Multi-way connecting structure and engine system

Abstract

The invention provides a multi-way connecting structure and an engine system. The multi-way connecting structure is used for connecting a propellant storage tank and at least two engines of the carrier rocket, and comprises a hollow shell, a first connecting piece and a second connecting piece, a propellant inlet is formed in the top end of the shell; at least two first propellant outlets are formed in the circumferential direction of the shell; the flow dividing assembly comprises a flow dividing piece and at least one partition plate; an opening in the top end of the flow dividing piece is smaller than the propellant inlet, and the bottom end of the flow dividing piece penetrates through the shell and is provided with a second propellant outlet; the diameter of the peripheral wall section starting from the top end of the shunting piece is gradually increased, and the bottom end is connected with the periphery of the bottom end of the shell; the partition plates are arranged at intervals in the circumferential direction of the peripheral wall section, a cavity between the peripheral wall section and the shell is divided into at least one independent first flow channel, and the first flow channels communicate with the first propellant outlets correspondingly. Compared with a right-angle flow channel, the first flow channel has a large transition angle, and the possibility that a propellant forms a vortex in the multi-way connecting structure can be reduced.

Description

Technical Field

[0001] The present application relates to the technical field of launch vehicle power systems, and more specifically, to a multi-way connection structure and an engine system. Background Art

[0002] Due to the thrust requirements of a launch vehicle, a launch vehicle may need to be equipped with multiple engines. Multiple engines are connected in parallel to form the power system of the launch vehicle to provide the thrust required by the launch vehicle.

[0003] The propellant of a launch vehicle with multiple engines connected in parallel generally adopts the delivery scheme of "main delivery pipe + multi-way connection structure + branch delivery pipe". The multi-way connection structure is used to realize the diversion of propellant, and the propellant in the same propellant tank is delivered to multiple different engines respectively.

[0004] The flow of propellant in the traditional multi-pass main body structure is easily obstructed, and vortexes are easily formed. Summary of the invention

[0005] In view of the shortcomings of the existing methods, the present application proposes a multi-pass connection structure and an engine system to solve the technical problem that the traditional right-angle multi-pass is prone to form vortices in the related art.

[0006] In a first aspect, an embodiment of the present application provides a multi-way connection structure for connecting a propellant tank and at least two engines of a launch vehicle, comprising: The shell is hollow; a propellant inlet is provided at the top of the shell; at least two first propellant outlets are provided around the shell; A flow dividing assembly, comprising a flow dividing member and at least one partition; The flow divider is hollow, the top opening is smaller than the propellant inlet, the bottom end passes through the shell and has a second propellant outlet; the outer peripheral wall section starting from the top of the flow divider has a gradually increasing diameter, and the bottom end is connected to the bottom periphery of the shell; The partitions are arranged along the circumferential spacing of the outer peripheral wall section, and the cavity between the outer peripheral wall section and the shell is divided into at least one independent first flow channel, each of which is connected to each first propellant outlet.

[0007] In some possible embodiments, the flow divider includes: The guide part, as a peripheral wall section, is hollow and trumpet-shaped; the top opening of the guide part is smaller than the bottom opening and is located at the center of the propellant inlet; the bottom peripheral edge of the guide part is connected to the opening edge of the bottom end of the shell.

[0008] In some possible embodiments, the partition extends in a radial direction of the guide portion and is connected to the shell; a top end of the partition extends to an edge of the propellant inlet.

[0009] In some possible embodiments, the partition is fan-shaped, with an arc edge that is closely connected to the outer peripheral surface of the guide portion, a top edge that is flush with the top of the guide portion, and a side edge that is connected to the inner peripheral wall of the shell.

[0010] In some possible embodiments, the flow divider further includes: The straight part is cylindrical, open at both ends and hollow; The straight tube part is arranged in the guide part, the top end is connected with the top end of the guide part as a whole, and a gap is formed between the part close to the bottom end and the part close to the bottom end of the guide part.

[0011] In some possible embodiments, the inlets of the first flow channels are arranged around the outer periphery of the top opening of the guide portion at circumferential intervals along the outer peripheral wall segment; In the plane where the propellant inlet is located, the inlet of each first flow channel and the orthographic projection of the top end opening of the guide portion all fall within the range of the propellant inlet.

