A rapidly reconfigurable modular rocket engine structure

Abstract

The present invention discloses a rocket engine structure that can be quickly reconfigured and modularized, and relates to the field of rocket engine technology. The device includes a first combustion chamber, a surface of which is provided with a female joint insulation structure, the female joint insulation structure is arranged on the outer surface of the first combustion chamber, and the joint portion of the female joint insulation structure is provided with a female joint tooth-groove structure; a second combustion chamber, a surface of which is provided with a sub-joint insulation structure, the sub-joint insulation structure is arranged on the outer surface of the second combustion chamber of the rocket, the joint portion of the sub-joint insulation structure is provided with a sub-joint tooth-groove structure, and the sub-joint tooth-groove structure is used to engage with the female joint tooth-groove structure. The docking insulation layer in this application can be engaged through the tooth-groove, and the gap between the insulation layers is closed and the airflow channel is closed to achieve the effect of insulation sealing. This makes it unnecessary to spend a lot of time applying insulation coating and waiting for the coating to solidify after the two insulation structures are docked.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket engines, and in particular to a rocket engine structure that can be rapidly reconfigured and modularized. Background Art

[0002] With the advancement of science and technology, rocket launch technology has gradually matured. Segmented rocket engines have become a common design. The combustion chamber surface of a rocket engine requires thermal insulation to ensure proper operation. However, segmented rocket engines require multiple sections to be connected together before use, so the gaps between the insulation structures need to be sealed to maintain their insulation effectiveness.

[0003] In the prior art, sealing gaps between multiple insulation sections is typically achieved by applying a sealant. However, this application process is time-consuming, and the sealant must wait for curing after application. This results in a significant time-consuming process for connecting multiple sections of rocket engines, making it difficult to meet the requirements for rapid disassembly and assembly. Summary of the Invention

[0004] In view of the defects existing in the prior art, the purpose of the present invention is to provide an insulating docking structure and a rocket engine assembly to solve the problem of long connection, assembly and disassembly time of multi-section rocket engines in the related art.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is to provide a rapidly reconfigurable modular rocket engine structure, comprising:

[0006] The first combustion chamber has a female joint insulation structure on its surface, the female joint insulation structure is arranged on the outer surface of the first combustion chamber, and the joint part of the female joint insulation structure is provided with a female joint tooth groove structure;

[0007] The second combustion chamber has a sub-joint insulation structure on its surface, and the sub-joint insulation structure is arranged on the outer surface of the second combustion chamber of the rocket. The joint part of the sub-joint insulation structure is provided with a sub-joint tooth groove structure, and the sub-joint tooth groove structure is used to engage with the mother joint tooth groove structure.

[0008] In some embodiments, the female connector insulation structure includes:

[0009] A female joint reinforcement layer, which is used to be arranged on the outer surface of the first combustion chamber, and the female joint tooth groove structure is provided at the joint end of the female joint reinforcement layer;

[0010] A female joint cover layer is used to be arranged on the outer surface of the first combustion chamber, and the female joint cover layer is arranged on the connection end of the female joint reinforcement layer.

[0011] In some embodiments, the connection portion between the female connector reinforcement layer and the female connector cover layer is stepped.

[0012] In some embodiments, the female connector reinforcement layer is stronger than the female connector cover layer.

[0013] In some embodiments, the sub-joint insulation structure includes:

[0014] a sub-joint reinforcement layer, which is used to be arranged on the outer surface of the second combustion chamber, and the sub-joint tooth-groove structure is arranged on a joint end of the sub-joint reinforcement layer;

[0015] The sub-joint cover layer is used to be arranged on the outer surface of the sub-joint, and the sub-joint cover layer is arranged on the connection end of the sub-joint reinforcement layer.

[0016] In some embodiments, a second thermal insulation layer is provided on the surface of the second combustion chamber.

[0017] In some embodiments, an extrusion groove is provided in the circumferential direction in the sub-joint reinforcement layer.

[0018] In some embodiments, the present invention further comprises:

[0019] A joint device is used to cover the outer surfaces of the female joint insulation structure and the female joint insulation structure, and the first combustion chamber is connected to the second combustion chamber through the joint device.

[0020] In some embodiments, the connector device comprises:

[0021] A female connector, which is used to be sleeved on the outer surface of the female connector insulation structure;

[0022] The sub-connector is used for being sleeved on the outer surface of the sub-connector thermal insulation structure, and the female connector is used for being clamped with the sub-connector.

[0023] In some embodiments, the connector device further comprises:

[0024] A radial locking device is provided in the female connector. When the female connector is engaged with the sub-connector, the radial locking device can move along the axial direction of the female connector to define a radially locked state and an unlocked state. In the radially locked state, the radial locking device partially abuts against the radially opposite surface of the sub-connector. In the unlocked state, the radial locking device is separated from the sub-connector.

