Integrated frame and engine connecting assembly of a liquid rocket engine

Abstract

This utility model relates to an integrated frame and engine connection assembly for a liquid rocket engine. The integrated frame includes a conical support cylinder and a first flange, a second flange, a first servo link mounting seat, and a second servo link mounting seat integrally formed and connected to the conical support cylinder. The diameter of the first flange is smaller than the diameter of the second flange. The first flange is integrally connected to the small-mouth end face of the conical support cylinder, and the second flange is integrally connected to the large-mouth end face of the conical support cylinder. Multiple first servo link mounting seats are provided on the outer wall of the small-mouth end of the conical support cylinder, and multiple second servo link mounting seats are provided on the side of the second flange near the first flange. The multiple first servo link mounting seats and multiple second servo link mounting seats are arranged one-to-one in the axial direction of the conical support cylinder. A servo link is connected to each set of corresponding first servo link mounting seats and second servo link mounting seats.

Description

Technical Field

[0001] This utility model relates to the technical field of liquid rocket engines, specifically to an integrated frame and engine connection assembly for a liquid rocket engine. Background Technology

[0002] Liquid rocket engines are connected to ground test devices or the rocket body via a frame. The engine frame plays a crucial role in connecting the structure and transmitting thrust. The structure of the engine frame is limited by factors such as engine thrust conditions, frame manufacturing processes, and usage and maintenance requirements.

[0003] Traditional liquid rocket engine frames are typically truss or truss-beam structures. The members are connected by welding, either to each other, to beams, or to joints. Materials generally chosen are low- to medium-carbon alloy steel or high-strength stainless steel, balancing strength and weldability. Truss or truss-beam frames rely primarily on end members or beams for rigidity and fixed support, with struts resisting axial compression and bending moments.

[0004] For liquid rocket engine frames, traditional truss-type and girder-type combined welded frames have the following problems:

[0005] (1) The structural form is not adaptable to multiple working conditions. The load-bearing capacity of the truss structure is mainly affected by the layout of the members, the cross-section of the members, and the joints. Under the condition of sway in all directions, the lateral component of the force will generate a huge additional bending moment at the root of the main load-bearing member, which will cause stress concentration at the root of the member or joint. For the combined welded frame, this problem can generally only be improved by optimizing the cross-sectional shape, increasing the cross-sectional size, and optimizing the transition radius of the joint, but cannot be optimized from the most fundamental material distribution;

[0006] (2) Stress concentration or material weakening during welding is a prominent issue. Stress concentration occurs at welding points such as between members and beams, and between members and joints, while the material properties of the weld and surrounding heat-affected zone are weakened. The deterioration of material properties at the weld joints, coupled with stress concentration, affects the overall performance of the frame. In the design process, compensation is generally achieved by introducing a weld strength coefficient (<1), which increases the overall structural mass of the frame.

[0007] (3) Poor process feasibility. The assembly welding process requires multiple positioning; welding quality and post-weld accuracy are difficult to guarantee; especially for the frame of a high-thrust liquid rocket engine, in order to meet the requirements of strength, rigidity and stability, the number of struts or cross-sectional dimensions are greatly increased, resulting in poor overall welding processability; the large number and density of struts affect the welding operation space, especially in situations where the frame size requirements are strict.

[0008] (4) Limited applicable materials. The welding process dictates that traditional trusses generally use medium and low carbon alloy steel and high-strength stainless steel to reduce welding process requirements, including pre- and post-weld treatment, and control of the welding environment and atmosphere. For ordinary welding processes, materials with high requirements for the welding environment, such as titanium alloys, are not suitable. Utility Model Content

[0009] In order to solve one or more technical problems existing in the prior art, this utility model provides an integrated frame for a liquid rocket engine and an engine connection assembly.

[0010] The technical solution of this utility model to solve the above-mentioned technical problems is as follows: This utility model provides an integrated frame for a liquid rocket engine, including a conical support cylinder and a first flange, a second flange, a first servo link mounting seat, and a second servo link mounting seat integrally formed and connected to the conical support cylinder. The diameter of the first flange is smaller than the diameter of the second flange and is arranged coaxially and parallel to the second flange. The first flange is integrally connected to the small-mouth end face of the conical support cylinder, and the second flange is integrally connected to the large-mouth end face of the conical support cylinder. A plurality of first servo link mounting seats are provided on the outer side wall of the small-mouth end of the conical support cylinder, and a plurality of second servo link mounting seats are provided on the side face of the second flange near the first flange. The plurality of first servo link mounting seats and the plurality of second servo link mounting seats are arranged one-to-one in the axial direction of the conical support cylinder. A servo link is connected to each set of corresponding first servo link mounting seats and second servo link mounting seats.

