A rocket propellant tank rear bottom structure, a propellant tank and a liquid rocket

Abstract

The application provides a rocket propellant tank rear bottom structure, a propellant tank and a liquid rocket, and the propellant tank rear bottom structure comprises 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 fins; the tunnel joint is located at the center of the tank rear bottom, the plurality of outflow flanges are arranged on the tank rear bottom and are distributed in a circle around the tunnel joint; the outer contour of the anti-collapse cover plate is connected with the inner wall of the tank rear bottom; 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 elimination fins are distributed in a circle around the tunnel joint, the vortex elimination fins are arranged below the anti-collapse cover plate and the filter screen, and the bottom edge of the vortex elimination fins is connected with the inner profile of the tank rear bottom in a fit mode. The outflow device is designed in an integrated mode, has the functions of vortex elimination, anti-collapse and propellant filtering, and has the advantages of compact system structure, reasonable overall layout, good stability, strong maintainability and satisfaction of general design requirements.

Description

Technical Field

[0001] This invention relates to the field of rocket engine device technology, specifically to a rear bottom structure of a rocket propellant tank, a propellant tank, and a liquid rocket. Background Technology

[0002] In recent years, with the development of commercial spaceflight, liquid rockets employing multiple engines in parallel have become a trend. This type of rocket requires a corresponding number of oxidizer and propellant delivery pipes based on the number of engines. The oxidizer or propellant flows through the outlet flange at the bottom of the tank to the corresponding delivery pipe, ultimately entering the rocket engine. When the propellant level is close to the outlet flange, a dip and vortex flow phenomenon occurs. This phenomenon can cause propellant entrainment and pressure loss, preventing the engine from functioning properly and even leading to an explosion.

[0003] Furthermore, foreign matter, especially metallic impurities, can damage the turbopump after entering the engine with the propellant, leading to rocket launch failure. To prevent propellant sagging, suppress vortex generation, and filter propellant impurities, anti-collapse covers, anti-vortex blades, and filters are typically installed near the outlet flange inlet to improve outflow. However, due to the large number of outlet flanges (N≥5) in multi-engine parallel liquid rockets, installing anti-vortex, anti-collapse, and filtering structures near the inlet of all outlet flanges would result in low structural efficiency, poor stability, and inconvenient installation, increasing research and production costs. Summary of the Invention

[0004] In view of this, the purpose of this 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 and has the functions of anti-vortex, anti-collapse and filtration. Its structure is simple and compact, with good overall rigidity, strong maintainability, meets general design requirements, and has low development cost.

[0005] To achieve the above objectives, in a first aspect, embodiments of the present invention provide a rear bottom structure for a rocket propellant tank, comprising: a rear bottom of the tank, a tunnel joint, several outflow flanges, an anti-collapse cover plate, a filter screen, and several anti-vortex fins;

[0006] The tunnel joint is located at the center of the rear bottom of the tank, and several outlet flanges are arranged on the rear bottom of the tank and distributed in a circle around the tunnel joint. The anti-collapse cover and the filter screen are both located above the outlet flanges.

[0007] The outer contour of the anti-collapse cover is connected to the inner wall of the rear bottom of the storage 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 said vortex elimination fins are circumferentially distributed around said tunnel joint, said vortex elimination fins are arranged below said anti-collapse cover plate and said filter screen, and the bottom edge of said vortex elimination fins is connected to the inner profile of the rear bottom of said tank.

[0010] In some possible embodiments, said rocket propellant tank rear bottom structure further comprises a plurality of connecting plates;

[0011] Said connecting plates extend in the direction of said tunnel joint pointing to the inner wall of said tank rear bottom, and said connecting plates are arranged above said vortex elimination fins, and a plurality of said connecting plates are circumferentially distributed around said tunnel joint;

[0012] Said vortex elimination fins, said anti-collapse cover plate and said filter screen are all connected to said connecting plates.

