Automatic positioning and blade retraction mechanism for rotorcraft

Abstract

The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to an automatic positioning and blade-retracting mechanism for a rotorcraft, comprising: a platform placed in a charging box for providing a docking position for the UAV; a clamping assembly arranged on the platform for clamping and fixing the UAV after docking; a plurality of blade-retracting assemblies, wherein the plurality of blade-retracting assemblies are respectively located on each side of the platform. In the present invention, a design of automatically resisting a rocker arm is adopted in the process of positioning the UAV by a clamping rod, and the linked design has higher movement accuracy and lower manufacturing cost. At the same time, a design of four clamping rods is adopted to ensure synchronous clamping of the UAV to ensure that the UAV is positioned in the upper middle part of the platform. Thereafter, the driving force generated by the movement of the clamping rod drives the rocker arm to move to position and retract the blades on the UAV to avoid the problem of the blades protruding from the outside of the platform and being damaged by impact during descent.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to an automatic positioning and blade-retracting mechanism for a rotorcraft. Background Art

[0002] Endurance is one of the important performance indicators of drones. After a drone has been working for a long time, it is usually necessary to replace the battery to ensure the drone's endurance. At present, in order to realize the convenient replacement of drone batteries, a movable battery replacement device is used, such as a drone autonomous charging and battery replacement device disclosed in Chinese patent publication number "CN112009295A", which includes: a drone landing platform, the drone landing platform includes an antenna receiver for data connection with the drone and a docking platform for the drone to dock; a battery replacement manipulator for replacing the battery of the drone docked on the docking platform; and a battery charging platform for charging the battery.

[0003] Since the stopping position of the drone's blades is random after it is parked on the platform, the drone's blades may protrude from the side of the platform. During the subsequent descent of the platform, the protruding blades are very likely to conflict with the inner wall of the charging box, which can easily cause damage to the drone's blades. Based on this, we propose an automatic positioning and propeller retraction mechanism for a rotorcraft. Summary of the Invention

[0004] The purpose of the present invention is to solve the above-mentioned shortcomings in the prior art and to propose an automatic positioning and blade retracting mechanism for a rotorcraft.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] Design an automatic positioning and retracting blade mechanism for a rotorcraft, including:

[0007] The platform is placed in the charging box and is used to provide a docking location for the drone;

[0008] A clamping assembly, provided on the platform, for clamping and fixing the docked drone;

[0009] There are multiple propeller retracting assemblies, which are respectively located on each side of the platform. The propeller retracting assemblies include at least one rocker arm, which can drive the rocker arm to rotate when the clamping assembly moves.

[0010] Furthermore, the clamping assembly includes four clamping rods, which slide relative to each other in groups of two, and the sliding directions of the clamping rods in the two groups are perpendicular to each other. A driving assembly for driving the four clamping rods to move is also provided at the bottom of the platform.

[0011] Furthermore, the driving assembly includes a fixed frame fixed to the bottom of the platform, and a pulley is rotatably connected to the fixed frame, wherein the four pulleys are sequentially driven by a synchronous belt;

[0012] Wherein, clamping seats are fixedly installed on both sides of the synchronous belt, the two clamping seats on the same synchronous belt are connected to two clamping rods in a group, and any one of the pulleys is connected to the driving member.

[0013] Furthermore, a resisting member is provided on the side of the clamping rod, and the resisting member is used to resist the rocker arm.

[0014] Furthermore, the resisting member includes a resisting rod, and a roller is rotatably connected to the free end of the resisting rod;

[0015] An eccentric rod is further provided on one side of the rocker arm, a connecting piece is provided at the bottom of the platform, and an elastic member is provided between the eccentric rod and the connecting piece.

[0016] Furthermore, the elastic member is a tension spring, which has through holes on the end faces of the eccentric rod and the connecting piece, and both ends of the tension spring have hook portions that are clamped in the two through holes.

[0017] Furthermore, it also includes at least one limiting component, which is used to detect the moving position of the clamping component.

[0018] Furthermore, the limiting assembly includes a guide rail fixed to the bottom of the platform, and two mounting seats are provided on the guide rail, wherein both of the mounting seats are provided with a detection member.

[0019] Furthermore, the detection component is a travel switch.

[0020] Furthermore, the mounting seat is slidably connected to the guide rail, and a bolt for locking the mounting seat is provided on the mounting seat.