[0012] In some possible embodiments, the edges of the propellant inlet and the first propellant outlet each have a flange extending toward the outside of the shell; The multi-pass connection structure also includes: An inlet flange, one side of which is connected to the flange at the propellant inlet; At least two outlet flanges are respectively connected to the flange at the first propellant outlet and the second propellant outlet.

[0013] In some possible embodiments, the inlet flange includes an inner ring and an outer ring, and along the radial direction of the inlet flange, the inner ring and the outer ring are both suspended outside the flange; The inner ring has a plurality of threaded holes distributed along the circumferential spacing for connecting with the delivery pipe of the propellant tank, and the outer ring of the inlet flange has a plurality of oblong holes distributed along the circumferential spacing for connecting with the bottom of the propellant tank.

[0014] In a second aspect, the present application further provides an engine system, comprising: a propellant tank, at least two engines, and any multi-way connection structure provided in the first aspect above; The propellant inlet of the multi-way connection structure is connected to the propellant tank, and the first propellant outlet and the second propellant outlet of the multi-way connection structure are respectively connected to the engine in a one-to-one correspondence.

[0015] In some possible embodiments, the engines connected to the first propellant outlet are evenly distributed around the engines connected to the second propellant outlet.

[0016] The beneficial technical effects brought about by the technical solution provided by the embodiment of the present application include: The multi-way connection structure of the embodiment of the present application includes a hollow shell, and the splitter divides the shell into independent spaces inside and outside the splitter. The space outside the splitter is divided into at least one independent first flow channel by a partition, connecting the propellant inlet and the first propellant outlet; the space inside the splitter connects the propellant inlet and the second propellant outlet.

[0017] The outer wall section starting from the top of the flow divider gradually increases in diameter, so that the side wall of the first flow channel is arc-shaped. Compared with the right-angle flow channel, the first flow channel of the present application has a larger transition angle, which can reduce the possibility of the propellant forming vortices in the multi-way connection structure.

[0018] The flow divider penetrates the shell, so that the space inside the flow divider forms a vertical flow channel, so that the flow direction of the fluid is consistent with the direction of the flow channel, which can reduce friction and turbulence during the flow process, reduce the resistance to the flow of the propellant, improve the transmission efficiency, and further reduce the possibility of the propellant forming vortices in the multi-way connection structure.

[0019] Additional aspects and advantages of the present application will be partially given in the following description, which will become apparent from the following description, or will be understood through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which: Figure 1 A schematic diagram of the structure of a multi-channel connection structure provided in an embodiment of the present application from a first perspective; Figure 2 A schematic diagram of the structure of a multi-channel connection structure provided in an embodiment of the present application from a second viewing angle; Figure 3 A schematic diagram of a front view of a multi-channel connection structure provided in an embodiment of the present application; Figure 4 A schematic cross-sectional structure diagram of a multi-channel connection structure provided in an embodiment of the present application; Figure 5 A schematic structural diagram of a flow diversion component of a multi-channel connection structure provided in an embodiment of the present application.

[0021] Reference numerals: 100-multi-way connection structure; 101-first flow channel; 10- housing; 11-propellant inlet; 12-first propellant outlet; 20- shunt assembly; 21-flow dividing member; 210-second propellant outlet; 211-guiding portion; 212-straight cylinder portion; 22-partition; 30-Flanging; 40-inlet flange; 41-threaded hole; 42-oblong hole; 50-Outlet flange. DETAILED DESCRIPTION

[0022] The embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the implementation methods described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0023] Those skilled in the art will appreciate that, unless expressly stated, the "said" and "the" used herein may also include plural forms. It should be further understood that the term "including" used in the specification of the present application refers to the presence of the features, integers, elements and / or components, but does not exclude the implementation of other features, information, data, operations, elements, components and / or combinations thereof supported by the technical field. The term "and / or" used herein refers to at least one of the items defined by the term, for example, "A and / or B" may be implemented as "A", or as "B", or as "A and B".

[0024] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0025] First, the nouns involved in this application are introduced and explained: Multi-way connection structure: connected between the propellant tank and multiple engines, to divert the propellant to multiple engines.

[0026] Propellant tank: A structure that stores propellant.

[0027] Due to the thrust requirements of a launch vehicle, a launch vehicle may need to be equipped with multiple engines. Multiple engines are connected in parallel to form the power system of the launch vehicle to provide the thrust required by the launch vehicle.