[0013] In some possible embodiments, said anti-collapse cover plate comprises a plurality of sector ring cover plates, a plurality of said sector ring cover plates are circumferentially distributed around said tunnel joint, and adjacent two said sector ring cover plates are connected to the same said connecting plate; and / or,

[0014] Said filter screen comprises a plurality of sector ring filter screens, a plurality of said sector ring filter screens are circumferentially distributed around said tunnel joint, and adjacent two said sector ring filter screens are connected to the same said connecting plate.

[0015] In some possible embodiments, the same said connecting plate is connected to said vortex elimination fins, adjacent two said sector ring cover plates and adjacent two said sector ring filter screens respectively.

[0016] In some possible embodiments, the inner edge of said vortex elimination fins is connected to said tunnel joint through an L-shaped bracket, said L-shaped bracket comprises a vertical part and horizontal parts located at the upper and lower ends of said vertical part, said vertical part is fixedly connected to said vortex elimination fins, and said horizontal parts are fixedly connected to said tunnel joint.

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

[0018] In some possible embodiments, said sector ring filter screen is arranged above said upper step part, and said connecting plate is located above said sector ring filter screen;

[0019] The top of said vortex elimination fins is fixedly connected to said connecting plate, and the bottom of said vortex elimination fins is fixedly connected to said tank rear bottom.

[0020] In some possible embodiments, the inner contour of said sector ring cover plate and the outer contour of said sector ring filter screen are both arc-shaped.

[0021] The inner contour of the fan ring-shaped cover plate is provided with a first upward turned flange, the outer contour of the fan ring-shaped filter screen is provided with a second upward turned flange, and the first flange and the second flange are connected together.

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

[0023] The outflow flanges are used to output propellants to the rocket engine one by one.

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

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

[0026] l=r*alpha;

[0027] wherein, r is the radius of the large circular arc edge of the fan ring-shaped cover plate, l is the arc length of the large circular arc edge of the fan ring-shaped cover plate, alpha is the included angle of the fan ring-shaped cover plate, h is the distribution height of the outflow flanges, a is the long semi-axis of the ellipse, and b is the short semi-axis of the ellipse.

[0028] In some possible embodiments, in the projection direction of the fan ring-shaped cover plate vertically downward, the small circular arc edge of the fan ring-shaped cover plate covers the outflow port of the outflow flange.

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

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

[0031] The above technical solution has the following beneficial technical effects:

[0032] 1. The outflow device is designed integrally, and has the functions of vortex elimination, anti-collapse and propellant filtering; at the same time, the outflow device system has compact structure, reasonable overall layout, good stability and strong maintainability, meets the general design requirements, and reduces the production cost; 2. The filter screen and the anti-collapse cover plate are located on the same tank bottom horizontal plane, which reduces the area of the filter screen, and the connection of the two makes the local structure more stable;

[0033] 3. The vortex elimination fin plate is arranged below the fan ring-shaped filter screen and the fan ring-shaped cover plate, which can meet the propellant vortex elimination function, will not increase the gap between the two adjacent fan ring-shaped filter screens, and will not affect the propellant filtering;

[0034] 4. The vortex breaker wing can provide support for the fan ring filter screen and the fan ring cover plate, and enhance the rigidity of the whole structure;

[0035] 5. The multiple piece outflow flanges are evenly arranged on the rear bottom of the tank, and can meet the liquid rocket propellant delivery needs of multiple parallel engines. BRIEF DESCRIPTION OF DRAWINGS

[0036] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description only constitute some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.

