Attitude control engine system, method of manufacture and rocket

Abstract

The present application relates to the technical field of rockets, and particularly relates to a system of attitude control engines, a manufacturing method and a rocket. The system of attitude control engines comprises: a plurality of engine assemblies and a plurality of annular pipes; the engine assembly comprises: a plurality of engines and at least one collection block, the plurality of engines are arranged on the collection block, and an internal flow channel system is arranged in the collection block; the plurality of annular pipes are connected with the internal flow channel system of the collection block of each engine assembly, and form an annular structure. The system of attitude control engines, the manufacturing method and the rocket provided by the present application have the advantages of simple structure, high integration, high reliability, modular processing and assembly, reduced production cost and construction period; the internal flow channel system is arranged in the collection block, air and liquid can be supplied to the engines on both sides, and the collection block is fixedly connected with the rocket body structure, the annular pipes are used to connect the engine assemblies, and the annular distribution of the engine system and the function requirements of synchronous air and liquid supply are realized.

Description

Technical Field

[0001] This invention relates to the field of rocket technology, and in particular to an attitude control engine system, a manufacturing method, and a rocket. Background Technology

[0002] To adjust the rocket's attitude during flight, an attitude control engine system is typically installed on the rocket body. To achieve circumferential roll control of the rocket body, a two-engine configuration is used, with each pair of engines facing each other forming a dual-engine group. Four such dual-engine groups are then evenly distributed circumferentially to meet the overall control force output requirements for rocket roll control. The attitude control engine system in this technology employs a regenerative cooling engine scheme, which requires fuel to cool the engine thrust chamber during operation. Simultaneously, it needs to ensure high synchronization between pneumatic valve air supply and engine fluid supply. Therefore, this approach requires multiple connecting channels and valves between adjacent engines, resulting in complex structures, high production costs, long processing cycles, difficulty in highly integrating the system structure, and poor reliability, making it difficult to meet the requirements of regenerative cooling engines. Summary of the Invention

[0003] This invention provides an attitude control engine system, a manufacturing method, and a rocket to address the shortcomings of existing attitude control engine systems, such as complex structure, high production cost, long processing cycle, difficulty in highly integrating the system structure, poor reliability, and inability to meet the usage requirements of regenerative cooling engines.

[0004] This invention provides an attitude control engine system, comprising:

[0005] A multi-engine assembly includes: a plurality of engines and at least one assembly block, wherein the plurality of engines are disposed on the assembly block, and the assembly block has an internal flow channel system for distributing oxidant, driving gas and fuel to the engines;

[0006] Multiple ring pipes are connected to the internal flow channel system of the assembly block of each of the engine assemblies, and the multiple engine assemblies are connected end to end to form a ring structure.

[0007] According to the attitude control engine system provided by the present invention, four engine assemblies are provided, and each engine assembly is distributed at a 90° interval.

[0008] Each of the engine assemblies includes two engines and a collection block, with first mounting interfaces for mounting the engines provided on the left and right sides of the collection block.

[0009] According to the attitude control engine system provided by the present invention, the assembly block is provided with a driving gas inlet, an oxidant inlet and at least one fuel inlet. The driving gas inlet, the oxidant inlet and the fuel inlet are respectively used to receive driving gas, oxidant and fuel. The driving gas inlet, the oxidant inlet and the fuel inlet are respectively connected to the internal flow channel system. The internal flow channel system forms two sets of internal flow channel outlets. The two sets of internal flow channel outlets are respectively arranged on both sides of the assembly block and respectively connected to the two engines.

[0010] According to the attitude control engine system provided by the present invention, the internal flow channel system includes: two sets of oxidant internal flow channels, two sets of driving gas internal flow channels and two sets of fuel internal flow channels, and the two sets of oxidant internal flow channels, two sets of driving gas internal flow channels and two sets of fuel internal flow channels are respectively located on both sides of the assembly block;

[0011] The internal flow channel outlet includes two first oxidant outlets, two first driving gas outlets, and two fuel outlets;

[0012] The oxidant internal flow channel is connected to the oxidant inlet and the first oxidant outlet, the driving gas internal flow channel is connected to the driving gas inlet and the first driving gas outlet, the number of fuel inlets is two, and the two fuel inlets are located on both sides of the collection block, and the fuel internal flow channel is connected to the fuel inlet and the fuel outlet.

[0013] According to the attitude control engine system provided by the present invention, the first oxidant outlet, the fuel outlet and the first driving gas outlet are all connected to the valves of the engine;

[0014] The driving gas flows from the first driving gas outlet to the valve, and the driving gas is used to drive the valve to open; the fuel flows from the fuel outlet and passes through the valve, enters the cooling pipe located on the outer wall of the thrust chamber and regenerates and cools the thrust chamber; after the regeneration and cooling is completed, the fuel flows back to the valve; after the regeneration and cooling is completed, the valve opens, and the oxidant and the fuel enter the thrust chamber through the valve to mix and burn.

[0015] The attitude control engine system provided by the present invention further includes:

[0016] A filter assembly is installed at the first oxidant outlet and is used to filter impurities from the oxidant contained in the oxidant inner channel.

[0017] According to the attitude control engine system provided by the present invention, the assembly block further includes:

[0018] An external oxidant pipe is connected to the internal oxidant flow channel. Oxidant outer ring outlets are formed on both sides of the external oxidant pipe. The external oxidant outer ring outlets are connected to the internal flow channel system of the collection blocks on the left and right sides through the ring pipe to form an oxidant ring supply loop.

[0019] An external driving gas pipe is connected to the internal driving gas flow channel. External driving gas outlets are formed on both sides of the external driving gas pipe. The external driving gas outlets are connected to the internal flow channel system of the collection blocks on the left and right sides through the ring pipe to form an annular driving gas supply loop.

[0020] An external fuel pipeline has two fuel inlets at its two ends and is connected to two sets of internal fuel channels. The external fuel pipeline is connected to the internal channel system of the aggregate blocks on the left and right sides through the ring pipe to form a fuel ring supply loop.

[0021] According to the attitude control engine system provided by the present invention, the two ends of the oxidant external pipe are respectively provided with oxidant threaded connectors, the two ends of the driving gas external pipe are respectively provided with driving gas threaded connectors, and the two ends of the fuel external pipe are respectively provided with fuel threaded connectors.

[0022] According to the attitude control engine system provided by the present invention, the upper side of the assembly block is provided with an oxidant inner pipe and a driving gas inner pipe, the upper end of the oxidant inner pipe forms the oxidant inlet and a portion of the oxidant inner flow channel is formed inside it; the upper end of the driving gas inner pipe forms the driving gas inlet and a portion of the driving gas inner flow channel is formed inside it.

