Liquid rocket storage tank and parameter determination method

Abstract

The invention provides a liquid rocket storage tank and a parameter determination method. Comprising a barrel section, the inner side wall of the barrel section is provided with grid ribs, the grid ribs are provided with a plurality of fixing parts at intervals in the horizontal direction, and each fixing part is provided with a first installation opening; the anti-shaking plate assembly is arranged on the barrel section and comprises a fan-shaped plate; the curvature of the arc-shaped mounting plate is matched with the target mounting area of the inner wall of the cylinder section, and at least part of the arc-shaped mounting plate is riveted and fixed to the inner arc edge area of the sector plate in an overlapped mode; a plurality of mounting parts are formed on the edge of the outer side of the arc-shaped mounting plate at intervals, a polygonal second mounting opening is formed in each mounting part, and the second mounting openings correspond to the corresponding first mounting openings; a connecting piece; the fixing part and the mounting part are detachably connected in an inserted mode, and the locking parts at the two ends of the connecting piece lock the fixing part and the mounting part in the radial direction and the axial direction respectively. The connecting pieces are connected to the grid ribs of the anti-shaking plate and the storage tank in a riveting mode, disassembly and assembly are convenient, welding is avoided, and weight reduction of a rocket is facilitated.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of liquid rocket design, and further relates to a liquid rocket tank and a parameter determination method. BACKGROUND

[0002] The propellant of a large liquid rocket accounts for about 90% of the total mass of the rocket in terms of mass ratio, and the propellant in the tank will shake when the rocket is flying. The shaking is periodic, and the disturbance sources causing the shaking mainly include the following two kinds: 1) external disturbance force, i.e. shaking caused by yaw, pitch and roll of the rocket; and 2) disturbance caused by vibration of the engine and elastic vibration of the rocket body structure.

[0003] The anti-shaking plate is a mechanical device in the liquid tank for inhibiting liquid shaking and changing the shaking frequency. When the vibration frequency caused by the disturbance source is close to the natural vibration frequency of the tank, a very dangerous coupling response will occur, which will cause the rocket to be dangerous. In order to ensure continuous and reliable supply of the propellant and normal operation of the rocket, the structure, installation mode and layout of the anti-shaking plate need to be reasonably designed.

[0004] There are many types of anti-shaking plates for existing liquid rocket tanks. In general, the anti-shaking plate is required to be easy to manufacture and install, and has good damping effect. The existing anti-shaking plates mainly have the following forms: 1) ring plate; 2) conical section ring; 3) cross-shaped plate strip; and 4) asymmetric barrier plate.

[0005] The existing anti-shaking plate assembly is mainly riveted by sheet metal parts, and the number of parts is as high as ten or more. The anti-shaking plate assembly is welded to the cylinder segment through five or more corner pieces. Although the existing anti-shaking plate can achieve the related functions, the number of parts is large, the structure is complex, there are many welding areas, and the overall structural efficiency is relatively low, which is not conducive to weight reduction design of the rocket. SUMMARY

[0006] The technical problem to be solved by the present application is to provide a liquid rocket tank and a parameter determination method. The anti-shaking plate assembly is connected to the grid rib of the anti-shaking plate and the cylinder segment through the connecting piece, which reduces the welding thickening area and is beneficial to weight reduction of the rocket body.

[0007] To solve the above problems, the technical scheme of the present application is as follows: The present application provides a liquid rocket tank, comprising: a cylinder segment, the inner side wall of which is provided with a grid rib, the grid rib is provided with a plurality of fixed parts at intervals in the horizontal direction target area, and each fixed part is formed with a first mounting port; An anti-shaking plate assembly is arranged on the cylinder segment, comprising: A fan-shaped plate has an inner arc edge matched with the curvature of the inner wall of the cylinder segment; An arc-shaped mounting plate, the curvature of which is adapted to the curvature of the inner wall of the cylindrical section, and at least partially overlapped and riveted to the inner arc edge of the fan-shaped plate; the arc-shaped mounting plate is formed with a plurality of mounting parts corresponding to the fixing part at intervals, and each mounting part is formed with a polygonal second mounting opening; A connector has a rod portion and a first locking portion and a second locking portion respectively disposed at both ends of the rod portion; The fixing part is detachably inserted into the mounting part, the second mounting port is aligned with the corresponding first mounting port, the rod part passes through the aligned first mounting port and the second mounting port, and the cross-sectional shape of the rod part is adapted to the second mounting port to form an anti-rotation fit; the first locking part and the second locking part are respectively engaged with the mounting part and the fixing part to jointly constrain the axial and radial movement of the anti-sway plate assembly relative to the cylinder section.

[0008] Optionally, the mounting portion includes: an outwardly protruding positioning protrusion, wherein the positioning protrusion has a second mounting opening formed in its central region; The fixing part includes: a positioning groove, and the two sides of the edge of the positioning groove are provided with opposing first mounting openings; The junction between the first locking part and the rod part has a radially protruding locking platform; The positioning protrusion is inserted into the positioning groove; the rod passes through the aligned second mounting port and the first mounting port on one side of the positioning groove; the first locking part passes through the first mounting port on the other side wall of the positioning groove; the locking platform engages with the surface of the positioning protrusion; and the second locking part engages with the outer side wall of the positioning groove.

