Rocket propellant storage tank rear bottom structure, propellant storage tank and liquid rocket

Abstract

The invention provides a rocket propellant storage tank rear bottom structure, a propellant storage tank and a liquid rocket. The rocket propellant storage tank rear bottom structure comprises a storage tank rear bottom, a tunnel connector, a plurality of outflow flanges, an anti-collapse cover plate, a filter screen and a plurality of vortex eliminating fin plates. The tunnel connector is located in the center of the storage box rear bottom, and the multiple outflow flanges are arranged on the storage box rear bottom and distributed around the tunnel connector in a circumferential mode. The outer contour of the anti-collapse cover plate is connected with the inner wall of the rear bottom of the storage box; the inner contour of the filter screen is connected with the tunnel joint, and the outer contour of the filter screen is connected with the inner contour of the anti-collapse cover plate; the plurality of vortex eliminating fin plates are circumferentially distributed around the tunnel joint, the vortex eliminating fin plates are arranged below the anti-sloughing cover plate and the filter screen, and the bottom edges of the vortex eliminating fin plates are connected with the inner molded surface of the rear bottom of the storage box in an attached mode. The outflow device is integrally designed, has vortex eliminating, collapse preventing and propellant filtering functions, is compact in system structure, reasonable in overall layout, good in stability and high in maintainability, and meets general design requirements.

Description

Technical Field

[0001] The invention relates to the technical field of rocket engine devices, and in particular to a rocket propellant tank rear bottom structure, a propellant tank and a liquid rocket. Background Art

[0002] In recent years, with the development of commercial aerospace, liquid rockets with multiple engines in parallel have become a development trend. This type of rocket needs to install a corresponding number of oxidizer delivery pipes and fuel delivery pipes according to the number of engines. The oxidizer or fuel flows to the corresponding delivery pipe through the outlet flange at the bottom of the tank and finally enters the rocket engine. When the propellant liquid surface is close to the outlet flange, concave and vortex flow will occur, which will cause propellant air entrainment and pressure loss, causing the engine to fail to work normally or even explode.

[0003] In addition, foreign matter, especially metal impurities, will damage the turbo pump after entering the engine with the propellant, leading to the failure of the rocket launch mission. In order to avoid propellant depression, suppress the generation of vortexes and filter propellant impurities, anti-collapse covers, vortex-eliminating blades and filters are usually installed near the inlet of the outflow flange to improve the outflow effect. However, due to the multi-machine parallel structure of liquid rockets, the number of outflow flanges is large (N≥5), so it is necessary to install vortex-eliminating, anti-collapse and filtering structures near the inlet of all outflow flanges, which will lead to low structural efficiency, poor stability, and inconvenience in installation, increasing the development and production costs. Summary of the invention

[0004] In view of this, the purpose of the embodiments of the present invention is to provide a rocket propellant tank rear bottom structure, a propellant tank and a liquid rocket. The tank rear bottom structure adopts an integrated design, which has the functions of eliminating vortex, preventing collapse and filtering. It has a simple and compact structure, good overall rigidity, strong maintainability, meets general design requirements, and has low development cost.

[0005] To achieve the above-mentioned purpose, in a first aspect, an embodiment of the present invention provides a rocket propellant tank rear bottom structure, comprising: a tank rear bottom, a tunnel joint, a plurality of outflow flanges, an anti-collapse cover plate, a filter screen and a plurality of vortex elimination fin plates;

[0006] The tunnel joint is located at the center of the rear bottom of the tank, a plurality of outflow flanges are arranged on the rear bottom of the tank and are distributed in a circumference around the tunnel joint, and the anti-collapse cover plate and the filter screen are both located above the outflow flanges;

[0007] The outer contour of the anti-collapse cover plate is connected to the inner wall of the rear bottom of the tank;

[0008] The inner contour of the filter screen is connected to the tunnel joint, and the outer contour of the filter screen is connected to the inner contour of the anti-collapse cover plate;

[0009] A plurality of the swirl eliminating fins are circumferentially distributed around the tunnel joint. The swirl eliminating fins are arranged below the anti-collapse cover plate and the filter net. The bottom edge of the swirl eliminating fin is in fitting connection with the inner surface of the rear bottom of the storage tank.

