Multi-degree-of-freedom rocket engine hoisting and turning device

Abstract

The application discloses a multi-degree-of-freedom rocket engine hoisting and overturning device and belongs to the technical field of rocket launching preparation. The hoisting and overturning device comprises a connecting assembly and a supporting table. The connecting assembly comprises a first connecting end and a second connecting end. The first connecting end is used for being connected with a hoisting machine. The first connecting end and the second connecting end are used for connecting a rocket engine. The supporting base is used for supporting the rocket engine. The supporting base comprises a chassis frame and a follow-up assembly arranged on the chassis frame and rotationally connected with the chassis frame. The follow-up assembly is provided with a containing groove used for cooperating with the second connecting end. The follow-up assembly can rotate, so that when the hoisting machine overturns the rocket engine, the lateral force applied by the second connecting end to the containing groove can be inhibited or released in the rotation of the follow-up assembly relative to the chassis frame.

Description

Technical Field

[0001] This disclosure generally relates to the field of rocket launch preparation technology, and specifically to a multi-degree-of-freedom rocket engine lifting and tilting device. Background Technology

[0002] With the increasing demand for fast-paced, rapid-response, and multi-mission launches of space rockets, and the continuous increase in launch density, higher requirements are placed on the tilting and erection of rocket engines to facilitate docking of launch vehicles with launch pads.

[0003] Existing methods for erecting rocket engines involve using a hand-operated hoist, which is inefficient, has difficulty adjusting the hoist's lifting length, or uses a fixed end for rotation while the other end is lifted. This can easily exert additional forces on the rocket engine, affecting its normal lifting. Therefore, we propose a multi-degree-of-freedom rocket engine lifting and tilting device to solve these problems. Summary of the Invention

[0004] In view of the above-mentioned defects or deficiencies in the prior art, it is desirable to provide a multi-degree-of-freedom rocket engine lifting and tilting device with a simple structure that can solve the problem of additional force constraints.

[0005] In a first aspect, this application provides a multi-degree-of-freedom rocket engine lifting and tilting device, comprising: The lifting and tilting device includes: A connecting assembly, comprising: a first connecting end and a second connecting end; the first connecting end being used to connect to a crane; the first connecting end and the second connecting end being used to connect to a rocket engine; A support base is provided for supporting the rocket engine. The support base includes a chassis frame and a follower assembly disposed on the chassis frame and rotatably connected in a direction perpendicular to the upper surface of the chassis frame. The follower assembly has a receiving groove for cooperating with the second connection end. When the crane flips the rocket engine, the second connection end applies a lateral force to the receiving slot. Under the action of this lateral force, the follower component rotates relative to the chassis frame to suppress the increase of the lateral force.

[0006] According to the technical solution provided in the embodiments of this application, the follower component includes: a first support portion and a second support portion arranged along a first direction; The first support is mounted on the chassis frame, and its top has an arc-shaped section adapted to the rocket engine; The second support is provided with the receiving groove at its top.

[0007] According to the technical solution provided in the embodiments of this application, the second support includes two sets of support frames arranged along a second direction; the second direction is perpendicular to the first direction; The support frame consists of a main beam and inclined beams on both sides of the main beam; a U-shaped seat is provided on the top of the main beam, and the U-shaped seat forms the receiving groove.

[0008] According to the technical solution provided in the embodiments of this application, the follower component further includes: a first rotating part; The first rotating part is rotatably connected to the chassis frame, and the second supporting part is provided on the first rotating part; the first rotating part is used to drive the second supporting part to rotate.

[0009] According to the technical solution provided in the embodiments of this application, the first rotating part includes: A base plate, on which two sets of support frames are provided; a rotating shaft is provided on the side of the base plate away from the support frames; A positioning rotating seat is disposed on the chassis frame; the positioning rotating seat has a rotating hole corresponding to the rotating shaft; the rotating shaft and the rotating hole are engaged for rotation.

