A multi-engine parallel engine frame structure of a launch vehicle

Abstract

This invention provides a multi-engine parallel engine rack structure for a launch vehicle, comprising: a connecting ring frame connecting the upper and lower sections of the launch vehicle; a first force transmission frame connected to the connecting ring frame, the center of gravity of the first force transmission frame being located on the axis of the connecting ring frame; a first engine mounting base coaxially arranged with the connecting ring frame and connected to the first force transmission frame; multiple second force transmission frames connected to the connecting ring frame and the first force transmission frame, the multiple second force transmission frames being evenly distributed circumferentially with the axis of the connecting ring frame as a reference; and multiple second engine mounting bases, each of the multiple second engine mounting bases being connected to the multiple second force transmission frames. The solution of this invention transmits the thrust of multiple engines to the connecting ring frame through the first force transmission frame and multiple second force transmission frames, without stress on the propellant tank, eliminating the need for propellant tank reinforcement design, ensuring the thrust effect of the multiple engines of the launch vehicle, and contributing to improving the launch vehicle's carrying capacity.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of carrier rockets, in particular to a multi-engine parallel engine rack structure of a carrier rocket. BACKGROUND

[0002] The multi-engine parallel engine rack structure of the carrier rocket is mainly used for the installation of multiple engines of a sub-stage of a liquid carrier rocket to realize large-thrust take-off and improve the carrying capacity; however, the force transmission of the current multi-engine parallel engine rack structure of the carrier rocket is mainly concentrated on the tank bottom, the tank bottom is subjected to a large force, the tank needs to be designed to be strengthened, which increases the weight of the tank, the increase in the weight of the tank affects the thrust effect of the engine of the carrier rocket and the carrying capacity of the carrier rocket. SUMMARY

[0003] The present application provides a multi-engine parallel engine rack structure of a carrier rocket, which transmits the thrust of multiple engines to a connecting ring frame through a first force transmission frame and multiple second force transmission frames, the tank is not subjected to force, the tank does not need to be designed to be strengthened, the thrust effect of the multiple engines of the carrier rocket is ensured, and the carrying capacity of the carrier rocket is improved.

[0004] To solve the above technical problems, the technical scheme of the present application is as follows:

[0005] A multi-engine parallel engine rack structure of a carrier rocket, comprising:

[0006] a connecting ring frame connected between an upper cabin section and a lower cabin section of the carrier rocket;

[0007] a first force transmission frame connected with the connecting ring frame, the center of gravity of the first force transmission frame being located on the axis of the connecting ring frame;

[0008] a first engine mounting seat coaxially arranged with the connecting ring frame, the first engine mounting seat being connected with the first force transmission frame to transmit the thrust of a first engine to the connecting ring frame through the first force transmission frame;

[0009] multiple second force transmission frames connected with the connecting ring frame and the first force transmission frame, the multiple second force transmission frames being uniformly distributed in a circle with the axis of the connecting ring frame as the center;

[0010] multiple second engine mounting seats, the multiple second engine mounting seats being respectively connected with the multiple second force transmission frames to transmit the thrust of multiple second engines to the connecting ring frame through the multiple second force transmission frames and the first force transmission frame;

[0011] The multiple second engine mounting seats and the first engine mounting seat are coplanar.

[0012] Optionally, the connecting ring frame includes:

[0013] Connecting ring cylinder;

[0014] An upper connecting ring plate is connected to the upper outer edge of the connecting ring cylinder, and upper connecting holes are uniformly arranged on the surface of the upper connecting ring plate;

[0015] A lower connecting ring plate is connected to the lower outer edge of the connecting ring cylinder, and the bottom surface of the lower connecting ring plate is uniformly provided with lower connecting holes;

[0016] The upper connecting ring plate, the connecting ring cylinder, and the lower connecting ring plate form a horizontal U-shaped structure, and the open end of the horizontal U-shaped structure is far away from the axis of the connecting ring cylinder;

[0017] A reinforcing rib plate is connected to the upper connecting ring plate, the connecting ring cylinder, and the lower connecting ring plate, and the reinforcing rib plate is located within a horizontal U-shaped structure.

[0018] Optionally, the first force transmission frame includes:

[0019] A load-bearing cylinder is located below the connecting ring cylinder, and the load-bearing cylinder is coaxially arranged with the connecting ring cylinder. The first engine mounting base is connected to the bottom surface of the load-bearing cylinder.

[0020] Multiple force transmission beams are arranged at an angle, with the first end of each beam connected to the inner wall of the connecting ring cylinder and the second end connected to the outer wall of the load-bearing cylinder.

