Low temperature propellant rocket tank with single layer common base

Abstract

The utility model relates to a low temperature propellant rocket storage tank with single-layer common bottom, including front box, rear box, delivery pipe, front short shell and rear short shell, the front box includes front box cylinder section and respectively sets up the front bottom and common bottom at the both ends of front box cylinder section, the rear box includes rear box cylinder section and sets up the rear bottom at one end of rear box cylinder section, and the end of rear box cylinder section away from rear bottom is welded and is connected on common bottom, is set up with rear box propellant export on rear bottom, the front short shell is welded and is connected on the front bottom, and the rear short shell is welded and is connected on the rear bottom, the delivery pipe is located inside the rear box, one end of delivery pipe is welded and is connected on common bottom and is linked with the inside of front box, and the other end of delivery pipe is welded and is connected on rear bottom and is linked with the outside of rear box, common bottom is single-layer structure, and the heat insulation structure is set up on common bottom, the utility model can reduce the overall structure weight of the carrier rocket body, improves the carrying capacity and the stability of flight of carrier rocket.

Description

Technical Field

[0001] This utility model relates to the field of rocket propellant tank technology, and in particular to a cryogenic propellant rocket propellant tank with a single-layer common bottom. Background Technology

[0002] Traditional launch vehicle stages consist of separate oxidizer tanks, propellant tanks, and an inter-tank section between them. However, this structure results in a significant increase in axial length and structural weight, which can negatively impact the rocket's stability and payload capacity. Therefore, the oxidizer and propellant tanks can share a common bottom to form a common-bottom tank system. This eliminates the need for a forward short shell, a rear short shell, and an inter-tank section, reducing the rocket's axial length and structural weight, and improving its stability and payload capacity.

[0003] However, existing common-bottom propellant tanks for rockets have at least the following drawbacks: 1. Existing rocket common-bottom tanks have a double-layer structure, resulting in a large overall structural weight, which significantly reduces the launch vehicle's carrying capacity.

[0004] 2. The existing rocket common-base tank has an external delivery pipe structure, which will affect the aerodynamic shape of the rocket body and is not conducive to the stability of the launch vehicle during flight.

[0005] 3. Due to the large diameter of the delivery pipe, large pipe end caps and long pipe supports are required on the external delivery pipe to support it. At the same time, a long pipe cover is also required on the external delivery pipe to improve its aerodynamic shape. All of these features will increase the overall structural weight of the launch vehicle body and significantly reduce the launch vehicle's carrying capacity.

[0006] Therefore, how to reduce the overall structural weight of the launch vehicle body, thereby improving its carrying capacity and flight stability, has become an urgent problem to be solved. Utility Model Content

[0007] The purpose of this invention is to provide a cryogenic propellant rocket tank with a single-layer common bottom to solve the problems existing in the prior art.

[0008] To achieve the above objectives, this utility model provides the following solution: This utility model provides a cryogenic propellant rocket tank with a single-layer common bottom, comprising a front tank, a rear tank, a delivery pipe, a front short shell, and a rear short shell, wherein: The front box includes a front box cylindrical section and a front bottom and a common bottom respectively disposed at both ends of the front box cylindrical section; The rear box includes a rear box cylindrical section and a rear bottom disposed at one end of the rear box cylindrical section, and the end of the rear box cylindrical section away from the rear bottom is welded to the rear bottom; a rear box propellant outlet is provided on the rear bottom; The front short shell is welded to the front bottom, and the rear short shell is welded to the rear bottom; The conveying pipe is located inside the rear box. One end of the conveying pipe is welded to the bottom and communicates with the inside of the front box. The other end of the conveying pipe is welded to the bottom and communicates with the outside of the rear box. The common bottom is a single-layer structure, and an insulating structure is provided on the common bottom.

[0009] According to one embodiment of the present invention, both the common base and the rear base are semi-ellipsoidal structures; The propellant outlet of the rear chamber is located at the center of the rear bottom, the connection between the delivery pipe and the common bottom is located at the center of the common bottom, and the connection between the delivery pipe and the rear bottom is located on one side of the propellant outlet of the rear chamber. The conveying pipe is inclinedly arranged inside the rear box. The conveying pipe is also a single-layer structure and is also provided with a heat insulation structure. A sixth pipe flange is welded to the inner wall of the propellant outlet of the rear box. The sixth pipe flange is located outside the rear box, and the interior of the rear box is connected to the exterior of the rear box through the sixth pipe flange. The sixth pipe flange is provided with a first annular outward flange at one end near the rear bottom. The outer wall of the first annular outward flange is welded to the inner wall of the rear box propellant outlet. The sixth pipe flange is welded to the inner wall of the rear box propellant outlet through the first annular outward flange.

[0010] According to one embodiment of the present invention, a first connecting mechanism and a second connecting mechanism are respectively installed at both ends of the conveying pipe; One end of the conveying pipe is welded to the common bottom through the first connecting mechanism and communicates with the interior of the front box. The other end of the conveying pipe is welded to the rear bottom through the second connecting mechanism and communicates with the exterior of the rear box.

[0011] According to one embodiment of the present invention, the first connecting mechanism includes at least a first pipe flange and a second pipe flange, and the first pipe flange and the second pipe flange are bolted together and communicate with each other; The end of the second pipe flange furthest from the first pipe flange is welded to the end of the delivery pipe furthest from the rear bottom and they are interconnected. The bottom of the common bottom is provided with a first front box propellant outlet, and the first front box propellant outlet is located at the center of the common bottom. The end of the first pipe flange away from the second pipe flange is welded to the inner wall of the first front box propellant outlet. The first pipe flange communicates with the interior of the front box. The first pipe flange is provided with a second annular outward flange at one end near the common bottom. The outer wall of the second annular outward flange is welded to the inner wall of the first front box propellant outlet. The first pipe flange is welded to the inner wall of the first front box propellant outlet through the second annular outward flange.

