UAV payload mounting device

Abstract

The present invention discloses a load mounting device for an unmanned aerial vehicle, comprising a fuselage, two landing gears are arranged at the bottom of the fuselage, a fixed interface fixedly connected to the fuselage is arranged between the two landing gears; a fixed frame is arranged at the bottom of the fuselage, a connection interface is fixedly connected to the top of the fixed frame; a suspension rope is used to fix the load, the bottom end of the suspension rope is connected to the load, and the top end of the suspension rope is connected to the connection interface on the fixed frame through a movable interface. The present invention performs suspension fixing on the load by providing a fixed frame and a suspension rope, so that the center of gravity of different loads is always on the same vertical line, which does not affect the balance of the unmanned aerial vehicle, and is suitable for large-sized goods, especially some special-shaped goods. At the same time, through the automatic connection and separation of the fixed interface and the connection interface, no manual auxiliary operation is required, and the fixed interface and the connection interface can be separated only when the fuselage lands.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a payload mounting device for unmanned aerial vehicles. Background Art

[0002] At present, the application of drones in logistics, firefighting, surveying, agriculture and other fields is becoming more and more popular. At the same time, existing drones also need to carry different types of payloads to perform tasks. Drone payload mounting devices are devices used to fix and control various payloads carried by drones.

[0003] Currently, the drone payload mounting devices used for large-size cargo transportation are mainly in two forms: platform fixing and hoisting.

[0004] Platform fixing is to install a platform under the drone, and the large-sized cargo is directly fixed on the platform, and the cargo is fixed by bolts or clamps. Although this mounting method is relatively stable, it requires manual assistance during installation and disassembly. In addition, for large-sized cargo with heavy weight, the center of gravity is not fixed and varies with the cargo, which can easily cause the drone to lose balance.

[0005] Lifting and fixing is to hang the cargo under the drone through a hook or a ring. Due to the principle of balance in physics, for cargo of different shapes or sizes, the center of gravity is always directly below the hook or the ring, so that the center of gravity of the transported items is fixed, thereby better maintaining the balance of the drone. However, manual assistance is still required when installing and fixing cargo, and in order to ensure the safety of the operator, the lifting rope is generally longer. During the flight of the drone, the height of the drone from the ground is limited, and the items are easily affected by trees on the ground. In addition, during transportation, the items shake greatly, which has a certain impact on the drone.

[0006] Therefore, the current drone load mounting devices used for transporting large-sized cargo have the problem of affecting the balance of the drone due to the unstable center of gravity of the cargo or the excessive shaking of the cargo due to the long lifting rope. At the same time, due to its structural characteristics, manual assistance is required when fixing and dismantling the cargo, and the overall safety is poor. Summary of the invention

[0007] The purpose of the present invention is to provide a drone load mounting device to solve the technical problems in the prior art that the drone has poor balance and poor overall safety when carrying large-sized cargo.

[0008] In order to solve the above technical problems, the present invention specifically provides the following technical solutions:

[0009] A UAV payload mounting device, comprising:

[0010] A fuselage, wherein two landing gears are provided at the bottom of the fuselage, and a fixing interface fixedly connected to the fuselage is provided between the two landing gears;

[0011] A fixing frame is arranged at the bottom of the fuselage, and a connection interface is fixedly connected to the top of the fixing frame;

[0012] A suspension rope is used to fix the load, the bottom end of the suspension rope is connected to the load, and the top end of the suspension rope is connected to the connection interface on the fixed frame through the moving interface;

[0013] The load is suspended inside the fixed frame by a suspension rope, and the center of gravity of the load is always directly below the suspension rope through the rotation of the load itself, so that the centers of gravity of different loads are on the same vertical line;

[0014] When the fuselage lands, the fixed frame contacts and supports the landing gear, and the fixed interface and the connecting interface are automatically connected by relying on the gravity of the fuselage itself. After the fuselage takes off, the landing gear is separated from the fixed frame, and the gravity of the fixed frame and the load limits the separation of the fixed interface and the connecting interface. Only after the fuselage lands, relying on the thrust of the drive structure and the synchronous upward movement of the fuselage, can the fixed interface and the connecting interface be automatically separated, thereby realizing automatic installation and removal of the load.

[0015] Furthermore, the connection interface is arranged just above the center of gravity of the fixing frame, and when the load is connected to the fuselage through the fixing frame, the common center of gravity of the load and the fixing frame is always just below the center of gravity of the fuselage.