[0028] The propellant of a launch vehicle with multiple engines connected in parallel generally adopts the delivery scheme of "main delivery pipe + multi-way connection structure + branch delivery pipe". The multi-way connection structure is used to realize the diversion of propellant, and the propellant in the same propellant tank is delivered to multiple different engines respectively.

[0029] The traditional multi-channel main body structure is generally a right-angle multi-channel, and the internal inlet fluid channel is perpendicular to the outlet fluid channel, that is, the transition angle of the propellant flow channel is at a right angle, which makes the flow of the propellant greatly hindered and easily forms vortices.

[0030] The multi-way connection structure and engine system provided in this application are intended to solve the above technical problems of related technologies.

[0031] The following is a detailed description of the technical solution of the present application and how the technical solution of the present application solves the above technical problems with specific embodiments. It should be noted that the following implementations can refer to, draw on or combine with each other, and the same terms, similar features and similar implementation steps in different implementations will not be described repeatedly.

[0032] The present application embodiment provides a multi-way connection structure 100 for connecting a propellant tank of a launch vehicle and at least two engines. Figure 1-Figure 4 The multi-way connection structure 100 includes: a shell 10 and a flow dividing component 20.

[0033] The shell 10 is hollow; a propellant inlet 11 is provided at the top of the shell 10 ; and at least two first propellant outlets 12 are provided around the shell 10 .

[0034] The flow dividing assembly 20 includes a flow dividing piece 21 and at least one partition 22 .

[0035] The diverter 21 is hollow, with a top opening smaller than the propellant inlet 11 , and a bottom end passing through the shell 10 and having a second propellant outlet 210 ; the peripheral wall section starting from the top of the diverter 21 has a gradually increasing diameter, and the bottom end is connected to the bottom periphery of the shell 10 .

[0036] The partitions 22 are arranged along the circumferential spacing of the outer peripheral wall section, and separate the cavity between the outer peripheral wall section and the shell 10 into at least one independent first flow channel 101 , each of which is connected to each first propellant outlet 12 .

[0037] In this embodiment, the multi-way connection structure 100 includes a hollow housing 10, and the flow divider 21 divides the interior of the housing 10 into independent spaces inside and outside the flow divider 21. The space outside the flow divider 21 is divided into at least one independent first flow channel 101 by a partition 22, connecting the propellant inlet 11 and the first propellant outlet 12, and one first propellant outlet 12 is connected to one engine; the space inside the flow divider 21 is connected to the propellant inlet 11 and the second propellant outlet 210, and one second propellant outlet 210 is connected to one engine.

[0038] The outer wall section starting from the top of the flow divider 21 has a gradually increasing diameter, so that the side wall of the first flow channel 101 is arc-shaped. Compared with the right-angle flow channel, the first flow channel 101 of the present application has a larger transition angle, which can reduce the probability of the propellant forming vortices in the multi-way connection structure 100 or avoid vortices.

[0039] The flow divider 21 passes through the shell 10, so that the space inside the flow divider 21 forms a vertical flow channel, so that the flow direction of the fluid is consistent with the flow channel direction, which can reduce friction and turbulence during the flow process, reduce the resistance to the flow of the propellant, improve the transmission efficiency, and further reduce the possibility of the propellant forming vortices in the multi-way connection structure 100.

[0040] In some possible embodiments, the shell 10 is spherical, and the first propellant outlets 12 are spaced apart on the equatorial circle of the shell 10, which can improve the space utilization of the multi-way connection structure 100, increase the number of first propellant outlets 12, and then increase the number of engines, thereby improving the thrust of the launch vehicle.

[0041] For some possible embodiments, please refer to Figure 4 The flow divider 21 includes: a guiding portion 211 .

[0042] The guide portion 211 is a peripheral wall segment, hollow and trumpet-shaped; the top opening of the guide portion 211 is smaller than the bottom opening and is located in the center of the propellant inlet 11; the bottom outer periphery of the guide portion 211 is connected to the opening edge of the bottom end of the shell 10.

