Full-automatic flexible rocket supporting mechanism

Abstract

The invention discloses a full-automatic flexible rocket supporting mechanism which comprises two oppositely-arranged mounting seats, overturning frames and overturning electric cylinders are hinged to the front portions and the rear portions of the mounting seats correspondingly, the upper ends of the overturning frames are hinged to output shafts of the overturning electric cylinders, and hanging belts are installed between the two overturning frames and used for supporting a rocket. The supporting and adjusting mechanism makes full contact with the surface of the rocket, stress is uniform, and the characteristics of high adaptability, automation and the like are achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of launch vehicle launch technology, and in particular to a fully automatic flexible rocket support mechanism. Background Art

[0002] With the development of rocket launch technology, rapid launch and rapid evacuation of rockets have become a new development direction. The launch method of "three horizontals and one vertical" (horizontal assembly, horizontal testing, horizontal transfer, and vertical erection and launch scheme) has been widely used because of its rapid deployment and retraction. The support mechanism is mainly installed on the erection or transfer device to support the rocket. At present, most of the support mechanisms used in China are fixed brackets with the same shape processed according to the rocket's outer shape for support.

[0003] In the prior art, a patent for invention named "Rocket Support Bracket with Multifunctional Variable Diameter Device" is disclosed, with the publication number CN115773694A. It specifically includes a movable base device, on which two support seat devices are installed. Above the support seat device, a roller bracket device is provided, and a lift device is installed between the support seat device and the roller bracket device; the base device includes a base frame with multiple brake rollers, on which a base track with two groups of sliders is installed, and the bottoms of the two support seat devices are respectively fixedly connected to the two groups of sliders, and it also includes a base drive assembly; the roller bracket device includes a bracket base, on which a bracket guide rod with two groups of sliders is installed, and it also includes a front roller seat and a rear roller seat. The bottoms of the two roller seats are respectively fixedly connected to the two groups of sliders. A front support roller is installed on the front roller seat, and a rear support roller is installed on the rear roller seat, and it also includes a bracket drive assembly.

[0004] However, in the prior art, the contact area between this structure and the rocket is small, the contact stress between the rocket and this structure is large, so the pressure-bearing requirement for the rocket becomes higher. When supporting a rocket that is too heavy, damage is likely to occur, and the maintenance cost is relatively high. Summary of the Invention

[0005] To solve the above technical problems, the present invention provides a fully automatic flexible rocket support mechanism.

[0006] The present invention is achieved through the following technical solutions.

[0007] A fully automatic flexible rocket support mechanism provided by the present invention includes two oppositely arranged mounting seats. A turning frame and a turning electric cylinder are respectively hinged in front of and behind the mounting seat. The upper end of the turning frame is hinged to the output shaft of the turning electric cylinder. A sling is installed between the two turning frames, and the sling is used to support the rocket.

[0008] Preferably, a tightening electric cylinder is installed at the lower end of the turning frame. The output shaft of the tightening electric cylinder is connected to the tightening sliding shaft, and the tightening sliding shaft is slidably installed on the turning frame. The tightening electric cylinder drives the tightening sliding shaft to slide along the length direction of the turning frame. A sling pulley is installed at the top end of the turning frame. The sling passes through the sling pulley and is fixed on the tightening sliding shaft.

[0009] Preferably, a receiving cavity is formed between the two turning arms of the turning frame.

[0010] Preferably, sliding guide rails are respectively provided on the two turning arms of the turning frame along their length directions. Both ends of the tightening sliding shaft are respectively inserted into the two sliding guide rails, and at the same time, the tightening sliding shaft moves along the length direction of the receiving cavity.

[0011] Preferably, a plurality of limiting rods are arranged at the upper end part of the turning frame. The length direction of the limiting rods is the same as the axial direction of the sling pulley. The plurality of limiting rods semi-surround the sling pulley, and the sling shuttles between the limiting rods and the sling pulley.

[0012] Preferably, a tension sensor is arranged between the upper fulcrum of the output shaft of the tightening electric cylinder and the tightening sliding shaft.

[0013] Preferably, a position sensor is arranged at the installation position of the mounting seat and the turning frame.