[0016] Furthermore, after the fuselage lands, relying on the thrust of the driving structure and the coordination of the synchronous upward movement of the fuselage, the fixed interface and the connecting interface are automatically separated, and the connecting interface and the movable interface are also triggered to automatically separate synchronously, thereby achieving the separation of the fuselage from the fixed frame while the fixed frame and the load are also separated synchronously.

[0017] Furthermore, the fixed interface includes a fixed block, a fixed groove is provided at the bottom of the fixed block, a limit block is fixedly connected to the bottom of the inner wall of the fixed groove, a push block is provided inside the fixed groove, and the push block is controlled to move left and right by a hydraulic rod;

[0018] The connection interface comprises a connection rod fixed on the top of the fixing frame, a first inverted V-shaped spring sheet is connected to the top of the connection rod, a limiting groove is formed on the first spring sheet, and the limiting block is engaged with the limiting groove;

[0019] When the fuselage lands, the fixing frame contacts and supports the landing gear, and the first spring piece is inserted into the fixing groove by the gravity of the fuselage itself, so that the fixing interface and the connecting interface are automatically connected. At this time, the height of the bottom of the first spring piece is higher than the height of the limit block.

[0020] After the fuselage takes off, the landing gear is separated from the fixed frame, and the first spring piece and the limit block are relatively displaced by the gravity of the fixed frame and the load, so that the limit groove and the limit block are engaged, thereby limiting the first spring piece;

[0021] And only when the fuselage lands again, the first spring piece and the limit block are relatively displaced again, so that the height of the bottom of the first spring piece is higher than the height of the limit block, and the push block pushes the first spring piece to deform and move up with the fuselage through the hydraulic rod, thereby realizing the automatic separation of the fixed interface and the connecting interface.

[0022] Furthermore, the mobile interface includes a mobile rod, a second inverted V-shaped spring piece is fixedly connected to the top of the mobile rod, a slot is opened at the bottom of the connecting rod, a card block is fixedly connected to the bottom of the inner wall of the slot, and a through slot is formed in the middle of the card block;

[0023] The second spring piece is compressed when inserted into the through slot, and when the second spring piece is restored to its original shape after being inserted into the slot, the clamping block limits the second spring piece, so that the movable interface is connected to the connecting interface.

[0024] Furthermore, a movable plate connected to the connecting rod for left-right sliding is fixedly connected to the bottom of the first elastic sheet, and the bottom of the movable plate is arranged on one side of the top of the clamping block;

[0025] Among them, when the push block pushes the first spring sheet to deform, the first spring sheet is moved toward the middle of the connecting rod synchronously, and the movable plate is driven to move toward the middle of the connecting rod synchronously, and then the movable plate squeezes the second spring sheet to deform. Under the action of the load gravity, the second spring sheet is automatically separated from the connecting rod, and the fuselage is separated from the fixed frame, and the fixed frame is also separated from the load synchronously.

[0026] Furthermore, the number of the first spring pieces is set to two, the number of the push block and the limit block are both set to two, and a spring is fixedly connected between the two first spring pieces;

[0027] When the push block pushes the two first spring sheets to move toward the middle of the connecting rod, the spring is compressed and has a rebound force. When the first spring sheets lose the thrust of the push block, the two first spring sheets move to both sides and return to their original positions under the action of the spring rebound force.

[0028] Furthermore, an extension sleeve is threadedly connected to the outer surface of the movable rod, and the length of the movable rod is extended by rotating the extension sleeve, so as to adjust the distance between the bottom end of the suspension rope and the top of the fixed frame, so that when the load is suspended by the suspension rope, it does not contact the fixed frame during the rotation of the load.

[0029] Furthermore, a stopper is fixedly connected to the bottom of the moving rod, and a limiting sleeve is fixedly connected to the bottom of the extension sleeve. The stopper and the moving rod are both arranged inside the limiting sleeve, and the diameter of the stopper and the inner diameter of the limiting sleeve are both larger than the inner diameter of the extension sleeve.

[0030] Furthermore, a guide groove connected to the fixing groove is provided at the bottom of the fixing groove, and the diameter of the top of the guide groove is smaller than the diameter of the bottom thereof;

[0031] A universal ball is fixedly mounted on the top of the first spring piece;

[0032] When the fuselage falls, the universal ball on the top of the first spring piece first contacts the inner wall of the guide groove and rolls, and the position of the fuselage is continuously adjusted through the guiding effect of the guide groove, so that the first spring piece is inserted into the interior of the fixing groove, so that the fixing interface is connected to the connecting interface.

