A highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbances

Abstract

The patent of the present invention discloses a highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbances, specifically relating to the field of aerial docking technology. It includes a mounting flange, which can be connected to a docking mechanism by bolts, a rubber block provided on one side of the mounting flange, a connecting tube provided on one side of the rubber block, and through holes interconnected on the mounting flange, a limiting rod provided in the through hole, one end of the limiting rod is threadedly connected to a first slider, the first slider is slidably connected to the mounting flange, the other end of the limiting rod is covered with a second slider, a butterfly spring covered on the outside of the limiting rod is connected between the second slider and the limiting rod, a buffer mechanism is provided on the connecting tube, a guide rod is provided on the buffer mechanism, and the buffer mechanism is used to provide a buffering force for the guide rod during docking. The technical solution of the present invention solves the problem of how to successfully complete the docking of two spacecraft while ensuring the structural safety and attitude stability of the spacecraft, and can effectively reduce the adverse effects of the docking collision force.

Description

Technical Field

[0001] The present invention relates to the technical field of aerial docking, and in particular to a highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbance. Background Art

[0002] Aerial docking technology is the key to achieving a variety of aviation missions and operations. It makes it possible for aircraft to carry out tasks such as refueling, material supply, and emergency rescue in the air, greatly expanding the scope and flexibility of aviation missions.

[0003] However, the disturbances encountered by the aircraft while flying in the air (such as airflow, heading changes, etc.) will increase the difficulty of docking. The flexible docking rod can effectively reduce the negative impact caused by the position error and relative speed between the end of the docking rod and the capture point of the target in a disturbed environment. The principle is that the flexible design can make the docking rod have a certain deformation at the initial stage of contact, thereby avoiding violent collision between the docking surfaces and reducing vibration and impact. However, the flexibility of the docking rod cannot be too large, otherwise it may cause the docking rod to be unable to be inserted into the docking slot in a short time, resulting in docking failure and causing adverse consequences.

[0004] In summary, how to ensure the smooth docking of two spacecraft in a disturbed environment and ensure the structural safety and attitude stability of the spacecraft has become a key issue in the air docking process. Summary of the Invention

[0005] The present invention aims to provide a highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbances, which solves the problem of how to successfully complete the docking of two spacecraft under the premise of ensuring the structural safety and attitude stability of the spacecraft in a disturbed environment.

[0006] In order to achieve the above-mentioned purpose, the technical solution of the present invention is as follows: A highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbances, comprising a mounting flange, the mounting flange being capable of being connected to a docking mechanism by bolts, a rubber block being provided on one side of the mounting flange, a connecting tube being provided on one side of the rubber block, the mounting flange, the rubber block and the connecting tube being commonly provided with mutually interconnected through holes, a limiting rod being provided in the through hole, one end of the limiting rod being threadedly connected to a first slider, the first slider being slidably connected to the mounting flange, the other end of the limiting rod being covered with a second slider, the second slider being located in the connecting tube, a butterfly spring covered outside the limiting rod being connected between the second slider and the limiting rod, a buffer mechanism being provided on the connecting tube, a guide rod being provided on the buffer mechanism, and the buffer mechanism being used to provide buffering force for the guide rod during docking.

[0007] Furthermore, a first spherical surface is provided in both the mounting flange and the connecting tube, and a second spherical surface is provided in both the first sliding block and the second sliding block to match the first spherical surface.

[0008] With this arrangement, the second spherical surface on the first slider is in frictional contact with the first spherical surface on the mounting flange. When the docking rod is subjected to a circumferential impact, the first slider can slide on the spherical surface of the mounting flange. The low coefficient of friction between the two spherical surfaces reduces frictional resistance and enhances the cushioning effect. Similarly, the second spherical surface on the second slider is in frictional contact with the first spherical surface in the connecting tube. When the docking rod is subjected to a circumferential impact, the second slider can slide on the first spherical surface of the connecting tube. The low coefficient of friction between the two spherical surfaces reduces frictional resistance and enhances the cushioning effect.

[0009] Furthermore, the mounting flange and the connecting tube are both provided with grooves that match the rubber block.

[0010] Furthermore, the end of the guide rod adopts a third spherical surface.