[0023] Both the external oxidant pipe and the external driving gas pipe are located on the lower side of the collection block. The external oxidant pipe is connected to the internal oxidant pipe, and the external driving gas pipe is connected to the internal driving gas pipe.

[0024] According to the attitude control engine system provided by the present invention, the oxidant inner pipe and the driving gas inner pipe are arranged parallel to each other and staggered from each other, and the oxidant outer pipe and the driving gas outer pipe are arranged parallel to each other and staggered from each other;

[0025] The inner oxidant pipe is perpendicular to the outer oxidant pipe, and the inner driving gas pipe is perpendicular to the outer driving gas pipe.

[0026] The present invention also provides a method for manufacturing the attitude control engine system of the present invention, comprising:

[0027] Using 3D printing technology, modular components are created, and the engine is fixed onto these components to form an engine assembly.

[0028] Multiple engine assemblies are connected end to end in a ring shape using a ring tube.

[0029] The present invention also provides a rocket, comprising: the attitude control engine system provided by the present invention.

[0030] This invention provides an attitude control engine system, comprising: multiple engine assemblies and multiple ring pipes; each engine assembly includes: multiple engines and at least one assembly block, with the multiple engines mounted on the assembly block, and the assembly block having an internal flow channel system for distributing oxidizer, driving gas, and fuel to the engines; the multiple ring pipes are connected to the internal flow channel systems of the assembly blocks of each engine assembly, and the multiple engine assemblies are sequentially connected end-to-end to form a ring structure. This attitude control engine system utilizes an assembly block to integrate and install multiple engines to form a modular engine assembly, which features a simple structure, high integration, high reliability, modular processing and assembly, reducing production costs and time; and uses ring pipes to connect the engine assemblies into a ring structure, with the assembly block having an internal flow channel system capable of supplying gas and liquid to the engines on both sides and being fixedly connected to the rocket body structure, and the engine assemblies being connected by ring pipes, achieving the functional requirements of a ring-shaped engine system with synchronous gas and liquid supply.

[0031] Furthermore, the present invention proposes a method for manufacturing an attitude control engine system, which utilizes 3D printing technology to achieve a simple and highly integrated modular design. This design has the advantages of low cost, short processing cycle, and the ability to print multiple parts at once, meeting the requirements for the use of regenerative cooling engine assemblies and thus ensuring the safe and reliable operation of rockets.

[0032] Furthermore, the rocket provided by the present invention, since it includes the attitude control engine system of the above embodiments of the present invention, has the same advantages as described above. Attached Figure Description

[0033] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0034] Figure 1 This is a top view of an attitude control engine system provided in one embodiment of the present invention.

[0035] Figure 2 This is a front view of an attitude control engine system provided in one embodiment of the present invention.

[0036] Figure 3This is a schematic diagram of the engine assembly provided by the present invention.

[0037] Figure 4 This is one of the structural schematic diagrams of the assembly block provided by the present invention.

[0038] Figure 5 It is along Figure 4 A cross-sectional view along line AA in the middle.

[0039] Figure 6 It is along Figure 4 A cross-sectional view along the BB line.

[0040] Figure 7 It is along Figure 4 A cross-sectional view of the CC line.

[0041] Figure 8 It is along Figure 4 A cross-sectional view of the DD line.

[0042] Figure 9 This is the second schematic diagram of the structure of the assembly block provided by the present invention.

[0043] Figure 10 It is along Figure 9 A cross-sectional view of the EE line.

[0044] Figure 11 It is along Figure 9 A cross-sectional view of the FF line.

[0045] Figure 12 It is along Figure 9 A cross-sectional view of the GG line.

[0046] Figure 13 It is along Figure 9 A cross-sectional view of the middle HH line.

[0047] Figure label:

[0048] 100: Engine assembly; 200: Ring pipe;

[0049] 1. Assembly block; 2. Filter assembly; 3. Second mounting interface; 4. First mounting interface; 51. Oxidant internal flow channel; 52. Drive gas internal flow channel; 53. Oxidant internal pipe; 54. Drive gas internal pipe; 6. Drive gas inlet; 61. First drive gas outlet; 7. Oxidant inlet; 71. First oxidant outlet; 8. Engine;

[0050] 91. Oxidizer external pipe; 911. Oxidizer outer ring outlet; 912. Oxidizer threaded connector; 92. Driving gas external pipe; 921. Driving gas outer ring outlet; 922. Driving gas threaded connector; 101. Fuel inlet; 102. Fuel internal flow channel; 103. Fuel outlet; 104. Fuel external pipe; 105. Fuel threaded connector. Detailed Implementation

[0051] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0052] In the description of this embodiment, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this embodiment and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this embodiment.

[0053] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this embodiment, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0054] In this embodiment, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," "link," and "fix" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this embodiment based on the specific circumstances.

[0055] In embodiments of the present invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0056] The following is combined Figures 1-13 This invention describes an attitude control engine system. The attitude control engine system includes: multiple engine assemblies 100 and multiple annular tubes 200.

[0057] The engine assembly 100 includes: multiple engines and at least one assembly block. The multiple engines are mounted on the assembly block, and the assembly block has an internal flow channel system for distributing oxidant, driving gas and fuel to the engines. Multiple ring pipes 200 are connected to the internal flow channel system of the assembly block of each engine assembly 100, and the multiple engine assemblies 100 are connected end to end to form a ring structure.

[0058] Specifically, the engine assembly 100 is an integrated structure composed of multiple engines and assembly blocks. The assembly blocks integrate and install multiple engines into a modular structure, facilitating processing and assembly. An internal flow channel system is formed within the assembly blocks to distribute oxidizer, driving gas, and fuel to each engine. The assembly blocks can be manufactured using 3D printing technology, reducing production costs and shortening the production cycle. After the assembly blocks are manufactured, the engines can be fixed to them and connected using ring pipes 200 to form a ring structure.

[0059] Specifically, multiple ring pipes 200 are used to connect the internal flow channel systems inside the aggregate blocks included in multiple engine assemblies 100, thereby forming a ring-shaped supply system. Furthermore, the ring pipes 200 can be used to connect multiple engine assemblies 100 end to end to form a ring structure, which can then be installed on the rocket body.