[0025] Compared with the prior art, the advantages of the present invention are:

[0026] (1) The thermal insulation docking structure of the present invention provides a slot at the joint of the two thermal insulation structures, allowing the two to engage through the tooth grooves, closing the gap between the thermal insulation layers and sealing the air flow channel to achieve a thermal insulation seal. This eliminates the need to spend a lot of time applying thermal insulation coating and waiting for the coating to cure after the two thermal insulation structures are docked.

[0027] (2) The thermal insulation docking structure of the male and female connectors of the present invention is provided with a reinforcement layer and a cover layer, and the connection between the two forms a Z-shaped stepped connection. The segmented design of the thermal insulation structure makes disassembly and assembly more convenient and also provides greater flexibility in material selection. The reinforcement layer near the end has higher stress requirements, so the designer can use a higher-strength material to avoid deformation, while the cover layer can be made of a lower-strength material to control costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0029] Figure 1 is a cross-sectional view of a rocket engine structure according to an embodiment of the present invention;

[0030] Figure 2 is a partial cross-sectional view of the first combustion chamber in an embodiment of the present invention;

[0031] Figure 3 For the embodiment of the present invention Figure 2 A partial enlarged view of part A in the middle;

[0032] Figure 4 is a partial cross-sectional view of the second combustion chamber in an embodiment of the present invention;

[0033] Figure 5 For the embodiment of the present invention Figure 4 A partial enlarged view of area B in the middle.

[0034] In the figure: 1. Insulation structure of female joint; 11. Reinforcement layer of female joint; 111. Tooth-groove structure of female joint; 12. Cover layer of female joint; 13. First lining layer; 14. First artificial debonding layer; 15. First insulation layer; 2. Female joint; 3. First combustion chamber; 4. Insulation structure of sub-joint; 41. Reinforcement layer of sub-joint; 411. Tooth-groove structure of sub-joint; 42. Cover layer of sub-joint; 43. Second lining layer; 44. Second artificial debonding layer; 45. Extrusion groove; 46. Second insulation layer; 5. Sub-joint; 6. Second combustion chamber; 7. Joint device; 71. Radial locking device. DETAILED DESCRIPTION

[0035] To make the purpose, technical solutions, and advantages of the embodiments of this application more clear, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the described embodiments are part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0036] The embodiments of the present invention will be described in further detail below with reference to the accompanying drawings. Figure 1 and Figure 2 As shown, the present application provides a rapidly reconfigurable modular rocket engine structure, which includes:

[0037] The first combustion chamber 3 has a female joint insulation structure 1 on its surface. The female joint insulation structure 1 is arranged on the outer surface of the first combustion chamber 3. The female joint insulation structure 1 has a female joint tooth groove structure 111 on its joint portion.

[0038] The second combustion chamber 6 has a sub-joint insulation structure 4 on its surface. The sub-joint insulation structure 4 is arranged on the outer surface of the second combustion chamber 6 of the rocket. The joint part of the sub-joint insulation structure 4 is provided with a sub-joint tooth groove structure 411. The sub-joint tooth groove structure 411 is used to engage with the mother joint tooth groove structure 111.

[0039] It can be understood that the present application adopts a tooth-groove engagement structure at the joint, which is faster and more convenient to disassemble than the traditional sealing coating method, and there is no need to wait for the sealing coating to cure.

[0040] Specifically, the female joint insulation structure 1 includes: a female joint reinforcement layer 11, which is used to be arranged on the outer surface of the first combustion chamber 3, and the female joint tooth groove structure 111 is arranged at the joint end of the female joint reinforcement layer 11; a female joint cover layer 12, which is used to be arranged on the outer surface of the first combustion chamber 3, and the female joint cover layer 12 is arranged at the connection end of the female joint reinforcement layer 11.

[0041] It is worth mentioning that the above-mentioned thermal insulation structure is also designed to be segmented. This is because the stress strength of the thermal insulation structure is different near the end of the female connector and away from the end when the rocket is in operation. The stress strength near the end will be greater. Therefore, the segmented structure not only makes it more convenient for operators to disassemble, but also allows for segmented processing according to the stress conditions of the thermal insulation structure. The female connector reinforcement layer 11 is made of high-strength material. The female connector cover layer 12 is made of more economical materials, allowing designers to better control costs.

[0042] Preferably, the connection portion between the female connector reinforcement layer 11 and the female connector cover layer 12 is stepped. Figure 2 As shown, the connecting ends of the two are configured in a coordinated stepped and inverted stepped shape to improve assembly efficiency. The connector end of the female connector reinforcement layer 11 is the end closer to the connection between the first combustion chamber 3 and the second combustion chamber 6 when connected. The connecting end is the end away from the connection between the two combustion chambers.

