Fixing device for rocket

Abstract

The invention discloses a fixing device for a rocket, and relates to the technical field of spaceflight launching equipment, and the device comprises a bearing mechanism which is provided with an embracing clamp assembly and an embracing clamp adjusting assembly for driving the embracing clamp assembly to act; the holding clamp assembly comprises two holding clamp main bodies, each holding clamp main body is provided with a connecting section and a clamping section, the holding clamp adjusting assembly comprises a first mounting seat, a second mounting seat and a limiting seat which are mounted on the bearing mechanism, a driving part is arranged on the first mounting seat, a driving screw rod is rotationally connected between the second mounting seat and the limiting seat, and a driving shaft of the driving part is connected with the driving screw rod; the driving lead screw is provided with a first lead screw section and a second lead screw section which are oppositely arranged in a threaded mode, the driving lead screw is driven by the driving piece to rotate, so that the first driving nut and the second driving nut move along the driving lead screw, then the two holding clamp bodies are driven to rotate relative to the bearing mechanism, and the two clamping sections are matched to clamp or loosen a rocket to be fixed. And the operation process is simple and efficient.

Description

Technical Field

[0001] This application generally relates to the technical field of space launch equipment, and specifically relates to a fixing device for a rocket. Background Art

[0002] In the modern space launch process, the installation, fixing, and adjustment of the rocket are important links before launch. Traditional rocket support devices usually adopt a rigid structure, which is difficult to meet the diverse needs of different types of rockets. In addition, during the transfer and installation of the rocket, the attitude of the rocket needs to be precisely adjusted to ensure its alignment accuracy with the launch tower.

[0003] The two clamping structures of the existing clamping mechanism are respectively equipped with drive sources, and most of the drive sources are electric cylinders or hydraulic cylinders, resulting in complex control and low efficiency of the pre-launch preparation work. Therefore, we propose a fixing device for a rocket to solve the above 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 fixing device for a rocket that meets the requirements of low-cost, simple operation, and highly reliable launch in the space field.

[0005] This application provides a fixing device for a rocket, including: A bearing mechanism, on which a clamping component and a clamping adjustment component for driving the clamping component to act are installed; The clamping component includes: two cooperating clamping main bodies, the clamping main body has a connecting section and a clamping section, and an accommodating space is formed between the clamping sections of the two clamping main bodies for placing the rocket to be fixed; The clamping adjustment component includes: a first mounting seat, a second mounting seat, and a limit seat installed on the bearing mechanism, a driving member is provided on the first mounting seat, a driving lead screw is rotatably connected between the second mounting seat and the limit seat, and a driving shaft of the driving member is connected to the driving lead screw; the driving lead screw has a first lead screw section and a second lead screw section with opposite threads, the first lead screw section is threadedly connected to a first driving nut, the second lead screw section is threadedly connected to a second driving nut, a first pin is provided on the first driving nut and is rotatably connected to the connecting section of one of the clamping main bodies, and a second pin is provided on the second driving nut and is rotatably connected to the connecting section of the other clamping main body; By driving the driving lead screw to rotate through the driving member, the first driving nut and the second driving nut move along the driving lead screw, thereby driving the two clamping main bodies to rotate relative to the bearing mechanism, so that the two clamping sections cooperate to clamp or loosen the rocket to be fixed.

[0006] According to the technical solution provided by the embodiment of this application, the bearing mechanism includes: Adjusting structure, a support assembly is provided on the adjusting structure, the support assembly includes a support body, the interior of the support body is hollow to form an installation space for installing the gripper adjusting assembly; the adjusting structure is used to drive the support assembly to move along a first direction and a second direction; the first direction and the second direction are perpendicularly arranged, the first direction is perpendicular to the bottom surface of the support body, and the second direction is parallel to the length direction of the driving lead screw.

[0007] According to the technical solution provided by the embodiment of the present application, the adjusting structure includes: A lateral movement adjusting assembly, the lateral movement adjusting assembly includes: a bearing seat, a lead screw support seat and a lead screw clamping seat are provided on the bearing seat, and the two are distributed along the second direction; a lateral movement lead screw is rotatably connected between the lead screw support seat and the lead screw clamping seat, and a lateral movement nut slidably connected to the bearing seat is threadedly connected to the lateral movement lead screw; the upper surface of the lateral movement nut is connected to the lifting adjusting assembly, and the lifting adjusting assembly is used to drive the support assembly to move along the first direction; By rotating the lateral movement lead screw, the lifting adjusting assembly is driven to move along the second direction.

[0008] According to the technical solution provided by the embodiment of the present application, the lateral movement adjusting assembly further includes: Two guide rails, which are arranged on the bearing seat and are respectively located on both sides of the lateral movement lead screw; the extending direction of the guide rails is parallel to the length direction of the driving lead screw; a plurality of sliders are provided on each guide rail, and the sliders are connected to the bottom of the lifting adjusting assembly; When the lateral movement lead screw rotates, the sliders move synchronously with the lifting adjusting assembly.