[0043] In this embodiment, the top opening of the guide portion 211 is located at the center of the propellant inlet 11, dividing the propellant inlet 11 into different inlets connecting the inside and outside of the guide portion 211. The bottom end of the guide portion 211 is connected to the bottom end of the housing 10 as a whole, so that the spaces inside and outside the guide portion 211 are independent of each other. In the spaces inside and outside the guide portion 211, the circulation of the propellant does not affect each other, thereby reducing the possibility of vortex generation of the propellant in the multi-way connection structure 100.

[0044] For some possible embodiments, please refer to Figure 1 and Figure 5 The partition 22 extends along the radial direction of the guide portion 211 and is connected to the housing 10 ; the top end of the partition 22 extends to the edge of the propellant inlet 11 .

[0045] In this embodiment, the partition 22 is disposed between the housing 10 and the guide portion 211, dividing the space outside the guide portion 211 into a plurality of parallel first flow channels 101. Moreover, the top end of the partition 22 extends to the edge of the propellant inlet 11, dividing the propellant inlet 11 into a plurality of parallel entrances of the first flow channels 101. Moreover, the outlet of the first flow channel 101, i.e., the first propellant outlet 12, is disposed in the circumferential direction of the multi-way connection structure 100, and the guide portion 211 can reasonably transition the first flow channel 101 toward the first propellant outlet 12, thereby improving the space utilization of the housing 10.

[0046] For some possible embodiments, please refer to Figure 4The outer peripheral surface of the guide portion 211 has a smooth curved surface, so that the top end of the guide portion 211 and the bottom end of the guide portion 211 are in an arc-shaped transition, which has a certain flow-guiding effect and can guide the propellant to flow out toward the first propellant outlet 12. Moreover, the arc-shaped transition makes the first flow channel 101 have a larger transition angle, which can reduce the resistance of the propellant during the flow process, increase the flow speed of the propellant, and reduce the possibility of forming vortices in the multi-way connection structure 100.

[0047] For some possible embodiments, please refer to Figure 1 and Figure 5 The partition plate 22 is fan-shaped, with an arc edge fittingly connected to the outer peripheral surface of the guide portion 211 , a top edge flush with the top of the guide portion 211 , and a side edge connected to the inner peripheral wall of the shell 10 .

[0048] In this embodiment, the arc edge of the partition 22 is attached to the outer peripheral surface of the guide portion 211, and the side edge is connected to the inner peripheral wall of the shell 10, forming a plurality of mutually independent first flow channels 101. The top edge of the partition 22 is flush with the top of the guide portion 211, dividing the propellant inlet 11 into a plurality of parallel inlets of the first flow channels 101, which are respectively connected to the plurality of first flow channels 101.

[0049] For some possible embodiments, please refer to Figure 4 The flow divider 21 further includes a straight tube portion 212 .

[0050] The straight tube portion 212 is cylindrical in shape, open at both ends and hollow.

[0051] The straight tube portion 212 is disposed in the guide portion 211 , the top end of the straight tube portion 212 is connected to the top end of the guide portion 211 as a whole, and a gap is formed between the portion near the bottom end of the straight tube portion 212 and the portion near the bottom end of the guide portion 211 .

[0052] In this embodiment, a straight-tube portion 212 is provided in the guide portion 211, and the flow channel in the straight-tube portion 212 is straight and smooth, so that the resistance encountered by the propellant during the flow process is small, because the flow direction of the fluid is consistent with the flow channel direction, which reduces the friction and turbulence during the flow process, thereby improving the transmission efficiency of the fluid. Moreover, there is a gap between the portion of the straight-tube portion 212 near the bottom end and the portion of the guide portion 211 near the bottom end, which is equivalent to hollowing out the space between the guide portion 211 and the straight-tube portion 212, which can reduce the weight of the diverter 21 and save the material cost of the diverter 21.

[0053] In the related art, the multi-way connection structure 100 is spherical and is manufactured by integral machining or "pressurization and expansion + electron beam welding" process. The integral machining process can only manufacture a multi-way connection structure 100 of a smaller size, and the "pressurization and expansion + electron beam welding" process requires an additional molding die, and the volume of the entire sphere manufactured is larger.

[0054] Therefore, in some possible embodiments, the multi-way connection structure 100 can be manufactured using laser precision machining technology. Laser precision machining uses computer programming and can cut materials for products of different shapes. For example, a hollow design can be made between the guide portion 211 and the straight tube portion 212 to maximize material utilization, reduce the weight of the diverter 21, and save the material cost of the diverter 21.