[0011] The beneficial effects of this invention are as follows: The integrated frame of the liquid rocket engine of this invention adopts a one-piece molded conical load-bearing cylinder, resulting in better stress distribution and solving the problems of large frame structure weight and low efficiency. The conical load-bearing cylinder of this invention is integrally molded with the first flange, second flange, first servo linkage mounting base, and second servo linkage mounting base, eliminating the need for welding and resulting in excellent material mechanical properties. The integrated frame of this invention can be formed by additive manufacturing or 3D printing, without being limited by the local structural space dimensions of the frame, and can be applied to various materials such as high-strength stainless steel and titanium alloys.

[0012] Based on the above technical solution, the present invention can be further improved as follows.

[0013] Furthermore, the cone angle of the conical load-bearing cylinder is 60~70°.

[0014] The beneficial effects of adopting the above-mentioned further scheme are: by reasonably setting the cone angle of the conical load-bearing cylinder, the structure has high strength and stable and reliable force transmission.

[0015] Furthermore, the angle between the servo linkage and the central axis of the conical load-bearing cylinder is less than half the cone angle of the conical load-bearing cylinder.

[0016] The beneficial effect of adopting the above-mentioned further solution is that by setting the deviation angle of the servo linkage, a stable connection with the rocket engine can be achieved.

[0017] Furthermore, there are two of each of the first servo link mounting bases and the second servo link mounting bases, with the two first servo link mounting bases arranged vertically.

[0018] The beneficial effect of adopting the above-mentioned further solution is that by setting two first servo linkage mounting seats and two second servo linkage mounting seats, it is convenient for the engine to swing under force.

[0019] Furthermore, the first servo link mounting base extends radially outward along the small end of the conical load-bearing cylinder, and the second servo link mounting base is located outside the conical load-bearing cylinder and extends obliquely toward its small end. The extension length of the second servo link mounting base is less than the extension length of the first servo link mounting base.

[0020] Furthermore, the middle part of the servo link is mounted on the free end of the first servo link mounting base via a connector, one end of the servo link is mounted on the second servo link mounting base via a connector, and the other end of the servo link is provided with an engine connection hole.

[0021] Furthermore, the free end of the first servo link mounting base is fixed with two spaced-apart first lugs, and the second servo link mounting base is fixed with two spaced-apart second lugs. The middle part of the servo link is limited between the two first lugs and is connected and fixed to the two first lugs through a connector. One end of the servo link is limited between the two second lugs and is connected and fixed to the two second lugs through a connector.

[0022] The beneficial effect of adopting the above-mentioned further solution is that by installing the servo linkage on the first and second lugs through the connector, the connection limit is made more stable and reliable.

[0023] Furthermore, the conical load-bearing cylinder is provided with weight-reducing perforations.

[0024] The beneficial effect of adopting the above-mentioned further solutions is that, while ensuring the load-bearing effect of the conical load-bearing cylinder, the requirements for lightweighting and weight reduction are achieved.

[0025] Furthermore, the thickness of the conical load-bearing cylinder is 30~50mm.

[0026] The beneficial effect of adopting the above-mentioned further solution is that by reasonably setting the thickness of the conical load-bearing cylinder, the stable load-bearing capacity of the conical load-bearing cylinder can be guaranteed.

[0027] This utility model also provides an engine connection assembly, including an integrated frame for a liquid rocket engine as described above, and also includes an adapter frame and an engine. The engine is hinged to multiple servo linkages one-to-one through multiple servo power mechanisms. The two ends of the servo power mechanism are respectively hinged to the servo linkages and the connecting rods on the outer side wall of the engine through a first hinge shaft and a second hinge shaft. The first hinge shaft and the second hinge shaft are arranged in parallel, and the two first hinge shafts of two adjacent servo power mechanisms are arranged perpendicularly.

[0028] The adapter is fixed on the second flange, and the engine is movably connected to the first flange via a constant level seat. The constant level seat has a first rotating shaft and a second rotating shaft arranged vertically. The first rotating shaft is arranged parallel to the first hinge shaft, and the second rotating shaft is arranged parallel to the second hinge shaft.