[0009] Optionally, the cross-section of the rod is a polygon adapted to the second mounting port.

[0010] Optionally, the mesh reinforcement has horizontally and vertically intersecting reinforcement bars; The fixing parts are disposed on the horizontal ribs and are arranged at intervals along the horizontal direction.

[0011] Optionally, it also includes: a traction component, arranged along the axial direction of the cylindrical section, connecting at least two of the sector plates located at the same or similar circumferential positions and at different heights.

[0012] Optionally, the anti-sway baffle assemblies are arranged in staggered layers along the axial direction of the cylinder section, with an axial installation spacing H between adjacent layers of anti-sway baffle assemblies. plate Standard axial node spacing H of the mesh reinforcement rib satisfy: , where n is a positive integer.

[0013] Optionally, the ratio of the radius r of the sector plate to the inner radius R of the cylinder section, r / R, ranges from 0.2 to 0.35.

[0014] Optionally, the fan-shaped plate is provided with reinforcing vortices on both sides of the axis of symmetry; a T-shaped reinforcing rib riveted to the fan-shaped plate is provided on the axis of symmetry, and an L-shaped reinforcing rib riveted to the fan-shaped plate is provided on the outer side of the reinforcing vortex. The depth L of the reinforcing vortex and the height H of the T-shaped reinforcing rib t and the height H of the L-shaped reinforcing rib l All are less than 15mm.

[0015] The present invention also provides a method for determining the anti-sway plate parameters of a liquid rocket propellant tank, comprising: Obtain the structural parameters and sway suppression performance constraint data of the target tank. The structural parameters of the target tank include the inner radius R of the target tank's cylindrical section and the axial standard node spacing H of the internal mesh reinforcement. rib The sloshing suppression performance constraint data includes: the maximum allowable amplitude S of liquid sloshing. max The target mass M of the anti-sway plate assembly target ; Based on the structural parameters of the target tank, a fluid dynamics model is established, and simulation results are obtained. The simulation results include the dominant sloshing mode data and energy distribution region data of the liquid in the tank. Based on the simulation results, determine the layout data of the sector plate; Based on the layout data and sloshing performance constraint data of the sector plate, with the optimization goal of suppressing liquid sloshing and controlling the coefficient weight of the anti-sloshing plate, the key dimensional parameters of the anti-sloshing plate assembly are determined; the key dimensional parameters include at least the sector plate radius r and thickness t. Output the layout data of the sector plate and the key dimensional parameters of the anti-sway plate assembly.

[0016] Optionally, the optimization objective is achieved through a multi-objective optimization function, the specific process of which includes: By iteratively designing the variables X = [r, t, ...], the comprehensive objective function F(X) is minimized. The expression for the comprehensive objective function F(X) is: , in, The amplitude or energy index of liquid sloshing obtained through simulation; The total mass of the anti-sway panel assembly; These are reference values ​​for the sway suppression performance index and the sway protection panel component quality index, respectively. , These are weighting coefficients, and they satisfy... .

[0017] The above-described solution of the present invention has at least the following beneficial effects: The above-mentioned solution of the present invention connects the anti-sway plate to the grid reinforcement of the tank section by means of a connector, which is convenient for disassembly and assembly, avoids welding, and is conducive to reducing the weight of the rocket. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the structure of the first side of the anti-sway plate inside the liquid rocket propellant tank according to an embodiment of the present invention; Figure 2 This is a structural schematic diagram of the first side of the anti-sway plate inside the liquid rocket propellant tank according to an embodiment of the present invention. Figure 3 This is a schematic diagram of the structure of the second side of the anti-sway plate inside the liquid rocket propellant tank according to an embodiment of the present invention; Figures 4 to 6 This is a schematic diagram of the internal connecting component of the liquid rocket propellant tank according to an embodiment of the present invention; Figure 7 This is a schematic diagram of the mesh reinforcement of the liquid rocket propellant tank according to an embodiment of the present invention; Figure 8 yes Figure 7 A magnified view of part A in the image; Figure 9 This is a schematic diagram of the first side structure of the liquid rocket propellant tank according to an embodiment of the present invention; Figure 10 This is a partial structural diagram of the connection between the first side sector plate and the mesh reinforcement of the liquid rocket tank according to an embodiment of the present invention; Figure 11 This is a schematic diagram of the structure of the first side sector plate and the mesh reinforcement without the installation of the connecting parts in an embodiment of the present invention for a liquid rocket tank; Figure 12 This is a schematic diagram of the second side structure of the liquid rocket propellant tank according to an embodiment of the present invention; Figure 13 This is a partial schematic diagram of the connection between the second side sector plate and the mesh reinforcement of the liquid rocket tank according to an embodiment of the present invention; Figure 14 This is a schematic diagram of the structure of the second side sector plate and the mesh reinforcement without the installation of the connecting parts in an embodiment of the present invention for the liquid rocket tank; Figure 15 This is a partial perspective view of a liquid rocket propellant tank according to an embodiment of the present invention; Figure 16 This is a schematic flowchart of the method for determining the parameters of a liquid rocket propellant tank according to an embodiment of the present invention.