[0010] According to the technical solution provided in the embodiments of this application, the connecting component includes two sets of retaining rings; the two sets of retaining rings respectively form the first connecting end and the second connecting end; Each set of retaining rings includes two arc-shaped engaging sections, which are used to fix the rocket engine body on both sides.

[0011] According to the technical solution provided in the embodiments of this application, universal lifting rings are respectively provided on the two arc-shaped engaging sections used to form the first connecting end, and the universal lifting rings are located on the side of the arc-shaped engaging section away from its own opening; Movable rods are respectively provided on the two arc-shaped engaging sections used to form the second connecting end; the movable rods are used to be disposed in the receiving groove, and the movable rods are located on the side of the arc-shaped engaging section away from its own opening.

[0012] According to the technical solution provided in the embodiments of this application, the arc-shaped engaging sections are all bolted to the rocket engine.

[0013] In summary, this technical solution specifically discloses a multi-degree-of-freedom rocket engine lifting and tilting device, comprising: the lifting and tilting device comprising: A connecting assembly includes: a first connecting end and a second connecting end; the first connecting end is used to connect to a crane; the first connecting end and the second connecting end are used to connect to a rocket engine; a support base is used to support the rocket engine; the support base includes a chassis frame and a follower assembly disposed on the chassis frame and rotatably connected to the chassis frame, the follower assembly having a receiving groove for cooperating with the second connecting end; when the crane flips the rocket engine, the second connecting end applies a lateral force to the receiving groove, under the action of the lateral force, the follower assembly rotates relative to the chassis frame to suppress the increase of the lateral force.

[0014] Existing methods for erecting rocket engines using hand-operated hoists suffer from limitations such as difficulty in adjusting the lifting length or the need to lift one end of the rocket engine while rotating the other, which can easily exert additional forces on the engine. This application addresses these issues by designing a multi-degree-of-automation support platform. The support platform includes a follower component rotatably connected to the chassis frame. During lifting, when the rocket engine's front end is raised, the second connecting end applies a lateral force to the receiving slot. This lateral force is suppressed or eliminated by the rotation of the follower component relative to the chassis frame, preventing tearing of the rocket engine and ensuring its normal rotation. Attached Figure Description

[0015] Other features, objects, and advantages of this application will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the overall structure of a multi-degree-of-freedom rocket engine lifting and tilting device.

[0016] Figure 2 This is an explosion diagram of a multi-degree-of-freedom rocket engine lifting and tilting device.

[0017] Figure 3 This is a schematic diagram of the structure of the second support section in a multi-degree-of-freedom rocket engine lifting and tilting device.

[0018] Figure 4 This is a schematic diagram of the chassis frame structure in a multi-degree-of-freedom rocket engine lifting and tilting device.

[0019] Figure 5 This is a schematic diagram of the flipping operation of a multi-degree-of-freedom rocket engine lifting and flipping device.

[0020] The following numbers are labeled in the diagram: 100, rocket engine; 200, chassis frame; 201, support plate; 300, support frame; 301, main beam; 302, inclined beam; 303, U-shaped seat; 400, base plate; 401, rotating shaft; 402, rotating hole; 500, positioning rotating seat; 600, arc-shaped locking section; 601, universal joint; 602, movable rod. Detailed Implementation

[0021] The present application will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, only the parts relevant to the invention are shown in the accompanying drawings.

[0022] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0023] Example 1 Please refer to Figure 1 The diagram shown in this embodiment illustrates the structure of a multi-degree-of-freedom rocket engine lifting and tilting device, which includes: A connecting assembly, comprising: a first connecting end and a second connecting end; the first connecting end being used to connect to a crane; the first connecting end and the second connecting end being used to connect to a rocket engine 100; A support base is provided for supporting the rocket engine 100. The support base includes a chassis frame 200 and a follower assembly disposed on the chassis frame 200 and rotatably connected in a direction perpendicular to the upper surface of the chassis frame 200. The follower assembly has a receiving groove for cooperating with the second connection end. When the crane flips the rocket engine 100, the second connecting end applies a lateral force to the receiving slot. Under the action of this lateral force, the follower component rotates relative to the chassis frame 200 to suppress the increase of the lateral force.