[0029] The beneficial effects of this utility model are: the engine connection component of this utility model has good force transmission effect and high structural strength. Attached Figure Description

[0030] Figure 1 This is a three-dimensional structural diagram of the integrated frame for the liquid rocket engine of this utility model. Figure 1 ;

[0031] Figure 2 This is a three-dimensional structural diagram of the integrated frame for the liquid rocket engine of this utility model. Figure 2 ;

[0032] Figure 3 This is a three-dimensional structural diagram of the engine connection assembly of this utility model;

[0033] Figure 4 for Figure 3 Enlarged schematic diagram of the middle part of the structure.

[0034] The attached diagram lists the components represented by each number as follows:

[0035] 1. Conical bearing cylinder; 2. First flange; 3. Second flange; 4. First servo linkage mounting base; 5. Second servo linkage mounting base; 6. Servo linkage; 7. Servo power mechanism; 8. Weight reduction hollow; 9. Connecting piece; 10. Normal level seat; 11. Engine connection hole; 12. Adapter frame; 13. Engine; 14. First hinge shaft; 15. Second hinge shaft; 16. First rotating shaft; 17. Second rotating shaft; 18. First mounting hole; 19. Second mounting hole. Detailed Implementation

[0036] The principles and features of this utility model are described below. The examples given are only for explaining this utility model and are not intended to limit the scope of this utility model.

[0037] Example 1

[0038] like Figures 1-4 As shown, this embodiment of an integrated frame for a liquid rocket engine includes a conical support cylinder 1 and a first flange 2, a second flange 3, a first servo link mounting seat 4, and a second servo link mounting seat 5 integrally formed and connected to the conical support cylinder 1. The diameter of the first flange 2 is smaller than the diameter of the second flange 3 and is arranged coaxially and parallel to the second flange 3. The first flange 2 is integrally connected to the small-mouth end face of the conical support cylinder 1, and the second flange 3 is integrally connected to the large-mouth end face of the conical support cylinder 1. Multiple first servo link mounting seats 4 are provided on the outer wall of the small-mouth end of the conical support cylinder 1, and multiple second servo link mounting seats 5 are provided on the side of the second flange 3 near the first flange 2. The multiple first servo link mounting seats 4 and multiple second servo link mounting seats 5 are arranged one-to-one in the axial direction of the conical support cylinder 1. Each set of corresponding first servo link mounting seats 4 and second servo link mounting seats 5 is connected to a servo link 6.

[0039] In a preferred embodiment, the cone angle of the conical load-bearing cylinder 1 is 60~70°, preferably 64°. By reasonably setting the cone angle of the conical load-bearing cylinder, the structure has high strength and stable and reliable force transmission.

[0040] In a preferred embodiment, the angle between the servo link 6 and the central axis of the conical support cylinder 1 is less than half the cone angle of the conical support cylinder 1. By setting the offset angle of the servo link, a stable connection with the rocket engine can be achieved.

[0041] Optionally, the conical load-bearing cylinder 1 is provided with a weight-reducing perforation 8. The weight-reducing perforation achieves the requirement of lightweighting and weight reduction while ensuring the load-bearing effect of the conical load-bearing cylinder.

[0042] Optionally, the thickness of the conical load-bearing cylinder 1 is 30~50mm, preferably 40mm. By reasonably setting the thickness of the conical load-bearing cylinder, the stable load-bearing capacity of the conical load-bearing cylinder can be guaranteed.

[0043] Specifically, such as Figure 3 As shown, in this embodiment, a first mounting hole 18 can be opened on the first flange 2 for mounting the constant level seat 10 on the engine 13, and a second mounting hole 19 can be opened on the second flange 3 for mounting the adapter 12.

[0044] The liquid rocket engine frame in this implementation case is integrally formed by 3D printing, and the overall structure has the characteristics of high structural rigidity and uniform force transmission.

[0045] The integrated frame of the liquid rocket engine in this embodiment uses a one-piece molded conical load-bearing cylinder, resulting in better stress distribution and solving the problems of large frame structure weight and low efficiency. The conical load-bearing cylinder of this invention is integrally molded with the first flange, second flange, first servo linkage mounting base, and second servo linkage mounting base, eliminating the need for welding and resulting in excellent material mechanical properties. This integrated frame can be manufactured using additive manufacturing, without being limited by the spatial dimensions of the frame's local structure, and is applicable to various materials such as high-strength stainless steel and titanium alloys.