[0012] According to one embodiment of the present invention, the first connecting mechanism further includes a filter and a corrugated compensator; The filter is installed inside the first pipe flange, and the corrugated compensator is installed on the delivery pipe.

[0013] According to one embodiment of the present invention, the corrugated compensator is a sandwich structure of a double-layer corrugated pipe, and the interior of the sandwich structure of the double-layer corrugated pipe is a vacuum environment.

[0014] According to one embodiment of the present invention, the second connecting mechanism includes a third pipe flange, a fourth pipe flange, a connecting pipe, and a fifth pipe flange; The third pipe flange and the fourth pipe flange are bolted together and communicate with each other. The end of the third pipe flange away from the fourth pipe flange is welded to the end of the conveying pipe away from the common bottom and communicates with each other. A second front box propellant outlet is provided on the rear bottom. The second front box propellant outlet is located on one side of the rear box propellant outlet. The connecting pipe is welded to the inner wall of the second front box propellant outlet. The end of the connecting pipe near the fourth pipe flange is welded to the end of the fourth pipe flange away from the third pipe flange and they are interconnected. The fifth pipe flange is welded to the end of the connecting pipe away from the fourth pipe flange and is in communication with it. The fifth pipe flange is located outside the rear box.

[0015] According to one embodiment of the present invention, the thermal insulation structure includes a buffer layer, a thermal insulation layer, and a protective layer; The buffer layer, the heat insulation layer, and the protective layer on the common bottom are sequentially disposed at the top or bottom end of the common bottom in a direction away from the common bottom, and the buffer layer, the heat insulation layer, and the protective layer on the conveying pipe are sequentially disposed on the inner or outer side wall of the conveying pipe in a direction away from the conveying pipe.

[0016] According to one embodiment of the present invention, a first welding annular groove is provided on the outer side wall of the front bottom along its circumference, and the front short shell is welded to the first welding annular groove; A second welding annular groove is provided on the outer side wall of the common bottom along its circumference, and the end of the rear box section away from the rear bottom is welded to the second welding annular groove; A third welding annular groove is provided on the outer side wall of the rear bottom along its circumference, and the rear short shell is welded to the third welding annular groove.

[0017] According to one embodiment of the present invention, a sealing ring is provided between the first pipe flange and the second pipe flange, and between the third pipe flange and the fourth pipe flange.

[0018] Beneficial effects This utility model has at least the following technical effects: 1. By using a single-layer common bottom structure, this utility model can significantly reduce the overall structural weight of the rocket propellant tank compared to the traditional double-layer common bottom structure, thereby significantly improving the carrying capacity of the launch vehicle.

[0019] 2. By placing the delivery pipe inside the rear box, this utility model, compared to the traditional external delivery pipe structure, does not affect the aerodynamic shape of the rocket body and improves the stability of the launch vehicle during flight.

[0020] 3. By placing the delivery pipe inside the rear box, this utility model eliminates the need for pipe long cover, large pipe end cap, and pipe long support on the delivery pipe, compared to the traditional external delivery pipe structure. This does not increase the overall structural weight of the launch vehicle body and improves the launch vehicle's carrying capacity. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 for Figure 1 A schematic diagram of the overall structure from another angle; Figure 3 for Figure 2 A schematic diagram of the overall structure after removing the front and rear short shells; Figure 4 for Figure 1 A cross-sectional schematic diagram of the overall structure; Figure 5 for Figure 4 A magnified view of a section at point A in the middle; Figure 6 for Figure 4 A magnified view of a section at point B in the middle; Figure 7 for Figure 4 A magnified view of a section at point C; Figure 8 for Figure 4 A magnified view of a section at point D; Figure 9 for Figure 4 A magnified view of a section at point E in the middle; Figure 10 for Figure 4 A magnified view of a section at point F in the middle; Figure 11 This is a schematic diagram of the overall structure of the conveying pipe, the first connecting mechanism, and the second connecting mechanism in this utility model; Figure 12 This is a schematic diagram of the overall structure of the front box in this utility model; Figure 13 for Figure 12 A schematic diagram of the overall structure from another angle; Figure 14 This is a schematic diagram of the overall structure of the rear box in this utility model.

[0023] Explanation of reference numerals in the attached figures: 1. Front box section; 2. Front bottom; 3. Front short shell; 4. Rear box section; 5. Rear bottom; 6. Rear short shell; 7. Common bottom; 8. First pipe flange; 9. Filter; 10. Second pipe flange; 11. Delivery pipe; 12. Corrugated compensator; 13. Third pipe flange; 14. Fourth pipe flange; 15. Connecting pipe; 16. Fifth pipe flange; 17. Sixth pipe flange; 101. First welded annular groove; 102. Second welded annular groove; 401. Third welded annular groove. Detailed Implementation

[0024] The features and exemplary embodiments of various aspects of this utility model will be described in detail below. To make the objectives, technical solutions, and advantages of this utility model clearer, the following detailed description is provided in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain this utility model and to exemplarily illustrate the principles of this utility model, and are not configured to limit this utility model. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of this utility model.

[0025] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of this utility model. In the description of this utility model, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0026] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0027] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., without specifically indicating order or sequence, and should not be considered restrictive. Similar terms are used throughout the description to represent similar elements.

[0028] For those skilled in the art, this invention can be implemented without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples.

[0029] like Figures 1-14 As shown, this utility model provides a cryogenic propellant rocket tank with a single-layer common bottom. For ease of description, the cryogenic propellant rocket tank with a single-layer common bottom provided by this utility model will be referred to as "this rocket tank" or "the rocket tank" in the following text.

[0030] like Figures 1-4 As shown, the rocket propellant tank includes at least a front chamber, a rear chamber, a delivery pipe 11, a front short shell 3, and a rear short shell 6, wherein: The front chamber can be used to store liquid oxygen required by the launch vehicle, and the rear chamber can be used to store liquid methane required by the launch vehicle. The front short shell 3 and the rear short shell 6 can be connected to the launch vehicle's shell section (not shown in the figure) and the launch vehicle's engine (not shown in the figure), thereby installing the rocket's propellant tanks inside the launch vehicle. The above-mentioned contents are all prior art known in the art, and will not be described in detail here.