[0010] In some possible embodiments, the rear bottom structure of the rocket propellant storage tank further includes: a plurality of connecting plates;

[0011] The connecting plates extend along the direction from the tunnel joint to the inner wall of the rear bottom of the storage tank. Moreover, the connecting plates are arranged above the swirl eliminating fins, and a plurality of the connecting plates are circumferentially distributed around the tunnel joint;

[0012] The swirl eliminating fins, the anti-collapse cover plate and the filter net are all connected to the connecting plates.

[0013] In some possible embodiments, the anti-collapse cover plate includes a plurality of fan-shaped cover plates, and the plurality of fan-shaped cover plates are circumferentially distributed around the tunnel joint. Two adjacent fan-shaped cover plates are connected to the same connecting plate; and / or,

[0014] The filter net includes a plurality of fan-shaped filter meshes, and the plurality of fan-shaped filter meshes are circumferentially distributed around the tunnel joint. Two adjacent fan-shaped filter meshes are connected to the same connecting plate.

[0015] In some possible embodiments, the same connecting plate is respectively connected to the swirl eliminating fin, two adjacent fan-shaped cover plates and two adjacent fan-shaped filter meshes.

[0016] In some possible embodiments, the inner edge of the swirl eliminating fin is connected to the tunnel joint through a U-shaped bracket. The U-shaped bracket includes a vertical part and horizontal parts located at the upper and lower ends of the vertical part. The vertical part is fixedly connected to the swirl eliminating fin, and the horizontal parts are fixedly connected to the tunnel joint.

[0017] In some possible embodiments, the side wall of the tunnel joint is provided with an upper step portion and a lower step portion, and the two horizontal parts are respectively fixedly connected to the upper step portion and the lower step portion.

[0018] In some possible embodiments, the fan-shaped filter mesh is arranged above the upper step portion, and the connecting plate is located above the fan-shaped filter mesh;

[0019] The top of the swirl eliminating fin is fixedly connected to the connecting plate, and the bottom of the swirl eliminating fin is fixedly connected to the rear bottom of the storage tank.

[0020] In some possible embodiments, the inner contour of the fan-shaped cover plate and the outer contour of the fan-shaped filter mesh are both arc-shaped;

[0021] The inner contour of the fan-shaped cover plate is provided with a first flange that turns up, and the outer contour of the fan-shaped filter screen is provided with a second flange that turns up, and the first flange and the second flange are fixed together.

[0022] In some possible implementations, the number of the outflow flanges is N, where N≥9;

[0023] The outflow flange is used to output propellant to the rocket engine in a one-to-one correspondence.

[0024] In some possible implementations, the arc length and radius of the large arc side of the fan-shaped annular cover plate are determined according to the elliptical inner surface parameters of the rear bottom of the tank and the distribution height of the outflow flange, and the determination formula is as follows:

[0025] r=(a / b)*sqrt(2bh-h 2 );

[0026] l = r * α;

[0027] Among them, r is the radius of the large arc side of the fan-shaped cover plate, l is the arc length of the large arc side of the fan-shaped cover plate, α is the angle of the fan-shaped cover plate, h is the distribution height of the outflow flange, a is the major semi-axis of the ellipse, and b is the minor semi-axis of the ellipse.

[0028] In some possible implementations, in the vertical downward projection direction of the fan-shaped annular cover plate, the small arc edge of the fan-shaped annular cover plate covers the outflow port of the outflow flange.

[0029] In a second aspect, the present invention provides a rocket propellant tank, comprising a rocket propellant tank rear bottom structure as described in the first aspect.

[0030] In a third aspect, the present invention provides a liquid rocket with multiple parallel engines, the liquid rocket comprising a rocket propellant tank rear bottom structure as described in the first aspect.

[0031] The beneficial technical effects of the above technical solution are:

[0032] 1. The integrated design of the outflow device combines the functions of vortex elimination, anti-collapse and propellant filtering; at the same time, the outflow device system has a compact structure, a reasonable overall layout, good stability and strong maintainability, which meets the general design requirements and reduces production costs; 2. The filter screen and the anti-collapse cover are located on the same horizontal plane of the bottom of the box, which reduces the area of ​​the filter screen. At the same time, the two are connected to make the stability of the local structure better;

[0033] 3. The anti-vortex fin plate is arranged under the fan annular filter and the fan annular cover plate, which can meet the function of propellant anti-vortex, will not increase the gap between two adjacent fan annular filters, and will not affect the propellant filtration;

[0034] 4. The swirl dissipating vane can also provide support for the fan-shaped filter screen and the fan-shaped cover plate, enhancing the overall structural stiffness.

