Buffering and speed reducing mechanism of launching device of unmanned aerial vehicle

Abstract

The embodiment of the invention provides an unmanned aerial vehicle launching device buffering and speed reducing mechanism which is used in cooperation with an unmanned aerial vehicle launching device track, and the track comprises a track acceleration section and a track buffering section which are provided with a first fixed pulley and a second fixed pulley at the close ends correspondingly; the buffer speed reducing mechanism is arranged below a track buffer section and comprises a fixed supporting framework, a buffer speed reducing mechanism and a buffer speed reducing mechanism, and the fixed supporting framework is fixedly connected with the track buffer section; the mandrel is arranged on the fixed supporting framework, and one end of the mandrel is fixedly connected with the fixed supporting framework; the sliding welding plate is connected with the other end of the mandrel; the movable pulley is arranged on the sliding welding plate; according to the unmanned aerial vehicle launching device, a traction belt driven by a motor sequentially winds around a movable pulley and a first fixed pulley to conduct traction acceleration on a carrying tackle arranged on a track acceleration section, and after the carrying tackle slides to a track buffer section, the traction belt is separated from the first fixed pulley and winds around a second fixed pulley to generate pressing force on the movable pulley; the movable pulley is pressed to drive the sliding welding plate to move towards the motor side along the mandrel.

Description

Technical Field

[0001] The present invention relates to the field of shipborne aviation technology, in particular to a fixed-wing UAV launch device, and in particular to a buffering and deceleration mechanism of the UAV launch device. Background Art

[0002] As an important force in the future naval battlefield, shipborne drones have obvious advantages in maritime early warning reconnaissance, intelligence collection, communication relay, battlefield assessment, etc., and will become the key development direction of the navies of various countries in the future. The drone launcher is an important device for drones to achieve short-distance flight, especially in non-direct access narrow deck environments such as destroyers and frigates. The distance to achieve drone acceleration and deceleration is very valuable. Among them, the deceleration buffer mechanism of the drone launcher is an important part of the drone launcher. It can realize the rapid braking of the sliding trolley carrying the drone in a short distance, thereby realizing the function of buffering and decelerating or stopping the sliding trolley in a limited space.

[0003] There are two main ways for the existing UAV launcher carrier pulley to achieve buffering and stopping after acceleration:

[0004] One method is to directly hit the buffer device installed at the end of the launch device track after the carrier pulley is accelerated to achieve buffering. This method has a simple structure, but the buffer device needs to be replaced regularly; at the same time, because the carrier pulley is stopped at a very short distance, the impact force of the carrier pulley is relatively large. For details, see patent CN260984420.

[0005] Another type is that the carrying pulley is connected to the pulley through a traction belt at one end and connected to the hydraulic motor at the other end. Figure 1 As shown, when launching a UAV, during the movement of the carrier pulley from P0 to P1, the accumulator releases energy to drive the motor to rotate faster, and the carrier pulley and the UAV accelerate. When the carrier pulley moves to point P2, the motor drags the traction belt so that the force on the pulley changes from force to resistance. Under the action of the traction belt resistance, the carrier pulley moves from P2 to P3 until the speed becomes 0. This UAV launch device has the following problems: during the movement of the carrier pulley from point P1 to P2, there must be a point where the force of the traction belt on the carrier pulley suddenly changes direction without buffering, resulting in the traction force vertically downward at this time, causing the carrier pulley to be subjected to excessive force, affecting the reliability of the equipment. Summary of the invention

[0006] In view of the above-mentioned problems existing in the prior art, an embodiment of the present invention provides a buffering and deceleration mechanism for a UAV launch device, which adopts a movable pulley device for adjustment, so as to achieve buffering and deceleration of the carrying pulley when the traction force reaches the maximum, and the hydraulic motor drives the deceleration to buffer and decelerate the UAV.