[0031] like Figure 4 , Figure 12 and Figure 13 As shown, the front box includes a front box cylindrical section 1 and a front bottom 2 and a common bottom 7 respectively disposed at both ends of the front box cylindrical section 1.

[0032] In this embodiment, as Figure 4 As shown, the front box section 1 can be a hollow cylindrical structure with open ends. The front bottom 2 and the common bottom 7 are respectively installed at the open structures at both ends of the front box section 1. The front bottom 2 and the front box section 1, as well as the common bottom 7 and the front box section 1, can be connected by welding, which is not particularly limited here.

[0033] like Figure 4 and Figure 14 As shown, the rear box includes a rear box cylindrical section 4 and a section disposed at one end of the rear box cylindrical section 4 (i.e., Figure 4 The rear bottom 5 of the rear box section 4 (bottom end), the end of the rear box section 4 away from the rear bottom 5 (i.e. Figure 4 The top of the middle and rear box section 4 is welded to the common bottom 7. The rear bottom 5 has a rear box propellant outlet.

[0034] In this embodiment, as Figure 4 As shown, the rear box section 4 can also be a hollow cylindrical structure with open ends, and the cross-sectional diameter of the rear box section 4 (i.e., the section perpendicular to its axial direction) can be the same as the cross-sectional diameter of the front box section 1 (i.e., the section perpendicular to its axial direction). The rear bottom 5 and the rear box section 4 can be connected by welding, which is not particularly limited here. Specifically, when the end of the rear box section 4 away from the rear bottom 5 is welded to the common bottom 7, the internal volume of the rear box section 4 can be set to be exactly the same as the internal volume of the front box section 1. Alternatively, it can be set to a completely different volume depending on the actual situation.

[0035] Preferably, the front bottom 2, the rear bottom 5, and the common bottom 7 can all be integrally spun and formed using methods known in the art, which can reduce the welds between the three components and the petals (the petals are not shown in the figure and are components known in the art), thereby improving the reliability of the overall structure of the rocket's propellant tank.

[0036] like Figure 1 , Figure 2 and Figure 4 As shown, the front short shell 3 is welded to the front bottom 2, and the rear short shell 6 is welded to the rear bottom 5.

[0037] In this embodiment, as Figure 4 As shown, when the front short shell 3 is welded to the front bottom 2, the front short shell 3 will be located above the front box section 1, that is, the front bottom 2 will be located between the front short shell 3 and the front box section 1. When the rear short shell 6 is welded to the rear bottom 5, the rear short shell 6 will be located below the rear box section 4, that is, the rear bottom 5 will be located between the rear short shell 6 and the rear box section 4.

[0038] In this embodiment, as Figure 4 As shown, both the front short shell 3 and the rear short shell 6 can be annular structures with the same outer wall cross-sectional diameter as the front cylindrical section 1 and the rear cylindrical section 4, without any particular limitation. Wherein, as Figure 1 , Figure 2 and Figure 4 As shown, the end of the front short shell 3 that is away from the front box section 1 (i.e. Figure 4 The top of the front short shell 3), and the end of the rear short shell 6 away from the rear box section 4 (i.e. Figure 4 The bottom of the middle and rear short shell 6 can be provided with an inward flange of 90° or approximately 90°.

[0039] In this embodiment, as Figures 1-4 As shown, the front short shell 3, the front box section 1, the rear box section 4, and the rear short shell 6 are all coaxially arranged.

[0040] like Figure 4 As shown, the conveying pipe 11 is located inside the rear box, and one end of the conveying pipe 11 (i.e. Figure 4 The top end of the middle conveying pipe 11 is welded to the common bottom 7 and is configured to communicate with the interior of the front box. The other end of the conveying pipe 11 (i.e. Figure 4 The bottom end of the middle conveying pipe 11 is welded to the bottom 5 and is configured to be able to communicate with the outside of the rear box.

[0041] In this embodiment, as Figure 4 and Figure 11 As shown, the conveying pipe 11 can be a cylindrical structure or a roughly cylindrical structure, and no particular limitation is made here.

[0042] In this embodiment, the common bottom 7 is a single-layer structure, and an insulating structure (not shown in the figure) is provided on the common bottom 7.

[0043] By using a single-layer common bottom structure, compared to the traditional double-layer common bottom structure, the overall structural weight of the rocket propellant tank can be significantly reduced, thereby significantly improving the launch vehicle's carrying capacity.

[0044] By setting up an insulation structure, heat transfer between the front and rear compartments can be effectively isolated.

[0045] In this embodiment, the outer side wall of the front box section 1, the outer side wall of the rear box section 4, and the bottom end of the rear bottom 5 (i.e., Figure 4 The bottom of the middle and rear bottom 5) and the top of the front bottom 2 (i.e. Figure 4 The top of the front box 2 can also be provided with a heat insulation structure (not shown in the figure), which can effectively isolate the heat transfer between the front box and the external environment, and between the rear box and the external environment.

[0046] Preferably, the front short shell 3 and the rear short shell 6 can both be skinned stringers or grid-reinforced columnar structures (not shown in the figure), and the front box section 1 and the rear box section 4 can both be plain cylinder, grid-reinforced, or frame truss structures (not shown in the figure), which can improve the overall structural strength of the front short shell 3 and the rear short shell 6, the front box section 1 and the rear box section 4, and at the same time, can further reduce the weight of the front short shell 3 and the rear short shell 6, the front box section 1 and the rear box section 4.