[0021] Optionally, the first force transmission frame further includes:

[0022] Multiple reinforcing plates are formed on the inner wall of the connecting ring cylinder. The multiple reinforcing plates are flush with the upper connecting ring plate. The multiple reinforcing plates correspond one-to-one with and are connected to multiple force transmission beams. The surfaces of the multiple reinforcing plates are uniformly provided with through holes.

[0023] Optionally, a horizontally extending rigid tube connects two adjacent force transmission beams.

[0024] Optionally, multiple load-transfer beams may include:

[0025] Sternum;

[0026] The upper wing plate connected to the web plate;

[0027] The lower flange is connected to the web plate, and the lower flange forms an angle with the upper flange, which is larger at the bottom and smaller at the top. The upper flange, the web plate and the lower flange form a variable cross-section I-shaped structure.

[0028] Connecting stiffeners that connect to the upper flange, the web, and the lower flange.

[0029] Optionally, multiple second force transmission frames may include:

[0030] A load-bearing component, which is connected to the second engine mounting base and corresponds to the force transmission beam;

[0031] A force transmission frame tube is connected between the load-bearing member and the force transmission beam, and the axis of the force transmission frame tube is coplanar with the axis of the force transmission beam.

[0032] Two ring-frame force transmission tubes are connected between the load-bearing member and the inner wall of the connecting ring cylinder. The two ring-frame force transmission tubes are symmetrically distributed with reference to the coplanarity formed by the axis of the force transmission frame tube and the axis of the force transmission beam.

[0033] Optionally, the multi-engine parallel engine frame structure of the launch vehicle further includes:

[0034] Multiple rigid frames are connected between two adjacent second force transmission frames, and each rigid frame is connected to two adjacent force transmission beams.

[0035] Multiple rigid frames include:

[0036] A load-bearing ball located between two adjacent second force transmission frames;

[0037] Two first rigid tension tubes, the first ends of which are connected to the load-bearing ball, and the second ends of which are connected to two adjacent load-bearing components respectively;

[0038] Two second rigid tension tubes, the first end of which is connected to the load-bearing ball, and the second end of which is connected to two adjacent force-transmitting beams respectively.

[0039] Optionally, the multi-engine parallel engine frame structure of the launch vehicle further includes:

[0040] Multiple second servo actuator mounting brackets are connected to multiple second force transmission frames, multiple force transmission beams, and multiple rigid frames, respectively.

[0041] Multiple second servo actuator mounting brackets include:

[0042] The second servo actuator mounting component is located on one side of the second engine mounting bracket;

[0043] An engine mount pull tube is connected between the second servo actuator mounting component and the adjacent ring frame force transmission tube;

[0044] A force-transmitting ball pull tube is connected between the second servo actuator mounting and the adjacent force-bearing ball;

[0045] A ring frame tube is connected between the second servo actuator mounting component and the inner wall of the connecting ring cylinder;

[0046] A force transmission frame tube is connected between the second servo actuator mounting and the adjacent force transmission beam.

[0047] Optionally, the multi-engine parallel engine frame structure of the launch vehicle further includes:

[0048] A first servo actuator mounting bracket connected to the first force transmission frame, the first servo actuator mounting bracket being located on one side of the first engine mounting base;

[0049] The first servo actuator mounting bracket includes:

[0050] The first servo actuator mounting component is located on one side of the first engine mounting base;

[0051] A second connecting pipe is connected between the first servo actuator mounting component and the adjacent rigid pipe, and the second connecting pipe is coaxially arranged with the first servo actuator mounting component;

[0052] A first connecting pipe is provided between the first servo actuator mounting component and the adjacent force transmission beam. Two first connecting pipes are provided, and the two first connecting pipes are symmetrically distributed with respect to the axis of the second connecting pipe.

[0053] The above-described solution of the present invention has at least the following beneficial effects:

[0054] The above-described solution of the present invention transmits the thrust of multiple engines to the connecting ring frame through a first force transmission frame and multiple second force transmission frames. The propellant tank is not subjected to stress and there is no need to strengthen the propellant tank design, which ensures the thrust effect of multiple engines of the launch vehicle and helps to improve the carrying capacity of the launch vehicle. Attached Figure Description

[0055] Figure 1 This is a top-view three-dimensional structural diagram of the multi-engine parallel engine frame structure of a launch vehicle provided in an embodiment of the present invention;

[0056] Figure 2 This is a cross-sectional schematic diagram of the connecting ring frame in the multi-engine parallel engine frame structure of a launch vehicle provided in an embodiment of the present invention;