[0011] Through the above arrangement, the third spherical surface can be used to increase the contact area during docking, thereby dispersing the force, reducing local stress concentration, and improving overall durability and safety.

[0012] Furthermore, the upper end of the first sliding block is in the shape of a regular hexagonal prism, and the head of the limiting rod is provided with a hexagonal groove.

[0013] Through the above arrangement, the present invention is easy to disassemble and assemble, has a large load-bearing capacity, and is convenient for tightening the limit rod to compress the disc spring, thereby applying a larger preload force, thereby expanding the adjustment range of the flexible docking rod.

[0014] Furthermore, the buffer mechanism includes a movable rod, which is connected to the connecting tube by a connecting bolt. A movable cylinder is frictionally connected to the movable rod. The inner wall of the movable cylinder is frictionally connected to the outer wall of the movable rod. The movable cylinder is connected to the guide rod screw, and a compression spring is provided between the movable rod and the guide rod.

[0015] Furthermore, mounting step surfaces are cut on both sides of the connecting cylinder, and the movable rod and the corresponding part on the movable rod are commonly threadedly connected with connecting bolts arranged on the mounting step surfaces, and the connecting bolts connect the movable rod and the movable cylinder together through nuts and washers.

[0016] Compared with the existing technology, this solution has the following beneficial effects:

[0017] 1. This solution incorporates passive compliance technology into the docking rod, allowing it to naturally comply with the applied force during docking, effectively reducing force transmission and preventing the adverse consequences caused by excessive contact force. Stringent requirements are also placed on the rod's flexibility. Too little flexibility may result in insufficient cushioning and an inability to effectively reduce force transmission, while too much flexibility may prevent the rod from accurately inserting into the docking slot within the specified time, thus affecting the successful completion of the docking process. Therefore, the rod's adjustable flexibility, which allows it to be adjusted under different docking conditions to achieve optimal cushioning and docking accuracy, is crucial to ensuring successful aerial docking.

[0018] 2. The docking rod of this solution has the function of adjustable flexibility, which solves the problem that the existing docking rod is difficult to adjust the flexibility of the rod according to the working environment and achieve omnidirectional buffering, and can effectively reduce the adverse effects of the docking collision force. By controlling the depth of the limit rod screwed into the first slider, the compression of the disc spring is controlled, thereby controlling the size of the preload force. By controlling the preload force, the difficulty of the first slider and the second slider sliding on the corresponding spherical surface can be adjusted, thereby controlling the flexibility of the docking rod. At the same time, the flexibility of the docking rod can be further adjusted by using rubber blocks and disc springs of different hardness. The docking rod has the function of adjustable flexibility, so that its flexibility can be adjusted under different docking conditions to achieve the best buffering effect and docking accuracy.

[0019] 3. In this solution, the disc spring plays two roles: first, when the end of the docking rod is impacted, the first slider and the second slider slide on the corresponding first spherical surface, so that the distance between the second slider and the head of the limit rod becomes smaller, thereby compressing the disc spring, thereby achieving the effect of absorbing energy and buffering; second, the compression amount of the disc spring can be controlled by controlling the depth of the limit rod screwed into the first slider, that is, the size of the preload force can be controlled, so as to adjust the difficulty of the two sliders sliding on the corresponding spherical surface, thereby achieving the effect of controlling the flexibility of the docking rod.

[0020] 4. This solution has complete rotational symmetry along the axis of the docking rod, such as the rubber block, the first slider, the second slider, the movable rod, the movable cylinder, etc. Therefore, the docking rod can achieve a uniform and consistent buffering effect in the circumferential direction. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is an axonometric view of a highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbances according to the present invention;

[0022] Figure 2 This is a cross-sectional view of a highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbances according to the present invention;

[0023] Figure 3This is a schematic diagram of the mounting flange structure of a highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbances according to the present invention;

[0024] Figure 4 This is a schematic diagram of the connecting tube structure of a highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbances according to the present invention;

[0025] Figure 5 The present invention is a schematic diagram of the movable cylinder structure of a highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbance. DETAILED DESCRIPTION

[0026] The present invention will be further described in detail below through specific embodiments:

[0027] The figure marks in the drawings of the specification include: mounting flange 1, first slider 2, rubber block 3, limit rod 4, connecting tube 5, second slider 6, disc spring 7, movable rod 8, movable cylinder 9, compression spring 10, guide rod 11, screw 12, bolt 13, nut 14, washer 15, threaded hole 16, and mounting step surface 17.