[0047] According to one embodiment of the present invention, such as Figure 4 As shown, both the common base 7 and the rear base 5 are semi-ellipsoidal structures (i.e., facing...). Figure 4 (Lower recessed structure). The propellant outlet of the rear box is located at the center of the rear bottom 5 (i.e., the lowest point of the rear bottom 5). The connection between the delivery pipe 11 and the common bottom 7 is located at the center of the common bottom 7 (i.e., the lowest point of the common bottom 7). The connection between the delivery pipe 11 and the rear bottom 5 is located on one side of the propellant outlet of the rear box. That is, the delivery pipe 11 will be inclined inside the rear box (i.e., the delivery pipe 11 will be at a certain angle to the side wall of the rear box cylindrical section 4).

[0048] In this embodiment, the angle between the conveying pipe 11 and the side wall of the rear box section 4 can be 5°-10°, or it can be set to other angles as needed, without any particular limitation.

[0049] Since both the common base 7 and the rear base 5 are semi-ellipsoidal structures (i.e., facing...) Figure 4The concave structure below, the connection between the delivery pipe 11 and the common bottom 7 is located at the center of the common bottom 7, and the propellant outlet of the rear box is located at the center of the rear bottom 5. Therefore, during the flight of the launch vehicle, the amount of unusable propellant (i.e., liquid oxygen and liquid methane) in the front and rear boxes can be effectively reduced, and there can be no unusable propellant.

[0050] In this embodiment, the conveying pipe 11 is also a single-layer structure, and an insulation structure is also provided on the conveying pipe 11.

[0051] Compared to the traditional double-layered delivery pipe, the single-layered delivery pipe 11 further reduces the overall structural weight of the rocket propellant tank, thereby further improving the launch vehicle's carrying capacity. The inclusion of an insulation structure on the delivery pipe 11 effectively isolates heat transfer between the delivery pipe 11 and the rear chamber.

[0052] like Figure 4 and Figure 10 As shown, a sixth pipe flange 17 is welded to the inner wall of the propellant outlet of the rear chamber. The sixth pipe flange 17 is located outside the rear chamber and can be coaxially arranged with the opening direction of the propellant outlet of the rear chamber (i.e., coaxially arranged with the rear chamber section 4). The interior of the rear chamber is configured to communicate with the exterior of the rear chamber through the sixth pipe flange 17, that is, the sixth pipe flange 17 can be connected and communicated with the combustion chamber of the launch vehicle engine (not shown in the figure but known in the art), thereby enabling the liquid methane stored in the rear chamber to be introduced into the combustion chamber of the launch vehicle engine.

[0053] In this embodiment, the propellant outlet of the rear chamber can also serve as a manhole for personnel to enter and exit the rear chamber, and the sixth pipe flange 17 can also serve as a manhole cover. Since the propellant outlet of the rear chamber in this embodiment is located at the center of the rear bottom 5, personnel can also enter and exit the rear chamber through the propellant outlet when the rocket tank is undergoing horizontal rolling.

[0054] Specifically, such as Figure 10 As shown, the sixth pipe flange 17 is located at one end near the rear bottom 5 (i.e., the sixth pipe flange 17 is located at...). Figure 10 The top of the flange is provided with a first annular outward flange. The outer side wall of the first annular outward flange (i.e., the side wall of the first annular outward flange away from the sixth pipe flange 17) can be welded to the inner side wall of the rear box propellant outlet. That is, the sixth pipe flange 17 will be welded to the inner side wall of the rear box propellant outlet through the first annular outward flange.

[0055] According to one embodiment of the present invention, such as Figure 7 and Figure 9 As shown, a first connecting mechanism and a second connecting mechanism are respectively installed at both ends of the conveying pipe 11, wherein: One end of the delivery pipe 11 (i.e. Figure 4 The top end of the middle conveying pipe 11 is welded to the center of the common bottom 7 via the first connecting mechanism and is configured to communicate with the interior of the front box. The other end of the conveying pipe 11 (i.e. Figure 4 The bottom end of the middle conveying pipe 11 is welded to the rear bottom 5 through the second connecting mechanism and is configured to be able to communicate with the outside of the rear box.

[0056] Specifically, such as Figure 7 and Figure 11 As shown, the first connecting mechanism includes at least a first pipe flange 8 and a second pipe flange 10, and the first pipe flange 8 and the second pipe flange 10 are bolted together (not shown in the figure) and configured to communicate with each other. The first pipe flange 8 is configured to communicate with the interior of the front box.

[0057] Preferably, the cross-sectional diameter of the outer wall of the first pipe flange 8 (i.e., the section perpendicular to its axial direction) can be the same as the diameter of the cross-sectional diameter of the outer wall of the second pipe flange 10 (i.e., the section perpendicular to its axial direction), and the cross-sectional diameters of the inner walls of the first pipe flange 8 and the second pipe flange 10 can both be the same as the cross-sectional diameter of the inner wall of the conveying pipe 11 (i.e., the section perpendicular to its axial direction). The first pipe flange 8 and the second pipe flange 10 can be coaxially arranged.

[0058] like Figure 7 As shown, the end of the second pipe flange 10 furthest from the first pipe flange 8 (i.e. Figure 7 The bottom end of the second pipe flange 10 and the end of the conveying pipe 11 furthest from the bottom 5 (i.e. Figure 7 The top end of the middle conveying pipe 11 is welded and connected to it, and is configured to allow for mutual communication.

[0059] like Figure 7 and Figure 13 As shown, the bottom of the common bottom 7 has a first front box propellant outlet, and the first front box propellant outlet is located at the center of the common bottom 7 (see reference). Figure 4 and Figure 13 The end of the first pipe flange 8 furthest from the second pipe flange 10 (i.e. Figure 7 The top of the first pipe flange 8 is welded to the inner wall of the propellant outlet of the first front box, and the second pipe flange 10 is configured to communicate with the interior of the front box through the first pipe flange 8.

