A cluster block, engine assembly, and rocket attitude control engine system

Abstract

The application provides a cluster block, an engine assembly and a rocket attitude control engine system. The cluster block comprises a cluster block body, two sides of the cluster block body are used for mounting engines respectively, the cluster block body is provided with a driving gas inlet, an oxidant inlet and at least one fuel inlet; the inside of the cluster block body is further provided with an internal flow channel system for distributing the oxidant, the driving gas and the fuel into the engines, the driving gas inlet, the oxidant inlet and the fuel inlet are communicated to the internal flow channel system respectively, the internal flow channel system is formed with two groups of internal flow channel outlets, the two groups of internal flow channel outlets are arranged on the two sides of the cluster block body respectively and are communicated to the engines respectively. The cluster block for the rocket engine and the engine assembly of the rocket of the application realize the input of the oxidant, the fuel and the driving gas of two engines through the ingenious internal flow channel design, ensure the function realization of the double-engine combination scheme of the regenerative cooling engine and realize the simple and reliable integration of the new scheme engine.

Description

Technical Field

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

[0002] In related technologies, attitude control engines are used to adjust the attitude of rockets during flight. They are generally distributed circumferentially. In order to simplify the structure, multiple circumferentially arranged engines are often integrated with an oxidizer supply system to optimize the structural layout of the engines on the rocket system and improve the efficiency of gas and liquid supply.

[0003] However, traditional rocket engines typically use independent piping systems to supply each engine with the necessary fuel, oxidizer, and propellant gases. While this design can meet the needs of a single engine, when multiple engines need to work in coordination, the independent piping systems in the traditional approach significantly increase the complexity of the entire system. This not only increases manufacturing difficulty but can also affect system reliability. Furthermore, complex piping systems mean higher maintenance costs. Even a small malfunction can cause the entire system to shut down, increasing repair time and expenses. Summary of the Invention

[0004] This invention provides an assembly block, an engine component, and a rocket attitude control engine system to address the deficiencies in the prior art and achieve the following technical effects: through a clever internal flow channel design, the input of oxidizer, fuel, and control gas from both engines is realized, and the functionality of the dual-engine combination scheme of the regenerative cooling engine is ensured, achieving simple and reliable integration of the new engine scheme.

[0005] An assembly block for a rocket engine according to a first aspect embodiment of the present invention includes:

[0006] The main body of the assembly block has two sides for mounting the engine. The main body of the assembly block has 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.

[0007] The main body of the assembly block is also provided with an internal flow channel system for distributing oxidant, driving gas and fuel to the engine. 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, which are respectively located on both sides of the main body of the assembly block and respectively connected to the two engines.

[0008] According to one embodiment of 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, the two sets of driving gas internal flow channels, and the two sets of fuel internal flow channels are respectively located on both sides of the main body of the aggregate block;

[0009] The internal flow channel outlet includes two first oxidant outlets, two first driving gas outlets, and two fuel outlets;

[0010] 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 main body of the collection block, and the fuel internal flow channel is connected to the fuel inlet and the fuel outlet.

[0011] According to one embodiment of the present invention, the first oxidant outlet, the fuel outlet, and the first drive gas outlet are connected to a valve of the engine;

[0012] 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.

[0013] According to one embodiment of the present invention, a filter assembly is further included, the filter assembly being installed at the first oxidant outlet, and the filter assembly being used to filter impurities from the oxidant contained in the oxidant inner channel.

[0014] According to one embodiment of the present invention, it further includes:

[0015] An external oxidizer pipe is connected to the internal oxidizer flow channel. Oxidizer outer ring outlets are formed on both sides of the external oxidizer pipe. The external oxidizer pipe is used to form an oxidizer ring supply loop with the other engines on the rocket.

[0016] 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 pipe is used to form a driving gas annular supply loop with the other two engines on the rocket.

[0017] The external fuel conduit has two fuel inlets at its two ends and is connected to two sets of internal fuel channels. The external fuel conduit is used to form a fuel annular supply loop with the other two engines on the rocket.

[0018] According to one embodiment of the present invention, the two ends of the oxidant external pipeline are respectively provided with oxidant threaded connectors, the two ends of the driving gas external pipeline are respectively provided with driving gas threaded connectors, and the two ends of the fuel external pipeline are respectively provided with fuel threaded connectors.

[0019] According to one embodiment of the present invention, an oxidant inlet pipe and a driving gas inlet pipe are provided on the upper side of the main body of the collection block. The upper end of the oxidant inlet pipe forms the oxidant inlet and a portion of the oxidant inlet channel is formed inside it; the upper end of the driving gas inlet pipe forms the driving gas inlet and a portion of the driving gas inlet channel is formed inside it.