[0033] Compared with the prior art, the present invention has the following beneficial effects:

[0034] The present invention provides a fixing frame and a suspension rope to fix the load in a suspended manner, so that the center of gravity of different loads is always on the same vertical line, which does not affect the balance of the drone. The present invention is suitable for large-sized cargo, especially some special-shaped cargo. At the same time, through the automatic connection and separation of the fixing interface and the connecting interface, no manual auxiliary operation is required, and the fixing interface can be separated from the connecting interface only when the fuselage lands, thereby improving the overall safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the implementation methods of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for the implementation methods or the description of the prior art. Obviously, the drawings in the following description are only exemplary, and for ordinary technicians in this field, other implementation drawings can be derived from the provided drawings without creative work.

[0036] Figure 1 A schematic diagram of the overall structure provided by the present invention;

[0037] Figure 2 It is a structural schematic diagram of the fixed interface in the present invention;

[0038] Figure 3 A schematic diagram of the connection structure between the connection interface and the mobile interface in the present invention;

[0039] Figure 4 It is a structural schematic diagram of the mobile interface in the present invention;

[0040] Figure 5 It is a partial structural schematic diagram of the present invention before the fixed interface is connected to the connecting interface;

[0041] Figure 6 It is a partial structural schematic diagram of the fixed interface and the connecting interface when the fuselage is landing in the present invention;

[0042] Figure 7 It is a structural schematic diagram of the present invention when the fixed interface is connected to the connecting interface after the fuselage takes off.

[0043] The numbers in the figure represent the following:

[0044] 10. Fuselage; 20. Landing gear; 30. Fixed interface; 40. Fixed frame; 50. Connection interface; 60. Suspension rope; 70. Mobile interface;

[0045] 301, fixed block; 302, fixed groove; 303, limit block; 304, push block; 305, hydraulic rod; 306, guide groove;

[0046] 501, connecting rod; 502, first spring; 503, limiting groove; 504, moving plate; 505, spring; 506, universal ball;

[0047] 701, moving rod; 702, second spring piece; 703, slot; 704, block; 705, extension sleeve; 706, stop block; 707, limit sleeve. DETAILED DESCRIPTION

[0048] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0049] like Figure 1 As shown, the present invention provides a UAV payload mounting device, comprising:

[0050] A fuselage 10, two landing gears 20 are provided at the bottom of the fuselage 10, and a fixing interface 30 fixedly connected to the fuselage 10 is provided between the two landing gears 20;

[0051] A fixing frame 40 is disposed at the bottom of the body 10 , and a connection interface 50 is fixedly connected to the top of the fixing frame 40 ;

[0052] A suspension rope 60 is used to fix the load. The bottom end of the suspension rope 60 is connected to the load, and the top end of the suspension rope 60 is connected to the connection interface 50 on the fixed frame 40 through the moving interface 70;

[0053] The load is suspended inside the fixed frame 40 by the suspension rope 60. The center of gravity of the load is always directly below the suspension rope 60 through the rotation of the load itself, so that the center of gravity of different loads is on the same vertical line.

[0054] When the fuselage 10 lands, the fixing frame 40 contacts and supports the landing gear 20, and the fixing interface 30 is automatically connected to the connecting interface 50 by relying on the gravity of the fuselage 10 itself. After the fuselage 10 takes off, the landing gear 20 is separated from the fixing frame 40, and the fixing interface 30 is limited to separate from the connecting interface 50 by the gravity of the fixing frame 40 and the load. Only after the fuselage 10 lands, relying on the thrust of the driving structure and the synchronous upward movement of the fuselage 10, can the fixing interface 30 be automatically separated from the connecting interface 50, thereby realizing the automatic installation and removal of the load.

[0055] The current drone payload mounting devices used for large-size cargo transportation have the problem of affecting the balance of the drone due to the unstable center of gravity of the cargo or the excessive swaying of the cargo due to the long lifting rope. At the same time, due to its structural characteristics, manual assistance is required when fixing and removing the cargo, and the overall safety is poor. Therefore, it is necessary to develop a drone payload mounting device with better balance and safety that is suitable for large-size cargo transportation.