[0035] 5. Multiple outflow flanges are evenly arranged on the rear bottom of the storage tank, which can meet the liquid rocket propellant delivery requirements of multiple parallel engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required in the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0037] Figure 1 is the overall structural schematic diagram of an integrated outflow device for the rear bottom of a rocket propellant storage tank according to an embodiment of the present invention;

[0038] Figure 2 is the relationship diagram between the arc length and radius of the large arc edge of the fan-shaped anti-collapse cover plate and the parameters of the elliptical inner surface in the embodiment of the present invention;

[0039] Figure 3 is Figure 1 the partial enlarged view of.

[0040] Explanation of the reference numerals in the drawings:

[0041] 1. Rear bottom of the storage tank; 2. Anti-collapse cover plate; 2. Fan-shaped cover plate; 211. First flanging; 3. Filter net; 31. Fan-shaped filter screen; 311. Second flanging; 312. Mesh frame; 4. Swirl dissipating vane; 5. Outflow flange; 6. Tunnel joint; 61. Upper step portion; 62. Lower step portion; 7. Connecting plate; 8. Connecting lug; 9. C-shaped bracket; 91. Vertical portion; 92. Horizontal portion; 10. Connecting angle piece. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0042] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In the following detailed description, many specific details are presented to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by showing examples of the present invention. In the drawings and the following description, at least some of the well-known structures and technologies are not shown to avoid unnecessarily obscuring the present invention; and, for clarity, the dimensions of some structures may be exaggerated. In addition, the features, structures, or characteristics described below can be combined in any suitable manner in one or more embodiments.

[0043] like Figure 1 As shown, the rear bottom structure of the rocket propellant tank includes: a tank rear bottom 1, a tunnel joint 6, a plurality of outflow flanges 5, an anti-collapse cover plate 2, a filter screen 3 and a plurality of vortex-eliminating fin plates 4; the tunnel joint 6 is located at the center of the tank rear bottom 1, a plurality of outflow flanges 5 are arranged on the tank rear bottom 1 and are distributed circumferentially around the tunnel joint 6, and the anti-collapse cover plate and the filter screen are both located above the outflow flange 5; the outer contour of the anti-collapse cover plate 2 is connected to the inner wall of the tank rear bottom 1; the inner contour of the filter screen 3 is connected to the tunnel joint 6, and the outer contour of the filter screen 3 is connected to the inner contour of the anti-collapse cover plate 2; a plurality of vortex-eliminating fin plates 4 are distributed circumferentially around the tunnel joint 6, the vortex-eliminating fin plates 4 are arranged below the anti-collapse cover plate 2 and the filter screen 3, and the bottom edge of the vortex-eliminating fin plates 4 is fitted and connected to the inner surface of the tank rear bottom 1.

[0044] In the embodiment of the present invention, the outer contour of the filter screen 3 is connected to the inner contour of the anti-collapse cover plate 2, and the outer contour of the anti-collapse cover plate 2 is connected to the inner wall of the rear bottom 1 of the tank, that is, the filter screen 3, the anti-collapse cover plate 2 and the rear bottom 1 of the tank are connected into an integrated structure, and the vortex-eliminating fin plate 4 is arranged below the anti-collapse cover plate 2 and the filter screen 3, and the bottom edge of the vortex-eliminating fin plate 4 is fit-connected with the inner surface of the rear bottom 1 of the tank, which not only has high structural efficiency but also can improve the stability of the structure; in addition, the inner contour of the filter screen 3 can be directly connected to the tunnel joint 6, which is very convenient for installation; furthermore, the vortex-eliminating fin plate 4 is arranged below the anti-collapse cover plate 2 and the filter screen 3, which can not only play the role of eliminating vortex, but also can support the anti-collapse cover plate 2 and the filter screen 3, thereby further improving the stability of the structure.