[0024] The existing methods for erecting rocket engines in the prior art involve using a hand-operated hoist, which is inefficient and makes it difficult to adjust the hoist's lifting length. Alternatively, one end may be fixed while the other end is used for lifting, which can easily generate additional forces on the rocket engine and affect its normal lifting. In contrast, this embodiment cleverly eliminates the additional forces generated on the rocket engine 100 during the lifting process by using a rotatable follower component.

[0025] Specifically, in this embodiment, the connecting component is used to fix the rocket engine 100. At the same time, the connecting component is also the connecting unit between the crane and the rocket engine 100 to realize the lifting of the rocket engine 100. In fact, when the first connecting end and the second connecting end are connected to the rocket engine 100, they are respectively connected to the two ends of the rocket engine 100.

[0026] Specifically, such as Figure 2 As shown, the connecting assembly includes two sets of retaining rings; the two sets of retaining rings respectively form the first connecting end and the second connecting end. When connected to the rocket engine 100, the two sets of retaining rings are respectively disposed at both ends of the rocket engine 100. The one located at the front end of the rocket engine 100 can also be called the front lifting ring, corresponding to the first connecting end in this invention; the one located at the rear end of the rocket engine 100 can also be called the rear lifting ring, corresponding to the second connecting end in this application.

[0027] Furthermore, each set of retaining rings includes two arc-shaped engaging sections 600, which are used to fix the rocket engine 100 to both sides of the body. At the same time, each arc-shaped engaging section 600 is connected to the side of the rocket engine 100 by bolts. Multiple bolt connection holes are distributed on the arc-shaped engaging section 600, and the bolts are connected to the rocket engine 100 through these bolt connection holes.

[0028] Among them, two arc-shaped engaging sections 600 used to form the first connecting end are respectively provided with universal lifting rings 601. The universal lifting rings 601 are located on the side of the arc-shaped engaging section 600 away from its own opening, and the universal lifting rings 601 are used to connect with the crane.

[0029] The two arc-shaped engaging sections 600 used to form the second connecting end are respectively provided with movable rods 602; the movable rods 602 are used to be disposed in the receiving groove, and the movable rods 602 are located on the side of the arc-shaped engaging section 600 away from its own opening.

[0030] In layman's terms, the curved part of the arc-shaped locking section 600 is adapted to the shape of the rocket engine 100. When the arc-shaped locking section 600 is connected to the rocket engine 100 by bolts, the universal joint 601 and the movable rod 602 are both located outside the arc-shaped locking section 600. Therefore, the curved part of the arc-shaped locking section 600 needs to be adjusted according to the shape of the rocket engine 100 in the actual scenario. No special restrictions are imposed here.

[0031] In practical application scenarios, when the crane controls the rocket engine 100 to rotate, the universal lifting ring 7 is connected through the crane or other lifting tools. As the lifting progresses, the front end of the rocket engine 100 rises, and the movable rod 602 at the rear lifting ring becomes the point of force and rotates around the axis of the movable rod 602. The movable rod 602 will then apply a certain lateral force to the receiving groove. The lifting force is prone to tilting, which will affect the rotation of the rocket engine 100.

[0032] like Figure 5 As shown, in order to eliminate the aforementioned additional lateral force, a rotatable follower component is provided on the chassis frame 200 in the support base. The lateral force is eliminated by the multi-degree-of-freedom rotation of the follower component.

[0033] Specifically, the follower component includes: a first support portion and a second support portion arranged along a first direction; the first direction here refers to the horizontal direction, which can also be understood as the length direction of the rocket engine 100, and the first support portion and the second support portion are located at both ends of the rocket engine 100 respectively.