[0056] This embodiment provides a fixing frame 40 and a suspension rope 60 to suspend and fix the load, so that the center of gravity of different loads is always on the same vertical line, which does not affect the balance of the drone. It is suitable for large-sized cargo, especially some special-shaped cargo. At the same time, through the automatic connection and separation of the fixing interface 30 and the connecting interface 50, no manual auxiliary operation is required, and the fixing interface 30 can only be separated from the connecting interface 50 when the fuselage 10 lands, thereby improving the overall safety.

[0057] In actual use, 1. the load is connected to the fixed frame 40, the suspension rope 60 is fixed to the load in advance, and then the mobile interface 70 at the top of the suspension rope 60 is connected to the connection interface 50 on the fixed frame 40, so that the load is suspended inside the fixed frame 40;

[0058] 2. The fuselage 10 is connected to the fixing frame 40, and the fuselage 10 takes off and hovers on the top of the fixing frame 40, and then the fuselage 10 is landed, so that the fixing frame 40 contacts and supports the landing gear 20, and the fixing interface 30 and the connecting interface 50 are automatically connected by the gravity of the fuselage 10 itself, and the load is fixed at the bottom of the fuselage 10;

[0059] 3. Take-off transportation, so that the fuselage 10 takes off, and the fixing interface 30 and the connecting interface 50 are relatively displaced by the gravity of the fixing frame 40 and the load, so that the connection between the fixing interface 30 and the connecting interface 50 is more firmly established, and the separation of the fixing interface 30 and the connecting interface 50 is limited;

[0060] 4. The fuselage 10 is separated from the fixed frame 40. When the fuselage 10 transports the load to the specified position and starts to land, the bottom of the fixed frame 40 contacts the ground, and the fixed frame 40 supports the landing gear 20. At this time, the fixed interface 30 and the connecting interface 50 are relatively displaced. Relying on the thrust of the driving structure and the synchronous upward movement of the fuselage 10, the fixed interface 30 and the connecting interface 50 are automatically separated.

[0061] Even if the center of gravity of different loads is on the same vertical line through the suspension effect of the suspension rope 60, if the center of gravity of the load deviates too much from the center of gravity of the fuselage 10, it will still affect the balance of the fuselage 10. In order to solve this problem, the connection interface 50 is set just above the center of gravity of the fixed frame 40. When the load is connected to the fuselage 10 through the fixed frame 40, the common center of gravity of the load and the fixed frame 40 is always just below the center of gravity of the fuselage 10. The center of gravity of the fuselage 10, the center of gravity of the fixed frame 40 and the center of gravity of the load are always on the same vertical line, so that the balance of the fuselage 10 will not be affected for goods of different weights and sizes, thereby improving the scope of application of the device and the overall safety effect.

[0062] In order to achieve rapid separation of the load and prevent the load from falling off during flight, after the fuselage 10 lands, the thrust of the driving structure and the synchronous upward movement of the fuselage 10 are used to automatically separate the fixed interface 30 from the connection interface 50, and the connection interface 50 is triggered to automatically separate from the mobile interface 70, so that the fuselage 10 is separated from the fixed frame 40, and the fixed frame 40 is also separated from the load. In other words, when the fuselage 10 is in flight, the fixed interface 30 and the connection interface 50 cannot be separated, and the connection interface 50 and the mobile interface 70 cannot be separated, thereby improving the safety of the device and preventing the load from falling off during flight.

[0063] At the same time, when the fuselage 10 is separated from the fixing frame 40, the fixing frame 40 and the load are also separated synchronously, realizing automatic separation, improving the convenience of operation of the device, and no manual operation is required.

[0064] The above is an overall solution for realizing automatic connection and separation between the fuselage 10 and the payload. The specific solution structure is described in detail below:

[0065] The fixing interface 30 includes a fixing block 301, a fixing groove 302 is provided at the bottom of the fixing block 301, a limiting block 303 is fixedly connected to the bottom of the inner wall of the fixing groove 302, a push block 304 is provided inside the fixing groove 302, and the push block 304 is controlled to move left and right by a hydraulic rod 305;

[0066] The connection interface 50 includes a connection rod 501 fixed to the top of the fixing frame 40, and an inverted V-shaped first elastic sheet 502 is connected to the top of the connection rod 501. A limiting groove 503 is formed on the first elastic sheet 502, and the limiting block 303 is engaged with the limiting groove 503;

[0067] When the fuselage 10 lands, the fixing frame 40 contacts and supports the landing gear 20. The first spring piece 502 is inserted into the fixing groove 302 by the gravity of the fuselage 10, so that the fixing interface 30 and the connecting interface 50 are automatically connected. At this time, the height of the bottom of the first spring piece 502 is higher than the height of the limit block 303.