[0057] Figure 3 This is a top view of the multi-engine parallel engine frame structure of a launch vehicle provided in an embodiment of the present invention;

[0058] Figure 4 This is a front sectional view of the multi-engine parallel engine frame structure of a launch vehicle provided in an embodiment of the present invention;

[0059] Figure 5 This is a cross-sectional schematic diagram of the force transmission beam in the multi-engine parallel engine frame structure of a launch vehicle provided in an embodiment of the present invention;

[0060] Figure 6 This is a bottom view of the multi-engine parallel engine frame structure of a launch vehicle provided in an embodiment of the present invention;

[0061] Figure 7 This is a three-dimensional structural diagram of the multi-engine parallel engine frame structure of a launch vehicle provided in an embodiment of the present invention, viewed from an elevation angle.

[0062] Figure 8 This is a right view of the multi-engine parallel engine frame structure of a launch vehicle provided in an embodiment of the present invention.

[0063] The annotations in the attached figures are explained as follows:

[0064] 1. Connecting ring frame; 11. Connecting ring cylinder; 12. Upper connecting ring plate; 13. Upper connecting hole; 14. Reinforcing rib plate; 15. Lower connecting ring plate; 16. Lower connecting hole; 17. Reinforcing plate; 2. First force transmission frame; 21. Force transmission beam; 211. Web plate; 212. Upper flange plate; 213. Lower flange plate; 214. Connecting rib plate; 22. Load-bearing cylinder; 23. Rigid tube; 3. Second force transmission frame; 31. Load-bearing component; 32. Ring frame force transmission tube; 33. Force transmission frame tube; 4. Second Servo actuator mounting bracket; 41. Second servo actuator mounting component; 42. Engine mount pull tube; 43. Force transmission frame pull tube; 44. Force transmission ball pull tube; 45. Ring frame pull tube; 51. First engine mounting base; 52. Second engine mounting base; 6. Rigid frame; 61. Load-bearing ball; 62. First rigid pull tube; 63. Second rigid pull tube; 7. First servo actuator mounting bracket; 71. First servo actuator mounting component; 72. First connecting tube; 73. Second connecting tube. Detailed Implementation

[0065] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0066] like Figures 1 to 8 As shown, an embodiment of the present invention proposes a multi-engine parallel engine frame structure for a launch vehicle, comprising:

[0067] Connecting ring frame 1 between the upper and lower sections of the launch vehicle;

[0068] The first force transmission frame 2 is connected to the connecting ring frame 1, and the center of gravity of the first force transmission frame 2 is located on the axis of the connecting ring frame 1;

[0069] First engine mounting base 51, first engine mounting base 51 is coaxially arranged with connecting ring frame 1, first engine mounting base 51 is connected to first force transmission frame 2 so as to transmit the thrust of the first engine to connecting ring frame 1 through first force transmission frame 2;

[0070] Multiple second force transmission frames 3 are connected to the connecting ring frame 1 and the first force transmission frame 2. The multiple second force transmission frames 3 are evenly distributed around the axis of the connecting ring frame 1.

[0071] Multiple second engine mounting bases 52 are connected to multiple second force transmission frames 3 respectively, so as to transmit the thrust of multiple second engines to the connecting ring frame 1 through multiple second force transmission frames 3 and first force transmission frame 2;

[0072] Multiple second engine mounting bases 52 and first engine mounting bases 51 are coplanar.

[0073] In this embodiment, the first engine is mounted on the first engine mounting base 51, and the thrust of the first engine is transmitted to the connecting ring frame 1 through the first engine mounting base 51 and the first force transmission frame 2.

[0074] Multiple second engines are mounted on multiple second engine mounting bases 52. The thrust of the multiple second engines is transmitted to the first force transmission frame 2 and the connecting ring frame 1 through the multiple second engine mounting bases 52 and multiple second force transmission frames 3 respectively. The thrust received by the first force transmission frame 2 is also transmitted to the connecting ring frame 1.

[0075] The thrust of the first engine and multiple second engines is ultimately transmitted to the connecting ring frame 1, and then to the upper section of the launch vehicle. The propellant tank is not subjected to stress, so there is no need to strengthen the propellant tank design. This ensures the thrust effect of the multiple engines of the launch vehicle and helps to improve the launch vehicle's carrying capacity.

[0076] In practical applications, the number of second force transmission frames 3 is even. Multiple second force transmission frames 3 are evenly distributed around the axis of the connecting ring frame 1, which can ensure that the paired second engine mounting seats 52 are located in the same radial direction of the connecting ring frame 1, so that the connecting ring frame 1 is subjected to uniform force and ensures the thrust effect on the launch vehicle.