[0021] The automatic positioning and retracting blade mechanism of a rotorcraft proposed by the present invention has the following beneficial effects:

[0022] The present invention adopts a design that realizes automatic interference with the swing arm during the positioning of the drone by the clamping rod, and the linked design has higher action accuracy and lower manufacturing cost;

[0023] At the same time, a four-clamp rod design is used to ensure synchronous clamping of the drone to ensure that the drone is positioned in the upper middle part of the platform. After that, the driving force generated by the movement of the clamp rod drives the rocker arm to move, so as to position and retract the blades on the drone to avoid the blades protruding from the outside of the platform and being damaged by impact during descent. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 The present invention is a three-dimensional Figure 1 ;

[0025] Figure 2 The present invention is a three-dimensional Figure 2 ;

[0026] Figure 3 for Figure 2 Schematic diagram of the enlarged structure of area A;

[0027] Figure 4 for Figure 2 Schematic diagram of the enlarged structure of area B;

[0028] Figure 5 The present invention is a three-dimensional Figure 3 .

[0029] In the figure: 1. Platform; 11. Connecting plate; 2. Clamping assembly; 21. Clamping rod; 22. Fixing frame; 23. Pulley; 24. Synchronous belt; 25. Clamping seat; 26. Resistance rod; 27. Roller; 3. Paddle retracting assembly; 31. Rocker; 32. Eccentric rod; 33. Elastic member; 4. Limiting assembly; 41. Guide rail; 42. Mounting seat; 43. Detection member. DETAILED DESCRIPTION

[0030] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0031] Reference Figure 1-5 An embodiment of the present invention discloses an automatic positioning and retracting propeller mechanism for a rotorcraft, the retracting propeller mechanism comprising a platform 1, which is used to be placed in a charging box and is used to provide a docking position for a drone. Specifically, in this embodiment, the platform 1 is a rectangular structure;

[0032] and a clamping assembly 2, which is provided on the platform 1 and is used to clamp and fix the UAV after it has docked;

[0033] It also includes a propeller retracting assembly 3, and there are multiple propeller retracting assemblies 3. The multiple propeller retracting assemblies 3 are respectively located on each side of the platform 1, wherein the propeller retracting assembly 3 includes at least one rocker arm 31, which can drive the rocker arm 31 to rotate when the clamping assembly 2 moves.

[0034] In some embodiments, the clamping assembly 2 in the embodiment of the present invention includes four clamping rods 21, and the clamping rods 21 are U-shaped. The four clamping rods 21 slide relative to each other in groups of two. At the same time, a clamping space is formed between the four clamping rods 21. The sliding directions of the clamping rods 21 in the two groups are perpendicular to each other. A driving assembly for driving the four clamping rods 21 to move is also provided at the bottom of the platform 1.

[0035] In summary, in the embodiment of the present invention, when the drone is docked on the platform 1, the four clamping rods 21 move relative to each other to clamp and fix the drone's legs. At the same time, since the four clamping rods are grouped in pairs and slide relative to each other, it is possible to ensure that the drone is centered above the platform, thereby avoiding the problem of the drone offsetting on the platform 1 after clamping and hitting the inner wall of the charging box when it falls.

[0036] In addition, based on the above embodiment, the driving assembly in this embodiment includes a fixed frame 22 fixed to the bottom of the platform 1. The fixed frame 22 has a U-shaped structure. A pulley 23 is rotatably connected to the fixed frame 22. The pulley 23 is connected to the fixed frame 22 through a rotating shaft. Each of the rotating shafts is provided with two pulleys for transmission. The four pulleys 23 are sequentially driven by a synchronous belt 24.

[0037] Wherein, clamping seats 25 are fixedly installed on both sides of the synchronous belt 24, and the two clamping seats 25 on the same synchronous belt 24 are connected to two clamping rods 21 in a group, and any one of the pulleys 23 is connected to the driving component.

[0038] Specifically, in this embodiment, four synchronous belts 24 rotate. Since two clamping seats 25 are provided on each synchronous belt 24, when the synchronous wheel 24 rotates, the two clamping seats 25 on the same synchronous belt 24 move toward or away from each other. The two ends of the above-mentioned clamping rod 21 are respectively fixed on the two clamping seats 25 on both sides. In this way, when the clamping seat 25 moves, all the clamping rods 21 move at the same time to clamp and fix the drone.

[0039] In other words, in this embodiment, a resisting member is provided on the side of the clamping rod 21 , and the resisting member is used to resist the rocker rod 31 .

[0040] Exemplarily, the above-mentioned interference member includes an interference rod 26, which is fastened to one side of the clamping rod 21 by a bolt, and a roller 27 is rotatably connected to the free end of the interference rod 26;

[0041] An eccentric rod 32 is further provided on one side of the rocker arm 31 , a connecting piece 11 is provided at the bottom of the platform 1 , and an elastic member 33 is provided between the eccentric rod 32 and the connecting piece 11 .

