A large nozzle rocket transport support structure and method

Abstract

The present invention provides a large-nozzle rocket transportation support structure and method, belonging to the field of large-nozzle rocket transportation technology. The large-nozzle rocket transportation support structure includes a nozzle end airbag assembly and a nozzle tail support bracket arranged on the engine nozzle; the nozzle end airbag assembly is arranged at the end of the inner wall of the engine nozzle, used to support and limit the inner wall of the engine nozzle; the nozzle tail support bracket is arranged at the tail end of the engine nozzle, used to support and position the tail end of the engine nozzle. The present invention supports and limits the nozzle end and tail end respectively, provides support and protection during transportation, erection or reloading, avoids deformation or damage of the nozzle caused by external forces, and is conducive to improving the stability and reliability of transportation and erection; the method of the present invention is simple to operate and stable and reliable to use.

Description

Technical Field

[0001] The present invention relates to the technical field of large nozzle rocket transportation, and in particular to a large nozzle rocket transportation support structure and method. Background Art

[0002] Before the launch of a liquid rocket, a corresponding transport structure is required for transfer and erection operations. For example, the Chinese patent application number is: 202120496809.3, and the patent name is: A launch vehicle engine swing support device. Although it can meet the general use requirements, with the continuous development of liquid rocket systems, in order to maximize the rocket carrying efficiency, the upper stage rocket adopts an ultra-large nozzle structure to increase the expansion ratio, which can effectively increase the engine vacuum fall force load.

[0003] However, since the engine's super-large nozzles are mostly thin-walled structures, the ratio of their effective thickness to the nozzle's outlet diameter is large, and the nozzle structure has poor rigidity. Therefore, during conventional transportation, erection or transshipment, they are easily affected by external forces and deformed or damaged, causing the engine thrust line to deviate or the engine to fail, affecting the effectiveness and reliability of liquid rocket transportation and erection, and limiting their applicability. Summary of the Invention

[0004] In view of this, the purpose of the embodiments of the present invention is to provide a large nozzle rocket transportation support structure and method with a reasonable structural setting and conducive to improving the reliability of transportation or erection.

[0005] The embodiment of the present invention provides a large nozzle rocket transport support structure, which is arranged on the engine nozzle and includes a nozzle end airbag assembly and a nozzle tail support bracket;

[0006] The nozzle end airbag assembly is arranged at the end of the inner wall of the engine nozzle and is used to support and limit the inner wall of the engine nozzle;

[0007] The nozzle tail support bracket is arranged at the tail end of the engine nozzle and is used for supporting and positioning the tail end of the engine nozzle.

[0008] Further preferably, the nozzle end airbag assembly includes an airbag body, a support ring, an adjustment handwheel and an adjustment screw;

[0009] The support ring is fixed to the rocket stage or the transport vehicle by fastening bolts, the airbag body is located at the end of the inner wall of the engine nozzle, and the adjusting screw is fixed to the bottom surface of the airbag body;

[0010] The adjusting screw is threadedly connected to the supporting ring, and the adjusting hand wheel is fixed to the end of the adjusting screw.

[0011] It is further preferred that: the nozzle end airbag assembly further includes a plurality of inclined rods for increasing rigidity;

[0012] The plurality of inclined tie rods are arranged in a conical shape, and a guide channel is provided at the center of the cone and is on the same vertical line as the threaded hole;

[0013] The adjusting screw is arranged in the guide channel.

[0014] It is further preferred that the pressure in the airbag body is 0.13-0.25 MPa, and the airbag body is an independent airbag or a combination of several airbags.

[0015] It is further preferred that: the nozzle throat support assembly is further included;

[0016] The nozzle throat support assembly is fixed on the outer wall of the engine nozzle throat and is used to support and position the engine nozzle throat.

[0017] Further preferably, a threaded hole is provided on the support ring, and the adjusting screw is threadedly connected and passes through the threaded hole;

[0018] The adjusting hand wheel is used to rotate and drive the adjusting screw to rotate in the threaded hole, and to make the airbag body expand and contract in the engine nozzle along the arrow body axis direction, and the edge of the airbag body is tightly connected to the inner wall of the engine nozzle.