[0034] The first support is mounted on the chassis frame 200, and its top has an arc-shaped section adapted to the rocket engine 100. The first support can be a support plate 201, the top of which is designed with an arc-shaped section matching the shape of the rocket engine 100 to support the rocket engine 100. For example... Figure 4 and Figure 2 As shown, the chassis frame 200 is a rectangular frame, and there are multiple reinforcing beams inside the rectangular frame. The reinforcing beams divide the rectangular frame into multiple directional blocks, which facilitates assembly. At the same time, the reinforcing beams also serve to support the follower components.

[0035] The second support portion is correspondingly provided with the second connecting end, and the movable rod 602 in the second connecting end is located in the receiving groove provided at the top of the second support portion.

[0036] like Figure 3 As shown, the structure of the second support includes: Two sets of support frames 300 are arranged along a second direction; the second direction is perpendicular to the first direction, that is, located on both sides of the rocket engine 100, and corresponding to the two movable rods 602.

[0037] The support frame 300 consists of a main beam 301 and inclined beams 302 that are inclined on both sides of the main beam 301. The inclined beams 302 and the surface of the chassis frame 200 form a triangular support structure to improve stability. The main beam is set perpendicular to the chassis frame 200. The three together form a stable support frame 300. In terms of manufacturing process, the main beam 301 and the inclined beams 302 can be obtained by welding.

[0038] A U-shaped seat 303 is provided on the top of the main beam 301. The structure of the U-shaped seat 303 is essentially the receiving groove. The two movable rods 602 are respectively locked in the corresponding U-shaped seats 303, forming rotational freedom. The U-shaped seat 303 has a gentle curvature inside, which can make the movable rods 602 and the U-shaped seat 303 cooperate more smoothly. In terms of manufacturing process, the U-shaped seat 303 can also be connected to the main beam 301 by welding.

[0039] like Figure 4 and Figure 2 As shown, in conjunction with the rotation of the aforementioned follower component, the follower component further includes a first rotating part, which is the key to driving the follower component to rotate.

[0040] Specifically, the first rotating part is rotatably connected to the chassis frame 200, and the first rotating part is provided with the second support part. When the second support part is subjected to the force from the movable rod 602, the first rotating part will rotate under the force to suppress the growth of the lateral force and release it, so as to prevent the rocket engine 100 from being torn due to the tilt caused by the hoisting force (similar to jamming the rear end of the rocket engine 100).

[0041] Specifically, the first rotating part for driving the second support part to rotate includes: A base plate 400 is provided with two sets of support frames 300; a rotating shaft 401 is provided on the side of the base plate 400 away from the support frames 300; the rotating shaft 401 is located in the middle of the base plate 400. A positioning rotating seat 500 is welded to the chassis frame 200. The positioning rotating seat 500 has a rotating hole 402 corresponding to the rotating shaft 401. The rotating shaft 401 and the rotating hole 402 are in a shaft-hole fit for rotation. The rotation of the second support is achieved through the fit between the rotating shaft 401 and the rotating hole 402. Specifically, the positioning rotating seat 500 is made of Q235A material, and its rotating hole 402 is used to mate with the rotating shaft 401, with a certain gap between them, allowing for rotational freedom. It should be noted that this invention does not use an overly complex rotating structure to achieve the rotation of the second support, resulting in significant cost savings.

[0042] In summary, the specific working principle of this invention is as follows: When the rocket engine 100 is flipped, the universal lifting ring 601 is connected to the crane or other lifting equipment. As the lifting proceeds, the front end of the rocket engine 100 rises and rotates upward around the movable rod 602 and the U-shaped seat 303 at the top of the main beam 301. When lateral forces occur or the lifting force is skewed, the rotating shaft 401 under the base plate 400 can rotate around the positioning rotating seat 500 to prevent improper lifting operations from causing additional forces on the engine. When the rocket engine 100 is flipped to a vertical position, the rear end of the rocket engine 100 will detach from the U-shaped seat 303 under the control of the crane. At this time, the arc-shaped locking section 600 used to fix the rear end of the engine is no longer subjected to the force applied by the engine. The arc-shaped locking section 600 at the rear end can then be manually removed. At this time, the force on the rear lifting ring and the engine connecting bolts is very small, making the operation convenient.