[0037] Figure 1 is a whole structure schematic diagram of a rocket propellant tank rear bottom integrated outflow device according to an embodiment of the present application;

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

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

[0040] BRIEF DESCRIPTION OF DRAWINGS

[0041] 1. Tank rear bottom; 2. Anti-collapse cover plate; 2. Fan ring cover plate; 211. First flange; 3. Filter screen; 31. Fan ring filter screen; 311. Second flange; 312. Screen frame; 4. Vortex breaker wing; 5. Outflow flange; 6. Tunnel joint; 61. Upper step portion; 62. Lower step portion; 7. Connecting plate; 8. Connecting ear; 9. U-shaped support; 91. Vertical portion; 92. Horizontal portion; 10. Connecting angle piece. DETAILED DESCRIPTION

[0042] The features and exemplary embodiments of various aspects of the present application will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present application. However, it will be apparent to one of ordinary skill in the art that the present application can be practiced without some or all of these specific details. The description of the embodiments is merely intended to provide a better understanding of the present application by showing examples of the present application. In the drawings and the following description, at least some well-known structures and techniques are not shown in order to avoid unnecessary obscuring of the present application; and, for clarity, the sizes of some structures can 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 rear bottom 1, a tunnel joint 6, several outflow flanges 5, an anti-collapse cover 2, a filter screen 3, and several anti-vortex fins 4; the tunnel joint 6 is located at the center of the rear bottom 1, several outflow flanges 5 are arranged on the rear bottom 1 and distributed circumferentially around the tunnel joint 6, and the anti-collapse cover and the filter screen are both located above the outflow flanges 5; the outer contour of the anti-collapse cover 2 is connected to the inner wall of the 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 2; several anti-vortex fins 4 are distributed circumferentially around the tunnel joint 6, and the anti-vortex fins 4 are located below the anti-collapse cover 2 and the filter screen 3, with the bottom edge of the anti-vortex fins 4 fitting and connected to the inner surface of the rear bottom 1.

[0044] In this embodiment of the 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 storage tank. That is, the three components of the filter screen 3, the anti-collapse cover plate 2, and the rear bottom 1 of the storage tank are connected as an integral structure. Moreover, the anti-vortex fin plate 4 is set below the anti-collapse cover plate 2 and the filter screen 3, and the bottom edge of the anti-vortex fin plate 4 is fitted and connected to the inner surface of the rear bottom 1 of the storage tank. This not only has high structural efficiency, but also improves 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 anti-vortex fin plate 4 is set below the anti-collapse cover plate 2 and the filter screen 3, which not only plays a role in eliminating vortexes, but also supports the anti-collapse cover plate 2 and the filter screen 3, further improving the stability of the structure.

[0045] In this embodiment, the bottom edge of the anti-vortex fin plate 4 is connected to the rear bottom 1 of the storage tank via connecting lugs 8, rather than being directly welded. This is because the anti-vortex fin plate 4 is made of aluminum alloy sheet, and welding would cause thermal deformation due to heat input. Furthermore, while the rear bottom 1 of the storage tank is theoretically an ellipsoidal surface, deviations inevitably occur during actual production, leading to a misalignment between the anti-vortex fin plate 4 and the rear bottom 1. In this embodiment, the anti-vortex fin plate 4 is connected to the connecting lugs 8 with bolts, which facilitates disassembly and repair of the anti-vortex fin plate 4 and compensates for errors in the production of the rear bottom 1 of the storage tank and the anti-vortex fin plate 4. Additionally, welding is inconvenient due to the narrow operating space and the thermal deformation it causes; moreover, defects such as cracks and inclusions within the weld are difficult to detect.

[0046] The embodiments of the present invention not only have the functions of anti-vortex, anti-collapse and propellant filtration, but also make the rear bottom structure of the tank compact, the overall layout reasonable, the stability good and the maintainability strong, meeting the general design requirements and reducing production costs.