[0019] Further preferably, the end of the diagonal tie rod is fixed on the top surface of the support ring.

[0020] Further preferably, the top end of the inclined tie rod is fixed to an end of the adjusting screw rod close to the airbag body.

[0021] Further preferably, the nozzle tail support bracket includes an upper arc plate, a support and a lower arc plate;

[0022] The support is fixed on the rocket stage or the transport vehicle;

[0023] The upper arc plate and the lower arc plate are fixed on the support, and the tail end of the engine nozzle is clamped between the upper arc plate and the lower arc plate to limit the position.

[0024] It is further preferred that protective felt pads are provided between the upper arc plate and the tail end of the engine nozzle, and between the lower arc plate and the tail end of the engine nozzle.

[0025] Further preferably, the nozzle throat support assembly includes a split clamp, an ear seat, a double-rotating screw, a left-rotating nut, a right-rotating nut, a plurality of bolts and a bearing;

[0026] The ear seat is fixed on the rocket stage or the transport vehicle, and the split clamp is fixed on the outer wall of the engine nozzle throat;

[0027] The right-handed nut is connected to the split clamp or the ear seat through the bolt and the bearing, and the left-handed nut is connected to the ear seat or the split clamp through the bolt and the bearing.

[0028] The two ends of the twin-rotation screw are respectively threadedly connected to the left-handed nut and the right-handed nut.

[0029] More preferably, the twin-rotating screws are in two groups, and the angle between the two groups of twin-rotating screws is 45 degrees to 120 degrees.

[0030] On the other hand, the present invention also provides a method for supporting the transportation of a large nozzle rocket, the method comprising: providing a nozzle end airbag assembly at the end of the inner wall of the engine nozzle, and supporting and limiting the inner wall of the engine nozzle by the nozzle end airbag assembly during transportation;

[0031] A nozzle tail support bracket is provided at the tail end of the engine nozzle, and the tail end of the engine nozzle is supported and positioned by the nozzle tail support bracket during transportation.

[0032] The above technical solution has the following beneficial effects:

[0033] 1. The present invention has a rational structure, comprising a nozzle throat support assembly, a nozzle end airbag assembly, and a nozzle tail support bracket. These components can support and limit the nozzle throat, nozzle end, and tail, respectively, thereby providing support and protection during transportation, erection, or relocation. This prevents deformation or damage to the nozzle caused by external forces, improves the stability and reliability of transportation and erection, and ensures smooth and reliable use.

[0034] 2. The nozzle tip airbag assembly of the present invention includes an airbag body, a support ring, an adjustment handwheel, and an adjustment screw. During assembly, the airbag body is tightly attached to the inner wall of the engine nozzle, providing support and protection for the nozzle inner wall and preventing nozzle deformation or damage. Furthermore, the adjustment screw can also tighten the airbag body against the inner wall of the nozzle, ensuring a stable and reliable connection.

[0035] 3. The nozzle tip airbag assembly of the present invention also includes a diagonal tie rod for increasing rigidity. This, in conjunction with the support ring, ensures the stability of the adjustment screw, preventing it from tilting or shifting, thereby ensuring the smooth and effective lifting and lowering of the airbag body.

[0036] 4. The pressure inside the airbag body of the present invention is 0.13-0.25 MPa, and the airbag body is an independent airbag or a combination of several airbags, which can ensure the stability and effectiveness of the connection with the nozzle;

[0037] 5. The nozzle tail support bracket of the present invention includes an upper arc plate, a support seat, and a lower arc plate, which can not only effectively and quickly achieve support and positioning of the nozzle tail, but also ensure the stability and effectiveness of the connection;

[0038] 6. In the present invention, protective felt cushions are provided between the upper arc plate and the tail end of the engine nozzle, and between the lower arc plate and the tail end of the engine nozzle, which can provide auxiliary support for the tail end of the nozzle and prevent the nozzle from deformation or damage;

[0039] 7. The nozzle throat support assembly of the present invention includes a split clamp, an ear seat, a double-threaded screw, a left-handed nut, a right-handed nut, several bolts, and a bearing, which is convenient for assembly and disassembly and use. The double-threaded screw cooperates with the left-handed nut and the right-handed nut to achieve telescopic adjustment, ensuring a stable and reliable connection.