[0043] The above description is merely a preferred embodiment of this application and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of the invention involved in this application is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the inventive concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features with similar functions disclosed in this application.

Claims

1. A multi-degree-of-freedom rocket engine lifting and tilting device, characterized in that, The lifting and tilting device includes: A connecting assembly, comprising: a first connecting end and a second connecting end; the first connecting end being used to connect to a crane; the first connecting end and the second connecting end being used to connect to a rocket engine (100). A support base for supporting the rocket engine (100); the support base includes a chassis frame (200) and a follower assembly disposed on the chassis frame (200) and rotatably connected in a direction perpendicular to the upper surface of the chassis frame (200), the follower assembly having a receiving groove for cooperating with the second connection end; The follower component includes: a first support portion and a second support portion arranged along a first direction; The first support is disposed on the chassis frame (200), and its top is provided with an arc-shaped section adapted to the rocket engine (100) for supporting the rocket engine; The receiving groove is provided at the top of the second support portion; The second support includes two sets of support frames (300) arranged along a second direction; the second direction is perpendicular to the first direction; The support frame (300) is composed of a main beam (301) and inclined beams (302) on both sides of the main beam (301); a U-shaped seat (303) is provided on the top of the main beam (301), the U-shaped seat (303) forms a receiving groove for cooperating with the second connecting end, and the second connecting end has a degree of rotational freedom; The follower component further includes: a first rotating part; The first rotating part is rotatably connected to the chassis frame (200), and the second supporting part is provided on the first rotating part; the first rotating part is used to drive the second supporting part to rotate; When the crane flips the rocket engine (100) and the front end of the rocket engine (100) is lifted, the second connecting end rotates in the U-shaped seat (303); when a lateral force occurs and the lifting force applied by the crane is deflected, the second connecting end will apply a lateral force to the receiving groove. Under the action of this lateral force, the first rotating part drives the second supporting part to rotate relative to the chassis frame (200) to suppress the growth of the lateral force.

2. The multi-degree-of-freedom rocket engine lifting and tilting device according to claim 1, characterized in that, The first rotating part includes: a base plate (400), on which two sets of support frames (300) are provided; a rotating shaft (401) is provided on the side of the base plate (400) away from the support frames (300). A positioning rotating seat (500) is disposed on the chassis frame (200); the positioning rotating seat (500) is provided with a rotating hole (402) corresponding to the rotating shaft (401); the rotating shaft (401) and the rotating hole (402) are rotated by a shaft-hole fit.

3. The multi-degree-of-freedom rocket engine lifting and tilting device according to claim 1, characterized in that... The characteristic is that the connecting component includes two sets of retaining rings; the two sets of retaining rings respectively form the first connecting end and the second connecting end; Each set of retaining rings includes two arc-shaped engaging sections (600) for securing the rocket engine (100) to both sides of its body.

4. The multi-degree-of-freedom rocket engine lifting and tilting device according to claim 3, characterized in that, Universal joints (601) are respectively provided on the two arc-shaped engaging sections (600) used to form the first connecting end. The universal joints (601) are located on the side of the arc-shaped engaging section (600) away from its own opening. Movable rods (602) are respectively provided on the two arc-shaped engaging sections (600) used to form the second connecting end; the movable rods (602) are provided in the receiving groove, and the movable rods (602) are located on the side of the arc-shaped engaging section (600) away from its own opening.

5. A multi-degree-of-freedom rocket engine lifting and tilting device according to claim 3, characterized in that, The arc-shaped engaging sections (600) are all bolted to the rocket engine (100).

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