[0060] Specifically, such as Figure 7 As shown, the first pipe flange 8 is located at the end near the common bottom 7 (i.e., the first pipe flange 8 is located at...). Figure 7The top of the first pipe flange 8 is provided with a second annular outward flange. The outer wall of the second annular outward flange (i.e., the side wall of the second annular outward flange away from the first pipe flange 8) can be welded to the inner wall of the first front box propellant outlet. That is, the first pipe flange 8 will be welded to the inner wall of the first front box propellant outlet through the second annular outward flange.

[0061] More specifically, such as Figure 7 and Figure 11 As shown, the first connecting mechanism also includes a filter 9 and a corrugated compensator 12, wherein: like Figure 7 As shown, the filter 9 can be installed inside the first pipe flange 8. The bellows compensator 12 can be installed on the delivery pipe 11, preferably as shown in the figure. Figure 7 The installation shown is located at one end of the delivery pipe 11 near the second pipe flange 10.

[0062] In this embodiment, filter 9 can filter the cryogenic propellant (such as liquid oxygen) flowing into the delivery pipe 11 from the front chamber, thereby effectively preventing impurities in the front chamber from flowing into the valve body (not shown in the figure) of the launch vehicle engine through the delivery pipe 11, thus avoiding the situation where the valve body cannot open or close properly due to blockage. Filter 9 is prior art known in the art and will not be described in detail here.

[0063] In addition, a filter 9 (not shown in the figure) can be detachably installed inside the sixth pipe flange 17 to filter the cryogenic propellant (such as liquid methane) inside the rear chamber.

[0064] During the propellant loading process (i.e., liquid oxygen and liquid methane), the common bottom 7 and the rear bottom 5 are subject to deformation due to gravity and temperature, which in turn changes the relative distance between them. Simultaneously, changes in tank pressure and axial bending and shear loads within the front and rear chambers also alter the relative distance between the common bottom 7 and the rear bottom 5. The corrugated compensator 12 compensates for these changes in relative distance, ensuring the stable installation of the delivery pipe 11 within the rear chamber and guaranteeing the normal operation of the rocket's propellant tanks.

[0065] Furthermore, the bellows compensator 12 can be a sandwich structure of a double-layer bellows (not shown in the figure), and the sandwich structure of the double-layer bellows has a vacuum environment inside.

[0066] In this embodiment, the specific structure of the double-layer corrugated pipe sandwich structure can be (including but not limited to): the corrugated compensator 12 can include two corrugated pipes with the same axial length but different cross-sectional diameters (i.e., cross-sections perpendicular to their axial direction), and the corrugated pipe with the smaller cross-sectional diameter is located inside the corrugated pipe with the larger cross-sectional diameter and is coaxially arranged with each other. The space between the outer wall of the corrugated pipe with the smaller cross-sectional diameter and the inner wall of the corrugated pipe with the larger cross-sectional diameter is the sandwich structure of the aforementioned double-layer corrugated pipe. Meanwhile, the two ends of the aforementioned sandwich structure (i.e., Figure 7 The top and bottom of the structure are sealed.

[0067] Preferably, when the corrugated compensator 12 is installed on the conveying pipe 11, the corrugated pipe with a smaller cross-sectional diameter, the corrugated pipe with a larger cross-sectional diameter, and the conveying pipe 11 can all be arranged coaxially, and the cross-sectional diameter of the inner wall of the corrugated pipe with a smaller cross-sectional diameter (i.e. the cross-section perpendicular to its axial direction) can be the same as the cross-sectional diameter of the inner wall of the conveying pipe 11.

[0068] With the above setup, the vacuum environment inside the interlayer can be used to achieve heat insulation of the corrugated compensator 12, thereby effectively isolating the heat transfer between the inside of the corrugated compensator 12 and the inside of the rear box.

[0069] Furthermore, the front compartment is equipped with a vortex-resistant and collapse-preventing device (not shown in the figure).

[0070] In this embodiment, the anti-vortex and anti-collapse device can be installed on the top of the first pipe flange 8 by welding (i.e., the first pipe flange 8 is located at...). Figure 7 (The top of the text), without special limitation. Among them, the anti-vortex and anti-collapse device is a prior art known in the art, which can delay or eliminate the vortex and collapse generated during the outflow of cryogenic propellant in the front box, and will not be described in detail here.

[0071] Specifically, such as Figure 4 and Figure 9 As shown, the second connection mechanism includes at least a third pipe flange 13, a fourth pipe flange 14, a connecting pipe 15, and a fifth pipe flange 16, wherein: like Figure 9 As shown, the third pipe flange 13 and the fourth pipe flange 14 are bolted together (not shown in the figure) and configured to communicate with each other. The end of the third pipe flange 13 furthest from the fourth pipe flange 14 (i.e. Figure 9 The top of the third pipe flange 13) and the end of the delivery pipe 11 furthest from the common bottom 7 (i.e. Figure 4 and Figure 9 The bottom end of the middle conveying pipe 11 is welded and connected to it, and is configured to allow for mutual communication.

[0072] Preferably, the cross-sectional diameter of the outer wall of the third pipe flange 13 (i.e., the section perpendicular to its axial direction) can be the same as the diameter of the cross-sectional diameter of the outer wall of the fourth pipe flange 14 (i.e., the section perpendicular to its axial direction), and the cross-sectional diameters of the inner walls of the third pipe flange 13 and the fourth pipe flange 14 can both be the same as the cross-sectional diameter of the inner wall of the conveying pipe 11 (i.e., the section perpendicular to its axial direction). Wherein, for example... Figure 9 As shown, the third pipe flange 13, the fourth pipe flange 14, and the delivery pipe 11 can all be coaxially arranged.

[0073] like Figure 9 As shown, a second front box propellant outlet is provided on the rear bottom 5, located to the side of the rear box propellant outlet. A connecting pipe 15 is welded to the inner wall of the second front box propellant outlet; that is, the outer wall of the connecting pipe 15 is welded to the inner wall of the second front box propellant outlet. Specifically, the end of the connecting pipe 15 closest to the fourth pipe flange 14 (i.e.,...) Figure 9 The top end of the connecting pipe 15 and the end of the fourth pipe flange 14 furthest from the third pipe flange 13 (i.e., Figure 9 The bottom end of the fourth pipe flange 14 is welded and configured to be interconnected.