[0019] Explanation of reference numerals in the attached figures: 1. Fan-shaped plate; 11. Reinforcing vortex; 12. T-shaped reinforcing rib; 13. L-shaped reinforcing rib; 2. Arc-shaped mounting plate; 21. Mounting part; 22. Second mounting port; 3. Connector; 31. Rod part; 32. First locking part; 321. Locking platform; 33. Second locking part; 4. Mesh rib; 41. Horizontal rib; 42. Fixing part; 43. First mounting port; 44. Vertical rib; 5. Traction component. Detailed Implementation

[0020] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0021] like Figures 1 to 15 As shown, an embodiment of the present invention provides a liquid rocket propellant tank, comprising: The cylindrical section has a mesh reinforcement 4 on its inner sidewall. The mesh reinforcement 4 has a plurality of spaced fixing parts 42 in the horizontal target area. Each fixing part 42 is formed with a first mounting opening 43. The anti-sway baffle assembly installed on the cylindrical section includes: The fan-shaped plate 1 has an inner arc edge that matches the curvature of the inner wall of the cylindrical section; The arc-shaped mounting plate 2 has a curvature that matches the curvature of the inner wall of the cylindrical section, and is at least partially overlapped and riveted to the inner arc edge of the fan-shaped plate 1; the arc-shaped mounting plate 2 is formed with a plurality of mounting parts 21 corresponding to the fixing part 42 at intervals, and each mounting part 21 is formed with a polygonal second mounting opening 22; The connector 3 has a rod portion 31, and a first locking portion 32 and a second locking portion 33 respectively disposed at both ends of the rod portion 31; The fixing part 42 is detachably inserted into the mounting part 21, the second mounting port 22 is aligned with the corresponding first mounting port 43, the rod part 31 passes through the aligned first mounting port 43 and second mounting port 22, and the cross-sectional shape of the rod part 31 is adapted to the second mounting port 22 to form an anti-rotation fit; the first locking part 32 engages with the mounting part 21, and the second locking part 33 engages with the fixing part 42 to jointly constrain the radial and axial freedom of the anti-sway plate assembly relative to the cylindrical section.

[0022] In this embodiment of the invention, the liquid rocket propellant tank has a cylindrical shell section. Mesh ribs 4 are distributed along the circumferential and axial directions on the inner wall of the section, strengthening the structural strength of the tank. The curvature of the mesh ribs 4 is adapted to the curvature of the inner wall of the section. Multiple fixing parts 42 are evenly arranged at predetermined intervals within the horizontal target area of ​​the mesh ribs 4, each fixing part having a first mounting opening 43. The inner arc edge of the fan-shaped plate 1 is adapted to the curvature of the inner wall of the section. The arc-shaped plate mounting plate 2 is a strip plate of a certain width, at least partially overlapping and riveted to the fan-shaped plate 1, strengthening the connection with the fan-shaped plate 1. Riveting avoids the added weight of welding. Multiple mounting parts 21 are formed at predetermined intervals on the edge of the arc-shaped mounting plate 2 away from the fan-shaped plate 1, each mounting part 21 having a polygonal second mounting opening 22. The size and position of the mounting parts 21 precisely correspond to the predetermined fixing parts 42 on the mesh ribs 4, and the second mounting opening 22 corresponds one-to-one with the first mounting opening 43. The first locking part 32 and the second locking part 33 are respectively engaged with the mounting part 21 and the fixing part 42 to jointly constrain the axial and radial degrees of freedom of the anti-sway plate assembly relative to the cylindrical section. To suppress the sloshing of the liquid propellant during flight, the liquid rocket propellant tank adopts a semi-circular fan-shaped plate as an anti-sway plate. The fan-shaped plate 1 is also the anti-sway plate, which is semi-circular and can be a sheet metal part. The arc-shaped mounting plate 2 is also a sheet metal part.

[0023] In this embodiment of the invention, the arc-shaped mounting plate 2 and the fan-shaped plate 1 are connected by riveting. The anti-sway plate assembly does not involve welding during assembly with the cylinder section, resulting in high installation efficiency, convenient assembly and disassembly, and saving time and effort. Furthermore, the anti-sway plate assembly does not require a pre-reserved welding thickening area, which is beneficial for weight reduction design. The arc-shaped mounting plate 2 only overlaps and is riveted to the inner edge of the fan-shaped plate 1. This embodiment of the invention cleverly connects the anti-sway plate, i.e., the fan-shaped plate 1, to the tank structure by setting an independent arc-shaped mounting plate 2 as an installation interface. The arc-shaped mounting plate 2 is fixedly connected to the fan-shaped plate 1 on one hand, and has a dedicated mounting part 21 for quick insertion on the other. This design achieves modularity of the anti-sway plate assembly, separating and simplifying the manufacturing, transportation, and on-site installation of the anti-sway plate. During installation, simply align the mounting part 21 on the arc-shaped mounting plate 2 and insert it into the pre-fabricated fixing part 42 on the cylinder section's mesh reinforcement, then insert the connector 3 to lock it in place. This avoids cumbersome on-site welding or numerous bolt connections, improving assembly efficiency and accuracy, while also facilitating subsequent maintenance and replacement. Furthermore, the arc-shaped mounting plate 2, as an independent assembly unit, can be fine-tuned during assembly with the sector plate 1, or its own flexible absorption portion can be used to create tolerances, ensuring that multiple mounting parts 21 can be smoothly aligned and inserted with the fixing parts 42 on the grid rib 4 simultaneously. The arc-shaped mounting plate 2 and its mounting parts 21 bear the concentrated loads (such as the shearing and crushing of the pins) during the installation and disassembly process, avoiding these loads from acting directly on the anti-sway panel of the sector plate 1, thus improving the reliability and durability of the overall structure.

