Supporting and erecting platform for rocket sea launch

Abstract

The present invention relates to the technical field of rocket devices, and discloses a support and erection gantry for offshore rocket launch, which includes a support assembly, a lifting assembly, a first auxiliary assembly, a telescopic assembly and a second auxiliary assembly. The lifting assembly is hinged to the top of the support assembly, one end of the telescopic assembly is hinged to the support assembly, the middle part of the telescopic assembly is hinged to the lifting assembly, the bottom of the first auxiliary assembly is slidably connected to the support assembly, the top of the first auxiliary assembly is hinged to the telescopic assembly, and the top of the second auxiliary assembly is hinged to one end of the telescopic assembly. It solves the problems in the prior art that most rocket erection devices are driven by a single cylinder, lack corresponding shock-absorbing measures to slow down the swing of the rocket in the offshore strong wind environment, and the devices in the marine environment for a long time are prone to corrosion and aging, etc.

Description

Technical Field

[0001] This invention patent relates to the technical field of rocket devices. Specifically, it relates to a support erection gantry for offshore rocket launches. Background Art

[0002] Chinese Patent with Publication No. CN115574661A discloses a gear-driven solid launch vehicle rapid erection gantry, belonging to the field of offshore rocket launches. It includes a gantry base, a rocket erection arm, a first erection system, a second erection system, and a driving device; the rocket erection arm is hinged to the gantry base; the first erection system is configured to erect the rocket erection arm through the pulling action of the towing rope; the second erection system is configured to erect the rocket erection arm through the rotation of the towing gear; the driving device is configured to provide driving force for both the first erection system and the second erection system simultaneously.

[0003] Chinese Patent with Publication No. CN221376449U discloses a gantry system for rocket erection, related to the field of aerospace engineering technology. It includes a tower component and a flipping hanger component. The flipping hanger component consists of two symmetrically arranged jigs. One jig consists of a chuck and a clamping arm. The chuck is slidably arranged on the clamping arm. One end of each of the two clamping arms is rotatably provided with a fixed rotating shaft, and the fixed rotating shaft is fixedly arranged at the upper end of the launch pad. The launch pad consists of a support platform and several support components. The tower component consists of a tower and a mounting base plate. The tower is fixedly arranged at the upper end of the mounting base plate. The bottom end of the mounting base plate is fixedly provided with a chassis. The upper end of the tower is fixedly provided with a fixing plate. The upper end of the mounting base plate is provided with a traction mechanism for facilitating the traction and fixation of the clamping arms. Through the traction mechanism, it is convenient to traction and rotate the flipping hanger component, and at the same time, it is convenient to keep the flipping hanger component fixed.

[0004] However, most of the existing rocket erection devices are single-cylinder driven, lacking corresponding shock-absorbing measures to reduce the swing of the rocket in the offshore strong wind environment, and the devices in the marine environment for a long time are prone to corrosion and aging. Summary of the Invention

[0005] The purpose of the present invention is to provide a support erection gantry for offshore rocket launches, aiming to solve the problems in the prior art that most rocket erection devices are single-cylinder driven, lacking corresponding shock-absorbing measures to reduce the swing of the rocket in the offshore strong wind environment, and the devices in the marine environment for a long time are prone to corrosion and aging.

[0006] The present invention is realized as follows. The support and erection platform for rocket sea launch includes a support assembly, a hoisting assembly, a first auxiliary assembly, a telescopic assembly, and a second auxiliary assembly. The hoisting assembly is hinged to the top of the support assembly. One end of the telescopic assembly is hinged to the support assembly, and the middle of the telescopic assembly is hinged to the hoisting assembly. The bottom of the first auxiliary assembly is slidably connected to the support assembly, the top of the first auxiliary assembly is hinged to the telescopic assembly, and the top of the second auxiliary assembly is hinged to one end of the telescopic assembly.

[0007] A stress detector is installed in the middle of the first auxiliary assembly, and the second auxiliary assembly is placed in seawater.