[0055] For some possible embodiments, please refer to Figure 1 The inlet of each first flow channel 101 is arranged around the outer periphery of the top opening of the guide portion 211 at a circumferential spacing along the outer peripheral wall segment.

[0056] In the plane where the propellant inlet 11 is located, the inlet of each first flow channel 101 and the orthographic projection of the top opening of the guide portion 211 all fall within the range of the propellant inlet 11 .

[0057] In this embodiment, the inlet of each first flow channel 101 is arranged around the outer periphery of the top opening of the guide portion 211 along the circumferential spacing of the outer peripheral wall segment, and is evenly distributed, which can reduce the safety risks caused by uneven local pressure and improve the safety and reliability of the entire propulsion system. The inlet of each first flow channel 101 and the orthographic projection of the top opening of the guide portion 211 fall within the range of the propellant inlet 11, ensuring that the propellant inlet 11 area completely covers the inlet of each first flow channel 101 and the top opening area of ​​the guide portion 211, thereby ensuring the flow rate of the propellant flowing into each first flow channel 101 and the straight tube portion 212, and ensuring the effective operation of multiple engines.

[0058] For some possible embodiments, please refer to Figure 1 and Figure 3 The edges of the propellant inlet 11 and the first propellant outlet 12 each have a flange 30 extending toward the outside of the housing 10 .

[0059] The multi-channel connection structure 100 further includes: An inlet flange 40, one side of which is connected to the flange 30 at the propellant inlet 11; At least two outlet flanges 50 are respectively connected to the flange 30 at the first propellant outlet 12 and the second propellant outlet 210 .

[0060] In this embodiment, the flange 30 extends out of the propellant inlet 11 and the first propellant outlet 12, and the flange 30 at the propellant inlet 11 is fixedly connected to one side of the inlet flange 40, and the inlet flange 40 is connected to the propellant tank, so that the propellant inlet 11 is connected to the propellant tank.

[0061] In some possible embodiments, the size of the first propellant outlet 12 is consistent with the size of the second propellant outlet 210, and the corresponding outlet flanges 50 are consistent in size, which is convenient for connecting with multiple pipelines of the same specification.

[0062] For some possible embodiments, please refer to Figure 1 and Figure 2 The inlet flange 40 includes an inner ring and an outer ring. Along the radial direction of the inlet flange 40 , the inner ring and the outer ring are both suspended outside the flange 30 .

[0063] The inner ring has a plurality of threaded holes 41 distributed along the circumferential spacing for connecting to the delivery pipe of the propellant tank. The outer ring of the inlet flange 40 has a plurality of oblong holes 42 distributed along the circumferential spacing for connecting to the bottom of the propellant tank.

[0064] In this embodiment, the inner ring and the outer ring are both suspended outside the flange 30, which is convenient for the operator to operate and connect the inlet flange 40 with the delivery pipe of the propellant tank and the bottom of the propellant tank. In addition, the oblong hole 42 of the outer ring of the inlet flange 40 has a certain compensation effect, which is convenient for aligning the inner ring of the inlet flange 40 with the delivery pipe of the propellant, and improving the possibility of aligning the outer ring of the inlet flange 40 with the bottom of the propellant tank, thereby improving the connection efficiency.

[0065] Based on the same inventive concept, the present application also provides an engine system, comprising: a propellant tank, at least two engines, and a multi-way connection structure 100 as provided in any of the above embodiments.

[0066] The propellant inlet 11 of the multi-way connection structure 100 is connected to the propellant tank, and the first propellant outlet 12 and the second propellant outlet 210 of the multi-way connection structure 100 are respectively connected to the engines in a one-to-one correspondence.

[0067] In this embodiment, since the engine system adopts any of the multi-way connection structures 100 provided in the above embodiments, its principle and technical effect can be referred to in the above embodiments, and will not be described in detail here. The engine system also includes a plurality of engines connected in parallel through the multi-way connection structure 100, and the propellant tank delivers propellant to the plurality of engines through the multi-way connection structure 100, so that the plurality of engines can have a propellant source at the same time and can work when needed, thereby providing sufficient thrust for the launch vehicle.