[0020] Both the external oxidant pipe and the external driving gas pipe are located on the lower side of the main body of the assembly 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.

[0021] According to one embodiment of the present invention, the inner oxidant pipe and the inner driving gas pipe are arranged parallel to each other and staggered front to back, and the outer oxidant pipe and the outer driving gas pipe are arranged parallel to each other and staggered front to back and up to down;

[0022] 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.

[0023] According to one embodiment of the present invention, the left and right sides of the main body of the assembly block are respectively provided with second mounting interfaces for mounting with the engine, and the outer side of the main body of the assembly block is provided with a first mounting interface for mounting with the rocket body.

[0024] An engine assembly for a rocket according to a second aspect of the present invention includes:

[0025] As described in the first aspect of the present invention, an assembly block for a rocket engine;

[0026] Two engines are installed on the left and right sides of the main body of the assembly block, respectively.

[0027] A rocket attitude control engine system according to a third aspect of the present invention includes an engine assembly of a rocket as described in a second aspect of the present invention.

[0028] 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 from two engines, while ensuring the functional realization of the dual-engine combination scheme of regenerative cooling engine, achieving simple and reliable integration of the new engine scheme.

[0029] Furthermore, compared to related technologies, the present invention has at least the following advantages:

[0030] (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, 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.

[0031] (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 engine performance.

[0032] (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.

[0033] (4) Improved reliability: Through precise internal flow channel design and integrated filters, the assembly block helps improve the reliability of rocket engines and reduce the risk of failure due to oxidizers and oxidizer impurities.

[0034] (5) 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 the engine and extends the service life of the engine.

[0035] (6) Asymmetric input of oxidizer, fuel and control gas: The ingenious internal flow channel design enables asymmetric input of oxidizer, fuel and control gas for the two engines, which improves space utilization efficiency and adapts to specific rocket design requirements. Attached Figure Description

[0036] 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.

[0037] Figure 1 This is a schematic diagram of the rocket engine assembly provided by the present invention;

[0038] Figure 2This is one of the structural schematic diagrams of the assembly block for rocket engines provided by the present invention;

[0039] Figure 3 It is along Figure 2 Sectional view of line AA in the middle;

[0040] Figure 4 It is along Figure 2 Sectional view of the middle BB line;

[0041] Figure 5 It is along Figure 2 A cross-sectional view of the CC line;

[0042] Figure 6 It is along Figure 2 Sectional view of the DD line;

[0043] Figure 7 This is the second structural schematic diagram of the assembly block for rocket engines provided by the present invention;

[0044] Figure 8 It is along Figure 7 A cross-sectional view of the EE line;

[0045] Figure 9 It is along Figure 7 Sectional view of the middle FF line;

[0046] Figure 10 It is along Figure 7 A cross-sectional view of the GG line in the middle;

[0047] Figure 11 It is along Figure 7 A cross-sectional view of the middle HH line.

[0048] Figure label:

[0049] 1. Main body of the assembly block; 2. Filter assembly; 3. First mounting interface; 4. Second mounting interface; 51. Oxidant internal flow channel; 52. Driving gas internal flow channel; 53. Oxidant internal pipe; 54. Driving gas internal pipe; 6. Driving gas inlet; 61. First driving 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 the embodiments of the present invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of the present invention. In addition, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0053] In the description of the embodiments of the present invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; 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. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of the present invention based on the specific circumstances.

[0054] 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.

[0055] The following description, with reference to the accompanying drawings, illustrates an assembly block for a rocket engine and a rocket engine assembly. It should be noted that the aforementioned rocket engine assembly includes the aforementioned assembly block for a rocket engine.

[0056] like Figures 1 to 11 As shown, the assembly block for a rocket engine according to a first aspect embodiment of the present invention includes:

[0057] The main body 1 of the assembly block is used to install the engine 8 on both sides. The main body 1 of the assembly block 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 used to receive driving gas, oxidant and fuel respectively.

[0058] The main body 1 of the assembly block is also equipped with an internal flow channel system, which is used to distribute oxidant, driving gas and fuel into the engine 8. The driving gas inlet 6, oxidant inlet 7 and 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, which are respectively located on both sides of the main body 1 of the assembly block and are respectively connected to the engine 8.