[0045] In this embodiment, the bottom edge of the vortex-eliminating fin plate 4 is connected to the rear bottom 1 of the tank through the connecting ear piece 8, rather than directly welded, because the vortex-eliminating fin plate 4 is an aluminum alloy plate, which will cause thermal deformation due to heat input during welding, and the rear bottom 1 of the tank is theoretically an ellipsoidal surface, and there must be deviations in the actual production process, so there is a situation where the vortex-eliminating fin plate 4 and the rear bottom 1 of the tank are not in contact; in this embodiment, the vortex-eliminating fin plate 4 is connected to the connecting ear piece 8 by bolts, which is convenient for the disassembly and repair of the vortex-eliminating fin plate 4, and can also compensate for the errors in the production process of the parts such as the rear bottom 1 of the tank and the vortex-eliminating fin plate 4. In addition, due to the narrow operating space, welding is not easy to operate, and welding will also cause thermal deformation; and because there are defects inside the weld, such as cracks, pore inclusions, etc., it is difficult to detect.

[0046] The embodiment of the present invention not only has the functions of eliminating vortex, preventing collapse and filtering propellant, but also makes the rear bottom structure of the tank compact, the overall layout reasonable, the stability good, the maintainability strong, meets the general design requirements, and reduces the production cost.

[0047] In some embodiments, the rocket propellant tank rear bottom structure further includes: a plurality of connecting plates 7; the connecting plates 7 extend along the tunnel joint 6 in the direction pointing to the inner wall of the tank rear bottom 1, and the connecting plates 7 are arranged above the vortex-eliminating fin plate 4, and the plurality of connecting plates 7 are distributed in a circle around the tunnel joint 6; the vortex-eliminating fin plate 4, the anti-collapse cover plate 2 and the filter screen 3 are all connected to the connecting plates 3. In this embodiment, the vortex-eliminating fin plate 4, the anti-collapse cover plate 2 and the filter screen 3 are connected into an integrated structure through the connecting plates 7, which greatly improves the stability and compactness of the overall structure.

[0048] like Figure 3 As shown, in some embodiments, the anti-collapse cover plate 2 includes a plurality of fan-shaped cover plates 21, the plurality of fan-shaped cover plates 21 are distributed circumferentially around the tunnel joint 6, and two adjacent fan-shaped cover plates 21 are connected to the same connecting plate 7; and / or, the filter screen 3 includes a plurality of fan-shaped filter screens 31, the plurality of fan-shaped filter screens 31 are distributed circumferentially around the tunnel joint 6, and two adjacent fan-shaped filter screens 31 are connected to the same connecting plate 7.

[0049] In an embodiment of the present invention, the number of outflow flanges 5 can be equal to the number of fan-shaped cover plates 21, that is, a fan-shaped cover plate 21 is arranged on each outflow flange 5, and there is an anti-collapse cover plate corresponding to each outflow flange 5, which can fully prevent the air entrapment phenomenon caused by the collapse of the liquid level. In addition, the straight edges of multiple fan-shaped cover plates 21 are connected to each other to form a first ring shape, and the straight edges of multiple fan-shaped filter screens 31 are connected to each other to form a second ring shape. The outer ring edge of the second ring shape is connected to the inner ring edge of the first ring shape, and the two rings are located on the same horizontal plane of the bottom of the box, that is, multiple fan-shaped cover plates 21 and multiple fan-shaped filter screens 31 are on the same plane, which not only reduces the area of ​​the filter screen, but also makes the local structure more stable when the two are connected; the top edge of the vortex-eliminating fin plate 4 is connected to the fan-shaped cover plate 21 and the fan-shaped filter screen 31, and the side edge of the vortex-eliminating fin plate 4 is connected to the tunnel joint 6, that is, multiple fan-shaped cover plates 21, multiple fan-shaped filter screens 31 and several vortex-eliminating fin plates 4 are an integrated structure with the rear bottom 1 of the tank, which not only has the functions of vortex elimination, anti-collapse and propellant filtering; at the same time, it also makes the outflow device system structure compact, the overall layout reasonable, the stability good, the maintainability strong, meets the general design requirements, and reduces the production cost.

[0050] Specifically, the straight edge of the fan-shaped filter 31 can be aligned with the straight edge of the fan-shaped cover plate 21; the straight edges of any two adjacent fan-shaped cover plates 21 and any two adjacent fan-shaped filter screens 31 are connected by a connecting plate 7 (connected by screws in this embodiment). By aligning the straight edge of the fan-shaped filter 31 with the straight edge of the fan-shaped cover plate 21, they can be connected by the same connecting plate 7, reducing the number of connecting parts and improving the compactness of the structure. In addition, due to errors in the manufacture of parts, gaps may exist between adjacent mounting surfaces. If there is a gap, excess impurities in the box will flow into the engine along the gap, affecting the normal operation of the engine and even causing the engine to explode. The installation gap between any two adjacent fan-shaped cover plates 21 and the installation gap between any two adjacent fan-shaped filter screens 31 can also be covered by the connecting plate 7, and the installation gap between any two adjacent fan-shaped cover plates 21 and the installation gap between any two adjacent fan-shaped filter screens 31 can also be used to adjust the assembly error.