[0047] In some embodiments, the rocket propellant tank rear bottom structure further comprises: a plurality of connecting plates 7; the connecting plates 7 extend along the direction in which the tunnel joint 6 points to the inner wall of the tank rear bottom 1, and the connecting plates 7 are arranged above the vortex elimination fins 4, and the plurality of connecting plates 7 are distributed in a circle around the tunnel joint 6; the vortex elimination fins 4, the anti-collapse cover plate 2 and the filter screen 3 are connected with the connecting plates 3. In this embodiment, the vortex elimination fins 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] As shown in Figure 3 In some embodiments, the anti-collapse cover plate 2 comprises a plurality of fan-shaped ring cover plates 21, the plurality of fan-shaped ring cover plates 21 are distributed in a circle around the tunnel joint 6, and adjacent two fan-shaped ring cover plates 21 are connected with the same connecting plate 7; and / or the filter screen 3 comprises a plurality of fan-shaped ring filter screens 31, the plurality of fan-shaped ring filter screens 31 are distributed in a circle around the tunnel joint 6, and adjacent two fan-shaped ring filter screens 31 are connected with the same connecting plate 7.

[0049] In the embodiment of the application, the number of the outflow flanges 5 can be equal to the number of the fan-shaped ring cover plates 21, that is, one fan-shaped ring cover plate 21 is arranged above each outflow flange 5, and each outflow flange 5 corresponds to one anti-collapse cover plate, which can fully prevent the air entrainment caused by the collapse of the liquid surface. In addition, the straight edges of the plurality of fan-shaped ring cover plates 21 are connected with each other to form a first ring, the straight edges of the plurality of fan-shaped ring filter screens 31 are also connected with each other to form a second ring, the outer ring edge of the second ring is connected with the inner ring edge of the first ring, and the two rings are located on the same tank bottom horizontal plane, that is, the plurality of fan-shaped ring cover plates 21 and the plurality of fan-shaped ring 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 by connecting the two. The top edges of the vortex elimination fins 4 are connected with the fan-shaped ring cover plates 21 and the fan-shaped ring filter screens 31, and the side edges of the vortex elimination fins 4 are connected with the tunnel joint 6, that is, the plurality of fan-shaped ring cover plates 21, the plurality of fan-shaped ring filter screens 31 and the vortex elimination fins 4 are integrated with the tank rear bottom 1, which not only has the functions of vortex elimination, anti-collapse and propellant filtering, but also makes the outflow device system compact in structure, reasonable in overall layout, good in stability and strong in maintainability, meets the general design requirements and reduces the production cost.

[0050] Specifically, the straight edges of the sector-shaped filter screens 31 can be aligned with the straight edges of the sector-shaped cover plates 21; the straight edges of any two adjacent sector-shaped cover plates 21 and the straight edges of any two adjacent sector-shaped filter screens 31 are connected by the connecting plates 7 (screwed in this embodiment), and the straight edges of the sector-shaped filter screens 31 and the straight edges of the sector-shaped cover plates 21 are aligned, so that the same connecting plate 7 can be used for connection, reducing the number of connecting components and improving the compactness of the structure. In addition, due to manufacturing errors, gaps may exist between adjacent mounting surfaces, and if there are gaps, the excess impurities in the box will flow into the engine along the gaps, which will affect the normal operation of the engine and even cause the engine to explode. The connecting plates 7 can also cover the mounting gaps between any two adjacent sector-shaped cover plates 21 and the mounting gaps between any two adjacent sector-shaped filter screens 31, and can also adjust the assembly error.

[0051] As shown in Figure 3 some embodiments, the same connecting plate 7 is connected with the vortex elimination fin 4, the two adjacent sector-shaped cover plates 21 and the two adjacent sector-shaped filter screens 31. In this embodiment, the vortex elimination fin 4 is connected with any two adjacent sector-shaped cover plates 21 and any two adjacent sector-shaped filter screens 31 by the connecting plate 7 to form an integrated structure, which not only improves the stability of the structure, but also has the functions of vortex elimination and support.