[0046] Example 2

[0047] Based on Embodiment 1, this embodiment provides a preferred arrangement of the servo linkage mounting base. For example... Figures 1-4 As shown, two first servo linkage mounting seats 4 and two second servo linkage mounting seats 5 are respectively provided, with the two first servo linkage mounting seats 4 arranged vertically. By providing two first servo linkage mounting seats and two second servo linkage mounting seats, the engine can be easily oscillated under force.

[0048] Example 3

[0049] Based on Embodiment 1 or Embodiment 2, this embodiment provides a preferred arrangement of the servo linkage mounting base. For example... Figures 1-4 As shown, the first servo linkage mounting base 4 extends radially outward along the small end of the conical load-bearing cylinder 1, and the second servo linkage mounting base 5 is located outside the conical load-bearing cylinder 1 and extends obliquely toward its small end. The extension length of the second servo linkage mounting base 5 is less than the extension length of the first servo linkage mounting base 4.

[0050] Example 4

[0051] Based on any of the above embodiments, this embodiment provides a preferred installation scheme for the servo linkage 6. For example... Figures 1-4 As shown, the middle part of the servo link 6 is mounted on the free end of the first servo link mounting base 4 via the connector 9, one end of the servo link 6 is mounted on the second servo link mounting base 5 via the connector 9, and the other end of the servo link 6 is provided with an engine connection hole 11.

[0052] Further preferred, such as Figures 1-4As shown, the free end of the first servo link mounting base 4 is fixed with two spaced-apart first lugs, and the second servo link mounting base 5 is fixed with two spaced-apart second lugs. The middle part of the servo link 6 is limited between the two first lugs and is connected and fixed to the two first lugs through a connector 9. One end of the servo link 6 is limited between the two second lugs and is connected and fixed to the two second lugs through a connector 9. By mounting the servo link on the first and second lugs through the connector 9, the connection and positioning are made more stable and reliable.

[0053] Optionally, the connector 9 can use bolts or connecting shafts to achieve locking and positioning between the servo link 6 and the corresponding servo link mounting base.

[0054] Example 6

[0055] This embodiment provides an engine connection assembly, including an integrated frame for a liquid rocket engine as described in any of the above embodiments, such as... Figure 3 and Figure 4 As shown, it also includes an adapter frame 12 and an engine 13. The engine 13 is hinged to multiple servo linkages 6 one-to-one via multiple servo power mechanisms 7. The two ends of the servo power mechanism 7 are respectively hinged to the servo linkages 6 and the connecting rods on the outer side wall of the engine 13 via a first hinge shaft 14 and a second hinge shaft 15. The first hinge shaft 14 and the second hinge shaft 15 are arranged in parallel, and the two first hinge shafts 14 of two adjacent servo power mechanisms 7 are arranged perpendicularly. The adapter frame 12 is fixed on the second flange 3. The engine 13 is movably connected to the first flange 2 via a constant level seat 10. The constant level seat 10 has a vertically arranged first rotating shaft 16 and a second rotating shaft 17. The first rotating shaft 16 is arranged in parallel with the first hinge shaft 14, and the second rotating shaft 17 is arranged in parallel with the second hinge shaft 15.

[0056] In this embodiment, the engine 13, the constant-pressure seat 10, and other structures can be implemented using common liquid rocket structures. The engine 13 has conventional structures such as a nozzle, combustion chamber, and turbopump, and can be assembled using the constant-pressure seat 10 and servo linkage 6. The lower end of the constant-pressure seat 10 is connected and fixed to the engine 13, and the upper end of the constant-pressure seat 10 is connected and fixed to the first flange 2. The constant-pressure seat 10 has two degrees of freedom of swing, which is achieved using the first rotating shaft 16 and the second rotating shaft 17, as shown below. Figure 4 As shown. The servo power mechanism 7 can be any power mechanism capable of telescopic movement, such as a cylinder or hydraulic cylinder.