[0008] The first auxiliary assembly includes an auxiliary slider, an auxiliary support frame, an auxiliary support plate, auxiliary springs, and an auxiliary cylinder. The auxiliary slider is slidably connected to the top of the support assembly. The auxiliary support frame is fixedly connected to the top of the auxiliary slider. The auxiliary support plate is slidably connected to the middle of the auxiliary support frame. The auxiliary springs are symmetrically arranged at the top and bottom of the auxiliary support plate and are connected to the top and bottom of the auxiliary support frame. The bottom of the auxiliary cylinder is hinged to the top of the auxiliary support plate, and the top of the auxiliary cylinder is hinged to the outer wall of the telescopic assembly.

[0009] A plurality of buffer pads are fixedly connected to the top of the auxiliary support plate, and the plurality of buffer pads are detachably installed.

[0010] The second auxiliary assembly includes a second auxiliary hinge seat, a second auxiliary connecting plate, a second auxiliary slideway, an auxiliary water tank, and drainage wheels. The second auxiliary hinge seat is fixedly connected to one end of the telescopic assembly. The top of the second auxiliary connecting plate is hinged to the second auxiliary hinge seat. The second auxiliary slideway is fixedly connected to one end of the support assembly. The middle of the second auxiliary connecting plate is slidably connected to the second auxiliary slideway. The bottom of the second auxiliary connecting plate is hinged to the auxiliary water tank. The auxiliary water tank is placed in seawater. A plurality of the drainage wheels are symmetrically installed at the top and bottom of the auxiliary water tank. An angle induction control is installed at the hinge between the second auxiliary connecting plate and the second auxiliary hinge seat.

[0011] The hoisting assembly includes a hoisting oil cylinder. The top of the hoisting oil cylinder is hinged to the middle of the telescopic assembly, and the bottom of the hoisting oil cylinder is hinged to the top of the support assembly.

[0012] The telescopic assembly includes a plurality of telescopic support frames, telescopic rotating shafts, telescopic tie rods, and telescopic sensors. The plurality of telescopic support frames are slidably connected. The telescopic rotating shafts are rotatably connected to the middle of the telescopic support frames. The telescopic tie rods are installed in the middle of the telescopic support frames. The telescopic sensors are placed at the front end of the telescopic support frames.

[0013] It also includes a clamping assembly which is installed on the top of the telescopic support frame. The clamping assembly includes a clamping frame, a clamping oil cylinder, a clamping block, a plurality of clamping hinge rods and a clamping plate. The clamping frame is installed on the top of the telescopic support frame. The clamping oil cylinder is installed inside the clamping frame. The clamping block is fixedly connected to the extending end of the clamping oil cylinder. The clamping hinge rods are respectively hinged to the clamping block and the clamping plate.

[0014] It also includes a fixing assembly which includes a fixing base plate, a fixing bracket, a fixing oil cylinder, a fixing support block and a fixing support plate. The fixing bracket is installed on the top of the fixing base plate. The fixing oil cylinder is installed on one side of the fixing support block. The fixing support block is installed at the extending end of the fixing oil cylinder. The fixing support plate is slidably connected to the middle of the fixing support block.

[0015] It also includes a maintenance assembly which is installed on both sides of the telescopic assembly. The maintenance assembly includes a maintenance bracket, a screw support, a screw, a maintenance slideway, a driving motor, a driving slider and a maintenance seat. The screw support is installed on the maintenance bracket. The screw is rotatably connected to the screw support. The maintenance slideways are symmetrically arranged on both sides of the screw. The driving motor is in transmission connection with the screw. The driving slider is in threaded transmission connection with the screw. The driving slider is slidably connected to the maintenance slideway. The maintenance seat is installed on the top of the driving slider.