[0043] In some embodiments, a first artificial debonding layer 14 is provided between the female connector reinforcement layer 11 and the first combustion chamber 3. Of course, a first heat insulating layer 15 is further provided between the first artificial debonding layer 14 and the first combustion chamber 3.

[0044] It is worth noting that the first artificial debonding layer 14 is a pre-designed stress release structure between the insulation layers at the engine head. Its main function is to reduce the stress and strain levels at the engine grain inner hole, grain bonding interface and other parts, thereby maintaining the integrity of the grain structure.

[0045] In some embodiments, such as Figure 2 and Figure 3 As shown, a first lining layer 13 is further provided between the female joint cover layer 12 and the first combustion chamber 3. The first lining layer 13 is axially away from the joint portion of the first combustion chamber 3 relative to the first artificial debonding layer 14. Similarly, a first thermal insulation layer 15 is provided between the first lining layer 13 and the first combustion chamber 3.

[0046] Similarly, if Figure 4 and Figure 5 As shown, the sub-joint insulation structure 4 includes:

[0047] The sub-joint reinforcement layer 41 is used to be arranged on the outer surface of the second combustion chamber 6, and the sub-joint tooth-groove structure 411 is arranged at the joint end of the sub-joint reinforcement layer 41;

[0048] The sub-joint cover layer 42 is used to be arranged on the outer surface of the sub-joint 5 , and the sub-joint cover layer 42 is assembled on the connection end of the sub-joint reinforcement layer 41 .

[0049] Specifically, a second insulation layer 46 is provided on the surface of the second combustion chamber 6. The second insulation layer 46 is covered with a second lining layer 43 and a second artificial debonding layer 44. The second artificial debonding layer is disposed between the sub-joint reinforcement layer 41 and the second combustion chamber 6. The second lining layer 43 is also disposed between the sub-joint insulation structure 4 and the second combustion chamber 6, but is located farther from the joint portion of the second combustion chamber 6 than the second artificial debonding layer 44. The joint portion of the second combustion chamber 6 refers to the portion where the first combustion chamber 3 and the second combustion chamber 6 are connected after the connection is complete.

[0050] Preferably, if Figure 4 As shown, the sub-joint reinforcement layer 41 is provided with an extrusion groove 45 along the circumferential direction. The extrusion groove 45 is used to prevent the sub-joint reinforcement layer 41 from being deformed by excessive axial force. The extrusion groove 45 can provide a certain axial deformation space for it. The above-mentioned axial direction refers to Figure 4 Left and right direction in .

[0051] In some embodiments, the rocket engine structure further comprises:

[0052] The joint device 7 is used to cover the outer surfaces of the female joint insulation structure 1 and the female joint insulation structure 4 , and the first combustion chamber 3 is connected to the second combustion chamber 6 through the joint device 7 .

[0053] Specifically, if Figure 1 As shown, the connector device 7 includes: a female connector 2 and a female connector 5;

[0054] A female connector 2, which is used to be sleeved on the outer surface of the female connector insulation structure 1;

[0055] The sub-connector 5 is used to be sleeved on the outer surface of the sub-connector insulation structure 4, and the female connector 2 is used to be clamped with the sub-connector 5.

[0056] It's worth noting that the sub-connector 5 and female connector 2 are each secured to the outer casing of their respective combustion chambers, which also covers the aforementioned female connector insulation structure 1 and sub-connector insulation structure 4. Therefore, the female connector 2 and sub-connector 5 also cover the female connector insulation structure 1 and sub-connector insulation structure 4, respectively. Once secured, the two components are then engaged by teeth, allowing for rapid assembly of the first and second combustion chambers 3 and 6.

[0057] Preferably, in order to prevent the first combustion chamber 3 and the second combustion chamber 6 from being relatively displaced in the radial direction after being connected, the joint device 7 further includes:

[0058] A radial locking device 71 is provided in the female connector 2. When the female connector 2 is engaged with the sub-connector 5, the radial locking device 71 can move along the axial direction of the female connector 2 to define a radial locking state and an unlocking state. In the radial locking state, the radial locking device 71 partially abuts against the radially opposite surface of the sub-connector 5. In the unlocking state, the radial locking device 71 is separated from the sub-connector 5.