[0077] In this embodiment, six of each of the second engine mounting base 52 and the second force transmission frame 3 are provided.

[0078] like Figure 2 As shown, in an optional embodiment of the present invention, the connecting ring frame 1 includes:

[0079] Connecting ring cylinder 11;

[0080] The upper connecting ring plate 12 is connected to the upper outer edge of the connecting ring cylinder 11, and the surface of the upper connecting ring plate 12 is uniformly provided with upper connecting holes 13;

[0081] The lower connecting ring plate 15 is connected to the lower outer edge of the connecting ring cylinder 11, and the bottom surface of the lower connecting ring plate 15 is evenly provided with lower connecting holes 16;

[0082] The upper connecting ring plate 12, the connecting ring cylinder 11 and the lower connecting ring plate 15 form a horizontal U-shaped structure, and the open end of the horizontal U-shaped structure is far away from the axis of the connecting ring cylinder 11;

[0083] The reinforcing rib plate 14 is connected to the upper connecting ring plate 12, the connecting ring cylinder 11 and the lower connecting ring plate 15. The reinforcing rib plate 14 is located within the horizontal U-shaped structure.

[0084] In this embodiment, a U-shaped structure is formed by connecting ring cylinder 11, upper connecting ring plate 12 and lower connecting ring plate 15, and reinforcing rib plate 14 is provided in the U-shaped structure. While ensuring the overall strength of the connecting ring frame 1, it helps to reduce the weight of the connecting ring frame 1 and helps to improve the thrust effect of multiple engines.

[0085] The upper connecting ring plate 12 can be connected to the upper section of the launch vehicle through the upper connecting hole 13, and the lower connecting ring plate 15 can be connected to the lower section of the launch vehicle through the lower connecting hole 16, thereby realizing the connection of the connecting ring frame 1 to the upper and lower sections of the launch vehicle.

[0086] The connecting ring cylinder 11, the upper connecting ring plate 12, the lower connecting ring plate 15, and the reinforcing rib plate 14 are all welded together, which can further improve the overall strength of the connecting ring frame 1.

[0087] like Figure 3 and Figure 4 As shown, in an optional embodiment of the present invention, the first force transmission frame 2 includes:

[0088] The load-bearing cylinder 22 is located below the connecting ring cylinder 11 and is coaxially arranged with the connecting ring cylinder 11. The first engine mounting base 51 is connected to the bottom surface of the load-bearing cylinder 22.

[0089] Multiple force transmission beams 21 are inclined, with the first end of each beam connected to the inner wall of the connecting ring cylinder 11 and the second end connected to the outer wall of the load-bearing cylinder 22.

[0090] In this embodiment, a first force transmission frame 2 is formed by multiple force transmission beams 21 and a force-bearing cylinder 22. The thrust of the first engine is transmitted to the force-bearing cylinder 22 through the first engine mounting base 51, and then to the connecting ring frame 1 through multiple force transmission beams 21.

[0091] In this embodiment, the load-bearing cylinder 22 adopts a conical cylinder structure, which facilitates the welding connection between the multiple force transmission beams 21 and the load-bearing cylinder 22, and at the same time helps to improve the force transmission effect between the load-bearing cylinder 22 and the multiple force transmission beams 21.

[0092] In this embodiment, there are six force transmission beams 21, which can ensure that the thrust transmitted by the force transmission beams 21 to the connecting ring frame 1 is evenly distributed, ensure that the connecting ring frame 1 is subjected to uniform force, and ensure the thrust effect on the launch vehicle.

[0093] In this embodiment, the inclination angle between the force transmission beam 21 and the horizontal plane is 25°-30°, which can ensure the force transmission effect of the force transmission beam 21.

[0094] In this embodiment, the force transmission beam 21 adopts a variable cross-section structure. From the connecting ring cylinder 11 to the load-bearing cylinder 22, the cross-section of the force transmission beam 21 gradually increases, which can ensure the connection strength between the force transmission beam 21 and the load-bearing cylinder 22, thereby improving the force transmission effect between the load-bearing cylinder 22 and the force transmission beam 21.

[0095] like Figure 3 As shown, in an optional embodiment of the present invention, the first force transmission frame 2 further includes:

[0096] Multiple reinforcing plates 17 are formed on the inner wall of the connecting ring cylinder 11. The multiple reinforcing plates 17 are flush with the upper connecting ring plate 12. The multiple reinforcing plates 17 correspond one-to-one with and are connected to multiple force transmission beams 21. Through holes are uniformly provided on the surface of the multiple reinforcing plates 17.