[0068] After the fuselage 10 takes off, the landing gear 20 is separated from the fixing frame 40, and the first spring piece 502 and the limit block 303 are relatively displaced by the gravity of the fixing frame 40 and the load, so that the limit groove 503 is engaged with the limit block 303, thereby limiting the first spring piece 502;

[0069] And only when the fuselage 10 lands again, the first spring piece 502 and the limit block 303 are relatively displaced again, so that the height of the bottom of the first spring piece 502 is higher than the height of the limit block 303, and the push block 304 pushes the first spring piece 502 to deform through the hydraulic rod 305 while cooperating with the upward movement of the fuselage 10, thereby realizing the automatic separation of the fixed interface 30 and the connecting interface 50.

[0070] By providing the limit block 303 and the first spring piece 502, after the fixed interface 30 is connected to the connection interface 50 and after the fuselage 10 takes off, the fixed block 301 and the first spring piece 502 can still be relatively displaced by the gravity of the load to limit the first spring piece 502, thereby improving the connection firmness between the fixed interface 30 and the connection interface 50. At this time, no matter how the first spring 505 is pushed by the push block 304, the first spring 505 is limited due to the existence of the limit block 303, thereby preventing the connection interface 50 from being separated from the fixed interface 30 during the flight of the fuselage 10, thereby improving the overall safety.

[0071] At the same time, through the above structure, only when the fuselage 10 lands again, the support of the landing gear 20 by the fixed frame 40 makes the limit block 303 disengage from the first spring piece 502 and release the limit on the first spring piece 502, and then the first spring piece 502 can be pushed by the push block 304, and cooperate with the upward movement of the fuselage 10 to make the fixed interface 30 and the connection interface 50 automatically separated.

[0072] The connection operation and separation operation between the fixing interface 30 and the connection interface 50 described above do not require manual intervention and can be remotely controlled, thereby improving the convenience of using the device.

[0073] The specific structure of the mobile interface 70 is further provided below. Figure 3 and Figure 4 As shown, the mobile interface 70 includes a mobile rod 701, a second inverted V-shaped elastic piece 702 is fixedly connected to the top of the mobile rod 701, a slot 703 is opened at the bottom of the connecting rod 501, a clamping block 704 is fixedly connected to the bottom of the inner wall of the slot 703, and a through groove is formed in the middle of the clamping block 704;

[0074] The second spring piece 702 is compressed when inserted into the through slot, and returns to its original shape after being inserted into the slot 703 . The clamping block 704 limits the second spring piece 702 , so that the movable interface 70 is connected to the connecting interface 50 .

[0075] When fixing the load, the second spring piece 702 can be fixed by inserting the second spring piece 702 through the through slot into the slot 703, which is convenient for installation. At the same time, since the connection interface 50 is not connected to the fixed interface 30 when the mobile interface 70 is connected to the connection interface 50, there is no interference from the drone, and the overall safety is good.

[0076] Since the fixing interface 30 and the connecting interface 50 are automatically connected, the suspension rope 60 does not need to be too long, so as to prevent the load from shaking too much during transportation and affecting the balance of the drone.

[0077] Furthermore, in order to unload the load more quickly and conveniently, and to improve the connection firmness between the mobile interface 70 and the connection interface 50, and to prevent the mobile interface 70 from being separated from the connection interface 50 during transportation, as shown in FIG. Figure 3 and Figure 4 As shown, a movable plate 504 connected to the connecting rod 501 for left-right sliding is fixedly connected to the bottom of the first elastic sheet 502, and the bottom of the movable plate 504 is arranged on one side of the top of the clamping block 704;

[0078] Among them, when the pushing block 304 pushes the first spring piece 502 to deform, the first spring piece 502 is simultaneously moved toward the middle of the connecting rod 501, and the moving plate 504 is simultaneously driven to move toward the middle of the connecting rod 501, and then the moving plate 504 squeezes the second spring piece 702 to deform. Under the action of the gravity of the load, the second spring piece 702 is automatically separated from the connecting rod 501, so that the fuselage 10 is separated from the fixed frame 40, and the fixed frame 40 is also separated from the load synchronously.

