Bent pipe structure for ignition of rocket engine
Through the design of the bent pipe structure, the main pipeline and branch pipeline manufactured using 3D printing technology solve the problem that the rocket engine cannot ignite multiple times, realize the engine's multiple reliable ignition and structural stability, and avoid pipeline blockage caused by high-pressure gas residue.
Patent Information
- Application Number
- CN202422798595.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-18
- Publication Date
- 2025-08-05
- Estimated Expiration
- 2034-11-18
AI Technical Summary
The existing rocket engine ignition method cannot achieve multiple ignitions, and the traditional ignition method will affect the stability and strength of the engine combustion components.
It adopts a bent pipe structure, including the main pipe line, branch pipe line, first flange and second flange. It is formed in one piece by 3D printing, and provides multiple solid gunpowder igniter installation interfaces and channels. The main pipe line is connected to the engine combustion assembly, and the branch pipe line and the second flange are matched with a fixed ignition device to avoid opening multiple interfaces and channels outside the engine.
The reliability of multiple ignitions is achieved, the structural stability of the engine combustion assembly is ensured, the ignition success rate is improved, and pipeline blockage caused by high-pressure gas residue is prevented.
Smart Images
Figure CN223190528U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of rocket engines, in particular to a bent pipe structure used for ignition of rocket engines. Background Art
[0002] With the rapid development of the aerospace industry, various technologies involved in the rocket field have also achieved rapid progress.
[0003] Currently, the most common method of ignition for rocket engines is solid powder igniter ignition. This method is suitable for a variety of non-natural propellants and has the advantages of high ignition reliability and easy installation and maintenance.
[0004] Solid powder igniters are typically installed in an open position outside the engine, requiring mounting interfaces and channels to be opened in the rocket engine combustion assembly. A major drawback of traditional ignition methods is that they cannot achieve multiple ignitions. To achieve multiple ignitions, multiple independent mounting interfaces and channels must be opened in the engine combustion assembly. These additional interfaces can seriously affect the stability of the engine combustion assembly and even cause the engine to fail after ignition.
[0005] There is an urgent need to provide a rocket engine ignition structure with a reasonable design that can achieve multiple ignitions according to actual needs while ensuring the stability of the engine combustion component structure and improving the engine ignition success rate. Summary of the Invention
[0006] The purpose of the utility model is to overcome the shortcomings of the existing technology and provide a curved pipe structure for rocket engine ignition, which can realize multiple ignitions according to actual needs, while ensuring the stability of the engine combustion component structure and improving the engine ignition success rate.
[0007] The utility model provides a curved pipe structure for rocket engine ignition, comprising a main pipe, a plurality of branch pipes, a first flange and a plurality of second flanges, wherein:
[0008] One end of the main line is connected to the first flange and is used to be fixedly connected to the mounting interface on the rocket engine combustion assembly through the first flange. The other end of the main line is connected to one end of multiple branch lines, and the other ends of multiple branch lines are respectively connected to the corresponding second flanges. Each branch line and the second flange cooperate with each other to fix the ignition device.
[0009] Furthermore, the length of the main pipe is A, and the thickness of the first flange is B, wherein A≥5B.
[0010] Furthermore, the main pipe is a straight pipe, and the branch pipe is a curved pipe.
[0011] Furthermore, the main pipe has an outer shape of a sphere or an ellipsoid with two ends connected and a cavity inside.
[0012] Furthermore, at least one reverse pipeline is provided on the plurality of branch pipelines, and both ends of the reverse pipeline are respectively connected to the inner cavity of the branch pipeline.
[0013] Furthermore, the length of the reverse pipeline is C, and the length of the main pipeline is A, wherein C≥1 / 2A.
[0014] Furthermore, the diameter of the main pipeline is D, and the diameter of the branch pipeline is E, where D≥E.
[0015] Furthermore, the diameter of the reverse pipeline is F, wherein E>F.
[0016] Furthermore, the main pipeline, the plurality of branch pipelines, the first flange and the plurality of second flanges are integrally formed by 3D printing.
[0017] Furthermore, a fixing component for fixing the branch pipeline is provided on the outside of the branch pipeline.
[0018] Compared with the prior art, the present invention has at least one of the following beneficial effects:
[0019] The present invention provides a curved pipe structure for rocket engine ignition. This curved pipe structure utilizes a branch-main pipeline structure, with multiple branch pipelines providing multiple mounting interfaces and channels for solid propellant igniters. The main pipeline connects to the engine combustion assembly. When multiple ignitions are required, these can be achieved using propellant igniters attached to the branch pipelines, eliminating the need for multiple ignition channels within the engine combustion assembly.
[0020] The bent pipe structure of the present application cooperates with the branch pipeline and the second flange to fix the ignition device, which can ensure that the ignition device is firmly fixed and improve the reliability of the engine ignition process.