[0009] According to the technical solution provided by the embodiment of the present application, the lifting adjusting assembly includes: A support base, the support base is connected to the sliders and the lateral movement nut; a T-shaped commutator and a cross commutator are provided on the support base; the T-shaped commutator has a first connecting shaft, a second connecting shaft and a third connecting shaft; the cross commutator has a fourth connecting shaft, a fifth connecting shaft, a sixth connecting shaft and a seventh connecting shaft; the first connecting shaft is connected to the fourth connecting shaft through an intermediate connecting shaft; the fifth connecting shaft is connected to the transmission shaft of the power source; Four elevators, the driving ends of the elevators are connected to the support body; the driving shafts of the four elevators are respectively connected to the second connecting shaft, the third connecting shaft, the sixth connecting shaft and the seventh connecting shaft; The driving force generated by the power source is synchronously transmitted to each elevator through the T-shaped commutator and the cross commutator, so that the support assembly moves along the first direction.

[0010] According to the technical solution provided by the embodiment of the present application, the power source includes a speed reducer, and a first handwheel is provided at the end of the extension shaft of the speed reducer; a second handwheel is provided at the end of the transverse movement lead screw.

[0011] According to the technical solution provided by the embodiment of the present application, the support assembly further includes: at least two buffers, which are arranged on the side wall of the support body and are used to buffer the impact force borne by the adjacent gripper body.

[0012] According to the technical solution provided by the embodiment of the present application, a bearing is provided at the connecting section of the gripper body, an installation hole is formed in the support body, and the bearing is connected to the installation hole through a rotating pin shaft.

[0013] According to the technical solution provided by the embodiment of the present application, a bearing seat is provided on the support body, and the bearing seat is rotatably connected to the middle position of the driving lead screw.

[0014] According to the technical solution provided by the embodiment of the present application, an avoidance groove is formed in the support body at a position corresponding to the accommodation space.

[0015] It can be seen from the above technical solutions that the present application has at least the following beneficial effects: The present application provides a fixing device for a rocket, which includes: a bearing mechanism, on which a gripper assembly and a gripper adjustment assembly for driving the gripper assembly to act are installed; the gripper assembly includes: two cooperating gripper bodies, the gripper body has a connecting section and a clamping section, and an accommodation space is formed between the clamping sections of the two gripper bodies for placing the rocket to be fixed; the gripper adjustment assembly includes: a first mounting seat, a second mounting seat and a limit seat installed on the bearing mechanism, a driving member is provided on the first mounting seat, a driving lead screw is rotatably connected between the second mounting seat and the limit seat, and the driving shaft of the driving member is connected to the driving lead screw through a coupling; the driving lead screw has a first lead screw section and a second lead screw section with opposite threads, the first lead screw section is threadedly connected to a first driving nut, the second lead screw section is threadedly connected to a second driving nut, a first pin is provided on the first driving nut and is rotatably connected to the connecting section of one gripper body, a second pin is provided on the second driving nut and is rotatably connected to the connecting section of the other gripper body; by driving the driving lead screw to rotate through the driving member, the first driving nut and the second driving nut move along the driving lead screw, and then drive the two gripper bodies to rotate relative to the bearing mechanism, so that the two clamping sections cooperate to clamp or loosen the rocket to be fixed.

[0016] In this application, a clamping pliers assembly and a clamping pliers adjusting assembly are designed on a bearing mechanism. The driving member of the clamping pliers adjusting assembly drives the driving lead screw to rotate, thereby controlling the synchronous rotation of the two clamping pliers bodies, so as to clamp or release the rocket, making the operation process simple and efficient, greatly shortening the time for rocket fixing and releasing, and improving the working efficiency of the launch site. Description of the Drawings

[0017] Other features, objectives, and advantages of this application will become more apparent by reading the detailed description of the non-limiting embodiments with reference to the following drawings.

[0018] Figure 1 Structural schematic diagram of the fixing device for the rocket.

[0019] Figure 2 Structural schematic diagram of the clamping pliers assembly.

[0020] Figure 3 Structural schematic diagram of the support assembly.

[0021] Figure 4 Structural schematic diagram of the lifting adjustment assembly.

[0022] Figure 5 Structural schematic diagram of the transverse movement adjustment assembly.

[0023] Figure 6 Structural schematic diagram of the clamping pliers adjusting assembly.

[0024] Figure 7 Schematic diagram of the rocket fixing device in the state where the clamping pliers are loosened.

[0025] Figure 8 Schematic diagram of the rocket fixing device in the state where the clamping pliers are clamped.