[0040] 8. The method of the present invention is simple to operate and stable and reliable to use. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0042] Figure 1 It is a structural diagram of an embodiment of the present invention;

[0043] Figure 2 This is an embodiment of the present invention Figure 1 The AA section in the middle shows the schematic structure;

[0044] Figure 3 This is an embodiment of the present invention Figure 2 The enlarged structural diagram at B in the middle;

[0045] Figure 4 This is an embodiment of the present invention Figure 1 The enlarged structural diagram at C in the middle;

[0046] Figure 5 This is an embodiment of the present invention Figure 4 Enlarged structural diagram at point D in the middle.

[0047] Description of reference numerals:

[0048] 1. Rocket stage interstage; 2. Engine nozzle;

[0049] 3. Nozzle throat support assembly; 31. Split clamp; 32. Ear seat; 33. Double-thread screw; 34. Left-hand nut; 35. Right-hand nut; 36. Bolt; 37. Bearing;

[0050] 4. Nozzle end airbag assembly; 41. Airbag body; 42. Support ring; 43. Adjustment handwheel; 44. Adjustment screw; 45. Threaded hole; 46. Diagonal tie rod;

[0051] 5. Nozzle tail support bracket; 51. Upper arc plate; 52. Support; 53. Lower arc plate;

[0052] 6. Guide channel. DETAILED DESCRIPTION

[0053] The features and exemplary embodiments of various aspects of the present invention are described in detail below. In the detailed description that follows, many specific details are set forth in order to provide a comprehensive understanding of the present invention. However, it will be apparent to those skilled in the art that the present invention can be implemented without some of these specific details. The following description of the embodiments is intended only to provide a better understanding of the present invention by illustrating examples of the present invention. In the accompanying drawings and the following description, at least some of the well-known structures and techniques are not shown in order to avoid unnecessary ambiguity in the present invention; and, for clarity, the sizes of some structures may be exaggerated. In addition, the features, structures, or characteristics described below may be combined in any suitable manner in one or more embodiments.

[0054] like Figures 1 to 5 As shown, a large nozzle rocket transport support structure is arranged on the engine nozzle 2, or on a separate engine nozzle 2, and includes a nozzle end airbag assembly 4 and a nozzle tail support bracket 5; its rocket stage 1 or transport vehicle and engine nozzle 2 are conventional structures of the prior art, so they are not described in detail, but simply applied. The nozzle end airbag assembly 4 is arranged at the end of the inner wall of the engine nozzle 2, and is used to support and limit the inner wall of the engine nozzle 2; the nozzle tail support bracket 5 is arranged at the tail end of the engine nozzle 2, and is used to support and position the tail end of the engine nozzle 2. By supporting and limiting the nozzle throat and nozzle tail, and supporting and limiting the nozzle inner wall through the nozzle end airbag assembly 4, the inside and outside of the nozzle can be protected and supported at the same time during the reloading, transportation or erection process, thereby effectively preventing the nozzle from deformation or damage, and improving the convenience of operation and reliability of use.

[0055] In actual application, Figure 1 and Figure 4As shown, the nozzle end airbag assembly 4 includes an airbag body 41, a support ring 42, an adjustment handwheel 43, and an adjustment screw 44. The adjustment screw 44 is primarily used to rotate and adjust the position of the airbag body 41 so that it can be tightly braced against the inner wall of the nozzle, ensuring the stability and reliability of the nozzle inner wall protection. During assembly, the support ring 42 is fixed to the rocket stage 1 or the transport vehicle via fastening bolts, and the support ring 42 is provided with a threaded hole 45. During assembly, the airbag body 41 is located at the end of the inner wall of the engine nozzle 2, and the adjustment screw 44 is fixed to the bottom surface of the airbag body 41. The adjustment screw 44 is threadedly connected and passes through the threaded hole 45, and the adjustment handwheel 43 is fixed to the end of the adjustment screw 44. The adjustment handwheel 43 is used to rotate and drive the adjustment screw 44 in the threaded hole 45, thereby causing the airbag body 41 to expand and contract within the engine nozzle 2 along the rocket body axis, and the edge of the airbag body 41 is tightly braced against the inner wall of the engine nozzle 2.