[0014] Preferably, a triangular stabilizer is fixedly installed on the back side of the two turning frames. The end corners of the triangular stabilizer are hinged to the output shaft of the turning electric cylinder through a pin shaft I.

[0015] Preferably, a plurality of mounting holes are provided at the bottom of the mounting seat.

[0016] Preferably, the tightening electric cylinder is installed at the lower end of the turning frame through a pin shaft II.

[0017] The beneficial effects of the present invention are as follows:

[0018] ① This structure uses a sling to flexibly support the rocket, which is more conformable to the rocket surface, the force on the rocket surface is uniform, and at the same time, the contact area between the rocket and the sling can be adjusted, so that the contact area between the sling and the rocket becomes larger, reducing the contact stress between the rocket and this structure. It is applicable to multiple rockets with different weights, is not easy to be damaged, and reduces the maintenance cost.

[0019] ② This structure can adjust the tightening sliding shaft and the sling through the tightening electric cylinder, adjust the working length of the sling for flexible support, and also combine with the angle adjustment of the turning frames on both sides to adjust steplessly to adapt to different rocket diameters, with a wide application range.

[0020] ③This structure uses a position sensor and a tension sensor to monitor and control the angle adjustment of the tipping frame and the tightness of the sling. It can achieve one-key start of the overall structure, automatically judge and stop after reaching the position, with convenient operation. At the same time, it also realizes real-time monitoring of the force on this structure during the operation of the erection device and the transfer device, avoiding abnormal support force and damage to the rocket.

[0021] ④This structure can lower the height of the sling and the tipping frame before rocket hoisting, increase the available height space for rocket hoisting, increase the safety distance between the rocket and the sling during hoisting, reduce the difficulty of rocket hoisting, effectively save the height space for rocket hoisting, and has strong safety during the installation process, which helps to protect the rocket.

[0022] ⑤This structure uses the force on the sling as the basis for judging the support in place, and can adapt to the change of the required support surface caused by the shape deviation of rockets in different batches, with strong adaptability. Description of the Drawings

[0023] Figure 1 is the structural schematic diagram of the present invention;

[0024] Figure 2 is the front view of the present invention in the support state;

[0025] Figure 3 is the left view of the present invention in the support state;

[0026] Figure 4 is the front view of the present invention in the open state;

[0027] In the figure: 1 - tipping electric cylinder; 2 - tipping frame; 3 - tightness sliding shaft; 4 - tension sensor; 5 - pin shaft one; 6 - sling pulley and limit; 7 - sling; 8 - tightness electric cylinder; 9 - pin shaft two; 10 - slewing trunnion; 11 - position sensor; 12 - mounting seat, 13 - pin shaft three; 14 - accommodating cavity; 15 - sliding guide rail; 16 - limiting rod; 17 - triangular stabilizer; 18 - mounting hole. Detailed Embodiments

[0028] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0029] It should be noted that all directional indications (such as up, down, left, right, front, back...) in the embodiments of the present invention are only used to explain the relative positional relationship and movement conditions between components in a specific posture (as shown in the attached drawings). If the specific posture changes, the directional indications will also change accordingly.

[0030] In this embodiment, referring to Figure 1 , a fully automatic flexible rocket support mechanism includes two oppositely arranged mounting seats 12. A plurality of mounting holes 18 are provided at the bottom of the mounting seat 12. The mounting seat 12 is mounted on the rocket erection or transportation device by screws, which is suitable for installation in various environments and is convenient to install.

[0031] In this embodiment, referring to Figure 1 , the two turning arms of the turning frame 2 are hinged to the mounting seat 12 through a rotary trunnion 10, so that the turning frame 2 rotates along the rotary trunnion 10. The two turning frames 2 are arranged oppositely, and the two turning frames 2 rotate in opposite directions, which is convenient for adjusting the angle of the turning frame 2.