[0079] When the fixed interface 30 is separated from the connecting interface 50, the first spring piece 502 is deformed under the push of the push block 304. Since the movable plate 504 is connected to the connecting rod 501 by sliding left and right, the first spring piece 502 will also move toward the center of the connecting rod 501, and simultaneously drive the movable plate 504 to move toward the center of the connecting rod 501. When the movable plate 504 moves, it will touch the second spring piece 702, causing the second spring piece 702 to deform. Then, under the action of the gravity of the load, the second spring piece 702 will automatically fall off from the inside of the connecting rod 501, thereby realizing the automatic separation of the load and the fixed frame 40.

[0080] Correspondingly, when the fuselage 10 is in flight, the first spring piece 502 cannot move because the limit block 303 limits the first spring piece 502, and the movable plate 504 cannot apply force to the second spring piece 702, so that the second spring piece 702 will not fall off from the inside of the connecting rod 501. In other words, when the fuselage 10 is in flight, the load and the fixed frame 40 cannot be separated, and the fixed frame 40 and the fuselage 10 cannot be separated at the same time. Therefore, during the flight of the fuselage 10, the load and the fuselage 10 are firmly fixed, and only when the fuselage 10 lands and the fixed frame 40 supports the landing gear 20, the load can be separated from the fuselage 10, and it can be achieved that when the fuselage 10 is separated from the fixed frame 40, the fixed frame 40 and the load are also separated synchronously, thereby improving the flight safety of the fuselage 10 and the convenience of load removal.

[0081] After the first spring piece 502 moves toward the connecting rod 501 under the push of the push block 304, if it does not return to the original position, the movable interface 70 can no longer be connected to the fixed interface 30. The number of the first spring pieces 502 is set to two, and the number of the push block 304 and the limit block 303 are both set to two. A spring 505 is fixedly connected between the two first spring pieces 502.

[0082] When the push block 304 pushes the two first spring pieces 502 to move toward the middle of the connecting rod 501, the spring 505 is compressed and has a rebound force. When the first spring pieces 502 lose the thrust of the push block 304, the rebound force of the spring 505 causes the two first spring pieces 502 to move to both sides and return to their original positions.

[0083] By providing the spring 505 , the first elastic sheet 502 can be moved to both sides and restored to the original position, so that the movable interface 70 can be connected to the fixed interface 30 multiple times.

[0084] If the suspension rope 60 is too long, the center of gravity of the load may shift too much due to the acceleration of the fuselage 10 during transportation. If the distance between the load and the fixed frame 40 is too short, the load may touch the fixed frame 40 when adjusting its placement state, causing the fixed frame 40 to exert a force on the load, which will cause the center of gravity of the load and the suspension rope 60 to be not on the same vertical line, affecting the balance of the fuselage 10.

[0085] In order to solve the above problems, Figure 3 and Figure 4 As shown, the outer surface of the moving rod 701 is threadedly connected with an extension sleeve 705, and the length of the moving rod 701 is extended by rotating the extension sleeve 705, so as to adjust the distance between the bottom end of the suspension rope 60 and the top of the fixed frame 40, so that when the load is suspended by the suspension rope 60, it does not contact the fixed frame 40 during the rotation process of the load. By rotating the extension sleeve 705, the distance between the bottom end of the suspension rope 60 and the top of the fixed frame 40 can be adjusted, so that the load does not contact the fixed frame 40 during the process of adjusting its placement state, so that the center of gravity of the load is always directly below the suspension rope 60.

[0086] Furthermore, in order to prevent the moving rod 701 from falling off from the extension sleeve 705, thereby preventing the load from accidentally falling off, a stopper 706 is fixedly connected to the bottom of the moving rod 701, and a limiting sleeve 707 is fixedly connected to the bottom of the extension sleeve 705. The stopper 706 and the moving rod 701 are both arranged inside the limiting sleeve 707, and the diameter of the stopper 706 and the inner diameter of the limiting sleeve 707 are both larger than the inner diameter of the extension sleeve 705. Due to the existence of the stopper 706 and the limiting sleeve 707, no matter how the extension sleeve 705 is rotated, the stopper 706 is limited, so that the moving rod 701 is connected to the limiting sleeve 707.