[0059] In the above description of the structure of the assembly block used for rocket engines, the assembly block is mainly composed of the following parts: the main body 1 of the assembly block is the core part of the assembly block, designed to install the engines 8 on both sides; the driving gas inlet 6, that is, an inlet on the main body 1 of the assembly block is used to receive driving gas; the oxidizer inlet 7, similarly, an inlet on the main body 1 of the assembly block is used to receive oxidizer; the fuel inlet 101 is used to receive fuel; and the internal flow channel system, that is, an internal flow channel system is designed inside the main body 1 of the assembly block, which is responsible for distributing the received oxidizer, driving gas and fuel into the engine 8.

[0060] The driving gas inlet 6, oxidizer inlet 7, and fuel inlet 101 are all connected to the internal flow channel system to ensure smooth fluid flow. The internal flow channel system forms two sets of internal flow channel outlets on the left and right sides of the main body 1, respectively. Each set of internal flow channel outlets is directly connected to an engine 8 to deliver oxidizer, driving gas, and fuel to the corresponding components of the engine 8.

[0061] Specifically, within the assembly block of the present invention, the flow path of the oxidant is as follows: the oxidant enters the assembly block body 1 through the oxidant inlet 7. Inside the assembly 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 1 to 3 as well as Figure 5 and Figure 6As 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 to other external components). 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.

[0062] Within the assembly block of this invention, the flow path of the driving gas is as follows: the driving gas enters the assembly block body 1 through the driving gas inlet 6. The driving gas flows within the assembly block along specific internal channels, which differ from the oxidant channels to ensure that both can be controlled independently. For example... Figures 1 to 3 as well as Figure 9 As 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 to other external components). 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.

[0063] In the regenerative cooling engine 8, after the fuel (a propellant) flows through the valve housing of the engine 8, it first flows through the 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.

[0064] 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.

[0065] 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 8, achieving simple and reliable integration of the new engine 8.

[0066] Furthermore, compared to related technologies, the present invention has at least the following advantages:

[0067] (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.

[0068] (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.

[0069] (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.

[0070] (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.

[0071] (5) Regenerative cooling function: The design of the fuel block allows the fuel to cool the thrust chamber body before entering the valve, which improves the combustion efficiency of the engine 8 and extends the service life of the engine 8.

[0072] (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.

[0073] like Figures 2 to 6 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 main body 1 of the aggregate block.

[0074] The internal flow channel outlets include two first oxidant outlets 71, two first driving gas outlets 61, and two fuel outlets 103.

[0075] 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 main body 1 of the aggregate block, and the fuel internal flow channel 102 is connected to the fuel inlet 101 and the fuel outlet 103.

[0076] 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.

[0077] 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.

[0078] 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, which is used to control the opening and closing of the valves or perform other auxiliary functions.

[0079] The fuel flow path is as follows: Taking the engine 8 located on the left side of the main body 1 of the assembly block 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 main body 1 of the assembly block 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 main body 1 of the assembly block is similar to the above embodiment, and will not be described again here.

[0080] 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.

[0081] In addition, independent flow channels simplify the maintenance and inspection process because each flow channel can be inspected and maintained individually.

[0082] 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.

[0083] 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.

[0084] In this embodiment, the actual working process is described as follows:

[0085] (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.

[0086] (2) Regeneration and Cooling Stage: Fuel enters the internal flow channel system through the fuel inlet 101 of the main body 1 of the aggregate block. The fuel flows along the internal fuel flow channel 102 inside the aggregate block, 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 the driving gas drives the valve to open, the fuel flows out, passes through the valve, and flows into the engine. The valve here plays a role in controlling the fuel flow rate and direction.

[0087] 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.

[0088] 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.

[0089] (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.

[0090] 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.

[0091] 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.

[0092] like Figures 2 to 6As 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 from the oxidant contained in the oxidant inner channel.

[0093] 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 in the oxidant and remove any impurities that may be present, such as solid particles, rust, or other foreign substances.

[0094] 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.

[0095] 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.

[0096] 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.

[0097] 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.

[0098] 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.

[0099] like Figures 7 to 11As shown, according to some embodiments 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.

[0100] The oxidizer outer pipe 91 is connected to the oxidizer inner flow channel 51. Oxidizer outer ring outlets 911 are formed on both sides of the oxidizer outer pipe 91. The oxidizer outer pipe 91 is used to form an oxidizer ring supply loop with the other engines 8 on the rocket.

[0101] 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 pipe 92 is used to form a driving gas annular supply loop with the other engines 8 on the rocket.

[0102] 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 used to form a fuel annular supply loop with the other engines on the rocket.

[0103] In this embodiment, the oxidizer outer conduit 91 is connected to the oxidizer inner 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. Through the oxidizer outer conduit 91 and its outer ring outlet, the assembly block can form a ring supply loop with the other engines 8 on the rocket, achieving uniform distribution and continuous supply of oxidizer.