[0051] like Figure 3 As shown, in some embodiments, the same connecting plate 7 is respectively connected to the vortex-eliminating fin plate 4, two adjacent fan-shaped cover plates 21, and two adjacent fan-shaped filter screens 31. In this embodiment, the vortex-eliminating fin plate 4 can be respectively connected to any two adjacent fan-shaped cover plates 21 and any two adjacent fan-shaped filter screens 31 through the connecting plate 7 as an integrated structure, which can not only improve the stability of the structure, but also have the functions of vortex elimination and support.

[0052] In addition, the vortex-eliminating fin plate 4 is arranged below the fan-shaped cover plate 21 and the fan-shaped filter screen 31, so that there is no installation gap between any two adjacent fan-shaped cover plates 21 and the fan-shaped filter screen 31, which does not affect the filtration of the propellant, and at the same time can provide support for the fan-shaped cover plate 21 and the fan-shaped filter screen 31, thereby enhancing the overall structural rigidity. Because if the vortex-eliminating fin plate 4 is not installed below the fan-shaped cover plate 21 and the fan-shaped filter screen 31, it will protrude above the fan-shaped cover plate 21 and the fan-shaped filter screen 31 during installation, so when the straight edges of the two adjacent fan-shaped cover plates 21 are connected, and when the straight edges of the two adjacent fan-shaped filter screens 31 are connected, there will inevitably be an installation gap.

[0053] As an example, the length of the top edge of the anti-vortex fin plate 4 can be equal to the sum of the lengths of the straight edge of the fan-shaped cover plate 21 and the fan-shaped filter screen 31. In this way, it can not only eliminate the vortex, but also fully support and stabilize the fan-shaped cover plate 21 and the fan-shaped filter screen 31.

[0054] In addition, during actual use, although there is no strict requirement for the size of a single aperture, the porosity needs to meet certain requirements. Because too small a porosity will lead to excessive flow resistance, affecting the efficiency of the propellant entering the engine; too large a porosity will not attenuate the vortex velocity well and will cause the strength of the vortex dissipation fin 4 to decay. Therefore, the porosity of the vortex dissipation fin 4 in this embodiment is greater than 20%, which can weaken the vortex energy, dissipate the vortex velocity in a given direction to weaken the local vortex velocity, and will not cause secondary flow. As an example, the porosity in this embodiment is 53% and the aperture is 20 mm.

[0055] As Figure 3 shown, in some embodiments, the inner edge of the vortex dissipation fin 4 is connected to the tunnel joint 6 through a U-shaped bracket 9. The U-shaped bracket 9 includes a vertical portion 91 and horizontal portions 92 located at the upper and lower ends of the vertical portion 81. The vertical portion 91 is fixedly connected to the vortex dissipation fin 4, and the horizontal portions 92 are fixedly connected to the tunnel joint 6.

[0056] Specifically, the vertical portion 91 of the U-shaped bracket 9 is connected to the vortex dissipation fin 4 by screws, and the upper and lower horizontal portions 92 are respectively connected to the tunnel joint 6 by screws. The top edge of the vortex dissipation fin 4 is connected to the connecting plate 7 through a connecting angle piece 10. In this embodiment, by providing the connecting angle piece 10 and the U-shaped bracket 9, it is not only convenient for the installation of the vortex dissipation fin 4, but also convenient for disassembly and maintenance. At the same time, it can also eliminate the errors in the production process of parts such as the vortex dissipation fin 4, the connecting plate 7 and the tunnel joint 6.

[0057] As Figure 3 shown, in some embodiments, the side wall of the tunnel joint 6 is provided with an upper step portion 62 and a lower step portion 62. The two horizontal portions 92 are respectively fixedly connected to the upper step portion 61 and the lower step portion 62. The upper step portion 61 is welded to the cylindrical body of the tunnel joint 6, and its height can be flexibly adjusted according to the actual assembly situation of the product. The lower step portion 62 is an outward-turned edge structure integral with the tunnel joint 6, which has a large load-bearing strength and avoids insufficient strength caused by the heat influence of the weld; the upper and lower horizontal portions 92 of the U-shaped bracket 9 are respectively connected to the step portions 61 and 62 of the tunnel joint 6 by screws.