[0024] like Figures 1 to 3 As shown, in an optional embodiment of the present invention, the mounting part 21 includes: an outwardly protruding positioning protrusion, wherein the positioning protrusion has a second mounting opening 22 formed in the central region.

[0025] In this embodiment, the arc-shaped mounting plate 2 faces away from the edge of the fan-shaped plate and protrudes outward with multiple mounting portions 21. Each mounting portion 21 is preferably a locally stamped protrusion or welded reinforcing block. The size and position of the positioning protrusion precisely correspond to the fixing portion 42 on the mesh reinforcement 4.

[0026] like Figure 7 and Figure 8 As shown, the fixing part 42 includes a positioning groove, and the two sides of the edge of the positioning groove are provided with symmetrical first mounting ports 43.

[0027] In this embodiment, the central area of ​​the horizontal ribs of the mesh rib 4 is recessed inward to form an elongated fixing part 42. Each fixing part 42 is preferably a positioning groove formed by a partial indentation. The size and position of the positioning groove correspond to the size and position of the positioning protrusion of the arc-shaped mounting plate 2 for precise connection. The two side walls of the positioning groove are recessed inward to form two opposing first mounting openings 43.

[0028] like Figure 5 As shown, the junction of the first locking part 32 and the rod part 31 has a radially protruding locking platform 321.

[0029] In this embodiment, the junction of the first locking part 32 and the rod part 31 has a radially protruding locking platform 321. The cross-section of the rod part 31 is polygonal and adapted to the shape of the second mounting port 22 to prevent the connector 3 from rotating. The first locking part 32 of the connector 3 can also be designed as a polygonal shape adapted to the shape of the first mounting port 43 to provide additional anti-rotation protection. The second mounting port 22 is slightly smaller than the first mounting port 43.

[0030] The positioning protrusion is inserted into the positioning groove; the rod portion 31 passes through the aligned second mounting port 22 and the first mounting port 43 on one side of the positioning groove; the first locking portion 32 passes through the first mounting port 43 on the other side wall of the positioning groove; the locking platform 321 engages with the surface of the positioning protrusion; and the second locking portion 33 of the connector 3 engages with the other side wall of the positioning groove. Specifically, the locking platform 321 engages with the surface of the positioning protrusion for radial limiting, and the second locking portion 33 of the connector 3 engages with the end face of the first mounting port 43 on the other side wall of the positioning groove for axial limiting.

[0031] In this embodiment, the connector 3 can be a pin, and the connector 3 can be riveted to connect the fixing part 42 and the mounting part 21. The arc-shaped mounting plate 2 and the fan-shaped plate 1 are connected by riveting. Each mounting part 21 of the arc-shaped mounting plate 2 is inserted into the corresponding fixing part of the grid rib 4, that is, the positioning protrusion is inserted into the corresponding positioning groove. The connector 3 at this time includes a rod part 31 and a first locking part 32. One end of the rod part 31 passes through the first mounting port 43 on one side of the positioning groove, the second mounting port 22 of the positioning protrusion, and the first mounting port 43 on the other side of the positioning groove. The first locking part 32 passes through the first mounting port 43 on one side of the positioning groove. The mounting plate 321 engages with the mounting opening 43 on one side of the positioning groove. The first locking part 32 engages with the first mounting opening 43 on the other side of the positioning groove. A section of the rod protruding from the first mounting opening 43 on the other side of the positioning groove forms a second locking part 33 under the action of a riveting tool, which engages with the outer wall of the first mounting opening 43. This achieves a fastening connection between the fixing part 42 and the mounting part 21. The first locking part 32 fully engages with the first mounting opening 43 on one side of the positioning groove, restricting the radial movement of the anti-sway plate assembly. The second locking part 33 engages with the outer wall of the first mounting opening 43 on the other side of the positioning groove, restricting the axial movement of the anti-sway plate assembly. In this embodiment, the connector 3 connects the anti-sway plate assembly and the cylindrical section, making disassembly and assembly simple and avoiding the increase in weight due to welding and the deformation of the anti-sway plate assembly.

[0032] In another embodiment of the present invention, the fixing part can be disposed on the arc-shaped mounting plate 2, and the mounting part can be disposed on the mesh reinforcement 4. In another embodiment, the fixing part and the mounting part can adopt the above-described structural method, with a change in their placement. Similarly, the fixing part and the mounting part can be connected by the connector 3, which also constrains the radial and axial degrees of freedom of the anti-sway plate assembly relative to the cylinder segment.

[0033] like Figure 7 As shown, in an optional embodiment of the present invention, the mesh reinforcement 4 has horizontally and vertically intersecting ribs to form a distribution along the circumferential and axial directions on the inner wall of the cylinder section. The fixing part 42 is disposed on the horizontal rib 41 and is arranged at intervals along the horizontal direction.