[0007] An embodiment of the present invention provides a buffer deceleration mechanism for a drone launch device, wherein the buffer deceleration mechanism for the drone launch device is used in conjunction with a drone launch device track, wherein the drone launch device track comprises a track acceleration section and a track buffer section, wherein the track acceleration section and the track buffer section are respectively provided with a first fixed pulley and a second fixed pulley at adjacent ends;

[0008] The buffer deceleration mechanism of the UAV launch device is arranged below the track buffer section, and includes:

[0009] A fixed support structure, which is fixedly connected to the track buffer section;

[0010] A core shaft, which is arranged on the fixed support structure and has one end fixedly connected to the fixed support structure;

[0011] a sliding welding plate connected to the other end of the mandrel;

[0012] A movable pulley, which is arranged on the sliding welding plate;

[0013] Among them, the UAV launching device is driven by a motor and the traction belt is sequentially wound around the movable pulley. The first fixed pulley pulls and accelerates the carrying pulley arranged on the track acceleration section. After the carrying pulley slides to the track buffer section, the traction belt is separated from the first fixed pulley and arranged around the second fixed pulley, thereby generating a clamping force on the movable pulley, pressing the movable pulley to drive the sliding welding plate to move along the core axis toward the motor side, thereby increasing the buffer distance.

[0014] In some embodiments of the present invention, a portion of the sliding welding plate through which the traction belt wound around the movable pulley passes is provided with a groove for the traction belt to pass through.

[0015] In some embodiments of the present invention, the sliding welding plate is arranged in an H-shape, and two openings corresponding to the H-shaped structure are used for the traction belt to pass through.

[0016] In some embodiments of the present invention, a self-lubricating copper sleeve is provided between the sliding welding plate and the core shaft to reduce the contact friction between the sliding welding plate and the inner wall of the track buffer section.

[0017] In some embodiments of the present invention, upper and lower sliders and left and right sliders are installed on the contact surface between the sliding welding plate and the inner wall of the track buffer section, so that the movable pulley and the sliding welding plate can move smoothly along the core shaft.

[0018] In some embodiments of the present invention, the fixed support structure is specifically a base plate fixedly connected to the track buffer section, and one end of the core shaft is provided with a thread and fixedly connected to the base plate with bolts, and the other end of the core shaft is also provided with a thread and connected to the sliding welding plate through the thread.

[0019] In some embodiments of the present invention, there are at least two core shafts, and each core shaft is sleeved with a spring, and the spring is in an original length state between the sliding welding plate and the bottom plate.

[0020] In some embodiments of the present invention, the moving direction of the movable pulley is parallel to the track directions of the track acceleration section and the track buffer section.

[0021] Compared with the prior art, the beneficial effect of the buffer and deceleration mechanism of the drone launch device provided by the embodiment of the present invention is that it adds a set of movable pulleys and a buffer and deceleration mechanism used in combination with spring buffer in the buffer track segment. The buffer compression distance provided by the buffer stop mechanism spring increases the braking length of the traction belt under limited resource space, reduces the instantaneous force on the carrying pulley, improves the reliability of the ejection device, and extends the life of the equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a simple schematic diagram of UAV launch in the prior art;

[0023] Figure 2a A schematic diagram of the winding direction of the traction belt around the fixed pulley and the movable pulley of the buffer deceleration mechanism of the UAV launch device provided by the embodiment of the present invention during the acceleration process of the UAV and the acceleration movement of the UAV and the carrying pulley;

[0024] Figure 2b A schematic diagram of the direction of the traction belt of the UAV launch device buffering and deceleration mechanism winding around the fixed pulley and the movable pulley of the buffering and deceleration mechanism after the UAV is separated from the carrying pulley provided in an embodiment of the present invention;

[0025] Figure 3 A schematic diagram of the partial structure of the buffer deceleration mechanism of the UAV launch device provided by an embodiment of the present invention;

[0026] Figure 4 A schematic diagram of the side structure of the buffer deceleration mechanism of the UAV launch device provided by an embodiment of the present invention installed in the buffer track segment;