[0068] Moreover, the diameter of the peripheral wall section starting from the top of the flow divider 21 of the multi-way connection structure 100 gradually increases, so that the side wall of the first flow channel 101 is arc-shaped. Compared with the right-angle flow channel, the first flow channel 101 of the present application has a larger transition angle, which can reduce the possibility of the propellant forming vortices in the multi-way connection structure 100.

[0069] The flow divider 21 passes through the shell 10, so that the space inside the flow divider 21 forms a vertical flow channel, so that the flow direction of the fluid is consistent with the flow channel direction, which can reduce friction and turbulence during the flow process, reduce the resistance to the flow of the propellant, improve the transmission efficiency, and further reduce the possibility of the propellant forming vortices in the multi-way connection structure 100.

[0070] In some possible embodiments, the engines connected to the first propellant outlet 12 are evenly distributed around the engines connected to the second propellant outlet 210 .

[0071] In this embodiment, the engine connected to the second propellant outlet 210 is arranged in the center, and at least partially overlaps with the second propellant inlet 11 in the vertical direction, so that the pipeline connecting the second propellant outlet 210 and the engine is vertically downward and connected to the top of the engine without bending, so that the resistance of the propellant from the second propellant outlet 210 to the engine is always small and the transmission rate is high. Around the engine connected to the second propellant outlet 210, multiple engines are evenly distributed, and are connected to the first propellant outlet 12 one by one through pipelines. The pipeline is in the shape of a 7, starting from the first propellant outlet 12 arranged circumferentially of the multi-way connection structure 100, extending horizontally, bending downward in the middle, and then vertically connected to the top of the engine. The engine layout in this embodiment is reasonable, and can adapt to the orientation of each outlet of the multi-way connection structure 100, so that the spatial layout of the engine system is evenly distributed, which can optimize the weight distribution and is also conducive to improving the flow balance of the propellant flowing into each engine.

[0072] By applying the embodiments of the present application, at least the following beneficial effects can be achieved: 1. In some embodiments, the outer peripheral wall section starting from the top of the diverter 21 gradually increases in diameter, so that the side wall of the first flow channel 101 is arc-shaped. Compared with the right-angle flow channel, the first flow channel 101 of the present application has a larger transition angle, which can reduce the probability of the propellant forming vortices in the multi-way connection structure 100 or avoid vortices. The diverter 21 runs through the shell 10, so that the space inside the diverter 21 forms a vertical flow channel, so that the flow direction of the fluid is consistent with the flow channel direction, which can reduce friction and turbulence during the flow process, reduce the resistance of the propellant flow, improve the transmission efficiency, and thus reduce the possibility of the propellant forming vortices in the multi-way connection structure 100.

[0073] 2. In some embodiments, the top opening of the guide portion 211 is located in the center of the propellant inlet 11, dividing the propellant inlet 11 into different inlets connecting the inside and outside of the guide portion 211. The bottom end of the guide portion 211 is connected to the bottom end of the housing 10 as a whole, so that the spaces inside and outside the guide portion 211 are independent of each other. In the spaces inside and outside the guide portion 211, the circulation of the propellant does not affect each other, thereby reducing the possibility of vortex generation of the propellant in the multi-way connection structure 100.

[0074] 3. In some embodiments, a straight-tube portion 212 is provided in the guide portion 211, and the flow path in the straight-tube portion 212 is straight and smooth, so that the resistance encountered by the propellant during the flow process is small, because the flow direction of the fluid is consistent with the flow path direction, which reduces the friction and turbulence during the flow process, thereby improving the transmission efficiency of the fluid. Moreover, there is a gap between the portion of the straight-tube portion 212 near the bottom end and the portion of the guide portion 211 near the bottom end, which is equivalent to hollowing out the space between the guide portion 211 and the straight-tube portion 212, which can reduce the weight of the diverter 21 and save the material cost of the diverter 21.

[0075] 4. In some embodiments, the inlet of each first flow channel 101 is arranged around the outer periphery of the top opening of the guide portion 211 along the circumferential spacing of the outer wall segment, and is evenly distributed, which can reduce the safety risks caused by uneven local pressure and improve the safety and reliability of the entire propulsion system. The inlet of each first flow channel 101 and the orthographic projection of the top opening of the guide portion 211 fall within the range of the propellant inlet 11, ensuring that the propellant inlet 11 area completely covers the inlet of each first flow channel 101 and the top opening area of ​​the guide portion 211, thereby ensuring the flow of propellant flowing into each first flow channel 101 and the straight tube portion 212, and ensuring the effective operation of multiple engines.