[0034] In this embodiment, the mesh reinforcement 4 includes: horizontal reinforcement 41 and vertical reinforcement 44 arranged in a cross pattern. The fixing part 42 is disposed on the horizontal reinforcement 41 of the mesh reinforcement 4. The positioning protrusion is inserted into the positioning groove. The edges of the arc-shaped mounting plates 2 on both sides of the positioning protrusion have gaps with the horizontal reinforcement, and the liquid in the storage tank can flow through the gaps.

[0035] like Figures 4 to 6 As shown, in an optional embodiment of the present invention, the cross-section of the rod 31 is a polygon adapted to the second mounting port 22.

[0036] In this embodiment, the cross-sectional dimension of the first locking part 32 is larger than that of the rod part 31. The cross-sectional shape of the first locking part 32 is a polygon adapted to the first mounting opening 43. The second locking part 33 is perpendicular to the rod part 31 and extends horizontally. Specifically, the cross-section of the first locking part 32 is an axisymmetric polygon; the cross-sectional shape of the rod part 31 is a polygon formed by dividing the cross-sectional shape of the first locking part 32 along its axis of symmetry. Figure 11 and Figure 14 As shown, the cross-section of the first locking part 32 can be an isosceles trapezoid, the first mounting port 43 can be an isosceles trapezoid adapted to the first locking part 32, the cross-section of the rod part 31 can be half a right trapezoid of the first locking part 32, and the second mounting port 22 can be a right trapezoid adapted to the rod part.

[0037] like Figure 15 As shown, in an optional embodiment of the present invention, it further includes: a traction component 5, which is arranged along the axial direction of the cylindrical section and connects at least two of the sector plates 1 located at the same or similar circumferential positions and at different heights.

[0038] In this embodiment, the traction component 5 connects the fan-shaped plates at different heights to constrain their axial displacement and achieve synergistic suppression of vertical liquid sloshing modes. Two fan-shaped plates 1 can be cross-connected by at least two traction components 5. The traction component 5 can be a tension wire.

[0039] In an optional embodiment of the present invention, the anti-sway plate assemblies are arranged in staggered layers along the axial direction of the cylinder section, and the axial installation spacing H between two adjacent layers of anti-sway plate assemblies is... plate Standard axial node spacing H of the mesh reinforcement rib satisfy: , where n is a positive integer.

[0040] In this embodiment, the standard axial node spacing of the mesh reinforcement can be the distance between the center lines of two adjacent horizontal reinforcement bars of the mesh reinforcement 4.

[0041] In an optional embodiment of the present invention, the ratio r / R of the radius r of the sector plate 1 to the inner radius R of the cylindrical section of the storage tank ranges from 0.2 to 0.35.

[0042] In this embodiment, preferably, the ratio r / R of the radius r of the sector plate 1 to the inner radius R of the tank section is 0.25; the sector plate 1 is a semi-circular plate, and its thickness can be 1.5mm. The sector plate 1 is the main anti-sway structure of the anti-sway plate assembly. In this embodiment, the first layer of sector plates 1 can be set on the first and second quadrant lines of the cross-section of the tank section. The position of each quadrant can be determined according to the actual situation. The first layer is close to the top of the tank, and the layers are sequentially layered towards the bottom of the tank. The second layer of sector plates 1 is set on the third and fourth quadrant lines at a preset distance from the first layer. The subsequent layers (standard positions) are all installed alternately in quadrants at a preset distance. This preset distance can be 480mm.

[0043] In an optional embodiment of the present invention, reinforcing vortices 11 are respectively provided on both sides of the fan-shaped plate 1 along the axis of symmetry; T-shaped reinforcing ribs 12 riveted to the fan-shaped plate 1 are provided on the axis of symmetry, and L-shaped reinforcing ribs 13 riveted to the fan-shaped plate 1 are provided on the outer side of the reinforcing vortices 11; the depth L of the reinforcing vortex 11 and the height H of the T-shaped reinforcing ribs 12 are... t and the height H of L-shaped reinforcing rib 13 l All are less than 15mm.

[0044] The anti-sway plate of this embodiment has a short processing cycle, a small height of the reinforcing rib structure, and a smaller product weight, which is beneficial for weight reduction.

[0045] In this embodiment, the fan-shaped plate 1 is symmetrically provided with reinforcing vortices 11 that are recessed to one side along the radial direction; two L-shaped and T-shaped stringers are respectively provided on the outer side of the reinforcing vortex 11 and between the two reinforcing vortices. These stringers are reinforcing ribs, which are riveted and fixed to the sector plate 1 to improve its bending stiffness. This reinforcing vortex structure, by forming regularly distributed curved surface concave-convex shapes, effectively improves the out-of-plane stiffness and buckling resistance of the sector plate without significantly increasing its thickness and mass. This allows it to withstand the fluid pressure and sway load within the tank, enhancing the lightweight and high reliability of the anti-sway plate. The height of each reinforcing rib and the depth of the reinforcing vortex 11 are both less than 15mm. By limiting the height / depth of the reinforcing structure to within 15mm, sufficient structural stiffness is ensured while minimizing weight increase and avoiding excessive disturbance to the liquid flow within the tank. The anti-sway plate assembly in this embodiment includes: an arc-shaped mounting plate 2, a fan-shaped plate 1, and stringers. The anti-sway plate meets the internal surface pressure requirements of the storage tank and can effectively solve the problem of propellant swaying during rocket flight; it simplifies the assembly process and reduces the use of standard parts; the axial displacement between each layer of anti-sway plate is constrained by tension wires, reducing the number of tension wires; the anti-sway plate is fixed by riveting with connectors 3, reducing the welded thickening area and facilitating the weight reduction design of the rocket body.