[0016] The maintenance seat includes a maintenance air cylinder, moving wheels, a sandblasting nozzle, a detection head and an anti-rust spray head. The maintenance air cylinder is installed on the top of the maintenance seat. The moving wheels are rotatably connected to the bottom of the maintenance seat. The sandblasting nozzle and the detection head are symmetrically arranged at the bottom of the maintenance seat. The anti-rust spray head is arranged at the front end of the maintenance seat.

[0017] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0018] Through the collaborative work of multiple components, the present invention realizes the stable erection of the rocket. The addition of the stress detector greatly improves the safety of the whole structure, can monitor and adjust the stress state of the structure in real time, and prevent potential structural damage. The seawater placement design of the second auxiliary component utilizes the buoyancy and damping characteristics of seawater to effectively reduce the influence of wind and waves on the stability of the gantry, and enhances the reliability of rocket launch.

[0019] The present invention provides high flexibility and adaptability, enabling the gantry to adapt to rockets of different weights and sizes. The combination of the auxiliary spring and the auxiliary air cylinder not only provides a buffering effect, but also can maintain the stability of the structure under different sea conditions, reduce the impact and vibration caused by sea waves, and protect the rocket and the gantry from damage. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 is a schematic structural diagram of the support and erection gantry for offshore rocket launch of the present invention;

[0021] Figure 2 It is a schematic structural diagram of the telescopic component in the support and erection gantry for rocket sea launch of the present invention;

[0022] Figure 3 It is a schematic structural diagram of the first auxiliary component in the support and erection gantry for rocket sea launch of the present invention;

[0023] Figure 4 It is a schematic structural diagram of the second auxiliary component in the support and erection gantry for rocket sea launch of the present invention;

[0024] Figure 5 It is a schematic structural diagram of the clamping component in the support and erection gantry for rocket sea launch of the present invention;

[0025] Figure 6 It is a schematic structural diagram of the maintenance component in the support and erection gantry for rocket sea launch of the present invention;

[0026] Figure 7 is Figure 6 The partial enlarged view of part A in

[0027] Reference numerals:

[0028] 1, support component; 2, lifting component; 3, first auxiliary component; 4, telescopic component; 5, clamping component; 6, second auxiliary component; 7, fixing component; 8, maintenance component; 9, telescopic support frame; 10, telescopic rotating shaft; 11, telescopic pull rod; 12, telescopic inductor; 13, lifting oil cylinder; 15, auxiliary slider; 16, auxiliary support plate; 17, auxiliary spring; 18, buffer pad; 19, auxiliary cylinder; 20, fixed bottom plate; 21, fixed bracket; 22, fixed oil cylinder; 23, fixed support block; 24, fixed support plate; 25, second auxiliary hinge seat; 26, second auxiliary connecting plate; 27, second auxiliary slideway; 28, auxiliary water tank; 29, drainage wheel; 30, clamping frame; 31, clamping oil cylinder; 32, clamping block; 33, clamping hinge rod; 34, clamping plate; 35, maintenance bracket; 36, screw support; 37, screw; 38, maintenance slideway; 39, drive motor; 40, drive slider; 41, maintenance seat; 42, maintenance cylinder; 43, moving wheel; 44, sandblasting nozzle; 45, detection head; 46, rust-proof spray head; 47, auxiliary support frame. Detailed implementation manners

[0029] In order to make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0030] The implementation of the present invention will be described in detail below in conjunction with specific embodiments.

[0031] In the accompanying drawings of this embodiment, the same or similar reference numerals correspond to the same or similar components; in the description of the present invention, it should be understood that if there are terms such as "upper", "lower", "left", "right", etc. indicating the orientation or positional relationship, they are based on the orientation or positional relationship shown in the accompanying drawings. This is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, the terms describing the positional relationship in the accompanying drawings are only for illustrative purposes and cannot be construed as a limitation of this patent. For those of ordinary skill in the art, the specific meanings of the above terms can be understood according to specific circumstances.