[0060] Preferably, such as Figure 1 and Figure 2 In the embodiment shown, four sets of engine assemblies 100 are connected sequentially by a ring pipe 200. Each set of engine assemblies 100 is distributed at a 90° interval. Each set of engine assemblies 100 contains two engines and a collection block. By utilizing the cooperation of the ring pipe 200 and the internal flow channel system inside the collection block, annular air and liquid supply is achieved. The eight engines distributed along the circumference of the rocket body control the roll of the rocket body.

[0061] To achieve circumferential roll control of the rocket body, a dual-engine assembly is formed by two engines facing each other, and four sets of dual-engine assemblies are then evenly distributed circumferentially to meet the overall control force output requirements for rocket body roll control. This attitude control engine system adopts a regenerative cooling engine scheme, which requires fuel to cool the engine thrust chamber during operation. At the same time, it is necessary to achieve a high degree of synchronization between pneumatic valve air supply and engine fluid (oxidizer, fuel) supply. Therefore, air and fluid are supplied to the engines on both sides from the assembly block and fixed to the rocket body structure. The dual-engine assemblies are connected by a ring pipe 200, realizing the functional requirements of the ring-shaped engine system and reliable synchronous air and fluid supply.

[0062] In addition, the structure of the assembly block also facilitates the fixing of the engine to the rocket body, integrating the function of a mounting base.

[0063] The present invention provides an attitude control engine system, comprising: multiple engine assemblies 100 and multiple annular pipes 200; each engine assembly 100 includes: multiple engines and at least one assembly block, the multiple engines being disposed on the assembly block, and the assembly block having an internal flow channel system for distributing oxidant, driving gas and fuel to the engines; the multiple annular pipes 200 are connected to the internal flow channel system of the assembly block of each engine assembly 100, and the multiple engine assemblies 100 are connected end to end to form an annular structure. The present invention provides an attitude control engine system that integrates multiple engines into a modular engine assembly 100 using a block. This system features a simple structure, high integration, high reliability, modular processing and assembly, reducing production costs and time. The engine assembly 100 is connected into a ring structure using a ring pipe 200. The block has an internal flow channel system that supplies air and liquid to the engines on both sides and is fixedly connected to the rocket body structure. The engine assemblies 100 are connected by the ring pipe 200, achieving the functional requirements of a ring-shaped engine system with synchronous air and liquid supply.

[0064] In one embodiment of the present invention, such as Figure 1As shown, four engine assemblies 100 are arranged, with each engine assembly 100 spaced 90° apart. Each engine assembly 100 includes two engines and a collection block. The collection block has first mounting interfaces on its left and right sides for mounting the engines. In this embodiment, each engine assembly 100 uses the first mounting interfaces on the left and right sides of a collection block to fix two engines, i.e., one engine is mounted on the left side of the collection block and one engine is mounted on the right side, forming a modular engine assembly 100. The four engine assemblies 100 are connected by a ring pipe 200 to form a ring structure. The included angle between two adjacent engine assemblies 100 is 90°, thus forming eight engines. The four collection blocks enable the engines to be combined in pairs, forming four sets of engine double-body assemblies.

[0065] Additionally, it is understandable that the assembly block should be equipped with a driving gas inlet, an oxidizer inlet, and a fuel inlet to ensure that the driving gas, oxidizer, and fuel enter the loop. Specifically, such as... Figure 1 In the structure shown, the upper assembly block serves as the first quadrant assembly block, and the second, third, and fourth quadrant assembly blocks are arranged counterclockwise. The first and third quadrant assembly blocks have a second installation interface 3. The second quadrant assembly block has a fuel inlet, and the fourth quadrant assembly block has a driving gas inlet and an oxidizer inlet.

[0066] In the above embodiments, the aggregate blocks located in different quadrants can have different structures. For example, there are three types of aggregate blocks: one type has no liquid inlet in the middle, which is an aggregate block in the first and third quadrants; one type has a fuel inlet in the middle, which is an aggregate block in the second quadrant; and one type has an oxidant inlet and a driving gas inlet in the middle, which is an aggregate block in the fourth quadrant. This invention describes a general aggregate block structure. Of course, the internal flow channels of the aggregate block can be processed according to actual conditions to adapt to different application scenarios.

[0067] In one embodiment of the present invention, the assembly block 1 is provided with a driving gas inlet 6, an oxidant inlet 7 and at least one fuel inlet 101. The driving gas inlet 6, the oxidant inlet 7 and the fuel inlet 101 are respectively used to receive driving gas, oxidant and fuel. The assembly block 1 is provided with an internal flow channel system for distributing oxidant, driving gas and fuel to the engine 8. The driving gas inlet 6, the oxidant inlet 7 and the fuel inlet 101 are respectively connected to the internal flow channel system. The internal flow channel system forms two sets of internal flow channel outlets. The two sets of internal flow channel outlets are respectively located on both sides of the assembly block 1 and are respectively connected to the engine 8.

[0068] In the above description of the structure of the assembly block for the rocket engine, the assembly block mainly consists of the following parts: the assembly block is designed to mount the engines 8 on both sides; the driving gas inlet 6, that is, an inlet on the assembly block 1, for receiving driving gas; the oxidizer inlet 7, similarly, an inlet on the assembly block 1, for receiving oxidizer; the fuel inlet 101, for receiving fuel; and the internal flow channel system, that is, an internal flow channel system designed inside the assembly block 1, which is responsible for distributing the received oxidizer, driving gas, and fuel into the engine 8. The ring pipe 200 is connected to the internal flow channel system of each of the above-mentioned assemblies, for conveying oxidizer, driving gas, and fuel in different engine assemblies 100.

[0069] The driving gas inlet 6, oxidizer inlet 7, and fuel inlet 101 are all connected to the internal flow channel system to ensure smooth gas flow. The internal flow channel system forms two sets of internal flow channel outlets on the left and right sides of the assembly block 1, each set of outlets directly connected to an engine 8, used to deliver oxidizer, driving gas, and fuel to the corresponding components of the engine 8. If each engine assembly 100 has three engines, three sets of internal flow channel outlets are provided.

[0070] Specifically, within the collection block of the present invention, the flow path of the oxidant is as follows: the oxidant enters the collection block 1 through the oxidant inlet 7. Inside the collection block, the oxidant flows along an internal flow channel system, which is designed with specific paths and structures to ensure that the oxidant can be uniformly and effectively distributed. For example... Figures 3 to 5 as well as Figure 7 and Figure 8 As shown, the oxidant enters the inner oxidant pipe 53 from the oxidant inlet 7 and flows out from the inner oxidant pipe 53 to the outer oxidant pipe 91 below. In the outer oxidant pipe 91, the oxidant is divided into two paths and flows to two sets of inner oxidant channels 51 located on the left and right sides respectively (excess oxidant can flow out from the outer oxidant ring outlet 911 and through the ring pipe 200 to other collection blocks). After passing through a specific tortuous flow path in the inner oxidant channels 51, it flows out from the first oxidant outlet 71 and enters the valve of the engine 8. The oxidant finally enters the engine 8 through the inner channel outlet, where it typically mixes with the fuel and burns in the combustion chamber to generate thrust.