[0042] On the basis of the above embodiment, in this embodiment, the elastic member 33 is a tension spring, which has through holes on the end faces of the eccentric rod 32 and the connecting piece 11, and both ends of the tension spring have hook portions that are clamped in the two through holes.

[0043] Specifically, when the drone is docked on the platform 1, the propellers stop rotating. Since the propellers have no fixed stopping position after stopping, the sides of the propellers may protrude from the sides of the platform. In order to prevent the propellers from colliding with the inner wall of the charging box during the descent of the platform 1, the clamping rod 21 is designed to move with the clamping seat 24. The interference rod 26 on the clamping rod 21 will drive the roller 27 to rotate upward against the rocker rod 31. If the sides of the propellers protrude from the sides of the platform 1 at this time, the rocker rod 31 can move the propellers to push them back to the top of the platform 1, thereby achieving the positioning and folding of the propellers.

[0044] In addition, the present invention further includes at least one position-limiting component 4 , which is used to detect the moving position of the clamping component 2 .

[0045] In some embodiments, the limit assembly 4 includes a guide rail 41 fixed to the bottom of the platform 1, and two mounting seats 42 are provided on the guide rail 41, wherein both mounting seats 42 are provided with a detection member 43. Specifically, in an embodiment of the present invention, the detection member 43 is a travel switch.

[0046] Furthermore, in the present invention, the mounting seat 42 is slidably connected to the guide rail 41 , and a bolt for locking the mounting seat 42 is provided on the mounting seat 42 .

[0047] That is to say, in the embodiment of the present invention, a travel switch is used to detect the moving position of the clamp seat 24, so as to locate the maximum moving position and the reset position of the clamp seat 24, effectively avoiding the problem that the two clamp seats 24 move too far, causing the two clamp rods 21 to collide with each other. The overall structure is simple and has high installation performance.

[0048] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and inventive concept of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. An automatic positioning and retracting blade mechanism for a rotorcraft, characterized in that: include: A platform (1), placed in the charging box, is used to provide a docking location for the drone; A clamping assembly (2) is provided on the platform (1) and is used to clamp and fix the drone after it has docked; A plurality of paddle retracting assemblies (3) are provided, and the plurality of paddle retracting assemblies (3) are respectively located on each side of the platform (1), wherein the paddle retracting assemblies (3) include at least one rocker (31), which can drive the rocker (31) to rotate when the clamping assembly (2) moves; the clamping assembly (2) includes four clamping rods (21), and the four clamping rods (21) slide relative to each other in groups of two, and the sliding directions of the clamping rods (21) in the two groups are perpendicular to each other, wherein a driving assembly for driving the four clamping rods (21) to move is also provided at the bottom of the platform (1), and a resistance member is provided on the side of the clamping rod (21), and the resistance member is used to resist the rocker (31), and the resistance member includes a resistance rod (26), and a roller (27) is rotatably connected to the free end of the resistance rod (26); An eccentric rod (32) is further provided on one side of the rocker rod (31), a connecting piece (11) is provided at the bottom of the platform (1), an elastic member (33) is provided between the eccentric rod (32) and the connecting piece (11), and a contact rod (26) on the clamping rod (21) drives the roller (27) to contact the rocker rod (31) and rotate upward.

2. The automatic positioning and retracting blade mechanism for a rotorcraft according to claim 1, characterized in that: The elastic member (33) is a tension spring having through holes on the end faces of the eccentric rod (32) and the connecting piece (11), and both ends of the tension spring have hook portions that are clamped in the two through holes.

3. The automatic positioning and retracting blade mechanism for a rotorcraft according to any one of claims 1 to 2, characterized in that: It also includes at least one limiting component (4), and the limiting component (4) is used to detect the moving position of the clamping component (2).

4. The automatic positioning and retracting blade mechanism for a rotorcraft according to claim 3, characterized in that: The position limiting assembly (4) comprises a guide rail (41) fixed to the bottom of the platform (1), two mounting seats (42) are provided on the guide rail (41), and detection components (43) are provided on both mounting seats (42).

5. The automatic positioning and retracting blade mechanism for a rotorcraft according to claim 4, characterized in that: The detection member (43) is a travel switch.

6. The automatic positioning and retracting blade mechanism for a rotorcraft according to claim 4, characterized in that: The mounting seat (42) is slidably connected to the guide rail (41), and a bolt for locking the mounting seat (42) is provided on the mounting seat (42).

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