[0032] As Figures 1-7 shown, the present invention provides a support and erection gantry for rocket sea launch, including a support assembly 1, a hoisting assembly 2, a first auxiliary assembly 3, a telescopic assembly 4, and a second auxiliary assembly 6. The hoisting assembly 2 is hinged to the top of the support assembly 1. One end of the telescopic assembly 4 is hinged to the support assembly 1, and the middle of the telescopic assembly 4 is hinged to the hoisting assembly 2. The bottom of the first auxiliary assembly 3 is slidably connected to the support assembly 1, the top of the first auxiliary assembly 3 is hinged to the telescopic assembly 4, and the top of the second auxiliary assembly 6 is hinged to one end of the telescopic assembly 4;

[0033] A stress detector is installed in the middle of the first auxiliary assembly 3, and the second auxiliary assembly 6 is placed in seawater.

[0034] This design realizes the stable erection of the rocket through the coordinated work of multiple components. The addition of the stress detector greatly improves the safety of the entire structure, enabling real-time monitoring and adjustment of the stress state of the structure to prevent potential structural damage. The design of placing the second auxiliary assembly 6 in seawater utilizes the buoyancy and damping characteristics of seawater to effectively reduce the influence of wind and waves on the stability of the gantry and enhance the reliability of rocket launch.

[0035] The first auxiliary assembly 3 includes an auxiliary slider 15, an auxiliary support frame 47, an auxiliary support plate 16, an auxiliary spring 17, and an auxiliary cylinder 19. The auxiliary slider 15 is slidably connected to the top of the support assembly 1. The auxiliary support frame 47 is fixedly connected to the top of the auxiliary slider 15. The auxiliary support plate 16 is slidably connected to the middle of the auxiliary support frame 47. The auxiliary springs 17 are symmetrically arranged at the top and bottom of the auxiliary support plate 16, and the auxiliary springs 17 are connected to the top and bottom of the auxiliary support frame 47. The bottom of the auxiliary cylinder 19 is hinged to the top of the auxiliary support plate 16, and the top of the auxiliary cylinder 19 is hinged to the outer wall of the telescopic assembly 4.

[0036] This delicate design provides a high degree of flexibility and adaptability, enabling the gantry to accommodate rockets of different weights and sizes. The combination of the auxiliary spring 17 and the auxiliary cylinder 19 not only provides a buffering effect but also maintains the structural stability under different sea conditions, reducing the impact and vibration caused by waves and protecting the rocket and the gantry from damage.

[0037] A plurality of buffer pads 18 are fixedly connected to the top of the auxiliary support plate 16, and the plurality of buffer pads 18 are detachably installed.

[0038] The design of the buffer pad 18 allows for quick replacement and maintenance, improving the maintenance efficiency and service life of the equipment. This design also takes into account the wear in different launch environments. By simply replacing the buffer pad 18, it can adapt to different usage intensities and extend the service life of the entire system.

[0039] The second auxiliary component 6 includes a second auxiliary hinge seat 25, a second auxiliary connecting plate 26, a second auxiliary slideway 27, an auxiliary water tank 28, and a drainage wheel 29. The second auxiliary hinge seat 25 is fixedly connected to one end of the telescopic component 4. The top of the second auxiliary connecting plate 26 is hinged to the second auxiliary hinge seat 25. The second auxiliary slideway 27 is fixedly connected to one end of the support component 1. The middle of the second auxiliary connecting plate 26 is slidably connected to the second auxiliary slideway 27. The bottom of the second auxiliary connecting plate 26 is hinged to the auxiliary water tank 28. The auxiliary water tank 28 is placed in seawater. A plurality of drainage wheels 29 are symmetrically installed at the top and bottom of the auxiliary water tank 28. An angle induction control is installed at the hinge joint between the second auxiliary connecting plate 26 and the second auxiliary hinge seat 25.