[0071] Within the assembly block of this invention, the flow path of the driving gas is as follows: the driving gas enters the assembly block 1 through the driving gas inlet 6. The driving gas flows within the assembly block along specific internal channels, which are different from the oxidant channels to ensure that both can be controlled independently. For example... Figures 3 to 5 as well as Figure 11As shown, the driving gas enters the inner driving gas pipe 54 from the driving gas inlet 7 and flows out from the inner driving gas pipe 54 to the lower outer driving gas pipe 92. In the outer driving gas pipe 92, the driving gas is divided into two paths and flows to two sets of inner driving gas channels 52 located on the left and right sides respectively (excess driving gas can flow out from the outer driving gas ring outlet 921 and through the ring pipe 200 to other collection blocks). After passing through a specific tortuous flow path in the inner driving gas channels 52, it flows out from the first driving gas outlet 61 and enters the valve of the engine 8. The driving gas can control the opening and closing of the valve. Depending on different needs, the driving gas can also be used to perform various functions, such as purging air or moisture from the pipes, or blowing out residual gases in the combustion chamber after the engine 8 is turned off.

[0072] In the case of a regenerative cooling engine, after the fuel (a type of propellant) flows through the valve housing of engine 8, it first flows through a cooling pipe located inside the outer wall of the thrust chamber to cool the thrust chamber body, and then flows back into the valve inlet to achieve the function of regenerative cooling.

[0073] In summary, through the above design, the assembly block not only simplifies the structure of the engine assembly but also improves the reliability and efficiency of the rocket engine system. The assembly block of this invention can be manufactured using 3D printing technology, which enables the design of complex internal flow channels, further optimizing the flow paths of oxidizer, fuel, and propulsion gases.

[0074] This invention provides an assembly block for rocket engines. Through a clever internal flow channel design, it enables the input of oxidizer, fuel and control gas for two engines 8, and ensures the functional realization of the dual-engine combination scheme of regenerative cooling engine, achieving simple and reliable integration of the new engine 8.

[0075] Furthermore, compared to related technologies, the present invention has at least the following advantages:

[0076] (1) Simplified structure: Through integrated design, the assembly block integrates multiple functions (such as fuel input and output, oxidant input and output, driving gas input and output, engine regeneration cooling, etc.) into one component, which simplifies the structure of the engine assembly, reduces the number of components and connection points, thereby reducing the complexity of the system and potential failure points.

[0077] (2) High integration: The design of the assembly block improves the integration, making the distribution of oxidant, driving gas and fuel more precise and efficient, which helps to improve the performance of engine 8.

[0078] (3) Easy maintenance: The design of the modular unit simplifies the maintenance and replacement process because the integrated design reduces the number of parts that need to be maintained or replaced individually.

[0079] (4) Improved reliability: Through precise internal flow channel design and integrated filters, the assembly block helps improve the reliability of rocket engines and reduces the risk of failure due to impurities that may be contained in the oxidizer.

[0080] (4) Regenerative cooling function: The design of the fuel block allows the thrust chamber body to be cooled before entering the valve, which improves the combustion efficiency of engine 8 and extends the service life of engine 8.

[0081] (6) Asymmetric input of oxidizer, fuel and control gas: The ingenious internal flow channel design enables the input of oxidizer, fuel and control gas at asymmetric positions of the two engines, which improves space utilization efficiency and adapts to specific rocket design requirements.

[0082] like Figures 4 to 8 As shown, according to some embodiments of the present invention, the internal flow channel system includes two sets of oxidant internal flow channels 51, two sets of driving gas internal flow channels 52 and two sets of fuel internal flow channels 102, and the two sets of oxidant internal flow channels 51, two sets of driving gas internal flow channels 52 and two sets of fuel internal flow channels 102 are respectively located on both sides of the collection block 1.

[0083] The internal flow channel outlets include two first oxidant outlets 71, two first driving gas outlets 61, and two fuel outlets 103.

[0084] The oxidant internal flow channel 51 is connected to the oxidant inlet 7 and the first oxidant outlet 71, the driving gas internal flow channel 52 is connected to the driving gas inlet 6 and the first driving gas outlet 61, the number of fuel inlets 101 is two, and the two fuel inlets 101 are located on both sides of the collection block 1, and the fuel internal flow channel 102 is connected to the fuel inlet 101 and the fuel outlet 103.

[0085] In this embodiment, the above design allows the oxidant, driving gas, and fuel to flow through their respective independent paths. That is, the oxidant inner flow channel 51, the driving gas inner flow channel 52, and the fuel inner flow channel 102 are all independently designed, meaning there is no direct physical connection between them. Each inner flow channel is directly connected to its respective inlet and outlet, ensuring that the oxidant, driving gas, and fuel can enter the engine 8 independently.

[0086] Specifically, the oxidant flow path is as follows: the oxidant enters the collection block through the oxidant inlet 7, flows along the oxidant inner flow channel 51, and finally enters the combustion chamber of the engine 8 on both sides through the first oxidant outlet 71.

[0087] The driving gas flow path is as follows: the driving gas enters the manifold through the driving gas inlet 6, flows along the driving gas inner flow channel 52, and finally enters the engines 8 on both sides through the first driving gas outlet 61, for controlling valves or performing other auxiliary functions.

[0088] The fuel flow path is as follows: Taking the engine 8 located on the left side of the assembly block 1 as an example, fuel enters the assembly block through the fuel inlet 101 on the left side, flows along the fuel internal flow channel 102 on the left side, and finally enters the engine 8 located on the left side of the assembly block 1 through the fuel outlet 103 on the left side. It should be noted that the embodiment of the engine 8 located on the right side of the assembly block 1 is similar to the above embodiment, and will not be described again here.

[0089] In this way, because the oxidizer, driving gas, and fuel each have their own independent flow channels, their flow can be controlled independently, improving the operational flexibility of the engine 8. The internal flow channel system can also achieve precise distribution of the oxidizer, driving gas, and fuel, optimizing the performance of the engine 8. Furthermore, the independent flow channel design reduces the risk of accidental mixing between the oxidizer, driving gas, and fuel, improving system safety.