[0026] Reference numerals in the figures: 1, clamping pliers assembly; 2, support assembly; 3, lifting adjustment assembly; 4, transverse movement adjustment assembly; 5, clamping pliers adjusting assembly; 101, clamping pliers body; 102, bearing; 103, rotating pin shaft; 201, support body; 202, buffer; 301, elevator; 302, first handwheel; 303, reducer; 304, intermediate connecting shaft; 305, T-shaped commutator; 306, cross commutator; 307, support base; 401, bearing seat; 402, guide rail; 403, slider; 404, lead screw support seat; 405, transverse movement lead screw nut; 406, transverse movement lead screw; 407, lead screw clamping seat; 408, second handwheel; 501, driving member; 502, first mounting seat; 503, second mounting seat; 504, first driving nut; 505, bearing block; 506, driving lead screw; 507, second driving nut; 508, limit seat. Detailed Description of the Embodiment

[0027] The present application will be further described in detail below with reference to the accompanying drawings and embodiments. It can be understood that the specific embodiments described herein are only used to explain the related invention, rather than limiting the invention. In addition, it should be noted that, for the sake of convenience of description, only the parts related to the invention are shown in the drawings.

[0028] It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the drawings and embodiments.

[0029] In order to make the fixing device for a rocket provided by the embodiments of the present application clearer and easier to understand, the device will be introduced below with reference to the accompanying drawings. As Figure 1 shown, this figure is a schematic structural diagram of the fixing device for a rocket provided by the embodiments of the present application. The device includes: a bearing mechanism, on which a clamp assembly 1 and a clamp adjusting assembly 5 for driving the clamp assembly 1 to act are installed; The clamp assembly 1 includes: two cooperating clamp bodies 101. The clamp body 101 has a connecting section and a clamping section. An accommodating space is formed between the clamping sections of the two clamp bodies 101 for placing the rocket to be fixed; The clamp adjusting assembly 5 includes: a first mounting seat 502, a second mounting seat 503 and a limit seat 508 installed on the bearing mechanism. A driving member 501 is provided on the first mounting seat 502. A driving lead screw 506 is rotatably connected between the second mounting seat 503 and the limit seat 508. The driving shaft of the driving member 501 is connected to the driving lead screw 506 through a coupling; the driving lead screw 506 has a first lead screw section and a second lead screw section with opposite threads. The first lead screw section is threadedly connected to a first driving nut 504, and the second lead screw section is threadedly connected to a second driving nut 507. A first pin is provided on the first driving nut 504, which is rotatably connected to the connecting section of one clamp body 101. A second pin is provided on the second driving nut 507, which is rotatably connected to the connecting section of the other clamp body 101; By driving the driving member 501 to drive the driving lead screw 506 to rotate, the first driving nut 504 and the second driving nut 507 move along the driving lead screw 506, thereby driving the two clamp bodies 101 to rotate relative to the bearing mechanism, so that the two clamping sections cooperate to clamp or loosen the rocket to be fixed.

[0030] It should be noted that the bearing mechanism provides an installation and support platform for the clamping pliers assembly 1 and the clamping pliers adjustment assembly 5, enabling the stable operation of the entire device. The clamping pliers assembly 1 is used for clamping the rocket to be fixed, and the clamping pliers adjustment assembly 5 is used to control the action of the clamping pliers assembly 1 to achieve the clamping and loosening of the rocket. Here, the clamping pliers body 101 is formed by cutting a plate with a specific thickness and then welding it together. Reinforcing ribs are welded inside the cavity, and the arc surface is machined. The formed clamping pliers body 101 not only ensures the overall rigidity and strength but also better fits the rocket. The clamping sections of the two clamping pliers bodies 101 are arranged oppositely, and the accommodating space formed between them is used to place the rocket to be fixed. The clamping and loosening actions of the rocket are achieved by controlling the rotation of the clamping pliers body 101.

[0031] The first mounting seat 502 is used to mount the driving member 501, and the driving member 501 is used to provide driving force. Here, the driving member is, for example, a driving motor. There is a driving lead screw 506 rotatably connected between the second mounting seat 503 and the limit seat 508. The driving shaft of the driving member 501 is connected to the driving lead screw 506 through a coupling, so that the rotation of the driving member 501 can be transmitted to the driving lead screw 506.

[0032] The driving lead screw 506 has a first lead screw section and a second lead screw section with opposite threads, which are respectively threadedly connected to the first driving nut 504 and the second driving nut 507. When the driving member 501 drives the driving lead screw 506 to rotate, due to the effect of the threads, the first driving nut 504 and the second driving nut 507 will move in opposite directions along the driving lead screw 506. The first pin on the first driving nut 504 is rotatably connected to the connecting section of one clamping pliers body 101, and the second pin on the second driving nut 507 is rotatably connected to the connecting section of the other clamping pliers body 101. As the two driving nuts move, they will drive the two clamping pliers bodies 101 to rotate relative to the bearing mechanism respectively. When the two clamping pliers bodies 101 rotate towards each other, the two clamping sections gradually approach, and finally cooperate to clamp the rocket to be fixed. On the contrary, when the two clamping pliers bodies 101 rotate away from each other, the two clamping sections gradually separate to achieve the operation of loosening the rocket. Here, the threads of the first lead screw section and the second lead screw section are positive and reverse trapezoidal threads, which can ensure the self-locking of the first driving nut 504 and the second driving nut 507 at any position, making the clamping force of the two clamping sections stable and ensuring that the rocket does not shift or loosen during the erection process.