[0040] This structural design not only improves the stability of the gantry but also effectively utilizes the buoyancy and stability of water through the design of the auxiliary water tank 28 and the drainage wheel 29, reducing the sway of the gantry in waves and improving the launch accuracy. The addition of the angle induction control enables the gantry to automatically adjust to the optimal launch angle, reducing the error of manual operation. During the initial lifting, the first auxiliary component 3 assists the lifting component 2 to rotate the rocket from the horizontal position to a certain angle. When the angle induction controller senses that the rocket has rotated to the target position, the second auxiliary component 6 adds water to the auxiliary water tank 28 through the drainage wheel and controls the lowering of the auxiliary water tank 28 to provide a pulling force for the rocket to flip. When the rocket rotates to the next target angle, at this time the rocket is about to rotate to the vertical position, the drainage wheel 29 drains the water in the auxiliary water tank, using the buoyancy to provide a shock-absorbing effect for the rocket.

[0041] The lifting component 2 includes a lifting oil cylinder 13. The top of the lifting oil cylinder 13 is hinged to the middle of the telescopic component 4, and the bottom of the lifting oil cylinder 13 is hinged to the top of the support component 1.

[0042] The design of the lifting cylinder 13 provides powerful lifting capacity, ensuring that the rocket can be smoothly and safely lifted to the launch position. This design also allows for precise control of the lifting speed and force, reducing the risk of structural damage caused by improper operation.

[0043] The telescopic assembly 4 includes multiple telescopic support frames 9, telescopic rotating shafts 10, telescopic tie rods 11, and telescopic sensors 12. The multiple telescopic support frames 9 are slidably connected. The telescopic rotating shaft 10 is rotatably connected to the middle of the telescopic support frame 9. The telescopic tie rod 11 is installed in the middle of the telescopic support frame 9. The telescopic sensor is placed at the front end of the telescopic support frame 9.

[0044] The design of the telescopic assembly 4 enables the gantry to quickly adjust its length as needed to accommodate rockets of different sizes. The addition of the telescopic sensor 12 allows the operator to monitor the telescopic state in real time, ensuring the accuracy and safety of the operation.

[0045] It further includes a clamping assembly 5. The clamping assembly 5 is installed on the top of the telescopic support frame 9. The clamping assembly 5 includes a clamping frame 30, a clamping cylinder 31, a clamping block 32, multiple clamping hinge rods 33, and a clamping plate 34. The clamping frame 30 is installed on the top of the telescopic support frame 9. The clamping cylinder 31 is installed inside the clamping frame 30. The clamping block 32 is fixedly connected to the extending end of the clamping cylinder 31. The clamping hinge rods 33 are respectively hinged to the clamping block 32 and the clamping plate 34.

[0046] The design of the clamping assembly 5 provides powerful clamping force, ensuring the stability of the rocket during the erection process. This design also allows for quick adjustment of the clamping position and force to meet the clamping requirements of different rockets, improving the flexibility and safety of the operation.

[0047] It further includes a fixing assembly 7. The fixing assembly 7 includes a fixing bottom plate 20, a fixing bracket 21, a fixing cylinder 22, a fixing support block 23, and a fixing support plate 24. The fixing bracket 21 is installed on the top of the fixing bottom plate 20. The fixing cylinder 22 is installed on one side of the fixing support block 23. The fixing support block 23 is installed at the extending end of the fixing cylinder 22. The fixing bottom plate 20 is slidably connected to the middle of the fixing support block 23.

[0048] The design of the fixing assembly 7 provides additional stability and fixing ability, ensuring the stability of the rocket during the erection process and preventing instability caused by external factors such as waves. This design also allows for quick adjustment of the fixing position and force to meet the fixing requirements of different rockets, improving the flexibility and safety of the operation. The fixing assembly 7 fixes the bottom of the rocket when the rocket is in the vertical position.

[0049] It also includes a maintenance component 8, which is installed on both sides of the telescopic component 4. The maintenance component 8 includes a maintenance bracket 35, a screw support 36, a screw 37, a maintenance slideway 38, a driving motor 39, a driving slider 40 and a maintenance seat 41. The screw support 36 is installed on the maintenance bracket 35, the screw 37 is rotatably connected to the screw support 36, the maintenance slideways 38 are symmetrically arranged on both sides of the screw 37, the driving motor 39 is drivingly connected to the screw 37, the driving slider 40 is threadedly drivingly connected to the screw 37, the driving slider 40 is slidably connected to the maintenance slideway 38, and the maintenance seat 41 is installed on the top of the driving slider 40.