[0032] In this embodiment, referring to Figure 1 , the turning electric cylinder 1 is hinged to the mounting seat 12 through a pin shaft three 13, which is convenient for adjusting the offset angle of the turning electric cylinder 1. A triangular stabilizer 17 is fixedly installed on the back side of the two turning frames 2. The triangular stabilizer 17 is located at the upper end of the turning frame 2. The end angle of the triangular stabilizer 17 is hinged to the output shaft of the turning electric cylinder 1 through a pin shaft one 5, so that the turning electric cylinder 1 pushes the turning frame 2 to rotate along the pin shaft one 5, which is convenient for the turning electric cylinder 1 to adjust the angle of the turning frame 2.

[0033] In this embodiment, referring to Figure 1 , a sling 7 is installed between the two turning frames 2. The sling 7 is used to support the rocket; a receiving cavity 14 is formed between the two turning arms of the turning frame 2. The tightening electric cylinder 8 is installed at the lower end of the turning frame 2 through a pin shaft two 9. The tightening electric cylinder 8 is located in the receiving cavity 14, and the output shaft of the tightening electric cylinder 8 is connected with a tightening sliding shaft 3.

[0034] Referring to Figure 1 , sliding guide rails 15 are provided along the length direction of the two turning arms of the turning frame 2. The two ends of the tightening sliding shaft 3 are respectively inserted into the two sliding guide rails 15. At the same time, the tightening sliding shaft 3 moves along the length direction of the receiving cavity 14. The sliding guide rails 15 limit the tightening sliding shaft 3. The tightening electric cylinder 8 drives the tightening sliding shaft 3 to slide along the sliding guide rails 15. The two ends of the sling 7 are respectively connected to the two tightening sliding shafts 3 to realize the adjustment of the tension of the sling 7, so that the sling 7 is adjusted in the receiving cavity 14, which is convenient for saving installation space, and the whole structure is more beautiful and convenient to install.

[0035] To facilitate the sliding of the sling 7, refer to Figure 1 , a sling pulley 6 is rotatably installed between the tops of the two turning arms of the turning frame 2. The sling 7 passes over the sling pulley 6 from the tensioning sliding shaft 3 and is located between the two turning frames 2 to form a flexible support frame. Since the sling 7 is a flexible fabric and the tension of the sling 7 is used as the basis for judging the support in place, this structure can adapt to the machining deviations of the outer shapes of rockets in different batches, and the force on the rocket surface is more uniform.

[0036] In this embodiment, refer to Figure 1 , a plurality of limiting rods 16 are arranged at the upper end of the turning frame 2. The length direction of the limiting rods 16 is the same as the axial direction of the sling pulley 6. The plurality of limiting rods 16 semi-surround the sling pulley 6. The sling 7 shuttles between the limiting rods 16 and the sling pulley 6. The sling pulley 6 facilitates the sliding of the sling 7 and also facilitates the adjustment of the tension of the sling 7. At the same time, the limiting rods 16 limit the sling 7 during the shuttling process to prevent the sling 7 from slipping off, strengthening the structural stability.

[0037] In this embodiment, a position sensor 11 is arranged at the installation position of the mounting seat 12 and the turning frame 2. The position sensor 11 is installed on the mounting seat 12 by threaded connection. The movement position of the turning frame 2 is detected and controlled through the position sensor 11. A tension sensor 4 is installed between the upper fulcrum of the output shaft of the tensioning electric cylinder 8 and the tensioning sliding shaft 3. The force received by the sling 7 is monitored in real time through the tension sensor 4.

[0038] In this embodiment, through the combined cooperation of the position sensor 11 and the tension sensor 4, the movement state and the force received by the overall structure are monitored and controlled, which can realize the one-key start of the overall structure. After the rocket is supported in place, it automatically judges and stops, realizing the stable support of the rocket. At the same time, the force on this structure during the working process of the erection device and the transfer device is also monitored in real time to avoid abnormal support force and damage to the rocket.