[0058] In some embodiments, the fan-shaped filter screen 31 is arranged above the upper step portion, and the connecting plate 7 is located above the fan-shaped filter screen 31; the top of the vortex dissipation fin 4 is fixedly connected to the connecting plate 7, and the bottom of the vortex dissipation fin 4 is fixedly connected to the rear bottom 1 of the storage tank.

[0059] As Figure 3As shown, in some embodiments, the inner contour of the fan-shaped cover plate 21 and the outer contour of the fan-shaped filter screen 31 are both arc-shaped; the inner contour of the fan-shaped cover plate 21 is provided with a first flange 211 that is turned up, and the fan-shaped filter screen 31 adopts a structure of a mesh frame 312 and a + filter screen, and the outer contour of the mesh frame 312 is provided with a second flange 311 that is turned up, and the first flange 211 and the second flange 311 are fixed together by screws.

[0060] In some embodiments, the number of outflow flanges 5 is N, where N≥9; the outflow flanges 5 are used to output propellant to the rocket engine in a one-to-one correspondence.

[0061] In this embodiment, several outflow flanges 5 have the same size and are evenly arranged along the elliptical surface of the rear bottom 1 of the tank, which can not only meet the liquid rocket propellant transportation needs of multiple parallel engines, but also meet the universal design requirements due to the same size of the flow flanges, thereby reducing production costs and cycles.

[0062] like Figure 2 As shown, in some embodiments, the arc length and radius of the large arc side of the fan annular cover plate 21 are determined according to the elliptical inner surface parameters of the tank rear bottom 1 and the distribution height of the outflow flange 5, and the determination formula is as follows:

[0063] r=(a / b)*sqrt(2bh-h 2 );

[0064] l = r * α;

[0065] Among them, r is the radius of the large arc side of the fan-shaped cover plate 21, l is the arc length of the large arc side of the fan-shaped cover plate 21, α is the angle of the fan-shaped cover plate 21, h is the distribution height of the outflow flange 5, a is the major semi-axis of the ellipse, and b is the minor semi-axis of the ellipse.

[0066] Specifically, α is determined by the number N of the five outflow flanges. In this embodiment, the angle is 40°. The elliptical inner surface means that the shape of the box bottom is an ellipsoidal surface, which is swept out by an elliptical curve at 360°.

[0067] In some embodiments, in the vertical downward projection direction of the fan-shaped annular cover plate 21 , the small arc edge of the fan-shaped annular cover plate 21 covers the outflow port of the outflow flange 5 .

[0068] Specifically, in order to fully prevent collapse, the small arc edge of the fan-shaped cover plate 21 in the vertical downward projection direction should cover the outlet of the outlet flange 5, so the radius of the small arc edge of the fan-shaped cover plate 21 cannot be too large, but the radius of the small arc edge of the fan-shaped cover plate 21 cannot be too small. If it is too small, the flow resistance will be too large, affecting the flow rate of the propellant flowing into the engine; in addition, the radius of the small arc edge of the fan-shaped cover plate 21 is equal to the radius of the large arc edge of the fan-shaped filter screen 31. According to the requirements of the opening area of ​​the overall power filter screen, the radius of the large arc edge of the fan-shaped filter screen 31 cannot be too small. Too small will also increase the liquid flow resistance. Therefore, in this embodiment, the radius value range of the small arc of the fan-shaped cover plate 21 can be determined according to the size of the outlet flange 5. After the radius value range of the small arc of the fan-shaped cover plate 21 is determined, the arc length of the small arc of the fan-shaped cover plate 21 can be determined according to the angle of the fan-shaped cover plate 21, and then the size of the fan-shaped filter screen 31 can be determined. In addition, in this embodiment, the arc length of the small arc side of the fan-shaped cover plate 21 can also be equal to the arc length of the large arc side of the fan-shaped filter screen 31; the radius of the small arc side of the fan-shaped cover plate 21 is equal to the radius of the large arc side of the fan-shaped filter screen 31, so that the axially adjacent fan-shaped cover plate 21 and fan-shaped filter screen 31, that is, the straight edge of the fan-shaped filter screen 31 can be aligned with the straight edge of the fan-shaped cover plate 21; the straight edges of any two adjacent fan-shaped cover plates 21 and any two adjacent fan-shaped filter screens 31 are connected by the connecting plate 7. It can reduce the number of connecting parts and improve stability.