[0104] 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 the propulsion gas to the outside of the engine 8. Through the propulsion gas external conduit 92 and its outer ring outlet, the assembly block can form a propulsion gas annular supply loop with the other engines 8 on the rocket, ensuring a continuous supply of propulsion gas.

[0105] The external fuel pipe 104 simultaneously realizes the process of fuel input and output. Specifically, during use, the external fuel pipe 104 is connected to an external fuel pipe. On the one hand, the external fuel pipe can input fuel into the external fuel pipe 104, and the two ends of the external fuel pipe 104 serve as fuel inlets to realize the function of fuel input. On the other hand, there can be excess unused fuel in the external fuel pipe 104 and the internal fuel flow channel 102. At this time, the excess fuel can flow out along the external fuel pipe 104 to the external fuel pipe, so the two ends of the external fuel pipe 104 serve as fuel output.

[0106] 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 main body 1 of the aggregate block 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.

[0107] 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.

[0108] Furthermore, this design can accommodate different numbers and configurations of twin engines, increasing the flexibility of rocket design. The ring-loop design also reduces pipe length and connection points, thereby minimizing pressure loss and potential failure points.

[0109] 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.

[0110] like Figures 7 to 11 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.

[0111] Each end of the oxidizer external conduit 91, the propulsion gas external conduit 92, and the fuel external conduit 104 is equipped with a threaded connector. These connectors are used to connect to the corresponding conduits of other engines 8 on the rocket. It is understood that these threaded connectors provide a reliable and detachable connection method, facilitating installation, maintenance, and replacement.

[0112] Specifically, during rocket assembly, the threaded connectors of the oxidizer external pipe 91, the propulsion gas external pipe 92, and the fuel external pipe 104 are connected to the corresponding piping systems on the rocket. Through these connections, the oxidizer external pipe 91, the propulsion gas external pipe 92, and the fuel external pipe 104, respectively, form the required annular supply loops with the remaining dual engines on the rocket. Oxidizer, propulsion gas, and fuel are continuously delivered to 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.

[0113] 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.

[0114] 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.

[0115] 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.

[0116] like Figures 2 to 11 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.

[0117] 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.

[0118] In this embodiment, the drive and oxidant inner pipe 53 and the drive gas inner pipe 54 are both designed on the upper side of the assembly block body 1, while the oxidant outer pipe 91 and the drive gas outer pipe 92 are both designed on the lower side of the assembly block body 1, opposite to the inner pipes, for transporting the oxidant and drive gas to other parts outside the engine 8.

[0119] 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.

[0120] 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).

[0121] In the process of distributing to engine 8, firstly, the oxidant and driving gas flow into the corresponding inner channels (i.e., oxidant inner channel 51 and driving gas inner channel 52) through the outer pipes (i.e., oxidant outer channel 91 and driving gas outer channel 92), and then flow out from the corresponding outlets (i.e., first oxidant outlet 71 and first driving gas outlet 61) along the inner channels, and finally enter the valves of engine 8 and enter the thrust chamber for mixing and combustion.

[0122] 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.

[0123] 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.

[0124] Furthermore, the upper inlet design simplifies the connection with the external oxidizer and propulsion gas supply system, 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 8 on the rocket.

[0125] 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.

[0126] like Figures 7 to 11 As 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.

[0127] 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.

[0128] 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.

[0129] 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.

[0130] 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.

[0131] 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.

[0132] Furthermore, the staggered layout of the oxidant and driving gas pipelines can reduce potential interference between them and improve system stability.

[0133] 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 flows from the inner pipes to the outer pipes through vertically connected outlets. The fluid then flows through the outer pipes to the remaining eight engines on the rocket, forming the required annular supply loop.

[0134] 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.

[0135] like Figures 7 to 11As shown, according to some embodiments of the present invention, the left and right sides of the assembly block body 1 are respectively provided with second mounting interfaces 4 for mounting with the engine 8, and the outer side of the assembly block body 1 is provided with a first mounting interface 3 for mounting with the rocket body.

[0136] In this embodiment, the assembly block is docked and fixed to the corresponding mounting portion of the engine 8 via the second mounting interfaces 4 on both the left and right sides. The first mounting interface 3 on the outer side of the assembly block is docked and 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 to operate, 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.

[0137] 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.

[0138] 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.

[0139] 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.

[0140] like Figures 1 to 11 As shown, the rocket engine assembly according to a second aspect embodiment of the present invention includes two rocket engines and a assemblies for the rocket engines as described in the first aspect embodiment of the present invention. The two rocket engines are respectively mounted on the left and right sides of the assemblies body 1.