[0056] In this embodiment, the airbag body 41 can be annular or circular. During use, it can be filled with air, other gases, or liquid to impart flexibility to the airbag body 41, thereby achieving corresponding support effectiveness and reliability. Furthermore, in actual use, the nozzle tip airbag assembly 4 also includes multiple inclined rods 46 for increasing rigidity. Furthermore, the multiple inclined rods 46 are conically arranged, with a guide channel 6 disposed at the center of the cone, aligned vertically with the threaded hole 45. The adjustment screw 44 is disposed within the guide channel 6. In this embodiment, the inclined rods 46 can also be replaced with other tie rod-type structures, primarily to prevent the adjustment screw 44 from tilting. This is primarily used to stabilize the adjustment screw 44, preventing it from tilting or shifting, and improving its stability and reliability. The number of inclined rods ranges from six to twelve, and they are evenly distributed circumferentially to ensure support effectiveness and stability. The material used is Q690D.

[0057] In actual use, the pressure within the airbag body 41 can be 0.13-0.25 MPa. The airbag body 41 can be a standalone airbag or composed of several smaller airbags. During assembly, the ends of the diagonal tie rods 46 are fixed to the top surface of the support ring 42. Alternatively, the top end of the diagonal tie rods 46 is fixed to the end of the adjustment screw 44 near the airbag body 41. This ensures effective and reliable support.

[0058] like Figure 5As shown, in actual use, the nozzle tail support bracket 5 includes an upper arc plate 51, a support 52, and a lower arc plate 53. In this embodiment, the upper arc plate 51 and the lower arc plate 53 are shaped according to the nozzle nozzle size, with a circumferential angle of approximately 45°. During assembly, the support 52 is fixed to the rocket stage 1 or the transport vehicle. The upper arc plate 51 and the lower arc plate 53 are fixed to the support 52, and the tail end of the engine nozzle 2 is clamped between the upper arc plate 51 and the lower arc plate 53 to limit the position. Protective felt pads are provided between the upper arc plate 51 and the tail end of the engine nozzle 2, and between the lower arc plate 53 and the tail end of the engine nozzle 2. These can also be replaced with other soft materials to prevent damage to the engine nozzle 2 during assembly, improving stability and reliability.

[0059] like Figure 2 As shown, it also includes a nozzle throat support assembly 3. During assembly, the nozzle throat support assembly 3 is fixed to the outer wall of the throat of the engine nozzle 2 to support and position the throat of the engine nozzle 2.

[0060] The nozzle throat support assembly 3 includes a split clamp 31, an ear seat 32, a twin-threaded screw 33, a left-handed nut 34, a right-handed nut 35, several bolts 36, and a bearing 37. During assembly, the ear seat 32 is fixed to the rocket stage interstage 1 or the transport vehicle, and the split clamp 31 is fixed to the outer wall of the engine nozzle 2 throat. The right-handed nut 35 is connected to the split clamp 31 or the ear seat 32 via bolts 36 and bearings 37, and the left-handed nut 34 is connected to the ear seat 32 or the split clamp 31 via bolts 36 and bearings 37. The ends of the twin-threaded screw 33 are threadedly connected to the left-handed nut 34 and the right-handed nut 35, respectively. The twin-threaded screws 33 are arranged in two groups, and the angle between the two groups of twin-threaded screws 33 is 45 to 120 degrees. The bearings 37 ensure smooth relative rotation, and the twin-threaded screws 33 can be rotated as needed to adjust their position, improving operational stability and reliability.

[0061] In addition, an embodiment of the present invention further provides a method for transporting and supporting a large nozzle rocket, the method comprising:

[0062] A nozzle end airbag assembly 4 is provided at the inner wall end of the engine nozzle 2, and the nozzle end airbag assembly 4 supports and limits the inner wall of the engine nozzle 2 during transportation;

[0063] A nozzle tail support bracket 5 is provided at the tail end of the engine nozzle 2 , and the tail end of the engine nozzle 2 is supported and positioned by the nozzle tail support bracket 5 during transportation.