[0046] like Figure 16As shown, another embodiment of the present invention provides a method for determining the parameters of a liquid rocket propellant tank, comprising: Step S10: Obtain the structural parameters and sway suppression performance constraint data of the target tank, wherein the structural parameters of the target tank include: the inner radius R of the target tank's cylindrical section, and the axial standard node spacing H of the internal mesh reinforcement. rib The sloshing suppression performance constraint data includes: the maximum permissible amplitude S of liquid sloshing. max The target mass M of the anti-sway plate assembly target (or target weight loss percentage).

[0047] Step S20: Based on the structural parameters of the target tank, establish a fluid dynamics model and obtain simulation results. The simulation results include the dominant sloshing mode data and energy distribution region data of the liquid in the tank.

[0048] Step S30: Determine the layout data of sector plate 1 based on the simulation results.

[0049] Step S40: Based on the layout data and sway suppression performance constraint data of the sector plate, with the optimization goal of suppressing liquid swaying and controlling the coefficient weight of the anti-sway plate, determine the key dimensional parameters of the anti-sway plate assembly; the key dimensional parameters include at least the sector plate radius r and thickness t.

[0050] Step S50: Output the layout data of the sector plate and the key dimension parameters of the anti-sway plate assembly.

[0051] In step S10 of this embodiment, the structural parameters of the target tank are obtained. The structural parameters of the target tank mainly include: the inner radius R of the cylindrical section of the target tank, and the axial standard node spacing H of the internal mesh reinforcement. rib The axial standard node spacing H of the internal mesh reinforcement. rib This refers to the nominal distance between the corresponding installation reference surfaces of two adjacent horizontal reinforcing bars along the axial direction of the cylinder section. In actual engineering, this distance is usually taken as the distance between the center lines of adjacent horizontal reinforcing bars. Axial installation spacing of the anti-sway plate ( That is, planning is based on this standard node spacing to meet the requirements. n is a positive integer, thus enabling modular matching and installation with the internal structure of the storage tank.

[0052] In step S20, a three-dimensional fluid dynamics model of the liquid inside the target tank is established based on computational fluid dynamics (CFD) methods and the structural parameters of the tank (such as inner radius R, liquid level, etc.). After setting the corresponding boundary and initial conditions, numerical methods such as the finite volume method and finite element method are used to solve the model to simulate the sloshing response of the liquid under excitation. Those skilled in the art can use open-source CFD software to complete this simulation. By post-processing the simulation results (such as velocity field, pressure field) (such as modal analysis, energy integration), the dominant sloshing modes of the liquid inside the tank (such as the first-order transverse sloshing frequency) and the corresponding energy spatial distribution data (such as identifying 'antinodes' and 'nodal regions') can be extracted. The dominant sloshing modes and energy distribution data of the liquid inside the tank mentioned in step S20 refer to the spatial range where the liquid sloshing energy is most concentrated, identified based on the flow field information (such as velocity field, pressure field) obtained from the simulation. For example, for a first-order transverse sway mode, its energy is usually concentrated and symmetrically distributed in two opposite quadrants (such as quadrants I and III), which are called 'antinode regions'; while in the other two quadrants perpendicular to it (quadrants II and IV), the energy is lower and is called 'node regions'.

[0053] In step S30, the layout data is that the fan-shaped plates are arranged in a staggered, confined manner on at least two different height layers of the cylinder section, and the axial installation spacing H between two adjacent layers of fan-shaped plates is... plate Satisfying Relationships Where n is a positive integer; the installation position of the anti-sway plate is uniquely determined by the position of the fixing part 42 on the mesh reinforcement, and the axial installation spacing between two adjacent anti-sway plates ( ) and the standard axial node spacing of the mesh reinforcement ( )satisfy: , where n is a positive integer, meaning the anti-sway plates are installed according to the modular spacing of the mesh reinforcement. Based on the energy distribution region of the identified dominant liquid swaying mode, the layout rule for the sector plates is determined as follows: the first layer of anti-sway plates is placed in one or more quadrants where the energy is most concentrated (e.g., if the energy of the first-order transverse swaying mode is concentrated in quadrants I and II, then the first layer of anti-sway plates is placed in this region) to directly consume swaying energy; the next layer of anti-sway plates is staggered in one or more quadrants with lower energy (e.g., quadrants III and IV) to disrupt the symmetry of the swaying. The axial installation spacing between two adjacent layers of anti-sway plates. The standard axial node spacing of the mesh reinforcement satisfy: , where n is a positive integer.