[0090] In addition, independent flow channels simplify the maintenance and inspection process because each flow channel can be inspected and maintained individually.

[0091] According to some embodiments of the present invention, the first oxidant outlet 71, the fuel outlet 103 and the first driving gas outlet 61 are all connected to the valves of the engine 8.

[0092] The driving gas flows out from the first driving gas outlet 61 to the valve, and the driving gas is used to drive the valve to open; the fuel flows out from the fuel outlet 103 and passes through the valve, enters the cooling pipe located on the outer wall of the thrust chamber and regenerates and cools the thrust chamber. After the regeneration and cooling is completed, the fuel flows back to the valve; after the regeneration and cooling is completed, the valve opens, and the oxidant and fuel enter the thrust chamber through the valve to mix and burn.

[0093] In this embodiment, the actual working process is described as follows:

[0094] (1) Valve control stage: Drive gas is introduced into the drive gas inlet 6. The drive gas flows along the drive gas inner flow channel 52. Then the drive gas flows out from the first drive gas outlet 61 to the valve. At this time, the drive gas is used to drive the valve to open.

[0095] (2) Regeneration Cooling Stage: Fuel enters the internal flow channel system through the fuel inlet 101 of the manifold 1. The fuel flows along the internal fuel flow channel 102 inside the manifold, which is a channel specifically designed for fuel. The fuel flows out from the end of the internal flow channel system, namely the fuel outlet 103. The fuel outlet 103 is directly connected to the valve of the engine 8, which is the key interface for fuel to enter the engine 8. After flowing out, the fuel passes through the valve and flows into the engine. The valve here plays a role in controlling the fuel flow rate and direction.

[0096] After passing through the valve, the fuel enters the cooling pipes located on the outer wall of the thrust chamber and regenerates and cools the thrust chamber. At this point, the fuel is used to cool the body of the thrust chamber. This is because the fuel absorbs heat from the outer wall of the thrust chamber as it flows through the cooling pipes, thereby reducing the temperature of the thrust chamber and improving the thermal efficiency and lifespan of the engine.

[0097] After completing its cooling process, the fuel is not discharged directly but flows back into the valve. This method of recycling fuel for cooling is called regenerative cooling, a highly efficient cooling technology that can significantly improve rocket engine performance.

[0098] (3) Combustion stage: Finally, the fuel, after completing the cooling function, re-enters the valve to prepare for the next combustion process. At this time, the oxidant flows along the oxidant inner channel 51 and flows out to the valve through the first oxidant outlet 71. Under the control of the valve, the fuel and oxidant enter the thrust chamber and mix, then burn and generate thrust.

[0099] In this way, through the regenerative cooling process, the fuel can absorb and carry away the heat from the thrust chamber wall, improving the combustion efficiency of engine 8, reducing the temperature of the thrust chamber wall, reducing thermal stress, and thus extending the service life of engine 8. Furthermore, through regenerative cooling, the fuel is used for cooling before combustion, improving fuel utilization.

[0100] In summary, the above design achieves an efficient regenerative cooling process by cleverly utilizing the flow and circulation of fuel, which helps to improve the performance and reliability of rocket engines.

[0101] like Figures 4 to 8 As shown, according to some embodiments of the present invention, the assembly block further includes a filter assembly 2, which is installed at the first oxidant outlet 71 and is used to filter impurities contained in the oxidant.

[0102] In this embodiment, the filter assembly 2 is installed at the first oxidant outlet 71, which is the necessary path for the oxidant to flow from the collection block to the engine 8 valve. The main function of the filter assembly 2 is to filter the oxidant contained in the oxidant inner channel 51, removing any impurities that may be present, such as solid particles, rust, or other foreign substances.

[0103] In this way, by removing impurities from the oxidizer, the filter assembly 2 helps improve combustion efficiency within the combustion chamber of engine 8, as a cleaner oxidizer can react more effectively with the fuel. Furthermore, filtering impurities also protects the valves and other critical components of engine 8 from wear or damage, thereby extending the service life of engine 8. In addition, a cleaner oxidizer reduces the risk of engine 8 malfunction, which is crucial for ensuring the safety of rocket flight.

[0104] The filter assembly 2 can be made of high-temperature and corrosion-resistant materials to adapt to the oxidizer and its chemical properties, as well as the high-temperature environment of the engine 8. The filter can have a specific pore size and structural design to achieve efficient filtration while maintaining low flow resistance. Furthermore, the design of the filter assembly 2 facilitates maintenance and replacement to meet the needs of long-term use and repeated assembly during multiple launches.

[0105] Considering that the assembly block is manufactured using 3D printing technology, the filter assembly 2 may also be manufactured as a single piece using 3D printing technology to achieve a complex internal structure.

[0106] After the filter assembly 2 is installed, the oxidant flows as follows: the oxidant flows through the oxidant inner channel 51 to the first oxidant outlet 71. As the oxidant flows through the first oxidant outlet 71, the filter assembly 2 filters the oxidant, intercepting and removing impurities. The filtered, clean oxidant then flows into the valve of the engine 8, ready to enter the combustion chamber. The clean oxidant helps optimize the performance of the engine 8, improve the reliability of the engine 8, increase combustion efficiency, and reduce the probability of malfunctions and maintenance requirements.

[0107] In summary, by integrating the filter assembly 2 into the assembly block, this invention not only improves the cleanliness of the oxidizer but also contributes to enhancing the performance and reliability of the entire rocket engine system. This design is particularly suitable for the regenerative cooling engine 8, which has extremely high requirements for oxidizer quality, ensuring stable operation of the engine 8 under various flight conditions.

[0108] In one embodiment of the present invention, the assembly block further includes: an oxidant external pipe 91, a driving gas external pipe 92, and a fuel external pipe 104.

[0109] The oxidant outer pipe 91 is connected to the oxidant inner flow channel 51. Oxidant outer ring outlets 911 are formed on both sides of the oxidant outer pipe 91. The oxidant outer ring outlets 911 are connected to the inner flow channel system of the left and right aggregate blocks through the ring pipe 200 to form an oxidant ring supply loop.

[0110] The external driving gas pipe 92 is connected to the internal driving gas flow channel 52. The external driving gas pipe 92 forms an external driving gas outlet 921 on both sides. The external driving gas outlet 921 is connected to the internal flow channel system of the left and right aggregate blocks through the ring pipe 200 to form a driving gas ring supply loop.

[0111] Two fuel inlets 101 are formed at both ends of the external fuel pipe 104, and the external fuel pipe 104 is connected to two sets of internal fuel channels 102. The external fuel pipe 104 is connected to the internal channel system of the left and right aggregate blocks through the ring pipe 200 to form a fuel ring supply loop.