[0027] Figure 5 A schematic diagram of a top view of the structure of a buffer deceleration mechanism of a UAV launch device provided by an embodiment of the present invention installed in a buffer track segment;

[0028] Figure 6A partial schematic diagram of the connection position between the sliding welding plate and the mandrel of the buffer deceleration mechanism of the UAV launch device provided by an embodiment of the present invention;

[0029] Figure 7 An overall schematic diagram of a sliding welding plate in a buffer deceleration mechanism of a UAV launch device provided by an embodiment of the present invention;

[0030] Figure 8 A schematic diagram of the upper and lower sliders of the sliding welding plate in the buffering and deceleration mechanism of the drone launch device provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0031] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention is described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0032] Various aspects and features of the present application are described herein with reference to the accompanying drawings.

[0033] These and other characteristics of the present application will become apparent from the following description of a preferred form of embodiment given as a non-limiting example with reference to the accompanying drawings.

[0034] It should also be understood that, although the present application has been described with reference to some specific examples, those skilled in the art will be able to realize many other equivalent forms of the present application that have the features described in the claims and are therefore within the scope of protection defined thereby.

[0035] The above and other aspects, features and advantages of the present application will become more apparent in view of the following detailed description when taken in conjunction with the accompanying drawings.

[0036] Specific embodiments of the present application are described hereinafter with reference to the accompanying drawings; however, it should be understood that the embodiments applied for are merely examples of the present application, which may be implemented in a variety of ways. Well-known and / or repeated functions and structures are not described in detail to determine the true intent based on the user's historical operations and to avoid unnecessary or redundant details that make the present application unclear. Therefore, the specific structural and functional details applied for herein are not intended to be limiting, but are merely used as the basis and representative basis for the claims to teach those skilled in the art to use the present application in a variety of ways with substantially any suitable detailed structure.

[0037] This specification may use the phrases "in one embodiment," "in another embodiment," "in yet another embodiment," or "in other embodiments," all of which may refer to one or more of the same or different embodiments according to the present application.

[0038] The embodiment of the present invention provides a buffer deceleration mechanism for a UAV launch device, such as Figures 1 to 8As shown, the buffer deceleration mechanism of the UAV launch device is used in conjunction with the UAV launch device track. The UAV launch device track includes a track acceleration section and a track buffer section 9. The track acceleration section and the track buffer section 9 are respectively provided with a first fixed pulley and a second fixed pulley at one end close to each other.

[0039] The buffer deceleration mechanism of the UAV launch device is arranged below the track buffer section 9, and includes:

[0040] A fixed support structure, which is fixedly connected to the track buffer section 9;

[0041] A core shaft 2, which is arranged on the fixed support structure, and one end of which is fixedly connected to the fixed support structure;

[0042] a sliding welding plate 7 connected to the other end of the mandrel 2;

[0043] A movable pulley 8, which is arranged on the sliding welding plate 7;

[0044] Among them, the UAV launching device is driven by a motor and the traction belt 10 is sequentially wound around the movable pulley 8. The first fixed pulley pulls and accelerates the carrying pulley arranged on the track acceleration section. After the carrying pulley slides to the track buffer section 9, the traction belt 10 is separated from the first fixed pulley and arranged around the second fixed pulley, thereby generating a clamping force on the movable pulley 8, pressing the movable pulley 8 to drive the sliding welding plate 7 to move along the core shaft 2 toward the motor side, thereby increasing the buffer distance.

[0045] In this embodiment, the sliding welding plate 7 has a slot for passing the traction belt 10 through the portion through which the traction belt 10 wound around the movable pulley 8 passes. As an example, the sliding welding plate 7 can be arranged in an H-shape, and the two openings corresponding to the H-shape structure are used for passing the traction belt 10.