[0050] The design of the maintenance component 8 makes the maintenance and upkeep work more convenient and efficient. The combined use of the driving motor 39 and the driving slider 40 can reduce manual operation, improve the efficiency and safety of maintenance. This design also allows for quick adjustment of the maintenance position and intensity to adapt to the maintenance requirements of different components, enhancing the flexibility and comprehensiveness of maintenance.

[0051] The maintenance seat 41 includes a maintenance cylinder 42, moving wheels 43, a sandblasting nozzle 44, a detection head 45 and an anti-rust spray head 46. The maintenance cylinder 42 is installed on the top of the maintenance seat 41, the moving wheels 43 are rotatably connected to the bottom of the maintenance seat 41, the sandblasting nozzle 44 and the detection head 45 are symmetrically arranged at the bottom of the maintenance seat 41, and the anti-rust spray head 46 is placed at the front end of the maintenance seat 41.

[0052] The design of the maintenance seat 41 makes the maintenance work more comprehensive and efficient. The sandblasting nozzle 44 and the anti-rust spray head 46 can effectively perform cleaning and anti-rust treatments, extending the service life of the equipment, while the detection head 45 can monitor the maintenance effect to ensure the maintenance quality. This design also allows for quick adjustment of the maintenance position and intensity to adapt to the maintenance requirements of different components, enhancing the flexibility and comprehensiveness of maintenance. Through these innovative designs, the overall performance of the support and erection gantry for rocket sea launch has been significantly improved, not only increasing the launch success rate, but also reducing the maintenance cost and operation risk, providing strong technical support for rocket sea launch.

[0053] Referring to the figures shown, it is a preferred embodiment provided by the present invention.

[0054] The working process of this embodiment is as follows:

[0055] S1. Place the support component 1 at a predetermined position and ensure its stability. Hinge the lifting component 2 to the top of the support component 1. Hinge one end of the telescopic component 4 to the support component 1 and ensure that its middle part is hinged to the lifting component 2.

[0056] S2. Slide-connect the bottom of the first auxiliary component 3 to the support component 1, and hinge its top to the telescopic component 4. Install a stress detector in the middle of the first auxiliary component 3 to monitor the force condition. Hinge the top of the second auxiliary component 6 to one end of the telescopic component 4, and place it in seawater to improve the stability in seawater.

[0057] S3. Slide-connect the auxiliary slider 15 to the top of the support component 1. Fix the auxiliary support frame 47 to the top of the auxiliary slider 15. Slide-connect the auxiliary support plate 16 to the middle of the auxiliary support frame 47, and symmetrically install auxiliary springs 17 at the top and bottom of the auxiliary support plate 16. Hinge the bottom of the auxiliary cylinder 19 to the top of the auxiliary support plate 16, and its top to the outer wall of the telescopic component 4.

[0058] S4. Fix a plurality of detachable buffer pads 18 to the top of the auxiliary support plate 16.

[0059] S5. Fix the second auxiliary hinge seat 25 to one end of the telescopic component 4. Hinge the top of the second auxiliary connecting plate 26 to the second auxiliary hinge seat 25. Slide-connect the middle of the second auxiliary connecting plate 26 to the second auxiliary slideway 27 fixed to one end of the support component 1. Hinge the auxiliary water tank 28 to the bottom of the second auxiliary connecting plate 26, and place it in seawater. Symmetrically install a plurality of drainage wheels 29 at the top and bottom of the auxiliary water tank 28, and install an angle induction control at the hinge joint between the second auxiliary connecting plate 26 and the second auxiliary hinge seat 25.