[0097] In this embodiment, by setting multiple reinforcing plates 17, the strength of the connection between the force transmission beam 21 and the connecting ring cylinder 11 can be improved, ensuring that the force transmission beam 21 can accurately transmit the thrust of the transmitter to the connecting ring frame 1.

[0098] like Figure 3 As shown, in an optional embodiment of the present invention, a horizontally extending rigid tube 23 is connected between two adjacent force transmission beams 21.

[0099] In this embodiment, by welding and connecting a horizontally extending rigid tube 23 between two adjacent force transmission beams 21, the overall strength of the first force transmission frame 2 can be further improved, ensuring the force transmission effect of the first force transmission frame 2.

[0100] like Figure 5 As shown, in an optional embodiment of the present invention, each of the multiple force-transmitting beams 21 includes:

[0101] Web plate 211;

[0102] Upper flange 212 connected to web 211;

[0103] The lower flange 213 is connected to the web 211. The lower flange 213 and the upper flange 212 form an angle with the lower flange being larger than the upper flange. The upper flange 212, the web 211 and the lower flange 213 form a variable cross-section I-shaped structure.

[0104] Connecting stiffener 214 is connected to the upper flange 212, web 211 and lower flange 213.

[0105] In this embodiment, the upper wing plate 212, the web plate 211 and the lower wing plate 213 are welded together to form a variable cross-section I-shaped structure, which can ensure the overall strength of the force transmission beam 21, reduce the weight of the force transmission beam 21, and help improve the thrust effect of the engine on the launch vehicle; at the same time, the connecting stiffener plate 214 is welded to the inner cavity of the variable cross-section I-shaped structure, which can further improve the overall strength of the force transmission beam 21.

[0106] In this embodiment, the lower flange 213 and the upper flange 212 form an angle with the lower flange being larger than the upper flange. That is, from the connecting ring cylinder 11 to the load-bearing cylinder 22, the angle formed by the lower flange 213 and the upper flange 212 gradually increases, thereby forming a variable cross-section I-shaped structure with the upper flange 212, the web 211 and the lower flange 213. This helps to improve the overall strength of the force transmission beam 21, thereby improving the force transmission effect between the load-bearing cylinder 22 and the force transmission beam 21.

[0107] like Figures 6 to 8 As shown, in an optional embodiment of the present invention, each of the plurality of second force transmission frames 3 includes:

[0108] The load-bearing component 31 is connected to the second engine mounting base 52 and corresponds to the force transmission beam 21.

[0109] The force transmission frame tube 33 is connected between the load-bearing member 31 and the force transmission beam 21, and the axis of the force transmission frame tube 33 is coplanar with the axis of the force transmission beam 21.

[0110] Two ring-frame force transmission pipes 32 are connected between the load-bearing component 31 and the inner wall of the connecting ring cylinder 11. The two ring-frame force transmission pipes 32 are symmetrically distributed with reference to the coplanarity formed by the axis of the force transmission frame pipe 33 and the axis of the force transmission beam 21.

[0111] In this embodiment, the connection between the load-bearing component 31 and the connecting ring cylinder 11 and the transmission of thrust are achieved through two ring frame force transmission pipes 32, so that the thrust of the second engine is transmitted to the connecting ring cylinder 11; the connection between the load-bearing component 31 and the force transmission beam 21 and the transmission of thrust are achieved through the force transmission frame pipe 33, so that the thrust of the second engine is transmitted to the force transmission beam 21.

[0112] The load-bearing component 31 adopts a hollow hemispherical structure to ensure the welding connection strength between the load-bearing component 31 and the force transmission frame tube 33 and the two ring frame force transmission tubes 32, while reducing the overall weight of the second force transmission frame 3 and ensuring the thrust effect on the launch vehicle.

[0113] The axis of the force transmission frame tube 33 is coplanar with the axis of the force transmission beam 21, which can ensure the force transmission effect of the force transmission frame tube 33 and the force transmission beam 21. The included angle between the axis of the force transmission frame tube 33 and the axis of the load-bearing member 31 is 30°-35°, which can ensure the force transmission effect between the load-bearing member 31, the force transmission frame tube 33 and the force transmission beam 21.