[0064] The above technical solution has the following beneficial effects:

[0065] 1. The embodiment of the present invention has a reasonable structural arrangement, comprising a nozzle throat support assembly, a nozzle end airbag assembly, and a nozzle tail support bracket. These components can support and limit the nozzle throat, nozzle end, and tail, respectively, thereby providing support and protection during transportation, erection, or relocation. This prevents deformation or damage to the nozzle caused by external forces, thereby improving the stability and reliability of transportation and erection, and ensuring smooth and reliable use.

[0066] 2. The nozzle tip airbag assembly in the embodiment of the present invention includes an airbag body, a support ring, an adjustment handwheel, and an adjustment screw. During assembly, the airbag body is tightly attached to the inner wall of the engine nozzle, providing support and protection for the nozzle inner wall and preventing nozzle deformation or damage. Furthermore, the adjustment screw can also securely hold the airbag body against the inner wall of the nozzle, ensuring a stable and reliable connection.

[0067] 3. The nozzle tip airbag assembly in this embodiment of the present invention also includes a diagonal tie rod for increasing rigidity. This, in conjunction with the support ring, ensures the stability of the adjustment screw, preventing it from tilting or shifting, thereby ensuring smooth and effective lifting and lowering of the airbag body.

[0068] 4. In the embodiment of the present invention, the pressure inside the airbag body is 0.13-0.25 MPa, and the airbag body is an independent airbag or a combination of multiple airbags, which can ensure the stability and effectiveness of the connection with the nozzle;

[0069] 5. The nozzle tail support bracket in the embodiment of the present invention includes an upper arc plate, a support, and a lower arc plate. It can not only effectively and quickly achieve support and positioning of the nozzle tail, but also ensure the stability and effectiveness of the connection;

[0070] 6. In the embodiment of the present invention, protective felt pads are installed between the upper arc plate and the tail end of the engine nozzle, and between the lower arc plate and the tail end of the engine nozzle. These pads can provide auxiliary support for the tail end of the nozzle to prevent deformation or damage to the nozzle.

[0071] 7. The nozzle throat support assembly in the embodiment of the present invention includes a split clamp, an ear seat, a double-threaded screw, a left-handed nut, a right-handed nut, several bolts and bearings, which are convenient for disassembly, assembly and use. The double-threaded screw is combined with the left-handed nut and the right-handed nut to achieve telescopic adjustment, ensuring the stability and reliability of the connection.

[0072] 8. The method of the present invention is simple to operate and stable and reliable to use.

[0073] In the description of the present invention, it should be noted that the terms "upper, lower, inner, and outer" and other references to orientations or positional relationships are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limitations on the present invention. Furthermore, the terms "first, second, or third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0074] In this disclosure, unless otherwise specified or limited, the terms "mounted," "connected," and "connected" should be interpreted broadly. For example, they may refer to fixed, removable, or integral connections. They may also refer to mechanical, electrical, or direct connections, indirect connections through an intermediary, or internal communication between two components. Those skilled in the art will understand the specific meanings of these terms in this disclosure.

[0075] While the present invention has been described with reference to preferred embodiments, various modifications may be made and equivalent components may be substituted without departing from the scope of the present invention. In particular, the various technical features described in the various embodiments may be combined in any manner, provided no structural conflicts exist. The present invention is not limited to the specific embodiments disclosed herein, but encompasses all technical solutions within the scope of the claims.

Claims

1. A large nozzle rocket transport support structure, arranged on the engine nozzle (2), characterized in that: It comprises a nozzle end airbag assembly (4) and a nozzle tail support bracket (5); The nozzle end airbag assembly (4) is arranged at the end of the inner wall of the engine nozzle (2) and is used for supporting and limiting the inner wall of the engine nozzle (2); The nozzle tail support bracket (5) is arranged at the tail end of the engine nozzle (2) and is used for supporting and positioning the tail end of the engine nozzle (2); The nozzle end airbag assembly (4) comprises an airbag body (41), a support ring (42), an adjusting hand wheel (43) and an adjusting screw (44); The support ring (42) is fixed to the rocket stage section (1) or the transport vehicle by fastening bolts, the airbag body (41) is located at the end of the inner wall of the engine nozzle (2), and the adjusting screw (44) is fixed to the bottom surface of the airbag body (41); The adjusting screw (44) is threadedly connected to the supporting ring (42), and the adjusting hand wheel (43) is fixed to the end of the adjusting screw (44).