[0076] In the description of the present application, the directions or positional relationships indicated by words such as "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the exemplary directions or positional relationships shown in the accompanying drawings. They are for the convenience of describing or simplifying the description of the embodiments of the present application, and do not indicate or imply that the referred device or component must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present application.

[0077] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0078] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "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 be a direct connection, or an indirect connection 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 this application can be understood according to specific circumstances.

[0079] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0080] The above is only a partial implementation method of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the scheme of the present application, other similar implementation methods based on the technical ideas of the present application are also within the protection scope of the embodiments of the present application.

Claims

1. A multi-way connection structure, characterized in that: A propellant tank for connection to a launch vehicle and at least two engines, comprising: The shell is hollow; a propellant inlet is provided at the top of the shell; at least two first propellant outlets are provided around the shell; A flow dividing assembly, comprising a flow dividing member and at least one partition; The flow divider is hollow, the top opening is smaller than the propellant inlet, the bottom end passes through the shell and has a second propellant outlet; the outer peripheral wall section starting from the top of the flow divider has a gradually increasing diameter, and the bottom end is connected to the bottom periphery of the shell; The partitions are arranged along the circumferential spacing of the outer peripheral wall section to separate the cavity between the outer peripheral wall section and the shell into at least one independent first flow channel, each of which is connected to each of the first propellant outlets.

2. The multi-way connection structure according to claim 1, characterized in that: The flow divider comprises: The guide part, as the peripheral wall section, is hollow and trumpet-shaped; the top opening of the guide part is smaller than the bottom opening and is located in the center of the propellant inlet; the bottom peripheral edge of the guide part is connected to the opening edge of the bottom end of the shell.

3. The multi-way connection structure according to claim 2, characterized in that: The partition extends along the radial direction of the guide portion and is connected to the shell; the top end of the partition extends to the edge of the propellant inlet.

4. The multi-way connection structure according to claim 3, characterized in that: The partition is fan-shaped, with an arc edge that is closely connected to the outer peripheral surface of the guide portion, a top edge that is flush with the top end of the guide portion, and a side edge that is connected to the inner peripheral wall of the shell.

5. The multi-way connection structure according to claim 2, characterized in that: The diverter also includes: The straight part is cylindrical, open at both ends and hollow; The straight tube portion is arranged in the guide portion, the top end is connected to the top end of the guide portion as a whole, and a gap is formed between the portion close to the bottom end and the portion close to the bottom end of the guide portion.

6. The multi-way connection structure according to claim 2, characterized in that: The inlets of the first flow channels are arranged around the outer periphery of the top opening of the guide portion at a circumferential spacing along the outer peripheral wall segment; In the plane where the propellant inlet is located, the inlet of each of the first flow channels and the orthographic projection of the top end opening of the guide portion all fall within the range of the propellant inlet.

7. The multi-way connection structure according to claim 1, characterized in that: The edges of the propellant inlet and the first propellant outlet each have a flange extending toward the outside of the shell; The multi-channel connection structure also includes: An inlet flange, one side of which is connected to the flange at the propellant inlet; At least two outlet flanges are respectively connected to the flange at the first propellant outlet and the second propellant outlet.

8. The multi-way connection structure according to claim 7, characterized in that: The inlet flange comprises an inner ring and an outer ring, and along the radial direction of the inlet flange, the inner ring and the outer ring are both suspended outside the flange; The inner ring has a plurality of threaded holes distributed along the circumferential spacing for connecting with the delivery pipe of the propellant tank, and the outer ring of the inlet flange has a plurality of oblong holes distributed along the circumferential spacing for connecting with the bottom of the propellant tank.

9. An engine system, characterized in that: include: A propellant tank, at least two engines and a multi-way connection structure as described in any one of claims 1 to 8; The propellant inlet of the multi-way connection structure is connected to the propellant tank, and the first propellant outlet and the second propellant outlet of the multi-way connection structure are respectively connected to the engine in a one-to-one correspondence.

10. The engine system according to claim 9, characterized in that: The engines connected to the first propellant outlet are evenly distributed around the engines connected to the second propellant outlet.

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