[0060] S6. Hinge the top of the lifting oil cylinder 13 to the middle of the telescopic component 4, and its bottom to the top of the support component 1, and get ready to lift the rocket.

[0061] S7. Ensure that the telescopic support frame 9 is slide-connected, and the telescopic rotating shaft 10 is rotatably connected to the middle of the telescopic support frame 9. Install the telescopic pull rod 11 in the middle of the telescopic support frame 9, and place the telescopic inductor 12 at the front end of the telescopic support frame 9.

[0062] S8. Install the clamping component 5 on the top of the telescopic support frame 9. It includes a clamping frame 30, a clamping oil cylinder 31, a clamping block 32, a plurality of clamping hinge rods 33 and a clamping plate 34, and ensure that they are correctly installed and hinged.

[0063] S9. There are a fixed bottom plate 20, a fixed support 21, a fixed oil cylinder 22, a fixed support block 23 and a fixed support plate 24, and ensure that they are correctly installed and hinged.

[0064] S10. Install the maintenance component 8 on both sides of the telescopic component 4. It includes a maintenance support 35, a screw support 36, a screw 37, a maintenance slideway 38, a driving motor 39, a driving slider 40 and a maintenance seat 41, and ensure that they are correctly installed and connected.

[0065] S11. Install a maintenance cylinder 42, moving wheels 43, a sandblasting nozzle 44, a detection head 45, and an anti-rust spray head 46 on the maintenance base 41, and ensure that they are correctly installed and connected.

[0066] S12. Conduct a final inspection to ensure that all components are correctly installed and the sensors and control systems are working properly. Adjust the erection parameters according to the real-time data to ensure the smoothness and accuracy of the erection process.

[0067] S13. After confirming that all systems are ready, execute the rocket erection and launch procedures.

[0068] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, and improvements made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. The support and erection gantry for rocket sea launch comprises a support assembly (1), a hoisting assembly (2) and a telescopic assembly (4). The hoisting assembly (2) is hinged to the top of the support assembly (1). One end of the telescopic assembly (4) is hinged to the support assembly (1), and the middle part of the telescopic assembly (4) is hinged to the hoisting assembly (2). It is characterized in that, A first auxiliary component (3) and a second auxiliary component (6) are further provided. The bottom of the first auxiliary component (3) is slidably connected to the support component (1), the top of the first auxiliary component (3) is hinged to the telescopic component (4), and the top of the second auxiliary component (6) is hinged to one end of the telescopic component (4). A stress detector is installed in the middle of the first auxiliary component (3), and the second auxiliary component (6) is placed in seawater. The first auxiliary component (3) includes an auxiliary slider (15), an auxiliary support frame (47), an auxiliary support plate (16), an auxiliary spring (17), and an auxiliary cylinder (19). The auxiliary slider (15) is slidably connected to the top of the support component (1). The auxiliary support frame (47) is fixedly connected to the top of the auxiliary slider (15). The auxiliary support plate (16) is slidably connected to the middle of the auxiliary support frame (47). The auxiliary springs (17) are symmetrically arranged at the top and bottom of the auxiliary support plate (16), and the auxiliary springs (17) are connected to the top and bottom of the auxiliary support frame (47). The bottom of the auxiliary cylinder (19) is hinged to the top of the auxiliary support plate (16), and the top of the auxiliary cylinder (19) is hinged to the outer wall of the telescopic component (4). A plurality of buffer pads (18) are fixedly connected to the top of the auxiliary support plate (16), and the plurality of buffer pads (18) are detachably installed. The second auxiliary component (6) includes a second auxiliary hinge seat (25), a second auxiliary connecting plate (26), a second auxiliary slideway (27), an auxiliary water tank (28), and a drainage wheel (29). The second auxiliary hinge seat (25) is fixedly connected to one end of the telescopic component (4). The top of the second auxiliary connecting plate (26) is hinged to the second auxiliary hinge seat (25). The second auxiliary slideway (27) is fixedly connected to one end of the support component (1). The middle of the second auxiliary connecting plate (26) is slidably connected to the second auxiliary slideway (27). The bottom of the second auxiliary connecting plate (26) is hinged to the auxiliary water tank (28). The auxiliary water tank (28) is placed in seawater. A plurality of drainage wheels (29) are symmetrically installed at the top and bottom of the auxiliary water tank (28). An angle induction control is installed at the hinge joint between the second auxiliary connecting plate (26) and the second auxiliary hinge seat (25).