[0033] It should be noted that a reserved notch extending along the length direction is provided at the bottom of the clamp body 101. When the corresponding nut (the first driving nut 504 / the second driving nut 507) moves in the horizontal direction, the corresponding pin (the first pin / the second pin) thereon acts on the clamp body 101. On the one hand, it will cause the clamp body 101 to rotate relative to the pin, and on the other hand, it will cause the position of the pin relative to the reserved notch to change. Among them, the middle part of the clamp body 101 is hinged to the bearing mechanism, and the clamp body 101 rotates around the hinge.

[0034] Furthermore, as Figure 3 shown, the bearing mechanism includes: An adjusting structure, on which a support assembly 2 is provided. The support assembly 2 includes a support body 201, and a hollow installation space is formed inside the support body 201 for installing the clamp adjusting assembly 5; the adjusting structure is used to drive the support assembly 2 to move in a first direction and a second direction; the first direction and the second direction are perpendicularly arranged, the first direction is perpendicularly arranged with the bottom surface of the support body 201, and the second direction is parallel to the length direction of the driving lead screw 506.

[0035] It should be noted that the adjusting structure is the core structure for realizing the position and attitude adjustment of the rocket. Through the coordinated work with the support assembly 2 and other related components, the adjusting structure can finely adjust the rocket in different directions. In the actual space launch scenario, the installation accuracy requirements of the rocket are extremely high. The adjusting structure can ensure that the rocket always maintains the correct position and attitude during fixation and transportation, providing strong guarantee for the subsequent launch work.

[0036] As Figure 3 shown, the support body 201 includes a bottom plate and a plurality of side plates arranged on the bottom plate, and an arc-shaped top plate is provided on the side of the side plate away from the bottom plate. The arc surface of the arc-shaped top plate can be fitted with the arc surface of the rocket to be fixed. The space for installing the clamp adjusting assembly 5 is enclosed by these plates, which not only saves the overall space of the device, but also enables the clamp adjusting assembly 5 to be closely combined with the support assembly 2, improving the structural compactness and stability of the whole device. In addition, the surface of the support body 201 is usually subjected to special treatment, such as being processed into an arc surface that fits the shape of the rocket, so as to better support the rocket, reduce local stress concentration, and ensure the safety and stability of the rocket during the fixation process.

[0037] In addition, as Figure 3 shown, the support assembly 2 further includes: at least two buffers 202, and the buffers 202 are arranged on the side wall of the support body 201 for buffering the impact force borne by the adjacent clamp body 101.

[0038] Among them, when the clamping tongs assembly 1 clamps or releases the rocket, a large impact force will be generated. If not buffered, these impact forces will act concentratedly on the connection part between the clamping tongs main body 101 and the support main body 201, which may cause component damage or affect the stability of the rocket. Installing the buffer 202 on the side wall of the support main body 201, that is, on the side plate forming the support main body 201, can directly and effectively receive the impact force transmitted from the clamping tongs main body 101. For example, buffers 202 are respectively arranged on both sides of the support main body 201, which can evenly disperse the impact force generated when the clamping tongs main body 101 acts, and avoid the impact force of the clamping tongs assembly 1 acting directly on the rocket, causing damage to the rocket surface. Here, the buffer 202 is generally made of an elastic material or a mechanical structure with a buffering function. For example, it is a rubber buffer, a spring buffer, etc.

[0039] In addition, an avoidance groove is opened at the position of the support main body 201 corresponding to the accommodation space. The avoidance groove is located in the central area of the bottom plate of the support main body 201, and its purpose is to avoid interference with the rocket to be fixed placed between the two clamping sections of the clamping tongs assembly 1. During the installation and fixation of the rocket, the external dimensions and structure of the rocket are key factors to be considered when designing the device. Different models of rockets have different shapes and protruding parts, and the design of the avoidance groove can be customized according to the actual shape of the rocket to ensure that when the clamping tongs main body 101 clamps the rocket, the support main body 201 will not collide or squeeze with any part of the rocket, ensuring the integrity and safety of the rocket.