[0054] In step S40 of this embodiment, the key dimensional parameters also include: the ratio r / R of the sector radius r to the tank section radius R satisfies: greater than or equal to 0.2 and less than or equal to 0.35. The optimization objective in step S40 is achieved through a multi-objective optimization function, and the specific process includes: By iteratively designing the variables X = [r, t, ...], the comprehensive objective function F(X) is minimized. F ( X The expression for ) is: , in, The value represents the amplitude or energy of liquid sloshing obtained through simulation; the smaller the value, the better the sloshing suppression effect. The total mass of the anti-sway panel assembly; These are reference values ​​for sway suppression performance indicators and sway barrier component quality indicators, respectively. The indicator values ​​corresponding to the initial design scheme can be selected, or target values ​​set according to task requirements; , ; , These are weighting coefficients, and they satisfy... .

[0055] X = [r, t, ...], including: r representing the radius of the sector plate, t representing the thickness of the sector plate, R representing the inner radius of the cylinder section, ρ representing the density of the sector plate, and H... rib This indicates the standard spacing of the storage tank mesh reinforcement. This represents the axial installation spacing between two adjacent anti-sway panels. The radius r and thickness t of the sector-shaped panel are variables to be optimized. It is a strong constraint, with n as one of the discrete design variables. The design variable X = [r, t, n, ...], where n represents the integer of the installation layer spacing, i.e., a complete set of parameters that needs to be determined by the method.

[0056] Optimization goal: Minimize. In step S40, the design variable X includes: the sector radius r of the anti-sway plate, the plate thickness t, and an integer n representing the spacing between installation layers. Wherein, n satisfies... The optimization process involves satisfying the strength constraint σ. max Under the premise of (X)≤[σ] and geometric constraints 0.2R≤r≤0.35R, the comprehensive objective function F(X) is minimized by iteratively designing the variable X=[r,t,n].

[0057] S ( XThe sloshing intensity (SHI) is a performance index obtained through fluid dynamics simulation calculations and used to quantitatively evaluate the sloshing suppression effect. This index can be the maximum amplitude of liquid sloshing, average kinetic energy, modal energy at a specific frequency, or other physical quantities that characterize the intensity of sloshing. It is a function of variables such as r and n and needs to be obtained through simulation. S ( X This refers to a quantitative indicator used to evaluate the sloshing suppression effect, obtained through fluid dynamics simulation calculations (e.g., solving the Navier-Stokes equations using the finite volume method) under given design variables X (such as r and t). This indicator can be the maximum sloshing amplitude of the liquid in the tank, the average kinetic energy, or the modal energy at a specific frequency, etc.

[0058] M(X) is the system mass, a function of variables such as r, t, and n and the material density, and can be calculated directly. M(X) represents the total mass of the anti-sway panel assembly, and its value can be obtained from the design variables X (such as the anti-sway panel radius r, panel thickness t, and material density ρ) and geometry through conventional physical calculations (such as mass = volume × density).

[0059] When optimizing the target, structural strength constraints must also be met. This means that when optimizing and determining parameters such as the thickness t of the anti-sway plate, it is necessary to ensure that the maximum working stress generated by the anti-sway plate under the expected fluid load does not exceed the allowable stress [σ] of its material (such as aluminum alloy). This can be verified through conventional mechanical calculations or simulations. Constraints include (prerequisites that must be met): Strength constraint: σ max (X)≤[σ](Working stress≤Allowable stress); Geometric constraint: 0.20R≤r≤0.35R (i.e. 0.20≤r / R≤0.35); Matching constraint: (This is a strong constraint that directly eliminates one degree of freedom.)

[0060] Optimization objective function inputs (environment and constraints): R (tank size), H rib (Stiffener spacing), task requirements (such as maximum allowable sway amplitude), anti-sway plate material properties (density, allowable stress [σ]).

[0061] The radius *r* and thickness *t* of the sector plate are the variables to be optimized. The radius *r* directly affects the sway suppression effect *S(X)* and the system mass *M(X)*. The thickness of the sector plate, under the strength constraint, aims to find the thinnest, weight-reducing thickness. It primarily affects the system mass *M(X)* and the strength constraint. The inner radius *R* of the cylinder segment is used to define the dimensionless optimization variable *r / R*.

[0062] During the optimization process, the value of the plate thickness t must ensure that the anti-sway plate meets the strength constraint, that is, its maximum working stress does not exceed the allowable stress of the material (such as aluminum alloy). This can be verified by conventional static calculations or finite element analysis.

[0063] The requirement to meet structural strength constraints refers to the working stress σ of the anti-sway plate under all expected operating conditions (such as maximum acceleration and fluid impact). max The stress must not exceed the allowable stress [σ] of its constituent materials.

[0064] In the optimization method, this condition is manifested as a lower boundary constraint on the design variable (such as plate thickness t), that is, the optimized plate thickness t must ensure that the maximum working stress σ max ≤[σ] holds true.

[0065] Step S50 outputs one or more sets of sector layout data and key dimension parameters of the anti-sway plate components that conform to the rules, and verifies whether the anti-sway effect meets the preset requirements through simulation.