[0074] In this embodiment, as Figure 9 As shown, the connecting pipe 15 can be a cylindrical structure. The cross-sectional diameter of the inner wall of the connecting pipe 15 (i.e., the cross-section perpendicular to its axial direction) can be the same as the cross-sectional diameter of the inner wall of the fourth pipe flange 14, and the connecting pipe 15 can be coaxially arranged with the third pipe flange 13, the fourth pipe flange 14 and the conveying pipe 11.

[0075] like Figure 9 As shown, the fifth pipe flange 16 is located near the end of the connecting pipe 15 (i.e. Figure 9 The top of the fifth pipe flange 16) and the end of the connecting pipe 15 furthest from the fourth pipe flange 14 (i.e. Figure 9 The bottom end of the connecting pipe 15 is welded and configured to allow for interconnection. The fifth pipe flange 16 is located outside the rear casing.

[0076] In this embodiment, the cross-sectional diameter of the inner wall of the fifth pipe flange 16 (i.e., the cross-section perpendicular to its axial direction) can be the same as the cross-sectional diameter of the inner wall of the connecting pipe 15, and the fifth pipe flange 16 can be coaxially arranged with the connecting pipe 15. The fifth pipe flange 16 can be connected and communicated with the combustion chamber of the launch vehicle engine, thereby enabling the liquid oxygen stored in the forward chamber to be introduced into the combustion chamber of the launch vehicle engine.

[0077] Furthermore, the connection between the fourth pipe flange 14, the connecting pipe 15, and the fifth pipe flange 16 can also be integrally formed, meaning that the fourth pipe flange 14, the connecting pipe 15, and the fifth pipe flange 16 can be considered as a single component. The outer wall of the connecting pipe 15 can be provided with a third annular outward flange (not shown in the figure), and the outer wall of the third annular outward flange (i.e., the side wall of the third annular outward flange away from the connecting pipe 15) can be welded to the inner wall of the propellant outlet of the second front box. In other words, the connecting pipe 15 will be welded to the inner wall of the propellant outlet of the second front box via the third annular outward flange.

[0078] Specifically, the thermal insulation structure includes at least a buffer layer, a thermal insulation layer, and a protective layer (none shown in the figure). The buffer layer, thermal insulation layer, and protective layer on the common bottom 7 are sequentially arranged at the top or bottom of the common bottom 7 in a direction away from the common bottom 7 (i.e.,...). Figure 4 The buffer layer, insulation layer and protective layer on the conveying pipe 11 are sequentially arranged on the inner or outer side wall of the conveying pipe 11 in a direction away from the conveying pipe 11 (the top or bottom of the 7th section of the pipe).

[0079] More specifically, the buffer layer comprises DW-3 adhesive and DW-1 adhesive (not shown in the figure), preferably DW-3 adhesive and DW-1 adhesive. The insulation layer comprises polyurethane foam (not shown in the figure), preferably polyurethane foam. The protective layer comprises DW-1 adhesive (not shown in the figure), preferably DW-1 adhesive. DW-3 adhesive, DW-1 adhesive, and polyurethane foam are all existing materials known in the art and will not be described in detail here.

[0080] Furthermore, the protective layer can also be alkali-free glass fiber cloth impregnated with DW-1 adhesive, as is known in the art. When the insulation structure accidentally cracks at low temperatures, the alkali-free glass fiber cloth can effectively prevent fragmented impurities generated during the cracking of the insulation structure from entering the interior of the front box, rear box, and conveying pipe 11.

[0081] According to one embodiment of the present invention, such as Figure 5 and Figure 12 As shown, a first welding annular groove 101 is provided on the outer side wall of the front bottom 2 along its circumference, and the bottom end of the front short shell 3 (i.e. Figure 4 and Figure 5 The bottom end of the front short shell 3 is welded to the first welding annular groove 101.

[0082] In this embodiment, the width of the first welding annular groove 101 can be the same as the width of the side wall of the front short shell 3.

[0083] like Figure 6 and Figure 13 As shown, a second welded annular groove 102 is provided on the outer side wall of the common bottom 7 along its circumference, and the end of the rear box section 4 away from the rear bottom 5 (i.e. Figure 4The top of the middle and rear box section 4 is welded to the second welding annular groove 102.

[0084] like Figure 3 and Figure 8 As shown, a third welding annular groove 401 is provided on the outer side wall of the rear bottom 5 along its circumference, and the top of the rear short shell 6 (i.e. Figure 4 and Figure 8 The top of the middle and rear short shell 6 is welded to the third welding annular groove 401.

[0085] In this embodiment, the width of the third welding annular groove 401 can be the same as the width of the side wall of the rear short shell 6.

[0086] Furthermore, sealing rings (not shown in the figure) are provided at the connection between the first pipe flange 8 and the second pipe flange 10, and at the connection between the third pipe flange 13 and the fourth pipe flange 14.

[0087] In this embodiment, specifically, as Figure 7 and Figure 9 As shown, annular mounting grooves for sealing rings are provided on the outer walls of the contact portions between the first pipe flange 8 and the second pipe flange 10, and on the outer walls of the contact portions between the third pipe flange 13 and the fourth pipe flange 14. The annular mounting grooves for sealing rings on the first pipe flange 8 and the second pipe flange 10 are coaxially arranged with the first pipe flange 8 and the second pipe flange 10, and their annular mounting grooves correspond to each other. Similarly, the annular mounting grooves for sealing rings on the third pipe flange 13 and the fourth pipe flange 14 are coaxially arranged with the third pipe flange 13 and the fourth pipe flange 14, and their annular mounting grooves correspond to each other. The sealing ring is adapted to the annular mounting groove and is designed to be installed (embedded) inside the annular mounting groove.