[0141] like Figures 1 to 11As shown, in a specific embodiment of the present invention, the assembly block consists of one main block 1 and two oxidizer path filters. One engine 8 is mounted on each side of the assembly block, forming a dual-engine assembly of engine 8. Oxidizer and driving gas enter through the central inlet of the assembly block, while fuel enters through the lower inlet of the assembly block and then through the internal flow channels at the bottom and sides of the assembly block to the corresponding valve inlet. The fuel path first passes through the valve into the cooling flow channel on the outer wall of the thrust chamber to cool the thrust chamber before returning to the valve, achieving regenerative cooling. A filter assembly is integrated at the outlet of the oxidizer internal pipe 53 to filter the oxidizer. Threaded connectors are integrated on both sides of the lower part of the assembly block, which can form a loop with the other dual-engine assemblies of engine 8 on the rocket through pipelines, achieving a circular supply of oxidizer, fuel, and driving gas. Through the integrated design of the internal flow channels of the assembly block itself and the application of 3D printing technology, the input of oxidizer, fuel, and driving gas to the corresponding positions is realized, simplifying the structure of the engine assembly.

[0142] In summary, this invention proposes a simple and highly integrated modular design using 3D printing technology. It has the advantages of low cost, short processing cycle, and the ability to print multiple parts at once, meeting the requirements of dual-engine regenerative cooling engines and thus ensuring the safe and reliable operation of rockets.

[0143] The present invention also protects a rocket attitude control engine system, comprising the rocket engine assembly as described in the second aspect of the present invention.

[0144] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0145] 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. A assemblies for rocket engines, characterized in that, include: The main body of the assembly block has two sides for mounting engines. The main body of the assembly block has 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 main body of the assembly block is also provided with an internal flow channel system for distributing oxidant, driving gas and fuel to the engine. 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 located on both sides of the main body of the assembly block and are respectively connected to the two engines. The internal flow 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. The assembly block for the rocket engine also includes: An external oxidizer pipe is connected to the internal oxidizer flow channel. Oxidizer outer ring outlets are formed on both sides of the external oxidizer pipe. The external oxidizer pipe is used to form an oxidizer ring supply loop with the other engines on the rocket. 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 pipe is used to form a driving gas annular supply loop with the other two engines on the rocket. The external fuel conduit has two fuel inlets at its two ends and is connected to two sets of internal fuel channels. The external fuel conduit is used to form a fuel annular supply loop with the other two engines on the rocket.

2. The assembly block for a rocket engine according to claim 1, characterized in that, Two sets of oxidant internal flow channels, two sets of driving gas internal flow channels, and two sets of fuel internal flow channels are located on both sides of the main body of the aggregate block; The internal flow channel outlet includes two first oxidant outlets, two first driving gas outlets, and two fuel outlets; 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 main body of the collection block, and the fuel internal flow channel is connected to the fuel inlet and the fuel outlet.

3. The assembly block for a rocket engine according to claim 2, characterized in that, The first oxidant outlet, the fuel outlet, and the first drive gas outlet are all connected to valves of the engine; 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.

4. The assembly block for a rocket engine according to claim 2, characterized in that, It also includes a filter assembly installed at the first oxidant outlet, and the filter assembly is used to filter impurities in the oxidant contained in the oxidant inner channel.

5. The assembly block for a rocket engine according to claim 1, characterized in that, The oxidant external pipeline has oxidant threaded connectors at both ends, the driving gas external pipeline has driving gas threaded connectors at both ends, and the fuel external pipeline has fuel threaded connectors at both ends.

6. The assembly block for a rocket engine according to claim 1, characterized in that, The upper side of the main body of the collection 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. Both the external oxidant pipe and the external driving gas pipe are located on the lower side of the main body of the assembly 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.

7. The assembly block for a rocket engine according to claim 6, characterized in that, The oxidant inner pipe and the driving gas inner pipe are parallel to each other and staggered front to back; the oxidant outer pipe and the driving gas outer pipe are parallel to each other and staggered front to back and up to down. 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.

8. The assembly block for a rocket engine according to any one of claims 1 to 4, characterized in that, The main body of the assembly block is provided with second mounting interfaces for mounting the engine on its left and right sides, and a first mounting interface for mounting the rocket body is provided on the outer side of the main body of the assembly block.

9. A rocket engine assembly, characterized in that, include: Assembly block for rocket motor as described in any one of claims 1 to 8; Two engines are installed on the left and right sides of the main body of the assembly block, respectively.

10. A rocket attitude control engine system, characterized in that, Includes the rocket engine assembly as described in claim 9.

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