[0069] The present invention also provides a rocket propellant tank, comprising the above-mentioned rocket propellant tank rear bottom structure.

[0070] The present invention also provides a liquid rocket with multiple parallel engines and the above-mentioned rocket propellant tank rear bottom structure of the liquid rocket.

[0071] Depend on Figure 2 It can be known that the arc length and radius of the large arc side of the fan-shaped cover plate 21 in this embodiment are determined according to the elliptical inner surface parameters of the tank rear bottom 1 and the distribution height of the outflow flange 5, so this embodiment has the characteristic of a large distribution diameter of the outflow flange 5, that is, the liquid rocket in this embodiment has an integrated large-diameter propellant tank rear bottom structure. During use, it is connected to multiple engines respectively through the outflow flanges 5 on the integrated tank rear bottom, and multiple engines are filled at the same time.

[0072] The embodiments of the present invention have the following beneficial technical effects:

[0073] The integrated design of the outflow device of the present invention integrates the functions of vortex elimination, collapse prevention and filtering in one device, thereby reducing structural complexity and optimizing space utilization; and the outflow device has a compact structure and a reasonable layout, which can improve overall stability and durability and facilitate maintenance.

[0074] The present invention can reduce the filter area and improve the stability and working efficiency of the local structure by placing the fan-shaped filter screen 31 and the fan-shaped cover plate 21 on the same horizontal plane.

[0075] The vortex-eliminating fin plate 4 of the present invention not only provides a vortex-eliminating function, but also provides support for the filter screen and the anti-collapse cover plate above it, thereby enhancing the rigidity of the overall structure.

[0076] The outflow flange 5 device of the present invention and the tank rear bottom 1 are standardized and universalized, thereby improving production efficiency and reducing manufacturing and installation costs.

[0077] The present invention can meet the propellant delivery requirements of liquid rockets with multiple parallel engines and has wide applicability.

[0078] The various components of the present invention are connected by bolts or other conveniently designed means for disassembly, which facilitates disassembly and maintenance of the device and improves maintainability.

[0079] The present invention is applicable to liquid rockets with multiple engines connected in parallel, and has significant advantages in cost-effectiveness, operational convenience and system reliability.

[0080] In the description of the embodiments of the present invention, it should be noted that the orientations or positional relationships indicated by the terms "upper, lower, inner and outer" are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first, second or third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0081] In the embodiments of the present invention, unless otherwise clearly specified and limited, the terms "installed, connected, connected" should be understood in a broad sense, for example: it can be a fixed connection, a detachable connection or an integral connection; it can also be a mechanical connection, an electrical connection or a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0082] Although the present invention has been described with reference to preferred embodiments, various modifications may be made thereto and parts thereof may be replaced by equivalents without departing from the scope of the present invention. In particular, the various technical features mentioned in the various embodiments may be combined in any manner as long as there are no structural conflicts. The present invention is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A rocket propellant tank rear bottom structure, characterized in that: Comprising: The rear bottom of the storage tank (1), the tunnel joint (6), several outflow flanges (5), the anti-collapse cover plate (2), the filter screen (3) and several anti-whirl fins (4); The tunnel joint (6) is located at the center of the rear bottom of the storage tank (1), and several of the outflow flanges (5) are arranged on the rear bottom of the storage tank (1) and are circumferentially distributed around the tunnel joint (6); The outer contour of the anti-collapse cover plate (2) is connected to the inner wall of the rear bottom of the storage tank (1); The inner contour of the filter screen (3) is connected to the tunnel joint (6), and the outer contour of the filter screen (3) is connected to the inner contour of the anti-collapse cover plate (2); Several of the anti-whirl fins (4) are circumferentially distributed around the tunnel joint (6), the anti-whirl fins (4) are arranged below the anti-collapse cover plate (2) and the filter screen (3), and the bottom edge of the anti-whirl fins (4) is fittingly connected to the inner surface of the rear bottom of the storage tank (1).