[0021] The elbow junction of the present application can realize multiple ignitions according to actual needs, and at the same time, by avoiding the opening of structures and channels in the external structure of the engine, the stability of the engine combustion component structure is ensured, thereby realizing multiple and reliable ignitions of the engine.
[0022] It should be understood that the above general description and the following detailed description are merely exemplary and illustrative and are not intended to limit the scope of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS
[0023] The following drawings are part of the specification of the present utility model, which illustrate exemplary embodiments of the present utility model. The accompanying drawings and the description of the specification are used to explain the principles of the present utility model.
[0024] Figure 1 This is a schematic structural diagram of the elbow structure in an embodiment of the present utility model;
[0025] Figure 2 This is a schematic structural diagram of the elbow structure and the reverse pipeline in an embodiment of the present utility model;
[0026] Figure 3 This is a front view of the main pipe in the embodiment of the present utility model.
[0027] Description of reference numerals:
[0028] 1 main line 2 branch lines
[0029] 3First flange 4Second flange
[0030] 5 Reverse pipe 6 Fixing assembly DETAILED DESCRIPTION
[0031] Various exemplary embodiments of the present invention will now be described in detail. This description should not be considered as limiting the present invention, but should be understood as a more detailed description of certain aspects, features, and embodiments of the present invention.
[0032] It will be apparent to those skilled in the art that various modifications and variations may be made to the specific embodiments described herein without departing from the scope or spirit of the present invention. Other embodiments derived from the present invention will be apparent to those skilled in the art. The present description and examples are intended to be illustrative only.
[0033] like Figure 1 、 Figure 2 and Figure 3 As shown, the utility model provides a curved pipe structure for rocket engine ignition, comprising a main pipe 1, multiple branch pipes 2, a first flange 3 and multiple second flanges 4.
[0034] One end of the main line 1 is connected to the first flange 3 and is used to be fixedly connected to the mounting interface on the rocket engine combustion assembly through the first flange 3. The other end of the main line 1 is connected to one end of multiple branch lines 2, and the other ends of the multiple branch lines 2 are respectively connected to the corresponding second flanges 4. Each branch line 2 and the second flange 4 cooperate with each other to fix the ignition device.
[0035] Specifically, the present invention provides an elbow structure for rocket engine ignition. This elbow structure utilizes a branch-to-main pipeline structure, where multiple branch pipelines 2 provide multiple solid powder igniter mounting interfaces and channels. A main pipeline 1 connects to the engine combustion assembly, enabling multiple engine ignitions without requiring multiple ignition channels within the combustion assembly. The elbow structure secures the ignition device by interlocking the branch pipelines 2 and the second flange 4, ensuring that the ignition device is securely fixed and prevented from slipping out of the internal channels of the branch pipelines 2.
[0036] The elbow junction of the present application can realize multiple ignitions according to actual needs, and at the same time, by avoiding the opening of too many interfaces and channels outside the engine, it can ensure the stability of the engine combustion component structure and improve the reliability of engine ignition.
[0037] In this embodiment, after the engine is ignited for the first time, in order to prevent the high-pressure gas in the engine combustion chamber from blowing the gunpowder residue back into the remaining branch pipes 2 and causing pipe blockage, the volume of the inner cavity of the main pipe 1 can be increased. For example, the length of the main pipe 1 can be increased or the diameter of the main pipe 1 can be increased, thereby increasing the inner cavity of the main pipe 1, thereby preventing the high-pressure gas in the engine combustion chamber from blowing the gunpowder residue back into the remaining branch pipes 2 and causing pipe blockage.
[0038] In the same embodiment, when the length of the main pipeline 1 is A, the thickness of the first flange 3 is B, and A≥5B is satisfied, high-pressure gas can be prevented from blowing gunpowder residue back into the remaining branch pipelines 2 to cause pipeline blockage, thereby ensuring subsequent normal ignition.
[0039] In the same embodiment, to ensure the structural stability of the main pipe 1, for example, the main pipe 1 is a straight pipe. To match the structure of the rocket engine and avoid mechanical interference and damage caused by contact therewith, for example, the branch pipe 2 is a curved pipe.
[0040] In this embodiment, to further prevent the high-pressure gas in the engine combustion chamber from blowing back powder residue into the remaining branch pipes 2 and causing pipe blockage, the main pipe 1 is shaped like a sphere or ellipsoid with two interconnected ends and a cavity inside. The sphere or ellipsoid inside the main pipe 1 increases the internal space of the cavity, thereby reducing the risk of powder residue blowing back into the remaining branch pipes and causing pipe blockage, facilitating subsequent re-ignition.