[0052] In addition, the vortex elimination fin 4 is arranged below the sector-shaped cover plates 21 and the sector-shaped filter screens 31, so that there is no mounting gap between any two adjacent sector-shaped cover plates 21 and any two adjacent sector-shaped filter screens 31, which does not affect the propellant filtration and can provide support for the sector-shaped cover plates 21 and the sector-shaped filter screens 31, thereby enhancing the overall structural rigidity. If the vortex elimination fin 4 is not installed below the sector-shaped cover plates 21 and the sector-shaped filter screens 31, it will protrude above the sector-shaped cover plates 21 and the sector-shaped filter screens 31 during installation, and there will be a mounting gap between the straight edges of the two adjacent sector-shaped cover plates 21 and the straight edges of the two adjacent sector-shaped filter screens 31 during connection.

[0053] As an example, the length of the top edge of the vortex elimination fin 4 can be equal to the sum of the length of the straight edge of the sector-shaped cover plate 21 and the length of the sector-shaped filter screen 31. In this way, the vortex elimination fin 4 not only plays a role in eliminating vortex, but also completely supports and stabilizes the sector-shaped cover plates 21 and the sector-shaped filter screens 31.

[0054] In addition, in actual use, although the size of the single aperture is not strictly required, the opening rate needs to meet certain requirements, because too small opening rate will result in too large flow resistance, affecting the efficiency of propellant entering the engine; too large opening rate will not well attenuate the vortex speed, and will weaken the strength of the vortex elimination fin 4. Therefore, the porosity of the vortex elimination fin 4 in the embodiment is greater than 20%, which can weaken the vortex energy, dissipate the vortex speed in a given direction to weaken the local vortex speed, and will not cause secondary flow. As an example, the porosity in the embodiment is 53%, and the aperture is 20mm.

[0055] As shown in Figure 3 some embodiments, the inner edge of the vortex elimination fin 4 is connected with the tunnel joint 6 through the H-shaped bracket 9, the H-shaped bracket 9 includes a vertical part 91 and a horizontal part 92 located at the upper and lower ends of the vertical part 81, the vertical part 91 is fixedly connected with the vortex elimination fin 4, and the horizontal part 92 is fixedly connected with the tunnel joint 6.

[0056] Specifically, the vertical part 91 of the H-shaped bracket 9 is screw-connected with the vortex elimination fin 4, the upper and lower horizontal parts 92 are respectively screw-connected with the tunnel joint 6, and the top edge of the vortex elimination fin 4 is connected with the connecting plate 7 through the connecting corner piece 10. In the embodiment, by arranging the connecting corner piece 10 and the H-shaped bracket 9, the installation of the vortex elimination fin 4 is facilitated, and the disassembly and maintenance are facilitated, and the errors in the production process of the vortex elimination fin 4, the connecting plate 7 and the tunnel joint 6 and the like can be eliminated.

[0057] As shown in Figure 3 some embodiments, the side wall of the tunnel joint 6 is provided with an upper step part 62 and a lower step part 62, and the two horizontal parts 92 are respectively fixedly connected with the upper step part 61 and the lower step part 62. The upper step part 61 is welded at the barrel of the tunnel joint 6, and the height can be flexibly adjusted according to the actual assembly of the product. The lower step part 62 is a turned-up edge structure integrated with the tunnel joint 6, has large bearing strength, and avoids insufficient strength caused by the heat influence of the weld joint. The upper and lower horizontal parts 92 of the H-shaped bracket 9 are respectively screw-connected with the step part 61 and the lower step part 62 of the tunnel joint 6.

[0058] In some embodiments, the fan ring filter screen 31 is arranged above the upper step part, and the connecting plate 7 is located above the fan ring filter screen 31. The top of the vortex elimination fin 4 is fixedly connected with the connecting plate 7, and the bottom of the vortex elimination fin 4 is fixedly connected with the tank rear bottom 1.

[0059] As shown in Figure 3As shown in the drawings, in some embodiments, the inner contour of the fan-shaped ring cover plate 21 and the outer contour of the fan-shaped ring filter screen 31 are both circular arcs; the inner contour of the fan-shaped ring cover plate 21 is provided with a first turned-up edge 211, the fan-shaped ring filter screen 31 adopts a structure of a screen frame 312 and a filter screen, the outer contour of the screen frame 312 is provided with a second turned-up edge 311, and the first turned-up edge 211 and the second turned-up edge 311 are fixedly connected together through screws.