[0114] The two ring-frame force transmission tubes 32 are symmetrically distributed with the coplanarity formed by the axis of the force transmission frame tube 33 and the axis of the force transmission beam 21 as the reference. The included angle between the axes of the two ring-frame force transmission tubes 32 is 30°-35°, and the included angle between the axis of the ring-frame force transmission tube 32 and the axis of the load-bearing member 31 is 22°-27°, which can ensure the force transmission effect between the load-bearing member 31, the ring-frame force transmission tubes 32 and the connecting ring cylinder 11.

[0115] The second force transmission frame 3 is formed by two ring frame force transmission tubes 32, force transmission frame tube 33 and load-bearing component 31. While ensuring the overall strength of the second force transmission frame 3, it can work with the second engine mounting seat 52 to accurately transfer the thrust of the second engine to the first force transmission frame 2 and the connecting ring cylinder 11.

[0116] like Figure 3 , Figure 7 and Figure 8 As shown, in an optional embodiment of the present invention, the multi-engine parallel engine frame structure of the launch vehicle further includes:

[0117] Multiple rigid frames 6 are connected between two adjacent second force transmission frames 3, and the multiple rigid frames 6 are connected to two adjacent force transmission beams 21 respectively.

[0118] Multiple rigid frames 6 all include:

[0119] A load-bearing ball 61 located between two adjacent second force transmission frames 3;

[0120] Two first rigid tension tubes 62, the first ends of which are connected to the load-bearing ball 61, and the second ends of which are connected to two adjacent load-bearing members 31 respectively;

[0121] Two second rigid tension tubes 63, the first end of which is connected to the load-bearing ball 61, and the second end of which is connected to the two adjacent force transmission beams 21 respectively.

[0122] In this embodiment, by connecting a rigid frame 6 between two adjacent second force transmission frames 3 and between two adjacent force transmission beams 21, the overall strength of the second force transmission frames 3 and force transmission beams 21 can be improved, ensuring the force transmission effect of the second force transmission frames 3 and force transmission beams 21.

[0123] The first rigid pull tube 62 and the second rigid pull tube 63 are coaxially arranged, that is, the two first rigid pull tubes 62 and the two second rigid pull tubes 63 form an X-shaped structure, which can ensure the overall strength of the rigid frame 6, thereby improving the overall strength of the second force transmission frame 3 and the force transmission beam 21, and ensuring the force transmission effect of the second force transmission frame 3 and the force transmission beam 21; the angle between the axis of the first rigid pull tube 62 and the axis of the load-bearing member 31 is 55°-60°, which ensures the connection stability of the rigid frame 6 with the load-bearing ball 61 and the force transmission beam 21, and ensures the overall strength.

[0124] like Figure 1 and Figure 7 As shown, in an optional embodiment of the present invention, the multi-engine parallel engine frame structure of the launch vehicle further includes:

[0125] Multiple second servo actuator mounting brackets 4 are connected to multiple second force transmission frames 3, multiple force transmission beams 21 and multiple rigid frames 6 respectively.

[0126] Each of the multiple second servo actuator mounting brackets 4 includes:

[0127] The second servo actuator mounting part 41 is located on one side of the second engine mounting base 52;

[0128] Engine mount pull tube 42 connecting the second servo actuator mounting part 41 and the adjacent ring frame force transmission tube 32;

[0129] A force-transmitting ball pull tube 44 connects the second servo actuator mounting part 41 and the adjacent load-bearing ball 61;

[0130] An annular frame tube 45 is connected between the second servo actuator mounting part 41 and the inner wall of the connecting ring cylinder 11;

[0131] The force transmission frame pull tube 43 is connected between the second servo actuator mounting part 41 and the adjacent force transmission beam 21.

[0132] In this embodiment, the second servo actuator mounting bracket 4 facilitates the installation of the second servo actuator. The second servo actuator enables the nozzle of the second engine to swing, thereby changing the direction of the jet flow and achieving attitude control such as pitch, yaw, and roll of the rocket body.

[0133] The second servo actuator mounting component 41 is connected to the ring frame force transmission tube 32, the force-bearing ball 61, the connecting ring cylinder 11, and the force transmission beam 21 by the engine base pull tube 42, the force transmission ball pull tube 44, the ring frame pull tube 45, and the force transmission frame pull tube 43, respectively, to ensure the stability of the second servo actuator mounting component 41.

[0134] like Figure 3 , Figure 6 andFigure 7 As shown, in an optional embodiment of the present invention, the multi-engine parallel engine frame structure of the launch vehicle further includes:

[0135] The first servo actuator mounting bracket 7 is connected to the first force transmission frame 2 and is located on one side of the first engine mounting base 51.