[0057] In this embodiment, as Figure 4As shown, after the engine 13 is assembled via the constant level seat 10 and the servo linkage 6, when the servo power mechanism 7 provides power, it can drive the engine 13 to swing relative to the adapter 12 around the first rotating shaft 16 or the second rotating shaft 17. When swinging, the first hinge shaft 14 and the second hinge shaft 15 at both ends of the servo power mechanism 7 also rotate.

[0058] The engine connection assembly of this embodiment has good force transmission effect and high structural strength.

[0059] In the description of this utility model, it should be understood that the terms "center", "length", "upper", "lower", "inner", "outer", "axial", "radial", "circumferential", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. They are only for the convenience of describing this utility model 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 this utility model.

[0060] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this utility model, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0061] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0062] In this utility model, 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.

[0063] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is 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.

[0064] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. An integrated frame for a liquid rocket engine, characterized in that, The device includes a tapered load-bearing cylinder and a first flange, a second flange, a first servo linkage mounting base, and a second servo linkage mounting base integrally formed and connected to the tapered load-bearing cylinder. The diameter of the first flange is smaller than that of the second flange and they are arranged coaxially and parallel to each other. The first flange is integrally connected to the small-mouth end face of the tapered load-bearing cylinder, and the second flange is integrally connected to the large-mouth end face of the tapered load-bearing cylinder. Multiple first servo linkage mounting bases are provided on the outer wall of the small-mouth end of the tapered load-bearing cylinder, and multiple second servo linkage mounting bases are provided on the side of the second flange near the first flange. The multiple first servo linkage mounting bases and multiple second servo linkage mounting bases are arranged one-to-one in the axial direction of the tapered load-bearing cylinder. A servo linkage is connected to each set of corresponding first servo linkage mounting bases and second servo linkage mounting bases.

2. The integrated frame for a liquid rocket engine according to claim 1, characterized in that, The cone angle of the conical load-bearing cylinder is 60~70°.

3. The integrated frame for a liquid rocket engine according to claim 1, characterized in that, The angle between the servo linkage and the central axis of the conical load-bearing cylinder is less than half the cone angle of the conical load-bearing cylinder.

4. The integrated frame for a liquid rocket engine according to claim 1, characterized in that, There are two first servo link mounting bases and two second servo link mounting bases, with the two first servo link mounting bases arranged vertically.

5. The integrated frame for a liquid rocket engine according to claim 1, characterized in that, The first servo link mounting base extends radially outward along the small end of the conical load-bearing cylinder, and the second servo link mounting base is located outside the conical load-bearing cylinder and extends obliquely toward its small end. The extension length of the second servo link mounting base is less than the extension length of the first servo link mounting base.

6. The integrated frame for a liquid rocket engine according to claim 1, characterized in that, The middle part of the servo link is mounted on the free end of the first servo link mounting base via a connector, one end of the servo link is mounted on the second servo link mounting base via a connector, and the other end of the servo link is provided with an engine connection hole.

7. The integrated frame for a liquid rocket engine according to claim 1, characterized in that, The free end of the first servo link mounting base is fixed with two spaced first lugs, and the second servo link mounting base is fixed with two spaced second lugs. The middle part of the servo link is limited between the two first lugs and is connected and fixed to the two first lugs through a connector. One end of the servo link is limited between the two second lugs and is connected and fixed to the two second lugs through a connector.

8. The integrated frame for a liquid rocket engine according to claim 1, characterized in that, The conical load-bearing cylinder has a weight-reducing perforation.

9. The integrated frame for a liquid rocket engine according to claim 1, characterized in that, The thickness of the conical load-bearing cylinder is 30~50mm.

10. An engine connection assembly, characterized in that, The system includes an integrated frame for a liquid rocket engine as described in any one of claims 1 to 9, and further includes a transfer frame and an engine. The engine is hinged to multiple servo linkages in a one-to-one correspondence through multiple servo power mechanisms. The two ends of the servo power mechanism are respectively hinged to the servo linkages and the connecting rods on the outer side wall of the engine through a first hinge shaft and a second hinge shaft. The first hinge shaft and the second hinge shaft are arranged in parallel, and the two first hinge shafts of two adjacent servo power mechanisms are arranged perpendicularly. The adapter is fixed on the second flange, and the engine is movably connected to the first flange via a constant level seat. The constant level seat has a first rotating shaft and a second rotating shaft arranged vertically. The first rotating shaft is arranged parallel to the first hinge shaft, and the second rotating shaft is arranged parallel to the second hinge shaft.

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