[0040] Furthermore, as Figure 5 shown, the adjustment structure includes: A transverse movement adjustment assembly 4, which includes: a carrier seat 401, on which a lead screw support seat 404 and a lead screw clamping seat 407 are provided, and the two are distributed along the second direction; a transverse movement lead screw 406 is rotatably connected between the lead screw support seat 404 and the lead screw clamping seat 407, and a transverse movement nut 405 slidably connected to the carrier seat 401 is threadedly connected to the transverse movement lead screw 406; the upper surface of the transverse movement nut 405 is connected to the lifting adjustment assembly 3, and the lifting adjustment assembly 3 is used to drive the support assembly 2 to move along the first direction; By rotating the transverse movement lead screw 406, the lifting adjustment assembly 3 is driven to move along the second direction.

[0041] It should be noted that the transverse movement adjustment assembly 4 is mainly used to realize the position adjustment of the rocket in the horizontal direction (i.e., the second direction). It works in coordination with the lifting adjustment assembly 3 to enable the rocket to be accurately positioned in three-dimensional space. The transverse movement adjustment assembly 4 is based on the carrier seat 401. Through the cooperation of the transverse movement lead screw 406 and the transverse movement nut 405, the rotation of the transverse movement lead screw 406 is converted into the linear movement of the transverse movement nut 405, thereby driving the lifting adjustment assembly 3 and the rocket to move.

[0042] The carrier seat 401 is the basic component of the transverse movement adjustment assembly 4, which provides a support platform for the sliding of the lead screw support seat 404, the lead screw clamping seat 407, and the transverse movement nut 405. The carrier seat 401 needs to have sufficient strength and stability to withstand the forces generated during the entire adjustment process. The lead screw support seat 404 and the lead screw clamping seat 407 are distributed on the carrier seat 401 along the length direction of the driving lead screw 506. Their main functions are to support and fix the transverse movement lead screw 406 so that it can rotate stably. The lead screw support seat 404 is used to provide a rotatable support point that allows the transverse movement lead screw 406 to rotate freely therein; the lead screw clamping seat 407 further fixes the transverse movement lead screw 406 to prevent axial displacement of the transverse movement lead screw 406 during rotation. The transverse movement lead screw 406 is the core transmission component of the transverse movement adjustment assembly 4, and it is rotatably connected between the lead screw support seat 404 and the lead screw clamping seat 407. The transverse movement lead screw 406 is machined with threads, which cooperate with the transverse movement nut 405. When the transverse movement lead screw 406 rotates, due to the effect of the threads, it will drive the transverse movement nut 405 to move along the axial direction of the lead screw. The transverse movement nut 405 is threadedly connected to the transverse movement lead screw 406 and is also slidably connected to the carrier seat 401, that is: the transverse movement nut 405 can only slide along a specific track of the carrier seat 401. When the transverse movement lead screw 406 rotates, the transverse movement nut 405 will convert the rotational movement of the lead screw into its own linear movement. The upper surface of the transverse movement nut 405 is connected to the lifting adjustment assembly 3, so its movement will drive the lifting adjustment assembly 3 and the rocket to be fixed clamped at the clamp body 101 to move together. The lifting adjustment assembly 3 is connected to the transverse movement nut 405. The lifting adjustment assembly 3 is used to drive the support assembly 2 to move in the first direction, that is, to realize the lifting movement of the rocket.

[0043] By rotating the transverse movement lead screw 406, the transverse movement nut 405 will move along the axial direction of the transverse movement lead screw 406. Since the transverse movement nut 405 is connected to the lifting adjustment assembly 3, it will drive the lifting adjustment assembly 3 to move in the second direction, thereby realizing the position adjustment of the rocket in the horizontal direction.

[0044] Further, as Figure 5 shown, the transverse movement adjustment assembly 4 further includes: Two guide rails 402, which are arranged on the carrier seat 401 and are located on both sides of the transverse movement lead screw 406 respectively; the extending direction of the guide rails 402 is parallel to the length direction of the driving lead screw 506; a plurality of sliders 403 are provided on each guide rail 402, and the sliders 403 are connected to the bottom of the lifting adjustment assembly 3; When the transverse movement lead screw 406 rotates, the sliders 403 move synchronously with the lifting adjustment assembly 3.

[0045] It should be noted that the two guide rails 402 in the lateral movement adjustment assembly 4 are installed on the bearing seat 401 and are respectively located on both sides of the lateral movement lead screw 406, making the force on the lateral movement lead screw 406 more uniform during the transmission process. The extending direction of the guide rail 402 is parallel to the length direction of the driving lead screw 506, ensuring that the movement direction of the slider 403 is consistent with the axial movement direction of the lateral movement lead screw 406, providing a reliable guide for the precise lateral movement of the lifting adjustment assembly 3 and the rocket. A plurality of sliders 403 are arranged on each guide rail 402 and are connected to the bottom of the lifting adjustment assembly 3. The plurality of sliders 403 can evenly distribute the weight of the lifting adjustment assembly 3, improving the stability of the entire device.