[0088] Furthermore, the sealing ring can be a graphite sealing ring or a metal skeleton graphite sealing ring known in the art, without any particular limitation.

[0089] By setting a sealing ring, the sealing performance of the connection between the first pipe flange 8 and the second pipe flange 10, and the connection between the third pipe flange 13 and the fourth pipe flange 14 can be improved.

[0090] Furthermore, the outer walls of the contact portions between the first pipe flange 8 and the second pipe flange 10, and the outer walls of the contact portions between the third pipe flange 13 and the fourth pipe flange 14, can also be configured with the following structures: like Figure 7 As shown, the bottom end of the first pipe flange 8 is provided with a sealing ring annular mounting groove that matches the sealing ring annular mounting groove at the top end of the second pipe flange 10 and is correspondingly provided with a sealing ring annular mounting tenon (not shown in the figure); Figure 9As shown, the bottom end of the third pipe flange 13 is also provided with a sealing ring annular mounting tenon (not shown in the figure) that is adapted to and correspondingly provided with the sealing ring annular mounting groove opened at the top of the fourth pipe flange 14. When the first pipe flange 8 is connected to the second pipe flange 10, the third pipe flange 13 and the fourth pipe flange 14, the sealing ring annular mounting tenon will enter the sealing ring annular mounting groove and there is a certain space between it and the sealing ring annular mounting groove, and the sealing ring can be installed (embedded) in the above space.

[0091] In this embodiment, the two ends of the conveying pipe 11 (i.e., the welded connections with the second pipe flange 10 and the third pipe flange 13) can be welded thickened areas, while the middle portion can be a thin area. This allows for a reduction in the structural weight of the conveying pipe 11 while improving the connection strength between the conveying pipe 11 and the second pipe flange 10, and between the conveying pipe 11 and the third pipe flange 13. This structure of the conveying pipe 11 can be manufactured using a process known in the art called "chemical milling," further reducing the structural weight of the conveying pipe 11 while ensuring its straightness requirements.

[0092] Furthermore, at least bolts, flat washers, spring washers, and nuts (not shown in the diagram) are provided between the first pipe flange 8 and the second pipe flange 10, and between the third pipe flange 13 and the fourth pipe flange 14, wherein: The first pipe flange 8 is configured to be bolted to the second pipe flange 10 using bolts, flat washers, spring washers, and nuts; The third pipe flange 13 is configured to be bolted to the fourth pipe flange 14 using bolts, flat washers, spring washers, and nuts.

[0093] Specifically, the bolted connections between the first pipe flange 8 and the second pipe flange 10, and between the third pipe flange 13 and the fourth pipe flange 14, can all be configured as follows (including but not limited to): The bolted connection described above can be from top to bottom (i.e.) Figure 4 From top to bottom, the components are bolts, flat washers, spring washers (such as spring washers known in the art), and nuts (none of these components are shown in the figure). The nuts may have locking holes that are connected to adjacent nuts to prevent loosening. Bolts and nuts can be made of high-temperature alloys or stainless steel known in the art, while flat washers and spring washers can be made of stainless steel, thus enabling suitability for the low-temperature environments inside the front and rear compartments.

[0094] More specifically, taking the first pipe flange 8 and the second pipe flange 10 as examples, the bolt heads of the aforementioned bolts can be located at the top of the first pipe flange 8 (i.e., Figure 7The flat washer and the spring washer are both located at the top of the nut and the bottom of the second pipe flange 10 (i.e., the top of the first pipe flange 8). Figure 7 Between the bottom end of the first pipe flange 8 and the second pipe flange 10, the aforementioned nut can be threaded onto the threaded rod of the aforementioned bolt, thereby realizing the bolted connection between the first pipe flange 8 and the second pipe flange 10. The flat washer can be located between the spring washer and the bottom end of the second pipe flange 10, that is, the flat washer, spring washer, and nut are arranged sequentially from top to bottom. Specifically, the top end of the flat washer can abut against the bottom end of the second pipe flange 10, the bottom end of the spring washer can abut against the top end of the nut, and the bottom end of the flat washer can abut against the top end of the spring washer; no particular limitation is made here. Similarly, the bolted connection between the third pipe flange 13 and the fourth pipe flange 14 can also be configured as described above, which will not be elaborated further here.

[0095] Furthermore, the welding methods used for welds on existing rocket common-base tanks are mostly variable polarity tungsten inert gas welding (VPTIG) or variable polarity plasma arc welding (VPPA). However, the weld coefficient of VPTIG or VPPA is lower than that of friction stir welding (FSW). Consequently, under the same load, the thickness of the base material welded using VPTIG and VPPA is greater than that welded using FSW, which increases the structural weight of the launch vehicle and reduces the stability and payload capacity of the launch vehicle body. At the same time, VPTIG and VPPA are more prone to porosity, tungsten inclusions, and other defects at the weld joint compared to FSW.

[0096] In this embodiment, all the above-mentioned welding connections can be made using friction stir welding (FSW), which can effectively avoid the occurrence of the above-mentioned defects.

[0097] It should be understood that the above-described embodiments or examples of this utility model can be combined with each other and have corresponding technical effects.

[0098] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A cryogenic propellant rocket tank with a single-layer common bottom, characterized in that, Includes a front box, a rear box, a delivery pipe (11), a front short shell (3), and a rear short shell (6), wherein: The front box includes a front box cylindrical section (1) and a front bottom (2) and a common bottom (7) respectively disposed at both ends of the front box cylindrical section (1); The rear box includes a rear box cylindrical section (4) and a rear bottom (5) disposed at one end of the rear box cylindrical section (4). The end of the rear box cylindrical section (4) away from the rear bottom (5) is welded to the common bottom (7). The rear bottom (5) is provided with a rear box propellant outlet. The front short shell (3) is welded to the front bottom (2), and the rear short shell (6) is welded to the rear bottom (5); The conveying pipe (11) is located inside the rear box. One end of the conveying pipe (11) is welded to the common bottom (7) and communicates with the inside of the front box. The other end of the conveying pipe (11) is welded to the rear bottom (5) and communicates with the outside of the rear box. The common bottom (7) is a single-layer structure, and an insulating structure is provided on the common bottom (7).