[0060] In some embodiments, the number of the outflow flanges 5 is N, and N≥9; the outflow flanges 5 are used to correspondingly output propellants to the rocket engines.

[0061] In the embodiment, the sizes of the outflow flanges 5 are the same and are uniformly arranged along the elliptical surface of the tank rear bottom 1, which can meet the needs of liquid rocket propellant delivery of multiple parallel engines, and at the same time, due to the same size of the outflow flanges, the general design requirement can be met, and the production cost and period are reduced.

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

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

[0064] l=r*α;

[0065] Wherein, r is the radius of the large circular arc edge of the fan-shaped ring cover plate 21, l is the arc length of the large circular arc edge of the fan-shaped ring cover plate 21, α is the included angle of the fan-shaped ring cover plate 21, h is the distribution height of the outflow flanges 5, a is the major axis of the ellipse, and b is the minor axis of the ellipse.

[0066] Specifically, α is determined by the number N of the outflow flanges 5, and in the embodiment, the included angle is 40°, and the elliptical inner surface refers to that the tank bottom shape is an ellipsoidal surface, which is swept out by an elliptical curve of 360°.

[0067] In some embodiments, in the vertical downward projection direction of the fan-shaped ring cover plate 21, the small circular arc edge of the fan-shaped ring cover plate 21 covers the outflow ports of the outflow flanges 5.

[0068] ​Specifically, in order to play a full role in preventing collapse, the small arc edge of the fan ring cover plate 21 covers the outflow port of the outflow flange 5 in the vertical downward projection direction, so the radius of the small arc edge of the fan ring cover plate 21 cannot be too large, but the radius of the small arc edge of the fan ring cover plate 21 cannot be too small, if it is too small, the flow resistance is too large, which affects the flow of the propellant into the engine; in addition, the radius of the small arc edge of the fan ring cover plate 21 is equal to the radius of the large arc edge of the fan ring filter 31, according to the requirement of the filter opening area of the power overall, the radius of the large arc edge of the fan ring filter 31 also cannot be too small, too small will also increase the liquid flow resistance. Therefore, in the embodiment, the radius range of the small arc of the fan ring cover plate 21 can be determined according to the size of the outflow flange 5, after the radius range of the small arc of the fan ring cover plate 21 is determined, the arc length of the small arc of the fan ring cover plate 21 can be determined according to the included angle of the fan ring cover plate 21, and then the size of the fan ring filter 31 can be determined. In addition, the arc length of the small arc edge of the fan ring cover plate 21 in the embodiment can also be equal to the arc length of the large arc edge of the fan ring filter 31; the radius of the small arc edge of the fan ring cover plate 21 is equal to the radius of the large arc edge of the fan ring filter 31, so that the fan ring cover plate 21 and the fan ring filter 31 adjacent to the axis, that is, the straight edge of the fan ring filter 31 can be aligned with the straight edge of the fan ring cover plate 21; the straight edges of any two adjacent fan ring cover plates 21 and the straight edges of any two adjacent fan ring filters 31 are connected by the connecting plate 7. Both the connecting components are reduced and the stability is improved.

[0069] The application also provides a rocket propellant tank, comprising the rocket propellant tank rear bottom structure.

[0070] The application also provides a liquid rocket with multiple parallel engines, comprising the rocket propellant tank rear bottom structure.

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

[0072] The embodiment of the application has the following beneficial technical effects:

[0073] The outflow device of the application is designed integrally, the functions of vortex elimination, collapse prevention and filtration are integrated in one device, the structural complexity is reduced, the space utilization is optimized, the structure of the outflow device is compact and the layout is reasonable, the overall stability and durability can be improved, and the maintenance is convenient.