[0136] The first servo actuator mounting bracket 7 includes:

[0137] The first servo actuator mounting part 71 is located on one side of the first engine mounting base 51;

[0138] A second connecting pipe 73 is connected between the first servo actuator mounting 71 and the adjacent rigid pipe 23, and the second connecting pipe 73 is coaxially arranged with the first servo actuator mounting 71.

[0139] A first connecting pipe 72 is provided between the first servo actuator mounting part 71 and the adjacent force transmission beam 21. Two first connecting pipes 72 are provided, and the two first connecting pipes 72 are symmetrically distributed with respect to the axis of the second connecting pipe 73.

[0140] In this embodiment, there are two first servo actuator mounting brackets 7, and the two first servo actuator mounting brackets 7 are respectively located on both sides of the first engine mounting base 51. The first servo actuator is installed through the first servo actuator mounting brackets 7, and the nozzle of the first engine is oscillated through the first servo actuator, thereby changing the direction of the jet flow and realizing attitude control such as pitch, yaw, and roll of the rocket body.

[0141] The first servo actuator mounting component 71 is connected to the rigid pipe 23 and the force transmission beam 21 by two first connecting pipes 72 and second connecting pipes 73 respectively, ensuring the stability of the first servo actuator mounting component 71.

[0142] The multi-engine parallel engine frame structure of the launch vehicle provided in the above embodiments of the present invention is formed by connecting ring frame 1, first force transmission frame 2, multiple second force transmission frames 3, multiple rigid frames 6, multiple second servo actuator mounting frames 4, and first servo actuator mounting frame 7. The thrust of the engine is transmitted to the connecting ring frame 1 through multiple second force transmission frames 3 and first force transmission frames 2. The force transmission route is clear and reasonable, the propellant tank is not stressed, and there is no need to strengthen the propellant tank design, which ensures the thrust effect of multiple engines of the launch vehicle and helps to improve the carrying capacity of the launch vehicle. It is mainly welded from plate and pipe, and the structure is simple. The frame structure has high rigidity and strength, and small deformation under stress, which can significantly reduce the engine axis deviation, reduce the pressure on the rocket body attitude control, reduce the amount of attitude control while improving the carrying capacity. The connection with the upper and lower sections of the launch vehicle is realized through the connecting ring frame 1, which is simple and quick to assemble.

[0143] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A multi-engine parallel engine frame structure for a launch vehicle, characterized in that, include: Connecting ring frame (1) between the upper and lower sections of the launch vehicle; A first force transmission frame (2) connected to the connecting ring frame (1) has its center of gravity located on the axis of the connecting ring frame (1); First engine mounting base (51), the first engine mounting base (51) is coaxially arranged with the connecting ring frame (1), the first engine mounting base (51) is connected to the first force transmission frame (2) so as to transmit the thrust of the first engine to the connecting ring frame (1) through the first force transmission frame (2). Multiple second force transmission frames (3) are connected to the connecting ring frame (1) and the first force transmission frame (2), and the multiple second force transmission frames (3) are evenly distributed around the axis of the connecting ring frame (1). Multiple second engine mounting bases (52) are connected to multiple second force transmission frames (3) respectively, so as to transmit the thrust of multiple second engines to the connecting ring frame (1) through multiple second force transmission frames (3) and the first force transmission frame (2). Multiple second engine mounting brackets (52) and the first engine mounting bracket (51) are coplanar; The connecting ring frame (1) includes a connecting ring cylinder (11). The first force transmission frame (2) includes: A load-bearing cylinder (22) is located below the connecting ring cylinder (11), and the load-bearing cylinder (22) is coaxially arranged with the connecting ring cylinder (11). The first engine mounting base (51) is connected to the bottom surface of the load-bearing cylinder (22). Multiple force transmission beams (21) are inclined, with the first end of each beam (21) connected to the inner wall of the connecting ring cylinder (11) and the second end of each beam (21) connected to the outer wall of the load-bearing cylinder (22). Among them, multiple second force transmission frames (3) include: The load-bearing component (31) is connected to the second engine mounting base (52) and corresponds to the force transmission beam (21); A force transmission frame tube (33) is connected between the load-bearing member (31) and the force transmission beam (21), and the axis of the force transmission frame tube (33) is coplanar with the axis of the force transmission beam (21); Two ring-frame force transmission pipes (32) are connected between the load-bearing member (31) and the inner wall of the connecting ring cylinder (11). The two ring-frame force transmission pipes (32) are symmetrically distributed with reference to the coplanarity formed by the axis of the force transmission frame pipe (33) and the axis of the force transmission beam (21).