[0112] In this embodiment, the oxidizer external conduit 91 is connected to the oxidizer internal flow channel 51 inside the assembly block, and is responsible for transporting the oxidizer from the assembly block to other parts outside the engine 8. It can be transported to the assembly blocks on the left and right sides through the ring pipe 200. Through the oxidizer external conduit 91 and its outer ring outlet, the assembly block can form a ring supply loop with other engine assemblies 100 on the rocket, realizing uniform distribution and continuous supply of oxidizer.

[0113] Similar to the oxidizer external conduit 91, the propulsion gas external conduit 92 connects to the propulsion gas internal flow channel 52 inside the assembly block, responsible for delivering propulsion gas to other parts outside the engine 8. It can be delivered to the left and right assembly blocks via the ring pipe 200. Through the propulsion gas external conduit 92 and its outer ring outlet, the assembly block can form a propulsion gas annular supply loop with other engine assemblies 100 on the rocket, ensuring a continuous supply of propulsion gas.

[0114] The external fuel conduit 104 simultaneously handles both fuel input and output. Specifically, during operation, the external fuel conduit 104 connects to an external fuel conduit. On one hand, fuel can be fed into the external fuel conduit 104 from the external fuel conduit, with both ends serving as fuel inlets. On the other hand, excess unused fuel can exist within the external fuel conduit 104 and the internal fuel flow channel 102. This excess fuel can flow out along the external fuel conduit 104 to the external fuel conduit, thus enabling fuel output from both ends of the external fuel conduit 104. Similarly, fuel delivered from the external fuel conduit 104 can be transported through the ring pipe 200 to the left and right aggregator blocks, forming a fuel ring supply loop with the other engine assemblies 100 on the rocket, ensuring a continuous fuel supply.

[0115] In addition, the external fuel pipe 104 can also achieve precise distribution of fuel in the two sets of internal fuel channels 102. It can be understood that the two sets of internal fuel channels 102 located on the left and right sides of the collection block 1 can be indirectly connected through the middle external fuel pipe 104. Therefore, when the fuel in one set of internal fuel channels 102 is insufficient, it can be supplemented by the excess fuel in the other set of internal fuel channels 102, thereby achieving uniform distribution of fuel on both sides.

[0116] The annular supply loop design facilitates the uniform distribution of oxidizer, propellant gas, and fuel within the rocket engine. Furthermore, the annular loop ensures a continuous supply of oxidizer, propellant gas, and fuel, thereby improving system reliability.

[0117] Furthermore, this design can accommodate different numbers and configurations of engine assemblies 100, increasing the flexibility of rocket design. The ring-loop design also reduces pipe length and connection points, thereby reducing pressure loss and potential failure points.

[0118] Thus, the above design, by integrating the outer pipes and outer ring outlets into the assembly block, achieves a ring-shaped supply loop for oxidizer, propellant gas, and fuel, optimizing the supply efficiency and reliability of the rocket engine system. At the same time, this design also simplifies the system's piping layout, reduces maintenance difficulty, and improves overall performance.

[0119] like Figures 9 to 13 As shown, according to some embodiments of the present invention, the two ends of the oxidant external pipeline are respectively provided with oxidant threaded connectors 912, the two ends of the driving gas external pipeline are respectively provided with driving gas threaded connectors 922, and the two ends of the fuel external pipeline 104 are respectively provided with fuel threaded connectors 105.

[0120] Each end of the oxidizer external conduit 91, the propulsion gas external conduit 92, and the fuel external conduit 104 is provided with a threaded connector. These connectors are used to connect to corresponding conduits of other engine assemblies 100 on the rocket via the ring pipe 200. It is understood that these threaded connectors provide a reliable and detachable connection method, facilitating installation, maintenance, and replacement.

[0121] Specifically, during rocket assembly, the threaded connectors of the oxidizer external conduit 91, the propulsion gas external conduit 92, and the fuel external conduit 104 are used to connect to the corresponding piping systems on the rocket via the ring pipe 200. Through these connections, the oxidizer external conduit 91, the propulsion gas external conduit 92, and the fuel external conduit 104 respectively form the required annular supply loops with the remaining engine assemblies 100 on the rocket. Oxidizer, propulsion gas, and fuel are continuously delivered to the engine 8 through these loops, supporting the normal operation of the rocket. Before rocket launch, the system can be tested and maintained according to design requirements through threaded connectors at different locations to ensure the integrity and functionality of the supply loops, for example, by using the threaded connectors of the propulsion gas inlet 6 or the oxidizer inlet 7 for testing.

[0122] Threaded designs are typically used in conjunction with sealing elements (such as ball joints, gaskets, or O-rings) to ensure a tight seal at the connection and prevent leakage of oxidizers, drive gases, and fuel.

[0123] In this way, threaded fittings allow for quick and secure pipe connections, improving assembly efficiency. Furthermore, the detachable nature of threaded connections simplifies maintenance and repair processes, facilitating inspection and replacement of components within the piping system.

[0124] Furthermore, the threaded nozzle design allows the piping system to adapt to different connection requirements and rocket configurations. The threaded nozzle design also adheres to specific standards, enabling interchangeability between components from different manufacturers.

[0125] like Figures 4 to 13 As shown, according to some embodiments of the present invention, the upper side of the main body 1 of the assembly block is provided with an oxidant inner pipe 53 and a driving gas inner pipe 54. The upper end of the oxidant inner pipe 53 forms an oxidant inlet 7 and a partial oxidant inner flow channel 51 is formed inside it; the upper end of the driving gas inner pipe 54 forms a driving gas inlet 6 and a partial driving gas inner flow channel 52 is formed inside it.

[0126] Both the external oxidant pipe 91 and the external driving gas pipe 92 are located on the lower side of the main body 1 of the assembly block. The external oxidant pipe 91 is connected to the internal oxidant pipe 53, and the external driving gas pipe 92 is connected to the internal driving gas pipe 54.

[0127] In this embodiment, the oxidant inner pipe 53 and the driving gas inner pipe 54 are both designed on the upper side of the main body 1 of the assembly block, while the oxidant outer pipe 91 and the driving gas outer pipe 92 are both designed on the lower side of the main body 1 of the assembly block, opposite to the inner pipes, for transporting the oxidant and driving gas to other parts outside the engine 8.

[0128] The oxidant outer pipe 91 is connected to the oxidant inner pipe 53, ensuring that the oxidant can flow from the inner pipe to the outer pipe. The driving gas outer pipe 92 is connected to the driving gas inner pipe 54, ensuring that the driving gas can flow from the inner pipe to the outer pipe.