[0046] Moreover, the number of sliders 403 on each guide rail 402 is at least three and they are evenly distributed on the corresponding guide rail 402. These sliders 403 can disperse the weight of the lifting adjustment assembly 3 and the rocket clamped at the clamp body 101 onto the guide rail 402, reducing the force on a single support point and improving the load-bearing capacity of the entire support structure. The sliding fit between the slider 403 and the guide rail 402 enables the lifting adjustment assembly 3 to move more smoothly during the lateral movement, reducing shaking and vibration, and further improving the stability of the rocket's lateral movement.

[0047] Furthermore, as Figure 4 shown, the lifting adjustment assembly 3 includes: A support base 307, which is connected to the slider 403 and the lateral movement nut 405; a T-shaped commutator 305 and a cross commutator 306 are provided on the support base 307; the T-shaped commutator 305 has a first connecting shaft, a second connecting shaft, and a third connecting shaft; the cross commutator 306 has a fourth connecting shaft, a fifth connecting shaft, a sixth connecting shaft, and a seventh connecting shaft; the first connecting shaft is connected to the fourth connecting shaft through an intermediate connecting shaft 304; the fifth connecting shaft is connected to the transmission shaft of the power source; Four elevators 301, the driving ends of the elevators 301 are connected to the support body 201; the driving shafts of the four elevators 301 are respectively connected to the second connecting shaft, the third connecting shaft, the sixth connecting shaft, and the seventh connecting shaft; The driving force generated by the power source is synchronously transmitted to each elevator 301 via the T-shaped commutator 305 and the cross commutator 306, causing the support assembly 2 to move in the first direction.

[0048] It should be noted that the support base 307 is the basic structure of the lifting adjustment assembly 3. It is connected to the slider 403 and the transverse movement nut 405, enabling the lifting adjustment assembly 3 to perform transverse movement following the action of the transverse movement adjustment assembly 4. A T-shaped commutator 305 and a cross commutator 306 are provided on the support base 307. These two commutators are key components for force and motion transmission. The first connecting shaft of the T-shaped commutator 305 is connected to the fourth connecting shaft of the cross commutator 306 through the intermediate connecting shaft 304, realizing the power transmission between the two commutators. The fifth connecting shaft of the cross commutator 306 is connected to the transmission shaft of the power source, capable of introducing the driving force generated by the power source into the entire lifting adjustment assembly 3.

[0049] The four elevators 301 are the direct actuating components for realizing the lifting movement of the rocket. The top wall of the elevator 301 is connected to the support main body 201, and the support main body 201 is associated with the clamping pliers assembly 1. Therefore, the lifting action of the elevator 301 can directly drive the rocket to be fixed clamped at the clamping pliers main body 101 to move up and down. The drive shafts of the four elevators 301 are respectively connected to the second connecting shaft, the third connecting shaft of the T-shaped commutator 305, and the sixth connecting shaft, the seventh connecting shaft of the cross commutator 306. When the power source generates a driving force, this driving force is transmitted to the four elevators 301 through the cross commutator 306 and the T-shaped commutator 305, enabling them to act synchronously and ensuring the smoothness of the rocket during the lifting process. Here, the adjustable height range of the lifting adjustment assembly 3 is 0 - 400 mm.

[0050] During actual operation, when the power source is started, the generated driving force is first transmitted to the cross commutator 306. The cross commutator 306 distributes the power to each shaft connected to it. Part of the power is transmitted to the first connecting shaft of the T-shaped commutator 305 through the fourth connecting shaft and the intermediate connecting shaft 304. The T-shaped commutator 305 further distributes the power to the second connecting shaft and the third connecting shaft. At the same time, the cross commutator 306 also directly transmits the power to the sixth connecting shaft and the seventh connecting shaft. These powers respectively drive the drive shafts of the four elevators 301 to rotate, and then the lifting mechanisms of the elevators 301 act, driving the support main body 201, the clamping pliers main body 101, and the rocket to move together in the first direction (the direction perpendicular to the upper surface of the bearing seat 401).

[0051] During the erection preparation process before rocket launch, it is necessary to precisely adjust the horizontal height of the rocket to ensure the precise docking of the rocket with equipment such as the launch tower after erection. The lifting adjustment assembly 3 can achieve stable and precise lifting adjustment, meeting the height adjustment requirements of the rocket in different working scenarios. The synchronous transmission structure of the lifting adjustment assembly 3 ensures the smoothness of the rocket during the lifting process, avoiding the risk of the rocket tilting or being damaged due to uneven lifting, and providing a strong guarantee for the safe launch of the rocket.

[0052] In addition, the power source includes a speed reducer 303, and a first handwheel 302 is provided at the end of the extension shaft of the speed reducer 303; a second handwheel 408 is provided at the end of the transverse movement lead screw 406.

[0053] It should be noted that the first handwheel 302 and the second handwheel 408 are used to provide manual adjustment for the operator. In actual operation, when the position of the rocket needs to be adjusted, the operator can control the operation of the speed reducer 303 by rotating the first handwheel 302 and control the rotation of the transverse movement lead screw 406 by rotating the second handwheel 408.