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

[0075] The vortex elimination fin plate 4 of the present application not only provides the vortex elimination 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 application is standardized and universalized with the tank rear bottom 1, thereby improving the production efficiency and reducing the manufacturing and installation costs.

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

[0078] The various components of the present application are connected in a bolted and other easily disassembled design, facilitating the disassembly and maintenance of the device and improving the maintainability.

[0079] The present application is suitable for multiple-engine parallel liquid rockets and has significant advantages in cost-effectiveness, operational convenience and system reliability.

[0080] In the description of the embodiments of the present application, it should be noted that the directions or positional relationships indicated by the terms "up, down, in and out" are based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first, second or third" are only for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0081] In the embodiments of the present application, unless otherwise explicitly specified and limited, the terms "mounting, connecting and connecting" should be understood broadly, for example: it can be fixedly connected, detachably connected or integrally connected; it can also be mechanically connected, electrically connected or directly connected, it can also be indirectly connected through an intermediate medium, or it can be the communication between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0082] Although the present application has been described with reference to the preferred embodiments, various modifications can be made thereto and equivalents can be substituted for elements thereof without departing from the scope of the present application. In particular, the technical features mentioned in each embodiment can be combined in any way as long as there is no structural conflict. The present application is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

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

2. The rear bottom structure of a rocket propellant tank according to claim 1, characterized in that, The rear bottom structure of the rocket propellant tank also includes: multiple connecting plates (7); The connecting plate (7) extends along the tunnel joint (6) toward the inner wall of the rear bottom (1) of the storage tank, and the connecting plate (7) is disposed above the anti-vortex fin plate (4), and a plurality of the connecting plates (7) are distributed in a circle around the tunnel joint (6); The anti-vortex fin plate (4), the anti-collapse cover plate (2), and the filter screen (3) are all connected to the connecting plate (7).

3. The rear bottom structure of a rocket propellant tank according to claim 2, characterized in that, The anti-collapse cover plate (2) includes multiple annular cover plates (21), which are circumferentially distributed around the tunnel joint (6). Two adjacent annular cover plates (21) are connected to the same connecting plate (7); and / or, The filter screen (3) includes multiple fan-shaped filter screens (31), which are distributed circumferentially around the tunnel joint (6), and two adjacent fan-shaped filter screens (31) are connected to the same connecting plate (7).

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

5. The rear bottom structure of a rocket propellant tank according to claim 4, characterized in that, The inner edge of the anti-vortex fin plate (4) is connected to the tunnel joint (6) through the U-shaped bracket (9); The slanted support (9) includes a vertical part (91) and a horizontal part (92) located at the upper and lower ends of the vertical part (91). The vertical part (91) is fixedly connected to the anti-vortex fin plate (4), and the horizontal part (92) is fixedly connected to the tunnel joint (6).

6. The rear bottom structure of a rocket propellant tank according to claim 5, characterized in that, The tunnel joint (6) has an upper step (61) and a lower step (62) on its sidewall, and the two horizontal parts (92) are respectively fixed to the upper step (61) and the lower step (62).

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

8. The rear bottom structure of a rocket propellant tank according to claim 3, characterized in that, 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 an upwardly turned first flange (211), and the outer contour of the fan-shaped filter screen (31) is provided with an upwardly turned second flange (311). The first flange (211) and the second flange (311) are fixed together.

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

10. The rear bottom structure of a rocket propellant tank according to claim 3, characterized in that, The arc length and radius of the large circular arc edge of the fan-shaped cover plate (21) are determined based on the elliptical inner surface parameters of the rear bottom (1) of the storage tank 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； Where r is the radius of the large arc edge of the fan-shaped annular cover plate (21), l is the arc length of the large arc edge of the fan-shaped annular cover plate (21), α is the included angle of the fan-shaped annular 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. The rear bottom structure of a rocket propellant tank according to claim 10, characterized in that, In the vertically downward projection direction, the small arc edge of the fan-shaped cover plate (21) covers the outlet of the outlet flange (5).

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

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

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