[0046] In some embodiments of the present invention, a self-lubricating copper sleeve 4 is provided between the sliding welding plate 7 and the core shaft 2 to reduce the contact friction between the sliding welding plate 7 and the inner wall of the track buffer section 9 .

[0047] In this embodiment, upper and lower sliders 5 and left and right sliders 6 are installed on the contact surface between the sliding welding plate 7 and the inner wall of the track buffer section 9, so that the movable pulley 8 and the sliding welding plate 7 can move smoothly along the core shaft 2.

[0048] In some embodiments of the present invention, the fixed support structure is specifically a base plate 1 fixedly connected to the track buffer segment 9, and one end of the core shaft 2 is provided with a thread and fixedly connected to the base plate 1 with bolts, and the other end of the core shaft 2 is also provided with a thread and connected to the sliding welding plate 7 through the thread.

[0049] In this embodiment, there are at least two core shafts 2 , and each core shaft 2 is sleeved with a spring 3 , and the spring 3 is in an original length state between the sliding welding plate 7 and the bottom plate 1 .

[0050] In some embodiments of the present invention, the moving direction of the movable pulley 8 is parallel to the track direction of the track acceleration section and the track buffer section 9 .

[0051] It can be known from the above technical scheme that the buffering and deceleration mechanism of the drone launching device provided by the above embodiment of the present invention adds a set of movable pulleys 8 and a buffering and deceleration mechanism used in combination with the spring 3 in the buffer track segment. The buffering compression distance provided by the buffer stop mechanism spring 3 increases the braking length of the traction belt 10 under limited resource space, reduces the instantaneous force on the carrying pulley, improves the reliability of the ejection device, and extends the life of the equipment.

[0052] In order to facilitate the understanding of the above technical solution, the following is a detailed description with reference to specific examples, as follows:

[0053] The above-mentioned UAV launch buffer device adds a buffer deceleration mechanism used in combination with a pulley and a spring buffer to the original launch device buffer track section, such as Figure 2a and Figure 2b The buffer deceleration mechanism is fixedly connected to the launch track and installed below the launch track. Figure 2a This is the winding diagram of the traction belt around the first fixed pulley and the movable pulley of the buffer reduction mechanism during the acceleration movement of the UAV and the carrier pulley. Figure 2b After the UAV is separated from the carrier pulley, the traction belt is wound around the second fixed pulley and the movable pulley of the buffer reduction mechanism. The moving direction of the movable pulley of the buffer reduction mechanism is parallel to the launch device track. The buffer reduction mechanism is fixed in the track. One end of the traction belt is connected to the pulley, and the other end is connected to the hydraulic motor through the movable pulley device. The accumulator drives the motor, which drives the launch pulley to move on the track through the drum and traction belt.

[0054] The buffer reduction mechanism used with pulley and spring buffer is composed of bottom plate 1, core shaft 2, spring 3, copper sleeve 4, upper and lower sliders 5, left and right sliders 6, sliding welding plate 7 and movable pulley 8. For details, please refer to Figures 3 to 8As shown. The bottom plate 1 is welded and fixedly connected with the buffer section track 9 to provide support for the buffer deceleration mechanism. The core shaft 2 is provided with threads at both ends, one end is fixedly connected with the bottom plate 1 by bolts, and the other end is connected with the sliding welding plate 7 by bolts. There are 4 threads at both ends of the core shaft 2, each of which is sleeved with a spring 3. The spring 3 is in the original length state between the sliding welding plate 7 and the bottom plate 1. The movable pulley 8 is fixedly connected with the sliding welding plate 7. The sliding welding plate 7 is an "H-shaped" structure as a whole, in which the upper and lower parts are grooved to facilitate the smooth passage of the traction belt 10. A self-lubricating copper sleeve 4 is provided between the sliding welding plate 7 and the core shaft 2, and the contact surface between the sliding welding plate 7 and the inner wall of the track buffer section 9 is installed with upper and lower sliders 5 and left and right sliders 6, so that the movable pulley 8 and the sliding welding plate 7 have a good guiding effect when moving toward the bottom plate 1 to avoid jamming. At the same time, the self-lubricating copper sleeve 4 can reduce the contact friction between the sliding welding plate 7 and the inner wall of the track buffer section 9.