[0054] Furthermore, as Figure 2 shown, a bearing 102 is provided at the connecting section of the clamp body 101, and an installation hole is formed on the support body 201. The bearing 102 is connected to the installation hole through a rotating pin shaft 103. Here, the cooperation of the installation hole on the support body 201 with the bearing 102 and the rotating pin shaft 103 ensures the stable connection of the clamp body 101 on the support body 201, reduces the frictional resistance when the clamp body 101 rotates, and at the same time ensures a certain rigidity and strength. The bearing 102 can be replaced with a wear-resistant copper sleeve.

[0055] Furthermore, as Figure 5 shown, a bearing seat 505 is provided on the support body 201, and the bearing seat 505 is rotatably connected to the middle position of the driving lead screw 506. Here, the bearing seat 505 plays a role in supporting and positioning the driving lead screw 506, enabling the driving lead screw 506 to rotate flexibly within the bearing seat 505 while restricting its displacement in other directions.

[0056] The specific working process of this rocket fixing device is as follows: As Figure 7 shown, when the device is in the state where the clamp is loosened, at this time, the driving member 501 of the clamp adjusting assembly 5 is activated (such as the operation of a motor, a motor, etc.), driving the driving lead screw 506 to rotate. Since the driving lead screw 506 has a first lead screw section and a second lead screw section with opposite threads, which are respectively threadedly connected to the first driving nut 504 and the second driving nut 507, when the driving lead screw 506 rotates, the first driving nut 504 and the second driving nut 507 will move in opposite directions along the lead screw. The first pin on the first driving nut 504 is rotatably connected to the connecting section of one clamp body 101, and the second pin on the second driving nut 507 is rotatably connected to the connecting section of the other clamp body 101. With the movement of the driving nuts, the two clamp bodies 101 rotate around the corresponding first pin and second pin, and the two clamping sections gradually separate, enabling the rocket to be fixed to be smoothly placed or taken out.

[0057] As Figure 8As shown, when it is necessary to clamp the rocket, the driving member 501 rotates in reverse, driving the driving lead screw 506 to rotate in the reverse direction. This causes the first driving nut 504 and the second driving nut 507 to move in opposite directions along the driving lead screw 506, thereby driving the two clamp body 101 to rotate relative to the bearing mechanism. The two clamping sections gradually approach and fit tightly, firmly clamping the rocket. During the closing process of the clamp, the buffer 202 of the support assembly 2 plays a role to prevent the impact force of the clamp from directly acting on the rocket and protect the surface of the rocket from being damaged.

[0058] After the clamp clamps the rocket, if it is necessary to adjust the position of the rocket, it can be achieved through the transverse movement adjustment assembly 4 and the lifting adjustment assembly 3. Specifically, rotate the second handwheel 408 at the end of the transverse movement lead screw 406. The transverse movement lead screw 406 rotates, driving the transverse movement nut 405 to slide on the bearing seat 401. The transverse movement nut 405 is connected to the lifting adjustment assembly 3. At the same time, the slider 403 on the guide rail 402 is also connected to the bottom of the lifting adjustment assembly 3 to ensure its stable movement, so that the lifting adjustment assembly 3 and the clamp body 101 holding the rocket move along the second direction to achieve the transverse movement adjustment of the rocket. Rotate the first handwheel 302 at the end of the extension shaft of the reducer 303. The power is transmitted to the four elevators 301 through the reducer 303, the cross commutator 306, and the T-shaped commutator 305. The top wall of the elevator 301 is connected to the support body 201, and the drive shafts are respectively connected to the commutator. Under the action of the power, the elevator 301 works, driving the support body 201, the clamp body 101, and the rocket to move along the first direction to achieve the lifting adjustment of the rocket.

[0059] The above description is only the preferred embodiment of the present application and the description of the applied technical principles. Those skilled in the art should understand that the scope of the invention involved in the present application is not limited to the technical solution formed by the specific combination of the above technical features, and should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept. For example, the technical solutions formed by mutually replacing the above features with the (but not limited to) technical features with similar functions disclosed in the present application.