2. The cryogenic propellant rocket tank with a single-layer common bottom according to claim 1, characterized in that, Both the common base (7) and the rear base (5) are semi-ellipsoidal structures; The rear propellant outlet is located at the center of the rear bottom (5), the connection between the delivery pipe (11) and the common bottom (7) is located at the center of the common bottom (7), and the connection between the delivery pipe (11) and the rear bottom (5) is located on one side of the rear propellant outlet; The conveying pipe (11) is inclinedly arranged inside the rear box. The conveying pipe (11) is also a single-layer structure, and a heat insulation structure is also provided on the conveying pipe (11). A sixth pipe flange (17) is welded to the inner wall of the propellant outlet of the rear box. The sixth pipe flange (17) is located outside the rear box, and the interior of the rear box is connected to the exterior of the rear box through the sixth pipe flange (17). The sixth pipe flange (17) is provided with a first annular outward flange at one end near the rear bottom (5). The outer wall of the first annular outward flange is welded to the inner wall of the rear box propellant outlet. The sixth pipe flange (17) is welded to the inner wall of the rear box propellant outlet through the first annular outward flange.

3. The cryogenic propellant rocket tank with a single-layer common bottom according to claim 2, characterized in that, The two ends of the conveying pipe (11) are respectively equipped with a first connecting mechanism and a second connecting mechanism; One end of the conveying pipe (11) is welded to the common bottom (7) through the first connecting mechanism and communicates with the inside of the front box. The other end of the conveying pipe (11) is welded to the rear bottom (5) through the second connecting mechanism and communicates with the outside of the rear box.

4. The cryogenic propellant rocket tank with a single-layer common bottom according to claim 3, characterized in that, The first connecting mechanism includes at least a first pipe flange (8) and a second pipe flange (10), and the first pipe flange (8) and the second pipe flange (10) are bolted together and communicate with each other; The end of the second pipe flange (10) away from the first pipe flange (8) is welded to the end of the conveying pipe (11) away from the rear bottom (5) and they are connected to each other; The bottom end of the common bottom (7) is provided with a first front box propellant outlet, and the first front box propellant outlet is located at the center of the common bottom (7). The end of the first pipe flange (8) away from the second pipe flange (10) is welded to the inner wall of the first front box propellant outlet. The first pipe flange (8) is in communication with the interior of the front box. The first pipe flange (8) is provided with a second annular outer flange at one end near the common bottom (7). The outer wall of the second annular outer flange is welded to the inner wall of the first front box propellant outlet. The first pipe flange (8) is welded to the inner wall of the first front box propellant outlet through the second annular outer flange.

5. The cryogenic propellant rocket tank with a single-layer common bottom according to claim 4, characterized in that, The first connecting mechanism also includes a filter (9) and a corrugated compensator (12); The filter (9) is installed inside the first pipe flange (8), and the corrugated compensator (12) is installed on the delivery pipe (11).

6. The cryogenic propellant rocket tank with a single-layer common bottom according to claim 5, characterized in that, The corrugated compensator (12) is a double-layer corrugated pipe sandwich structure, and the sandwich structure of the double-layer corrugated pipe has a vacuum environment inside.

7. The cryogenic propellant rocket tank with a single-layer common bottom according to claim 4, characterized in that, The second connection mechanism includes a third pipe flange (13), a fourth pipe flange (14), a connecting pipe (15), and a fifth pipe flange (16). The third pipe flange (13) and the fourth pipe flange (14) are bolted together and communicate with each other. The end of the third pipe flange (13) away from the fourth pipe flange (14) is welded to the end of the conveying pipe (11) away from the common bottom (7) and communicates with each other. The rear bottom (5) is provided with a second front box propellant outlet, which is located on one side of the rear box propellant outlet. The connecting pipe (15) is welded to the inner wall of the second front box propellant outlet. The end of the connecting pipe (15) near the fourth pipe flange (14) is welded to the end of the fourth pipe flange (14) away from the third pipe flange (13) and they are interconnected. The fifth pipe flange (16) is welded to the end of the connecting pipe (15) away from the fourth pipe flange (14) and communicates with each other. The fifth pipe flange (16) is located outside the rear box.

8. The cryogenic propellant rocket tank with a single-layer common bottom according to claim 2, characterized in that, The thermal insulation structure includes a buffer layer, a thermal insulation layer, and a protective layer; The buffer layer, the heat insulation layer and the protective layer on the common bottom (7) are sequentially disposed at the top or bottom end of the common bottom (7) in a direction away from the common bottom (7), and the buffer layer, the heat insulation layer and the protective layer on the conveying pipe (11) are sequentially disposed on the inner or outer side wall of the conveying pipe (11) in a direction away from the conveying pipe (11).

9. The cryogenic propellant rocket tank with a single-layer common bottom according to claim 1, characterized in that, A first welding annular groove (101) is provided on the outer side wall of the front bottom (2) along its circumference, and the front short shell (3) is welded to the first welding annular groove (101); A second welding annular groove (102) is provided on the outer side wall of the common bottom (7) along its circumference, and the end of the rear box section (4) away from the rear bottom (5) is welded to the second welding annular groove (102); A third welding annular groove (401) is provided on the outer side wall of the rear bottom (5) along its circumference, and the rear short shell (6) is welded to the third welding annular groove (401).

10. The cryogenic propellant rocket tank with a single-layer common bottom according to claim 7, characterized in that, A sealing ring is provided between the first pipe flange (8) and the second pipe flange (10), and between the third pipe flange (13) and the fourth pipe flange (14).

Images