[0087] During the landing of the fuselage 10, it is difficult to align the fixing interface 30 with the connecting interface 50, which increases the difficulty of connecting the fixing interface 30 with the connecting interface 50. In order to solve this problem, Figure 2 and Figure 3 As shown, a guide groove 306 connected to the fixing groove 302 is provided at the bottom thereof, and the diameter of the top of the guide groove 306 is smaller than the diameter of the bottom thereof;

[0088] A universal ball 506 is fixedly mounted on the top of the first elastic piece 502;

[0089] When the fuselage 10 falls, the universal ball 506 on the top of the first spring piece 502 first contacts the inner wall of the guide groove 306 and rolls, and the position of the fuselage 10 is continuously adjusted through the guiding effect of the guide groove 306, so that the first spring piece 502 is inserted into the interior of the fixing groove 302, so that the fixing interface 30 is connected to the connecting interface 50.

[0090] By providing a universal ball 506 on the top of the first spring sheet 502, when the fuselage 10 falls, the universal ball 506 contacts the guide groove 306 first and adjusts the position of the fuselage 10 in real time until the fixing interface 30 is just above the connecting interface 50, which is convenient for fixing.

[0091] Preferably, the first spring piece 502 and the second spring piece 702 are made of high-strength and high-toughness materials, such as alloy materials such as spring 505 steel, so that the first spring piece 502 and the second spring piece 702 have elasticity and strong strength.

[0092] The above embodiments are only exemplary embodiments of the present application and are not intended to limit the present application. The protection scope of the present application is defined by the claims. Those skilled in the art may make various modifications or equivalent substitutions to the present application within the essence and protection scope of the present application, and such modifications or equivalent substitutions shall also be deemed to fall within the protection scope of the present application.

Claims

1. A UAV payload mounting device, characterized in that: include: A fuselage (10), wherein two landing gears (20) are provided at the bottom of the fuselage (10), and a fixing interface (30) fixedly connected to the fuselage (10) is provided between the two landing gears (20); A fixing frame (40) is arranged at the bottom of the fuselage (10), and a connection interface (50) is fixedly connected to the top of the fixing frame (40); A suspension rope (60) is used to fix the load, the bottom end of the suspension rope (60) is connected to the load, and the top end of the suspension rope (60) is connected to a connection interface (50) on the fixed frame (40) via a moving interface (70); The load is suspended inside the fixed frame (40) via a suspension rope (60), and the center of gravity of the load is always directly below the suspension rope (60) through the rotation of the load itself, so that the centers of gravity of different loads are on the same vertical line; When the fuselage (10) is landing, the fixing frame (40) contacts the landing gear (20) and supports the landing gear (20), and the fixing interface (30) and the connecting interface (50) are automatically connected by the gravity of the fuselage (10) itself. After the fuselage (10) takes off, the landing gear (20) is separated from the fixing frame (40), and the fixing interface (30) and the connecting interface (50) are restricted from separating by the gravity of the fixing frame (40) and the load. Only after the fuselage (10) is landed, the fixing interface (30) and the connecting interface (50) are automatically separated by the thrust of the driving structure and the synchronous upward movement of the fuselage (10), thereby realizing automatic installation and removal of the load. The fixed interface (30) comprises a fixed block (301), a fixed groove (302) is provided at the bottom of the fixed block (301), a limit block (303) is fixedly connected to the bottom of the inner wall of the fixed groove (302), a push block (304) is provided inside the fixed groove (302), and the push block (304) is controlled to move left and right by a hydraulic rod (305); The connection interface (50) comprises a connection rod (501) fixed on the top of the fixing frame (40); a first inverted V-shaped spring sheet (502) is connected to the top of the connection rod (501); a limiting groove (503) is formed on the first spring sheet (502); and the limiting block (303) is engaged with the limiting groove (503); When the fuselage (10) lands, the fixing frame (40) contacts the landing gear (20) and supports the landing gear (20), and the first spring piece (502) is inserted into the fixing groove (302) by the gravity of the fuselage (10) itself, so that the fixing interface (30) and the connecting interface (50) are automatically connected. At this time, the height of the bottom of the first spring piece (502) is higher than the height of the limit block (303); After the fuselage (10) takes off, the landing gear (20) is separated from the fixing frame (40), and the first spring piece (502) and the limiting block (303) are relatively displaced by the gravity of the fixing frame (40) and the load, so that the limiting groove (503) and the limiting block (303) are engaged, thereby limiting the first spring piece (502); Only when the fuselage (10) descends again, the first spring sheet (502) and the limit block (303) are relatively displaced again, so that the height of the bottom of the first spring sheet (502) is higher than the height of the limit block (303), and the push block (304) pushes the first spring sheet (502) to deform through the hydraulic rod (305) and cooperates with the fuselage (10) to move upward, thereby achieving automatic separation of the fixed interface (30) and the connection interface (50).