[0039] The working principle of this embodiment: Refer to Figure 2 , Figure 3 and Figure 4 , after the rocket is placed horizontally, the turning electric 1 is used to push the turning frame 2 to rotate and start working. Before the rocket is hoisted, the height of the sling 7 and the turning frame 2 is adjusted to be low, and the hoisting safety distance is large, effectively saving the hoisting height space of the rocket and reducing the hoisting difficulty of the rocket;

[0040] Then, the tilting electric cylinder 1 is made to push the tilting frame 2 to rotate around the rotary trunnion 10. After reaching the predetermined angle of the position sensor 11, the tilting electric cylinder 1 stops working. The tightening and loosening electric cylinder 8 pulls the tightening and loosening sliding shaft 3 to slide on the sliding guide rail 15, driving the sling 7 to loosen or tighten, so as to fit and support or move away from the rocket. When the force on the sling 7 reaches the predetermined tension of the tension sensor 4, the tightening and loosening electric cylinder 8 stops working, and the sling 7 is in place. By adjusting the angle of the tilting frame 2 and the tightening force, it can adapt to the changes in the diameter and weight of the rocket. The flexible support frame is in full contact with the rocket surface, with uniform force, and has the characteristics of strong adaptability and automation.

[0041] The above are only the preferred embodiments of the present invention, and do not limit the patent scope of the present invention accordingly. Any equivalent structural transformation made under the concept of the present invention by using the content of the specification and drawings of the present invention, or directly / indirectly applied in other related technical fields, is included in the patent protection scope of the present invention.

Claims

1. A fully automatic flexible rocket support mechanism, characterized in that: It includes two oppositely arranged mounting seats (12). A tipping frame (2) and a tipping electric cylinder (1) are respectively hinged to the front and rear of the mounting seat (12). The upper end of the tipping frame (2) is hinged to the output shaft of the tipping electric cylinder (1). A sling (7) is installed between the two tipping frames (2), and the sling (7) is used to support the rocket.

2. The fully automatic flexible rocket support mechanism according to claim 1, wherein: A tightening and loosening electric cylinder (8) is installed at the lower end of the tipping frame (2). The output shaft of the tightening and loosening electric cylinder (8) is connected with a tightening and loosening sliding shaft (3). The tightening and loosening sliding shaft (3) is slidably installed on the tipping frame (2). The tightening and loosening electric cylinder (8) drives the tightening and loosening sliding shaft (3) to slide along the length direction of the tipping frame (2). A sling pulley (6) is installed at the top end of the tipping frame (2). The sling (7) passes through the sling pulley (6) and is fixed on the tightening and loosening sliding shaft (3).

3. The fully automatic flexible rocket support mechanism according to claim 1, wherein: An accommodation cavity (14) is formed between the two tipping arms of the tipping frame (2).

4. The fully automatic flexible rocket support mechanism according to claim 3, characterized in that: Sliding guide rails (15) are respectively formed along the length direction of the two tipping arms of the tipping frame (2). The two ends of the tightening and loosening sliding shaft (3) are respectively inserted into the two sliding guide rails (15). At the same time, the tightening and loosening sliding shaft (3) moves along the length direction of the accommodation cavity (14).

5. The fully automatic flexible rocket support mechanism according to claim 2, characterized in that: Multiple limiting rods (16) are arranged at the upper end part of the tipping frame (2). The length direction of the limiting rods (16) is the same as the axial direction of the sling pulley (6). The multiple limiting rods (16) semi-surround the sling pulley (6). The sling (7) shuttles between the limiting rods (16) and the sling pulley (6).

6. The fully automatic flexible rocket support mechanism according to claim 2, wherein: A tension sensor (4) is arranged between the upper fulcrum of the output shaft of the tightening and loosening electric cylinder (8) and the tightening and loosening sliding shaft (3).

7. The fully automatic flexible rocket support mechanism according to claim 1, characterized in that: A position sensor (11) is arranged at the installation position of the mounting seat (12) and the tipping frame (2).

8. The fully automatic flexible rocket support mechanism according to claim 1, characterized in that: On the opposite sides of the two tipping frames (2), a triangular stabilizer (17) is fixedly installed. The end angles of the triangular stabilizer (17) are hinged to the output shaft of the tipping electric cylinder (1) through a pin shaft one (5).

9. The fully automatic flexible rocket support mechanism according to claim 1, wherein: Multiple mounting holes (18) are provided at the bottom of the mounting seat (12).

10. The fully automatic flexible rocket support mechanism according to claim 2, wherein: The tightening and loosening electric cylinder (8) is installed at the bottom end of the tipping frame (2) through a pin shaft two (9).

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