[0066] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A liquid rocket propellant tank, characterized in that, include: The cylindrical section has a mesh reinforcement (4) on its inner sidewall. The mesh reinforcement (4) has multiple fixed parts (42) spaced apart in the horizontal target area. Each fixed part (42) has a first mounting port (43). The anti-sway baffle assembly installed on the cylindrical section includes: The fan-shaped plate (1) has an inner arc edge that matches the curvature of the inner wall of the cylindrical section; The arc-shaped mounting plate (2) has a curvature that matches the curvature of the inner wall of the cylindrical section and is at least partially overlapped and riveted to the inner arc edge of the fan-shaped plate (1); the arc-shaped mounting plate (2) is formed with a plurality of mounting parts (21) corresponding to the fixing part (42) at intervals, and each mounting part (21) is formed with a polygonal second mounting opening (22). The connector (3) has a rod (31) and a first locking part (32) and a second locking part (33) respectively disposed at both ends of the rod (31). The fixing part (42) is detachably inserted into the mounting part (21), the second mounting port (22) is aligned with the corresponding first mounting port (43), the rod part (31) passes through the aligned first mounting port (43) and the second mounting port (22), and the cross-sectional shape of the rod part (31) is adapted to the second mounting port (22) to form an anti-rotation fit; the first locking part (32) and the second locking part (33) are respectively engaged with the mounting part (21) and the fixing part (42) to jointly constrain the anti-sway plate assembly to move axially and radially relative to the cylinder section.

2. The liquid rocket propellant tank according to claim 1, characterized in that, The mounting part (21) includes: an outwardly protruding positioning protrusion, wherein the second mounting opening (22) is formed in the central area of ​​the positioning protrusion. The fixing part (42) includes: a positioning groove, and the two sides of the edge of the positioning groove are provided with opposing first mounting ports (43). The junction of the first locking part (32) and the rod part (31) has a radially protruding locking plate (321). The positioning protrusion is inserted into the positioning groove; the rod (31) passes through the aligned second mounting port (22) and the first mounting port (43) on one side of the positioning groove; the first locking part (32) passes through the first mounting port (43) on the other side wall of the positioning groove; the locking platform (321) engages with the surface of the positioning protrusion; and the second locking part (33) engages with the outer side wall of the positioning groove.

3. The liquid rocket propellant tank according to claim 2, characterized in that, The cross-section of the rod (31) is a polygon adapted to the second mounting port (22).

4. The liquid rocket propellant tank according to claim 1, characterized in that, The mesh reinforcement (4) has horizontally and vertically intersecting reinforcement bars; The fixing part (42) is disposed on the horizontal rib (41) and arranged at intervals along the horizontal direction.

5. The liquid rocket propellant tank according to claim 3 or 4, characterized in that, Also includes: The traction component (5) is arranged along the axial direction of the cylindrical section and connects at least two of the sector plates (1) located at the same or similar circumferential positions and at different heights.

6. The liquid rocket propellant tank according to claim 5, characterized in that, The anti-sway baffle assemblies are arranged in staggered layers along the axial direction of the cylinder section, with an axial installation spacing H between adjacent layers of anti-sway baffle assemblies. plate Standard axial node spacing H of the mesh reinforcement rib satisfy: , where n is a positive integer.

7. The liquid rocket propellant tank according to any one of claims 1 to 4, characterized in that, The ratio of the radius r of the sector plate (1) to the inner radius R of the cylinder section, r / R, ranges from 0.2 to 0.

35.

8. The liquid rocket propellant tank according to any one of claims 1 to 4, characterized in that, The fan-shaped plate (1) has reinforcing vortices (11) on both sides of the axis of symmetry; T-shaped reinforcing ribs (12) riveted to the fan-shaped plate (1) are provided on the axis of symmetry, and L-shaped reinforcing ribs (13) riveted to the fan-shaped plate (1) are provided on the outer side of the reinforcing vortex (11). The depth L of the reinforcing vortex (11) and the height H of the T-shaped reinforcing rib t The height H of the L-shaped reinforcing rib l All are less than 15mm.

9. A method for determining parameters of a liquid rocket propellant tank, characterized in that, Applied to the liquid rocket propellant tank according to any one of claims 1 to 8, comprising: Obtain the structural parameters and sway suppression performance constraint data of the target tank. The structural parameters of the target tank include the inner radius R of the tank's cylindrical section and the axial standard node spacing H of the internal mesh reinforcement. rib The sloshing suppression performance constraint data includes: the maximum allowable amplitude S of liquid sloshing. max The target mass M of the anti-sway plate assembly target ; Based on the structural parameters of the target tank, a fluid dynamics model is established, and simulation results are obtained. The simulation results include the dominant sloshing mode data and energy distribution region data of the liquid in the tank. Based on the simulation results, the layout data of the sector plate (1) is determined; Based on the layout data and sway suppression performance constraint data of the sector plate (1), with the optimization goal of suppressing liquid sloshing and controlling the coefficient weight of the anti-sloshing plate, the key dimension parameters of the anti-sloshing plate assembly are determined; the key dimension parameters include at least the sector plate radius r and thickness t. Output the layout data of the sector plate (1) and the key dimensional parameters of the anti-sway plate assembly.

10. The method for determining the parameters of a liquid rocket propellant tank according to claim 9, characterized in that, The optimization objective is achieved through a multi-objective optimization function, and the specific process includes: By iteratively designing the variables X = [r, t, ...], the comprehensive objective function F(X) is minimized. The expression for the comprehensive objective function F(X) is: ， in, The amplitude or energy index of liquid sloshing obtained through simulation; The total mass of the anti-sway panel assembly; These are reference values ​​for the sway suppression performance index and the sway protection panel component quality index, respectively. , These are weighting coefficients, and they satisfy... .

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