[0041] In another embodiment, in order to prevent the high-pressure gas in the engine combustion chamber from blowing the gunpowder residue back into the remaining branch pipelines 2 and causing pipeline blockage, for example, at least one reverse pipeline 5 is provided on multiple branch pipelines 2, and the two ends of the reverse pipeline 5 are respectively connected to the inner cavity of the branch pipeline 2.
[0042] It should be noted that when the length of the reverse pipeline 5 is C, the length of the main pipeline 1 is A, and C≥1 / 2A is satisfied, it can further prevent the high-pressure gas in the engine combustion chamber from blowing the gunpowder residue back into the remaining branch pipelines 2 to cause pipeline blockage.
[0043] In one embodiment, in order to facilitate the connection between the main line 1 and the branch line 2, for example, the diameter of the main line 1 is D, the diameter of the branch line 2 is E, and when D≥E is satisfied, it is convenient to connect the main line 1 and the branch line 2 while ensuring that there is enough capacity inside the main line 1, thereby avoiding the rocket gunpowder residue from being blown back into the remaining branch lines 2 and causing line blockage. In addition, it can also ensure that when the ignition device is started, it can quickly pass through the main line 1 to ignite the rocket engine.
[0044] Furthermore, to facilitate the connection of the reverse line 5 to the branch line 2, for example, if the diameter of the reverse line 5 is F and the diameter of the branch line 2 is E, and E>F, this not only facilitates the connection of the reverse line 5 to the branch line 2 and reduces the weight of the branch line 2, but also prevents the high-pressure gas in the engine combustion chamber from blowing back the gunpowder residue into the remaining branch lines 2, causing line blockage.
[0045] In addition, in order to ensure that the main line 1, the branch line 2, the first flange 3 and the second flange 4 are more tightly connected and more firmly fixed to each other, for example, the main line 1, multiple branch lines 2, the first flange 3 and the multiple second flanges 4 are designed as an integrated whole through 3D printing. The main line 1, multiple branch lines 2, the first flange 3 and the multiple second flanges 4 are designed as an integrated whole through 3D printing. This not only ensures that the connections with each other are more firmly established, but also facilitates the rapid production of parts through 3D printing technology, thereby improving assembly work efficiency.
[0046] like Figure 1 and Figure 2 As shown, in order to facilitate the fixing of the branch pipeline 2, for example, a fixing component 6 for fixing the branch pipeline 2 is further provided on the outside of the branch pipeline 2. In this embodiment, the fixing component 6 has an L-shaped structure.
[0047] The above description is only an illustrative embodiment of the present invention. Without departing from the concept and principle of the present invention, any equivalent changes and modifications made by those skilled in the art should fall within the scope of protection of the present invention.
Claims
1. A curved pipe structure for rocket engine ignition, characterized in that , comprising a main pipeline, a plurality of branch pipelines, a first flange and a plurality of second flanges, wherein, One end of the main line is connected to the first flange and is used to be fixedly connected to the mounting interface on the rocket engine combustion assembly through the first flange. The other end of the main line is connected to one end of multiple branch lines, and the other ends of multiple branch lines are respectively connected to the corresponding second flanges. Each branch line and the second flange cooperate with each other to fix the ignition device.
2. The curved pipe structure for rocket engine ignition according to claim 1, characterized in that , the length of the main pipeline is A, and the thickness of the first flange is B, where A≥5B.
3. The curved pipe structure for rocket engine ignition according to claim 1, characterized in that The main pipe is a straight pipe, and the branch pipe is a curved pipe.
4. The curved pipe structure for rocket engine ignition according to claim 1, characterized in that The main pipeline has an outer shape of a sphere or ellipsoid with two ends connected and a cavity inside.
5. The curved pipe structure for rocket engine ignition according to claim 1, characterized in that At least one reverse pipeline is provided on the multiple branch pipelines, and both ends of the reverse pipeline are respectively connected to the inner cavity of the branch pipeline.
6. The curved pipe structure for rocket engine ignition according to claim 5, characterized in that , the length of the reverse pipeline is C, and the length of the main pipeline is A, where C≥1 / 2A.
7. The curved pipe structure for rocket engine ignition according to claim 5, characterized in that , the diameter of the main pipeline is D, and the diameter of the branch pipeline is E, where D≥E.
8. The curved pipe structure for rocket engine ignition according to claim 7, characterized in that , the diameter of the reverse pipeline is F, where E>F.
9. The curved pipe structure for rocket engine ignition according to claim 1, characterized in that The main pipeline, the plurality of branch pipelines, the first flange and the plurality of the second flanges are integrally formed by 3D printing.
10. The curved pipe structure for rocket engine ignition according to claim 1, characterized in that , a fixing component for fixing the branch pipeline is also provided on the outside of the branch pipeline.