2. A rocket propellant tank rear bottom structure according to claim 1, characterized in that: The rear bottom structure of the rocket propellant storage tank further comprises: a plurality of connecting plates (7); The connecting plates (7) extend in the direction from the tunnel joint (6) towards the inner wall of the rear bottom of the storage tank (1), and the connecting plates (7) are arranged above the anti-whirl fins (4), and a plurality of the connecting plates (7) are circumferentially distributed around the tunnel joint (6); The anti-whirl fins (4), the anti-collapse cover plate (2) and the filter screen (3) are all connected to the connecting plate (3).

3. The rear bottom structure of a rocket propellant storage tank according to claim 2, wherein The anti-collapse cover plate (2) comprises a plurality of fan-shaped cover plates (21), the plurality of fan-shaped cover plates (21) are circumferentially distributed around the tunnel joint (6), and two adjacent fan-shaped cover plates (21) are connected to the same connecting plate (7); and / or, The filter screen (3) comprises a plurality of fan-shaped filter meshes (31), the plurality of fan-shaped filter meshes (31) are circumferentially distributed around the tunnel joint (6), and two adjacent fan-shaped filter meshes (31) are connected to the same connecting plate (7).

4. The rear bottom structure of a rocket propellant storage tank according to claim 3, wherein The same connecting plate (7) is respectively connected to the anti-whirl fin (4), two adjacent fan-shaped cover plates (21) and two adjacent fan-shaped filter meshes (31).

5. The rear bottom structure of a rocket propellant storage tank according to claim 4, wherein The inner edge of the anti-whirl fin (4) is connected to the tunnel joint (6) through a C-shaped bracket (9); The C-shaped bracket (9) comprises a vertical part (91) and horizontal parts (92) located at the upper and lower ends of the vertical part (81), the vertical part (91) is fixedly connected to the anti-whirl fin (4), and the horizontal parts (92) are fixedly connected to the tunnel joint (6).

6. The rear bottom structure of a rocket propellant storage tank according to claim 5, wherein The side wall of the tunnel joint (6) is provided with an upper step portion (62) and a lower step portion (62), and the two horizontal parts (92) are respectively fixedly connected to the upper step portion (61) and the lower step portion (62).

7. A rocket propellant tank rear bottom structure according to claim 6, characterized in that: The fan-shaped annular filter (31) is arranged above the upper step portion (61), and the connecting plate (7) is located above the fan-shaped annular filter (31); The top of the vortex-eliminating fin plate (4) is fixedly connected to the connecting plate (7), and the bottom of the vortex-eliminating fin plate (4) is fixedly connected to the rear bottom (1) of the storage tank.

8. A rocket propellant tank rear bottom structure according to claim 3, characterized in that: The inner contour of the fan-shaped annular cover plate (21) and the outer contour of the fan-shaped annular filter screen (31) are both in the shape of an arc; The inner contour of the fan-shaped annular cover plate (21) is provided with a first flange (211) that is turned up, and the outer contour of the fan-shaped annular filter (31) is provided with a second flange (311) that is turned up, and the first flange (211) and the second flange (311) are fixed together.

9. A rocket propellant tank rear bottom structure according to claim 3, characterized in that: The number of the outflow flanges (5) is N, N≥9; The outflow flange (5) is used to output propellant to the rocket engine in a one-to-one correspondence.

10. A rocket propellant tank rear bottom structure according to claim 3, characterized in that: The arc length and radius of the large arc side of the fan-shaped annular cover plate (21) are determined according to the elliptical inner surface parameters of the tank rear bottom (1) and the distribution height of the outflow flange (5), and the determination formula is as follows: r=(a / b)*sqrt(2bh-h 2 ); l＝r*α； Wherein, r is the radius of the large arc side of the fan-shaped cover plate (21), l is the arc length of the large arc side of the fan-shaped cover plate (21), α is the included angle of the fan-shaped cover plate (21), h is the distribution height of the outflow flange (5), a is the major semi-axis of the ellipse, and b is the minor semi-axis of the ellipse.

11. A rocket propellant tank rear bottom structure according to claim 10, characterized in that: In the vertical downward projection direction of the fan-shaped annular cover plate (21), the small arc edge of the fan-shaped annular cover plate (21) covers the outlet of the outlet flange (5).

12. A rocket propellant tank, characterized in that: The rocket propellant tank comprises a rocket propellant tank rear bottom structure as described in any one of claims 1-11.

13. A liquid rocket with multiple parallel engines, characterized in that: The liquid rocket comprises a rocket propellant tank rear bottom structure as described in any one of claims 1-11.

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