[0059] In summary, the thermal insulation docking structure of the present invention is provided with a card slot at the joint of the two thermal insulation structures, so that the two can be engaged through the tooth groove, the gap between the thermal insulation layers is closed, and the air flow channel is sealed to achieve the effect of thermal insulation sealing. This makes it unnecessary to spend a lot of time applying thermal insulation coating and waiting for the coating to solidify after the two thermal insulation structures are docked. The thermal insulation docking structure of the sub-joint and the female joint of the present invention is provided with a reinforcement layer and a cover layer, and the connection between the two is a Z-shaped step connection. The segmented design of the thermal insulation structure makes disassembly and assembly more convenient, and it is also more flexible in material selection. The reinforcement layer located near the end has higher force requirements, so the designer can choose a higher strength material to avoid its deformation, and the cover layer can use a lower strength material to control the cost.

[0060] In the description of this application, it should be noted that the terms "upper" and "lower" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances.

[0061] It should be noted that, in this application, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprising a ..." does not exclude the presence of other identical elements in the process, method, article or device comprising the element.

[0062] The foregoing is merely a list of specific embodiments of the present application, intended to enable those skilled in the art to understand or implement the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application is not limited to the embodiments shown herein, but is intended to conform to the broadest scope consistent with the principles and novel features of the present application.

Claims

1. A rapidly reconfigurable modular rocket engine structure, characterized in that: include: A first combustion chamber (3) has a female joint insulation structure (1) provided on its surface, the female joint insulation structure (1) being arranged on the outer surface of the first combustion chamber (3), and a female joint tooth groove structure (111) being provided on a joint portion of the female joint insulation structure (1); The second combustion chamber (6) has a sub-joint thermal insulation structure (4) provided on its surface, the sub-joint thermal insulation structure (4) being arranged on the outer surface of the second combustion chamber (6) of the rocket, the joint portion of the sub-joint thermal insulation structure (4) being provided with a sub-joint tooth groove structure (411), the sub-joint tooth groove structure (411) being used to engage with the female joint tooth groove structure (111); The female connector thermal insulation structure (1) comprises: a female connector reinforcement layer (11) and a female connector cover layer (12); wherein, The female joint reinforcement layer (11) is used to be arranged on the outer surface of the first combustion chamber (3), and the female joint tooth groove structure (111) is provided at the joint end of the female joint reinforcement layer (11); The female joint cover layer (12) is used to be arranged on the outer surface of the first combustion chamber (3), and the female joint cover layer (12) is assembled on the connection end of the female joint reinforcement layer (11).

2. The rapidly reconfigurable modular rocket engine structure according to claim 1, wherein: The connection portion between the female connector reinforcement layer (11) and the female connector cover layer (12) is stepped.

3. The rapidly reconfigurable modular rocket engine structure according to claim 2, wherein: The material strength of the female connector reinforcement layer (11) is greater than that of the female connector cover layer (12).

4. The rapidly reconfigurable modular rocket engine structure according to claim 1, wherein: The sub-joint insulation structure (4) comprises: A sub-joint reinforcement layer (41) is used to be arranged on the outer surface of the second combustion chamber (6), and the sub-joint tooth-groove structure (411) is arranged at a joint end of the sub-joint reinforcement layer (41); A sub-joint cover layer (42) is used to be arranged on the outer surface of the sub-joint (5), and the sub-joint cover layer (42) is arranged on the connection end of the sub-joint reinforcement layer (41).

5. The rapidly reconfigurable modular rocket engine structure according to claim 4, wherein: A second heat insulating layer (46) is provided on the surface of the second combustion chamber (6).

6. The rapidly reconfigurable modular rocket engine structure according to claim 4, wherein: An extrusion groove (45) is provided in the sub-joint reinforcement layer (41) along the circumferential direction.

7. The rapidly reconfigurable modular rocket engine structure according to claim 1, wherein: Also includes: A joint device (7) is used to cover the outer surfaces of the female joint insulation structure (1) and the female joint insulation structure (4), and the first combustion chamber (3) is connected to the second combustion chamber (6) through the joint device (7).

8. The rapidly reconfigurable modular rocket engine structure according to claim 7, wherein: The joint device (7) comprises: A female connector (2) for being sleeved on the outer surface of the female connector thermal insulation structure (1); The sub-joint (5) is used for being sleeved on the outer surface of the sub-joint thermal insulation structure (4), and the female joint (2) is used for being clamped with the sub-joint (5).

9. The rapidly reconfigurable modular rocket engine structure according to claim 8, wherein: The joint device (7) further comprises: A radial locking device (71) is provided in the female connector (2). When the female connector (2) is engaged with the sub-connector (5), the radial locking device (71) can be moved axially along the female connector (2) to define a radial locking state and an unlocking state. In the radial locking state, the radial locking device (71) partially abuts against a radially opposite surface of the sub-connector (5). In the unlocking state, the radial locking device (71) is separated from the sub-connector (5).

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