2. The large nozzle rocket transport support structure according to claim 1, characterized in that: The nozzle end airbag assembly (4) further includes a plurality of inclined tie rods (46) for increasing rigidity; The plurality of inclined tie rods (46) are arranged in a conical shape, and a guide channel (6) is provided at the center of the cone and is on the same vertical line as the threaded hole (45); The adjusting screw (44) is inserted into the guide channel (6).

3. The large nozzle rocket transport support structure according to claim 1, characterized in that: The pressure in the airbag body (41) is 0.13-0.25 MPa, and the airbag body (41) is an independent airbag or a combination of several airbags.

4. The large nozzle rocket transport support structure according to claim 1, characterized in that: The support ring (42) is provided with a threaded hole (45), and the adjusting screw (44) is threadedly connected and passes through the threaded hole (45); The adjusting hand wheel (43) is used to rotate and drive the adjusting screw (44) to rotate in the threaded hole (45), and to make the airbag body (41) expand and contract in the engine nozzle (2) along the arrow body axis direction, and the edge of the airbag body (41) is tightly connected to the inner wall of the engine nozzle (2).

5. The large nozzle rocket transport support structure according to claim 2, characterized in that: The end of the inclined tie rod (46) is fixed on the top surface of the support ring (42).

6. The large nozzle rocket transport support structure according to claim 2, characterized in that: The top end of the inclined tie rod (46) is fixed to an end of the adjusting screw (44) close to the airbag body (41).

7. The large nozzle rocket transport support structure according to claim 1, characterized in that: The nozzle tail support bracket (5) comprises an upper arc plate (51), a support (52) and a lower arc plate (53); The support (52) is fixed on the rocket stage (1) or the transport vehicle; The upper arc plate (51) and the lower arc plate (53) are fixed on the support (52), and the tail end of the engine nozzle (2) is clamped between the upper arc plate (51) and the lower arc plate (53) to limit the position.

8. The large nozzle rocket transport support structure according to claim 7, characterized in that: Protective felt cushions are provided between the upper arc plate (51) and the tail end of the engine nozzle (2), and between the lower arc plate (53) and the tail end of the engine nozzle (2).

9. The large nozzle rocket transport support structure according to claim 1, characterized in that: Also included is a nozzle throat support assembly (3); The nozzle throat support assembly (3) is fixed on the outer wall of the throat of the engine nozzle (2) and is used to support and position the throat of the engine nozzle (2).

10. The large nozzle rocket transport support structure according to claim 9, characterized in that: The nozzle throat support assembly (3) comprises a split hoop (31), an ear seat (32), a double-threaded screw (33), a left-handed nut (34), a right-handed nut (35), a plurality of bolts (36) and a bearing (37); The ear seat (32) is fixed on the rocket stage (1) or the transport vehicle, and the split clamp (31) is fixed on the outer wall of the throat of the engine nozzle (2); The right-handed nut (35) is connected to the split hoop (31) or the ear seat (32) through the bolt (36) and the bearing (37), and the left-handed nut (34) is connected to the ear seat (32) or the split hoop (31) through the bolt (36) and the bearing (37). The two ends of the double-rotation screw (33) are respectively threadedly connected to the left-rotation nut (34) and the right-rotation nut (35).

11. The large nozzle rocket transport support structure according to claim 10, characterized in that: There are two groups of twin-rotating screws (33), and the angle between the two groups of twin-rotating screws (33) is 45 degrees to 120 degrees.

12. A method for transporting and supporting a large nozzle rocket, characterized in that: The method is based on the large nozzle rocket transport support structure according to any one of claims 1 to 11, and the method comprises: A nozzle end airbag assembly (4) is provided at the end of the inner wall of the engine nozzle (2), and the nozzle end airbag assembly (4) supports and limits the inner wall of the engine nozzle (2) during transportation; A nozzle tail support bracket (5) is provided at the tail end of the engine nozzle (2), and the tail end of the engine nozzle (2) is supported and positioned by the nozzle tail support bracket (5) during transportation.

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