2. The multi-engine parallel engine frame structure of the launch vehicle according to claim 1, characterized in that, The connecting ring frame (1) further includes: The upper connecting ring plate (12) is connected to the upper outer edge of the connecting ring cylinder (11), and the surface of the upper connecting ring plate (12) is uniformly provided with upper connecting holes (13). The lower connecting ring plate (15) is connected to the lower outer edge of the connecting ring cylinder (11), and the bottom surface of the lower connecting ring plate (15) is uniformly provided with lower connecting holes (16). The upper connecting ring plate (12), the connecting ring cylinder (11) and the lower connecting ring plate (15) form a horizontal U-shaped structure, and the open end of the horizontal U-shaped structure is far away from the axis of the connecting ring cylinder (11); A reinforcing rib plate (14) is connected to the upper connecting ring plate (12), the connecting ring cylinder (11) and the lower connecting ring plate (15), and the reinforcing rib plate (14) is located in a horizontal U-shaped structure.

3. The multi-engine parallel engine frame structure of the launch vehicle according to claim 2, characterized in that, The first force transmission frame (2) also includes: Multiple reinforcing plates (17) are formed on the inner wall of the connecting ring cylinder (11). The multiple reinforcing plates (17) are flush with the upper connecting ring plate (12). The multiple reinforcing plates (17) correspond one-to-one with and are connected to multiple force transmission beams (21). Through holes are uniformly provided on the surface of the multiple reinforcing plates (17).

4. The multi-engine parallel engine frame structure of the launch vehicle according to claim 1, characterized in that, A horizontally extending rigid tube (23) connects two adjacent force transmission beams (21).

5. The multi-engine parallel engine frame structure of the launch vehicle according to claim 1, characterized in that, The multiple load-transfer beams (21) all include: Web (211); The upper wing plate (212) is connected to the web plate (211); The lower wing plate (213) is connected to the web plate (211). The lower wing plate (213) and the upper wing plate (212) form an angle with the lower wing plate being larger than the upper wing plate. The upper wing plate (212), the web plate (211) and the lower wing plate (213) form a variable cross-section I-shaped structure. A connecting stiffener plate (214) is connected to the upper wing plate (212), the web plate (211) and the lower wing plate (213).

6. The multi-engine parallel engine frame structure of the launch vehicle according to claim 1, characterized in that, Also includes: Multiple rigid frames (6) are connected between two adjacent second force transmission frames (3), and the multiple rigid frames (6) are connected to two adjacent force transmission beams (21); Multiple rigid frames (6) include: The load-bearing ball (61) is located between two adjacent second force transmission frames (3). Two first rigid pull tubes (62), the first ends of which are connected to the load-bearing ball (61), and the second ends of which are connected to two adjacent load-bearing members (31); Two second rigid tension tubes (63) are connected at their first ends to the load-bearing ball (61) and at their second ends to the two adjacent force transmission beams (21).

7. The multi-engine parallel engine frame structure of the launch vehicle according to claim 6, characterized in that, Also includes: Multiple second servo actuator mounting brackets (4) are connected to multiple second force transmission frames (3), multiple force transmission beams (21) and multiple rigid frames (6), respectively. Multiple second servo actuator mounting brackets (4) each include: The second servo actuator mounting part (41) is located on one side of the second engine mounting base (52); Engine mount pull tube (42) connecting the second servo actuator mount (41) and the adjacent ring force transmission tube (32); A force-transmitting ball pull tube (44) is connected between the second servo actuator mounting (41) and the adjacent force-bearing ball (61). A ring frame tube (45) is connected between the second servo actuator mounting part (41) and the inner wall of the connecting ring cylinder (11); A force transmission frame tube (43) is connected between the second servo actuator mount (41) and the adjacent force transmission beam (21).

8. The multi-engine parallel engine frame structure of the launch vehicle according to claim 4, characterized in that, Also includes: A first servo actuator mounting bracket (7) is connected to the first force transmission frame (2), and the first servo actuator mounting bracket (7) is located on one side of the first engine mounting base (51); The first servo actuator mounting bracket (7) includes: The first servo actuator mounting part (71) is located on one side of the first engine mounting base (51); A second connecting pipe (73) is connected between the first servo actuator mounting (71) and the adjacent rigid pipe (23), and the second connecting pipe (73) is coaxially arranged with the first servo actuator mounting (71); A first connecting pipe (72) is connected between the first servo actuator mounting part (71) and the adjacent force transmission beam (21). Two first connecting pipes (72) are provided, and the two first connecting pipes (72) are symmetrically distributed with respect to the axis of the second connecting pipe (73).

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