Claims

1. A fixing device for a rocket, characterized in that, Comprising: A bearing mechanism, on which a clamp assembly (1) and a clamp adjusting assembly (5) for driving the clamp assembly (1) to act are installed; The clamp assembly (1) includes: two cooperating clamp bodies (101), the clamp bodies (101) having a connecting section and a clamping section, and an accommodation space is formed between the clamping sections of the two clamp bodies (101) for placing the rocket to be fixed; The clamp adjusting assembly (5) includes: a first mounting seat (502), a second mounting seat (503) and a limit seat (508) installed on the bearing mechanism, a driving member (501) is provided on the first mounting seat (502), a driving lead screw (506) is rotatably connected between the second mounting seat (503) and the limit seat (508), and a driving shaft of the driving member (501) is connected to the driving lead screw (506); the driving lead screw (506) has a first lead screw section and a second lead screw section with opposite threads, the first lead screw section is threadedly connected to a first driving nut (504), the second lead screw section is threadedly connected to a second driving nut (507), a first pin is provided on the first driving nut (504) and is rotatably connected to the connecting section of one of the clamp bodies (101), and a second pin is provided on the second driving nut (507) and is rotatably connected to the connecting section of the other clamp body (101); By driving the driving lead screw (506) to rotate through the driving member (501), the first driving nut (504) and the second driving nut (507) are moved along the driving lead screw (506), thereby driving the two clamp bodies (101) to rotate relative to the bearing mechanism, so that the two clamping sections cooperate to clamp or release the rocket to be fixed.

2. The fixing device for a rocket according to claim 1, wherein The bearing mechanism includes: An adjusting structure, on which a support assembly (2) is provided, the support assembly (2) includes a support body (201), the interior of the support body (201) is hollow to form an installation space for installing the clamp adjusting assembly (5); the adjusting structure is used to drive the support assembly (2) to move in a first direction and a second direction; the first direction and the second direction are perpendicular to each other, the first direction is perpendicular to the bottom surface of the support body (201), and the second direction is parallel to the length direction of the driving lead screw (506).

3. The fixing device for a rocket according to claim 2, characterized in that, The adjusting structure includes: The transverse movement adjustment component (4), the transverse movement adjustment component (4) includes: a carrier seat (401), on which a lead screw support seat (404) and a lead screw clamping seat (407) are provided, and the two are distributed along the second direction; a transverse movement lead screw (406) is rotatably connected between the lead screw support seat (404) and the lead screw clamping seat (407), and a transverse movement nut (405) that is threadedly connected to the lead screw (406) and slidably connected to the carrier seat (401) is arranged on the transverse movement lead screw (406); the upper surface of the transverse movement nut (405) is connected to the lifting adjustment component (3), and the lifting adjustment component (3) is used to drive the support component (2) to move along the first direction; By rotating the transverse movement lead screw (406), the lifting adjustment component (3) is driven to move along the second direction.

4. The fixing device for a rocket according to claim 3, characterized in that, The transverse movement adjustment component (4) further includes: Two guide rails (402), which are arranged on the carrier seat (401) and are located on both sides of the transverse movement lead screw (406) respectively; the extending direction of the guide rail (402) is parallel to the length direction of the driving lead screw (506); a plurality of sliders (403) are arranged on each guide rail (402), and the sliders (403) are connected to the bottom of the lifting adjustment component (3); When the transverse movement lead screw (406) rotates, the sliders (403) move synchronously with the lifting adjustment component (3).

5. The fixing device for a rocket according to claim 4, characterized in that, The lifting adjustment component (3) includes: A support base (307), the support base (307) is connected to the slider (403) and the transverse movement nut (405); a T-shaped commutator (305) and a cross commutator (306) are provided on the support base (307); the T-shaped commutator (305) has a first connecting shaft, a second connecting shaft and a third connecting shaft; the cross commutator (306) has a fourth connecting shaft, a fifth connecting shaft, a sixth connecting shaft and a seventh connecting shaft; the first connecting shaft is connected to the fourth connecting shaft through an intermediate connecting shaft (304); the fifth connecting shaft is connected to the transmission shaft of the power source; Four elevators (301), the driving ends of the elevators (301) are connected to the support main body (201); the driving shafts of the four elevators (301) are respectively connected to the second connecting shaft, the third connecting shaft, the sixth connecting shaft and the seventh connecting shaft; The driving force generated by the power source is synchronously transmitted to each elevator (301) through the T-shaped commutator (305) and the cross commutator (306), so that the support component (2) moves along the first direction.

6. The fixing device for a rocket according to claim 5, characterized in that, The power source includes a reducer (303), and a first handwheel (302) is provided at the end of the extended shaft of the reducer (303); a second handwheel (408) is provided at the end of the transverse movement lead screw (406).

7. The fixing device for a rocket according to claim 2, wherein, The support component (2) further includes: at least two buffers (202), the buffers (202) are arranged on the side wall of the support main body (201) and are used to buffer the impact force borne by the adjacent gripper main body (101).

8. The fixing device for a rocket according to claim 2, characterized in that, A bearing (102) is provided on the connecting section of the clamping pliers body (101), an installation hole is formed on the support body (201), and the bearing (102) is connected to the installation hole through a rotating pin shaft (103).

9. The fixing device for a rocket according to claim 2, characterized in that, A bearing seat (505) is provided on the support body (201), and the bearing seat (505) is rotatably connected to the middle position of the driving lead screw (506).

10. The fixing device for a rocket according to claim 2, characterized in that, An avoidance groove is formed at the position of the support body (201) corresponding to the accommodation space.

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