[0129] Specifically, the flow paths of the oxidizer and driving gas within the manifold are as follows: The oxidizer and driving gas enter the manifold through the upper oxidizer inlet 7 and driving gas inlet 6, respectively. Inside the manifold, the oxidizer and driving gas flow through the inner pipes (i.e., the oxidizer inner pipe 53 and the driving gas inner pipe 54), undergoing filtration and distribution. The oxidizer and driving gas flow from the inner pipes (i.e., the oxidizer inner pipe 53 and the driving gas inner pipe 54) to the lower outer pipes (i.e., the oxidizer outer pipe 91 and the driving gas outer pipe 92), and are then distributed to the engine 8 or the annular supply loop through the outer pipes (i.e., the oxidizer outer pipe 91 and the driving gas outer pipe 92).

[0130] In the process of distributing to engine 8, firstly, the oxidant and the driving gas flow into the corresponding inner channels (i.e., the oxidant outer channel 91 and the driving gas outer channel 92) through the outer pipes, and then flow out from the corresponding outlets (i.e., the first oxidant outlet 71 and the first driving gas outlet 61) along the inner channels, and finally enter the valve of engine 8.

[0131] During the process of being distributed to the annular supply loop, the oxidant and the driving gas flow out through the outer pipes (i.e., the oxidant outer pipe 91 and the driving gas outer pipe 92) to the corresponding outer ring outlets (i.e., the oxidant outer ring outlet 911 and the driving gas outer ring outlet 921), and enter the annular supply loop from the outer ring outlets.

[0132] By placing the inner and outer pipes on opposite sides of the main body 1, a compact spatial layout can be achieved, reducing the space occupied. Furthermore, the design of the inner and outer pipes allows for effective distribution and control of the oxidizer and driving gas before they flow into the engine 8.

[0133] Furthermore, the upper inlet design simplifies the connection to the external oxidizer and propulsion gas supply systems, while the lower external pipe design facilitates maintenance and inspection due to its easier accessibility. Moreover, the external pipe is located on the lower side of the main assembly block 1, allowing it to form a ring-shaped supply loop with the other two engines on the rocket.

[0134] This design integrates internal and external pipes on the upper and lower sides of the main body 1 of the assembly block, respectively, to achieve efficient distribution and supply of oxidant and driving gas, while simplifying the layout and maintenance of the system.

[0135] like Figures 9 to 13As shown, according to some embodiments of the present invention, the oxidant inner pipe 53 and the driving gas inner pipe 54 are arranged parallel to each other and staggered front to back, and the oxidant outer pipe 91 and the driving gas outer pipe 92 are arranged parallel to each other and staggered front to back and up to down.

[0136] The oxidant inner pipe 53 is perpendicular to the oxidant outer pipe 91, and the driving gas inner pipe 54 is perpendicular to the driving gas outer pipe 92.

[0137] In this embodiment, the oxidant inner pipe 53 and the driving gas inner pipe 54 are arranged parallel to each other on the upper side of the main body 1 of the collection block, but are staggered in the front-back direction, which means that they are on the same horizontal plane but not on the same straight line.

[0138] The oxidant external pipe 91 and the driving gas external pipe 92 are parallel to each other on the lower side of the main body 1 of the assembly block, but they are staggered in both the front-to-back and vertical directions, providing flexible connection points and spatial layout. The oxidant internal pipe 53 and the oxidant external pipe 91, as well as the driving gas internal pipe 54 and the driving gas external pipe 92, are perpendicularly connected to each other.

[0139] This staggered and vertically connected design allows for more efficient use of the internal space of the manifold, reducing interference between pipes. Furthermore, this layout allows for better flow characteristics and lower fluid resistance for both the oxidant and the driving gas as they flow into and out of the manifold.

[0140] Furthermore, the staggered layout of the piping makes it easier to access each connection point during maintenance and inspection, improving the convenience of maintenance work. The parallel and vertical layout of the piping facilitates modular design, allowing for adjustments to be made according to different rocket engine configurations.

[0141] Furthermore, the staggered layout of the oxidant and driving gas pipelines can reduce potential interference between them and improve system stability.

[0142] The specific flow path is as follows: the oxidizer and propulsion gas enter the assembly block through staggered inner pipe inlets. The fluid flows within the inner pipes and channels of the assembly block, undergoing necessary treatments such as filtration. The fluid then flows from the inner pipes to the outer pipes through vertically connected outlets. Finally, the fluid flows through the outer pipes to the remaining dual engines on the rocket, forming the required annular supply loop.

[0143] The above design, through careful planning of the pipeline layout, achieves efficient utilization of the internal space of the assembly block, optimizes the fluid flow path, and improves the overall performance of the entire rocket engine system.

[0144] like Figures 9 to 13As shown, according to some embodiments of the present invention, the left and right sides of the assembly block body 1 are respectively provided with first mounting interfaces 4 for mounting with the engine 8, and the outer side of the assembly block body 1 is provided with a second mounting interface 3 for mounting with the rocket body.

[0145] In this embodiment, the assembly block is fixed to the corresponding mounting portion of the engine 8 via the first mounting interfaces 4 on both the left and right sides. The second mounting interface 3 on the outer side of the assembly block is fixed to the mounting portion of the rocket body. Through these mounting interfaces, the assembly block is firmly connected to the engine 8 and the rocket body, forming a complete rocket engine system. After installation, the piping system inside the assembly block begins operation, distributing oxidizer and propulsion gas to the engine 8. Before rocket launch, the assembly block connected via the mounting interfaces can undergo overall testing to ensure the integrity and functionality of the system.

[0146] In this way, the dedicated mounting interface ensures precise positioning and alignment between the assembly block and the engine 8 and the rocket body. A well-designed mounting interface simplifies the installation process of the assembly block with the engine 8 and the rocket body, improving assembly efficiency.

[0147] Furthermore, the fixing method implemented through a dedicated interface helps improve the stability and reliability of the overall structure, and facilitates subsequent maintenance, inspection, and possible replacement work.

[0148] This design, by setting a dedicated mounting interface at a specific location on the main body 1 of the assembly block, achieves an efficient and stable connection with the engine 8 and the rocket body, while simplifying the installation and maintenance process. This helps improve the reliability and ease of operation of the rocket engine system.

[0149] The present invention also provides a method for manufacturing the attitude control engine system according to the above embodiments of the present invention. The manufacturing method includes the following steps:

[0150] S1. Use 3D printing technology to create a block assembly, fix the engine onto the block assembly, and form an engine assembly 100.