[0028] Example

[0029] like Figures 1 to 5 As shown, a highly adaptable, flexible, and adjustable omnidirectional buffer docking rod for aircraft disturbances includes a mounting flange 1 with threaded holes 16 defined at each of its four corners. The mounting flange 1 can be connected to the end of a docking mechanism via threaded holes 16 and bolts 13. The size of the threaded holes 16 can be adjusted based on the actual operating environment. A square groove is defined at the bottom of the mounting flange 1, within which a rubber block 3 is positioned. A connecting tube 5 is located on one side of the rubber block 3, and a groove is defined at the top of the connecting tube 5 for mating with the rubber block 3. A coaxial through-hole is defined between the mounting flange 1, the rubber block 3, and the connecting tube 5. A stopper 4, smaller than the inner diameter of the through-hole, is located within the through-hole. The upper end of the stopper 4 is threadedly connected to a first slider 2, which is a regular hexagonal prism with dimensions consistent with a national standard hexagonal nut 14. The first slider 2 is slidably connected to the mounting flange 1. A first spherical surface is defined at the top of the mounting flange 1 for sliding movement of the first slider 2, and a second spherical surface is defined on the first slider 2 for mating with the first spherical surface of the mounting flange 1. The lower end of the limiting rod 4 is covered with a second slider 6, the center of which is defined by a through-hole that covers the outside of the limiting rod 4. The second slider 6 is located within the connecting tube 5, and the top wall of the connecting tube 5 is provided with a first spherical surface. The second slider 6 also has a second spherical surface that mates with the first spherical surface of the connecting tube 5. The head of the limiting rod 4 is provided with a hexagonal slot that meets the national standard for internal hexagonal dimensions. Eight disc springs 7, covering the outside of the limiting rod 4, are connected between the second slider 6 and the head of the limiting rod 4.

[0030] The connecting tube 5 is provided with a buffer mechanism, which is equipped with a guide rod 11. The end of the guide rod 11 adopts a third spherical surface. The buffer mechanism is used to provide a buffering force for the guide rod 11 during docking. The buffer mechanism includes a movable rod 8, which is fixedly connected to the connecting tube 5 by a connecting bolt 13. The lower end of the connecting tube 5 is cut with a mounting step surface 17 on both sides. The movable rod 8 and the corresponding part on the movable rod 8 are threadedly connected to the connecting bolt 13 set on the mounting step surface 17. The connecting bolt 13 connects the movable rod 8 to the movable cylinder 9 via a nut 14 and a washer 15. The mounting step surface 17 facilitates the installation of the connecting bolt 13, nut 14, and washer 15. The lower side of the movable rod 8 is frictionally connected to a movable cylinder 9. The lower end of the movable rod 8 passes through the movable cylinder 9 and is located inside the movable cylinder 9. The inner wall of the movable cylinder 9 is frictionally connected to the outer wall of the movable rod 8. The lower end of the movable cylinder 9 has six threaded holes 16 evenly distributed around the circumference. When the end of the docking rod is subjected to a vertical impact, the movable cylinder 9 can slide vertically upward along the movable rod 8. The friction coefficient of the contact surface between the two is low, thereby reducing frictional resistance and increasing the cushioning effect. The movable rod 8 is connected to the guide rod 11 via a screw 12 and a threaded hole 16. A compression spring 10 is in contact between the movable rod 8 and the guide rod 11.

[0031] The specific working process of this program is as follows:

[0032] By controlling the depth of the stopper rod 4 screwed into the first slider 2, the distance between the head of the stopper rod 4 and the second slider 6 is controlled, thereby controlling the compression of the disc spring 7. This allows for adjustment of the preload force. A greater preload force makes it more difficult for the first and second sliders 2 and 6 to slide, and the docking rod's flexibility decreases. Conversely, a lower preload force increases the docking rod's flexibility. Furthermore, the docking rod's flexibility can be adjusted by replacing the rubber block 3 and disc spring 7 with different hardnesses. Therefore, in practice, the docking rod's flexibility can be adjusted to suit different work tasks to achieve optimal cushioning and docking accuracy.