2. The support erection gantry for rocket sea launch according to claim 1, wherein The lifting component (2) includes a lifting oil cylinder (13). The top of the lifting oil cylinder (13) is hinged to the middle of the telescopic component (4), and the bottom of the lifting oil cylinder (13) is hinged to the top of the support component (1).

3. The support erection gantry for offshore rocket launch according to claim 2, characterized in that The telescopic component (4) includes a plurality of telescopic support frames (9), telescopic rotating shafts (10), telescopic pull rods (11), and telescopic sensors (12). The plurality of telescopic support frames (9) are slidably connected. The telescopic rotating shafts (10) are rotatably connected to the middle of the telescopic support frames (9). The telescopic pull rods (11) are installed in the middle of the telescopic support frames (9). The telescopic sensors (12) are placed at the front end of the telescopic support frames (9).

4. The support erection gantry for rocket sea launch according to claim 3, wherein It further includes a clamping assembly (5). The clamping assembly (5) is installed at the top of the telescopic support frame (9). The clamping assembly (5) includes a clamping frame (30), a clamping oil cylinder (31), a clamping block (32), a plurality of clamping hinge rods (33) and a clamping plate (34). The clamping frame (30) is installed at the top of the telescopic support frame (9). The clamping oil cylinder (31) is installed inside the clamping frame (30). The clamping block (32) is fixedly connected to the extending end of the clamping oil cylinder (31). The clamping hinge rods (33) are respectively hinged to the clamping block (32) and the clamping plate (34).

5. The support erection gantry for rocket sea launch according to claim 4, characterized in that, It further includes a fixing assembly (7). The fixing assembly (7) includes a fixing bottom plate (20), a fixing bracket (21), a fixing oil cylinder (22), a fixing support block (23) and a fixing support plate (24). The fixing bracket (21) is installed at the top of the fixing bottom plate (20). The fixing oil cylinder (22) is installed on one side of the fixing support block (23). The fixing support block (23) is installed at the extending end of the fixing oil cylinder (22). The middle part of the fixing bottom plate (20) is slidably connected to the fixing support block (23).

6. The support erection gantry for rocket sea launch according to claim 5, characterized in that, It further includes a maintenance assembly (8). The maintenance assembly (8) is installed on both sides of the telescopic assembly (4). The maintenance assembly (8) includes a maintenance bracket (35), a screw support (36), a screw (37), a maintenance slideway (38), a driving motor (39), a driving slider (40) and a maintenance seat (41). The screw support (36) is installed on the maintenance bracket (35). The screw (37) is rotatably connected to the screw support (36). The maintenance slideways (38) are symmetrically arranged on both sides of the screw (37). The driving motor (39) is in transmission connection with the screw (37). The driving slider (40) is in threaded transmission connection with the screw (37). The driving slider (40) is slidably connected to the maintenance slideway (38). The maintenance seat (41) is installed at the top of the driving slider (40).

7. The support erection gantry for rocket sea launch according to claim 6, characterized in that The maintenance seat (41) includes a maintenance cylinder (42), a moving wheel (43), a sandblasting nozzle (44), a detection head (45) and an anti-rust spray head (46). The maintenance cylinder (42) is installed at the top of the maintenance seat (41). The moving wheel (43) is rotatably connected to the bottom of the maintenance seat (41). The sandblasting nozzle (44) and the detection head (45) are symmetrically arranged at the bottom of the maintenance seat (41). The anti-rust spray head (46) is arranged at the front end of the maintenance seat (41).

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