[0055] After the UAV is separated from the carrying pulley, the carrying pulley enters the deceleration buffer stage, the traction belt 10 presses the movable pulley 8, and the movable pulley 8 transfers the pressure to the spring 3 through the sliding welding plate 7. The sliding welding plate 7 moves toward the bottom plate 1 under the guidance of the core shaft 2, thereby increasing the buffer distance in a limited space.

[0056] The above embodiments are only exemplary embodiments of the present invention and are not intended to limit the present invention. The protection scope of the present invention is defined by the claims. Those skilled in the art may make various modifications or equivalent substitutions to the present invention within the essence and protection scope of the present invention, and such modifications or equivalent substitutions shall also be deemed to fall within the protection scope of the present invention.

Claims

1. A buffer deceleration mechanism for a UAV launch device, characterized in that: The buffer deceleration mechanism of the UAV launch device is used in conjunction with the UAV launch device track. The UAV launch device track includes a track acceleration section and a track buffer section. The track acceleration section and the track buffer section are respectively provided with a first fixed pulley and a second fixed pulley at one end close to each other. The buffer deceleration mechanism of the UAV launch device is arranged below the track buffer section, and includes: A fixed support structure, which is fixedly connected to the track buffer section; A core shaft, which is arranged on the fixed support structure and has one end fixedly connected to the fixed support structure; a sliding welding plate connected to the other end of the mandrel; A movable pulley, which is arranged on the sliding welding plate; Among them, the UAV launching device is driven by a motor and the traction belt is sequentially wound around the movable pulley. The first fixed pulley pulls and accelerates the carrying pulley arranged on the track acceleration section. After the carrying pulley slides to the track buffer section, the traction belt is separated from the first fixed pulley and arranged around the second fixed pulley, thereby generating a clamping force on the movable pulley, pressing the movable pulley to drive the sliding welding plate to move along the core axis toward the motor side, thereby increasing the buffer distance.

2. The buffer deceleration mechanism of the UAV launch device according to claim 1 is characterized in that: The portion of the sliding welding plate through which the traction belt wound around the movable pulley passes is provided with a groove for the traction belt to pass through.

3. The buffer deceleration mechanism of the UAV launch device according to claim 2 is characterized in that: The sliding welding plate is arranged in an H shape, and two openings corresponding to the H shape structure are used for the traction belt to pass through.

4. The buffer deceleration mechanism of the UAV launch device according to claim 2 is characterized in that: A self-lubricating copper sleeve is provided between the sliding welding plate and the core shaft to reduce the contact friction between the sliding welding plate and the inner wall of the track buffer section.

5. The buffer deceleration mechanism of the UAV launch device according to claim 4 is characterized in that: The contact surface between the sliding welding plate and the inner wall of the track buffer section is equipped with upper and lower sliders and left and right sliders, so that the movable pulley and the sliding welding plate can move smoothly along the core shaft.

6. The buffer deceleration mechanism of the UAV launch device according to claim 1, characterized in that: The fixed support structure is specifically a base plate fixedly connected to the track buffer section, and one end of the core shaft is provided with a thread and fixedly connected to the base plate with a bolt, and the other end of the core shaft is also provided with a thread and connected to the sliding welding plate through the thread.

7. The buffer deceleration mechanism of the UAV launch device according to claim 6 is characterized in that: There are at least two core shafts, and each core shaft is sleeved with a spring, and the spring is in an original length state between the sliding welding plate and the bottom plate.

8. The buffer deceleration mechanism of the drone launch device according to claim 1, characterized in that: The moving direction of the movable pulley is parallel to the track directions of the track acceleration section and the track buffer section.

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