[0033] When the docking rod is subjected to a circumferential impact, it bends under force, causing the rubber block 3 to absorb energy through localized compression, thus providing a cushioning effect. Simultaneously, the first and second sliders 2 and 6 slide on their corresponding first spherical surfaces, reducing the distance between the second slider 6 and the head of the stop rod 4. This further compresses the disc spring 7, creating a multiple cushioning effect. When the impact force dissipates, the elasticity of the rubber block 3 and disc spring 7 allows the docking rod to automatically return to its original position within a short period of time.

[0034] Furthermore, when the docking rod is subjected to a vertical impact, the compression spring 10 in the movable cylinder 9 compresses to buffer energy consumption. To prevent the compression spring 10 from tipping or shifting, a certain preload is applied to the compression spring 10. Specifically, when not subjected to an impact, the distance from the bottom of the movable rod 8 to the top of the guide rod 11 is less than the original length of the compression spring. In this example, the distance from the bottom of the movable rod 8 to the top of the guide rod 11 is 40 mm, and the original length of the compression spring is 42 mm, with a preload of 2 mm. Furthermore, an appropriate preload also allows the compression spring 10 to return to its original state more quickly upon further compression and eliminates vibration.

[0035] The above are only embodiments of the present invention, and common knowledge such as the specific structure and / or characteristics of the scheme are not described in detail here. It should be pointed out that for those skilled in the art, without departing from the structure of the present invention, several variations and improvements can be made, which should also be regarded as the scope of protection of the present invention, and these will not affect the effect of the implementation of the present invention and the practicality of the patent. The scope of protection required by this application shall be based on the content of its claims, and the specific implementation methods and other records in the specification can be used to interpret the content of the claims.

Claims

1. A highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbances, characterized by: The invention comprises a mounting flange (1), wherein the mounting flange (1) can be connected to a docking mechanism by bolts, a rubber block (3) is provided on one side of the mounting flange (1), a connecting tube (5) is provided on one side of the rubber block (3), a through hole communicating with each other is provided on the mounting flange (1), a limiting rod (4) is provided in the through hole, one end of the limiting rod (4) is threadedly connected to a first slider (2), the first slider (2) is slidably connected to the mounting flange (1), the other end of the limiting rod (4) is covered with a second slider (6), the second slider (6) is located in the connecting tube (5), a butterfly spring (7) covered on the outside of the limiting rod (4) is connected between the second slider (6) and the limiting rod (4), a buffer mechanism is provided on the connecting tube (5), a guide rod (11) is provided on the buffer mechanism, and the buffer mechanism is used to provide a buffering force for the guide rod (11) during docking; The mounting flange (1) and the connecting cylinder (5) are both provided with a first spherical surface, and the first slider (2) and the second slider (6) are both provided with a second spherical surface that matches the first spherical surface; The buffer mechanism comprises a movable rod (8), the movable rod (8) being connected to the connecting cylinder (5) via a connecting bolt (13), a movable cylinder (9) being frictionally connected to the movable rod (8), an inner wall of the movable cylinder (9) being frictionally connected to an outer wall of the movable rod (8), the movable cylinder (9) being connected to a guide rod (11) via a screw (12), and a compression spring (10) being provided between the movable rod (8) and the guide rod (11).

2. The highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbance according to claim 1, characterized in that: The mounting flange (1) and the connecting tube (5) are both provided with grooves that match the rubber block (3).

3. The highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbance according to claim 1, characterized in that: The end of the guide rod (11) adopts a third spherical surface.

4. The highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbances according to claim 1, characterized in that: The upper end of the first sliding block (2) is in the shape of a regular hexagonal prism, and the head of the limiting rod (4) is provided with a hexagonal groove.

5. The highly adaptable, flexible, adjustable, omnidirectional buffer docking rod under aircraft disturbance according to claim 1, characterized in that: Both sides of the connecting cylinder (5) are cut with mounting step surfaces (17), and the movable rod (8) and the corresponding portion on the movable rod (8) are threadedly connected with a connecting bolt (13) provided on the mounting step surface (17), and the connecting bolt (13) connects the movable rod (8) and the movable cylinder (9) together through a nut (14) and a washer (15).

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