the ellipsoid of the main body of the storage tank, and b is the minor axis of the ellipsoid of the main body of the storage tank; D i —Inner diameter of the ellipsoid of the main body of the storage tank (mm); ρ — Design pressure of the main body of the tank (MPa); [σ] t —Allowable stress (MPa) of the main material of the tank; —The strength coefficient of the main weld of the storage tank is (0-1).
[0037] Please refer to this section for further information. Figure 2 In a propellant tank provided in this application embodiment, to prevent the high-temperature environment of the upper propellant from affecting the lower propellant and to avoid combustion of the lower propellant in the tank, the common-bottom partition layer 2 in this application embodiment includes: a common-bottom upper layer 21 and a heat insulation layer 22, with the heat insulation layer 22 disposed on the lower surface of the common-bottom upper layer 21. The heat insulation layer 22 effectively insulates the upper propellant from its high temperature, ensuring that the lower layer is at a safe operating temperature.
[0038] In practical applications, the heat insulation layer 22 and the common bottom upper layer 21 are connected by adhesive.
[0039] To further optimize the technical solution and prevent the lower propellant layer from corroding and damaging the heat insulation layer 22, effectively extend the service life of the propellant tank, and better protect the heat insulation layer 22, the common bottom partition layer 2 in this application embodiment further includes a common bottom lower layer 23, which is disposed on the lower surface of the heat insulation layer 22.
[0040] In the technical solution provided in this application embodiment, while ensuring good thermal insulation effect of the insulation layer 22, the design requirements of low propellant tank design cost and weight reduction are also taken into account. The insulation layer 22 includes any one or more of polyurethane foam, polyisocyanate foam, polyvinyl chloride foam, triaxial reinforced foam, and cork. Among them, polyurethane foam has the advantages of low material density and high cost performance, and can be widely used. In practical applications, the coating amount of the insulation layer 22 is determined according to the thermal conductivity and compressive strength of the selected insulation layer material.
[0041] In a propellant tank provided in this application embodiment, the common bottom upper layer 21 includes a stainless steel plate, which in practical applications may include an S30408 stainless steel plate or an S30110 stainless steel plate; the common bottom lower layer 23 also includes a stainless steel plate, which in practical applications may include an S30408 stainless steel plate or an S30110 stainless steel plate. This design ensures the structural stability of the common bottom upper layer 21 and the common bottom lower layer 23, and effectively extends their durability over long-term use.
[0042] In practical applications, in addition to stainless steel plates, materials such as 2219 aluminum-lithium alloy, 2195 aluminum alloy, and 5A06 aluminum alloy can also be selected for the common bottom upper layer 21 or common bottom lower layer 23.
[0043] To effectively ensure sufficient load-bearing capacity of the common bottom separating layer 2, the main purpose of the upper common bottom layer 21 is to provide stable support for the upper propellant. The main purpose of the lower common bottom layer 23 is to isolate the lower kerosene from the insulation layer, while also bearing a certain amount of back pressure. In the technical solution provided in this application embodiment, the thickness of the upper common bottom layer 21 is greater than that of the lower common bottom layer 23.
[0044] In the actual preparation process, the bottom separation layer 2 and the side wall of the tank body 1 can be connected by welding to prevent the connection. Specifically, the mature laser welding and argon arc welding processes in the existing technology can be used. The process is stable, reliable and low cost.
[0045] To further enhance the connection stability between the common-bottom partition layer 2 and the tank body 1, the propellant tank provided in this embodiment further includes a connecting assembly 3, which is connected to both the side wall of the tank body 1 and the upper surface of the common-bottom partition layer 2. By connecting and fixing the connection surfaces of the common-bottom partition layer 2 and the tank body 1 through the connecting assembly 3, the connection stability between the two is improved.
[0046] To further optimize the technical solution, in the technical solution provided in this application embodiment, the connecting component 3 is a fork-shaped ring and / or a π-shaped connector. The main purpose of the connecting component 3 is to integrate and weld the upper and lower cylinder sections with the ellipsoid of the propellant tank together. The fork-shaped ring and / or the π-shaped connector can effectively connect and fix the two after welding.
[0047] This application also provides an application of a propellant tank in a space launch vehicle. When applied to a space launch vehicle (such as a rocket), it is only necessary to make a through-hole in the upper and lower layers of the propellant tank and use a pipe to export the propellant from the tank. The application method is simple and easy to operate.
[0048] In summary, this application provides a propellant tank comprising: a tank body and a common-bottom partition layer, wherein the side of the common-bottom partition layer is connected to the side wall of the tank body for horizontally separating the tank body. This application also provides an application of the above-mentioned propellant tank in a space launch vehicle. In the technical solution provided by this application, the common-bottom partition layer replaces the inter-tank section structure, effectively reducing the overall weight of the propellant tank; during fabrication, only the common-bottom partition layer needs to be connected to the side wall of the tank body, making the fabrication process simple and inexpensive; it solves the technical defects of existing common-bottom propellant tanks, such as large weight, high fabrication cost, and complex fabrication process.
[0049] The technical features of the embodiments described above can be combined arbitrarily. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as the combination of these technical features does not contradict each other, it should be considered within the scope of this specification. Furthermore, other implementation methods can be derived from the above embodiments, allowing for structural and logical substitutions and changes without departing from the scope of this disclosure.
[0050] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.
Claims
1. A propellant storage tank, characterized in that, The propellant tank includes a tank body and a common-bottom partition layer, wherein the side of the common-bottom partition layer is connected to the side wall of the tank body and is used to separate the tank body in the horizontal direction.
2. The propellant tank according to claim 1, characterized in that, The formula for calculating the thickness d of the common-bottom separator layer is: Where K is the shape factor or stress enhancement factor, i.e. a is the major axis of the ellipsoid of the main body of the storage tank, and b is the minor axis of the ellipsoid of the main body of the storage tank; D i —The inner diameter of the ellipsoid of the main body of the storage tank; ρ—Design pressure of the main body of the storage tank; [σ] t —The allowable stress of the main material of the storage tank; —The strength coefficient of the main weld of the storage tank.
3. The propellant tank according to claim 1 or 2, characterized in that, The common-bottom separating layer includes a common-bottom upper layer and a heat insulation layer, wherein the heat insulation layer is disposed on the lower surface of the common-bottom upper layer.
4. The propellant tank according to claim 3, characterized in that, The common bottom separating layer also includes a common bottom layer, which is disposed on the lower surface of the heat insulation layer.
5. The propellant tank according to claim 3 or 4, characterized in that, The insulation layer includes any one or more of polyurethane foam, polyisocyanate foam, polyvinyl chloride foam, triaxial reinforced foam, and cork.
6. The propellant tank according to claim 4, characterized in that, The common bottom upper layer includes a stainless steel plate, and the common bottom lower layer includes a stainless steel plate.
7. The propellant tank according to claim 4 or 6, characterized in that, The thickness of the upper common-bottom layer is greater than that of the lower common-bottom layer.
8. The propellant tank according to any one of claims 1 to 7, characterized in that, The propellant tank further includes a connecting assembly, which is connected to the side wall of the tank body and the upper surface of the common-bottom partition layer, respectively.
9. The propellant tank according to claim 8, characterized in that, The connection assembly includes: a fork-shaped ring and / or a π-shaped connector.
10. The application of a propellant tank according to any one of claims 1 to 9 in a space launch vehicle.