[0151] S2. Multiple engine assemblies 100 are connected end to end in sequence using the ring pipe 200 to form a ring structure.

[0152] In this embodiment, structures such as the assembly block, ring pipe, or engine can be manufactured using 3D printing technology.

[0153] The present invention proposes a method for manufacturing an attitude control engine system. The method utilizes 3D printing technology to achieve a simple and highly integrated modular design, which has the advantages of low cost, short processing cycle, and the ability to print multiple parts at once. This method meets the usage requirements of the regenerative cooling engine assembly 100, thereby ensuring the safe and reliable operation of the rocket.

[0154] The present invention also provides a rocket. The rocket includes the attitude control engine system described in the above embodiments of the present invention.

[0155] The rocket provided by the present invention has the same advantages as described above because it includes the attitude control engine system in the above embodiments of the present invention.

[0156] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An attitude control engine system, characterized in that, include: A plurality of engine assembly (100) includes: a plurality of engines (8) and at least one assembly block (1), wherein the plurality of engines (8) are disposed on the assembly block (1), and the assembly block (1) is provided with an internal flow channel system for distributing oxidant, driving gas and fuel to the engines (8); Multiple ring pipes (200) are connected to the internal flow channel system of the assembly block (1) of each of the engine assemblies (100), and the multiple engine assemblies (100) are connected end to end to form a ring structure. The assembly block (1) is provided with a driving gas inlet (6), an oxidant inlet (7) and at least one fuel inlet (101), and the driving gas inlet (6), the oxidant inlet (7) and the fuel inlet (101) are respectively connected to the internal flow channel system; The internal flow system includes: two sets of oxidant internal flow channels (51), two sets of driving gas internal flow channels (52) and two sets of fuel internal flow channels (102). The assembly block (1) also includes: An external oxidant pipe (91) is connected to the internal oxidant flow channel (51). An external oxidant outlet (911) is formed on both sides of the external oxidant pipe (91). The external oxidant outlet (911) is connected to the internal flow channel system of the collection block (1) on the left and right sides through the ring pipe (200) to form an oxidant ring supply loop. An external driving gas pipe (92) is connected to the internal driving gas flow channel (52). External driving gas outlets (921) are formed on both sides of the external driving gas pipe (92). The external driving gas outlets (921) are connected to the internal flow channel system of the collection blocks (1) on the left and right sides through the ring pipe (200) to form a driving gas ring supply loop. The fuel external pipe (104) has two fuel inlets (101) at its two ends, and the fuel external pipe (104) is connected to two sets of fuel internal flow channels (102). The fuel external pipe (104) is connected to the internal flow channel system of the collection blocks (1) on the left and right sides through the ring pipe (200) to form a fuel ring supply loop.

2. The attitude control engine system according to claim 1, characterized in that, Four engine assemblies (100) are provided, and each engine assembly (100) is distributed at a 90° interval. Each of the engine assemblies (100) includes two engines (8) and an assembly block (1), with first mounting interfaces (4) for mounting the engines (8) on the left and right sides of the assembly block (1).

3. The attitude control engine system according to claim 2, characterized in that, The driving gas inlet (6), the oxidant inlet (7) and the fuel inlet (101) are used to receive driving gas, oxidant and fuel respectively. The internal flow channel system forms two sets of internal flow channel outlets. The two sets of internal flow channel outlets are respectively located on both sides of the collection block (1) and respectively connected to the two engines (8).

4. The attitude control engine system according to claim 3, characterized in that, Two sets of oxidant internal flow channels (51), two sets of driving gas internal flow channels (52) and two sets of fuel internal flow channels (102) are located on both sides of the aggregate block (1); The internal flow channel outlet includes two first oxidant outlets (71), two first driving gas outlets (61), and two fuel outlets (103). The oxidant internal flow channel (51) is connected to the oxidant inlet (7) and the first oxidant outlet (71), the driving gas internal flow channel (52) is connected to the driving gas inlet (6) and the first driving gas outlet (61), the number of fuel inlets (101) is two, and the two fuel inlets (101) are located on both sides of the collection block (1), and the fuel internal flow channel (102) is connected to the fuel inlet (101) and the fuel outlet (103).

5. The attitude control engine system according to claim 4, characterized in that, The first oxidant outlet (71), the fuel outlet (103) and the first drive gas outlet (61) are all connected to the valves of the engine (8); The driving gas flows from the first driving gas outlet (61) to the valve, and the driving gas is used to drive the valve to open.

6. The attitude control engine system according to claim 4, characterized in that, Also includes: A filter assembly (2) is installed at the first oxidant outlet (71) and is used to filter impurities in the oxidant contained in the oxidant inner channel (51).

7. The attitude control engine system according to claim 1, characterized in that, The oxidant external pipe (91) is provided with oxidant threaded connectors (912) at both ends, the driving gas external pipe (92) is provided with driving gas threaded connectors (922) at both ends, and the fuel external pipe (104) is provided with fuel threaded connectors (105) at both ends.

8. The attitude control engine system according to claim 1, characterized in that, The upper side of the collection block (1) is provided with an oxidant inner pipe (53) and a driving gas inner pipe (54). The upper end of the oxidant inner pipe (53) forms the oxidant inlet (7) and a portion of the oxidant inner flow channel (51) is formed inside it; the upper end of the driving gas inner pipe (54) forms the driving gas inlet (6) and a portion of the driving gas inner flow channel (52) is formed inside it. The oxidant external pipe (91) and the driving gas external pipe (92) are both located on the lower side of the collection block (1). The oxidant external pipe (91) is connected to the oxidant internal pipe (53), and the driving gas external pipe (92) is connected to the driving gas internal pipe (54).

9. The attitude control engine system according to claim 8, characterized in that, The oxidant inner pipe (53) and the driving gas inner pipe (54) are parallel to each other and staggered from each other, and the oxidant outer pipe (91) and the driving gas outer pipe (92) are parallel to each other and staggered from each other; The inner oxidant pipe (53) is perpendicular to the outer oxidant pipe (91), and the inner driving gas pipe (54) is perpendicular to the outer driving gas pipe (92).

10. A method for manufacturing an attitude control engine system according to any one of claims 1 to 9, characterized in that, include: Using 3D printing technology, a block (1) is made, and the engine (8) is fixed on the block (1) to form an engine assembly (100). Multiple engine assemblies (100) are connected end to end in sequence using a ring tube (200) to form a ring structure.

11. A rocket, characterized in that, include: The attitude control engine system according to any one of claims 1 to 9.

Images