2. The UAV payload mounting device according to claim 1, characterized in that: The connection interface (50) is arranged directly above the center of gravity of the fixing frame (40); when the load is connected to the fuselage (10) through the fixing frame (40), the common center of gravity of the load and the fixing frame (40) is always directly below the center of gravity of the fuselage (10).

3. The UAV payload mounting device according to claim 2, characterized in that: After the fuselage (10) lands, the thrust of the drive structure and the synchronous upward movement of the fuselage (10) are used to automatically separate the fixed interface (30) from the connection interface (50), triggering the connection interface (50) and the movable interface (70) to also automatically separate synchronously, thereby achieving the separation of the fuselage (10) from the fixed frame (40) and the synchronous separation of the fixed frame (40) from the load; The mobile interface (70) comprises a mobile rod (701), a second inverted V-shaped elastic sheet (702) is fixedly connected to the top of the mobile rod (701), a slot (703) is provided at the bottom of the connecting rod (501), a clamping block (704) is fixedly connected to the bottom of the inner wall of the slot (703), and a through slot is formed in the middle of the clamping block (704); The second spring piece (702) is compressed when inserted into the through slot, and when the second spring piece (702) is inserted into the slot (703), it returns to its original shape, and the clamping block (704) limits the position of the second spring piece (702), so that the movable interface (70) is connected to the connecting interface (50); A movable plate (504) is fixedly connected to the bottom of the first elastic sheet (502) and is slidably connected to the connecting rod (501) left and right, and the bottom of the movable plate (504) is arranged on one side of the top of the clamping block (704); When the push block (304) pushes the first spring sheet (502) to deform, the first spring sheet (502) is simultaneously moved toward the middle of the connecting rod (501), thereby simultaneously driving the moving plate (504) to move toward the middle of the connecting rod (501), and then the moving plate (504) squeezes the second spring sheet (702) to deform. Under the action of the gravity of the load, the second spring sheet (702) is automatically separated from the connecting rod (501), so that the fuselage (10) is separated from the fixed frame (40), and the fixed frame (40) is also separated from the load synchronously.

4. The UAV payload mounting device according to claim 3, characterized in that: The number of the first spring pieces (502) is set to two, the number of the push block (304) and the limit block (303) are both set to two, and a spring (505) is fixedly connected between the two first spring pieces (502); When the push block (304) pushes the two first spring sheets (502) to move toward the middle of the connecting rod (501), the spring (505) is compressed and has a rebound force. When the first spring sheets (502) lose the pushing force of the push block (304), the two first spring sheets (502) move to both sides and return to their original positions under the action of the rebound force of the spring (505).

5. The UAV payload mounting device according to claim 4, characterized in that: An extension sleeve (705) is threadedly connected to the outer surface of the moving rod (701), and the length of the moving rod (701) is extended by rotating the extension sleeve (705), thereby adjusting the distance between the bottom end of the suspension rope (60) and the top of the fixed frame (40), so that when the load is suspended by the suspension rope (60), the load does not contact the fixed frame (40) during the rotation process.

6. The UAV payload mounting device according to claim 5, characterized in that: A stopper (706) is fixedly connected to the bottom of the moving rod (701), and a limiting sleeve (707) is fixedly connected to the bottom of the extension sleeve (705). The stopper (706) and the moving rod (701) are both arranged inside the limiting sleeve (707), and the diameter of the stopper (706) and the inner diameter of the limiting sleeve (707) are both larger than the inner diameter of the extension sleeve (705).

7. The UAV payload mounting device according to claim 6, characterized in that: A guide groove (306) connected to the fixing groove (302) is provided at the bottom thereof, and the diameter of the top of the guide groove (306) is smaller than the diameter of the bottom thereof; A universal ball (506) is fixedly mounted on the top of the first elastic sheet (502); When the fuselage (10) falls, the universal ball (506) on the top of the first spring piece (502) first contacts the inner wall of the guide groove (306) and rolls, and the position of the fuselage (10) is continuously adjusted through the guiding effect of the guide groove (306), so that the first spring piece (502) is inserted into the interior of the fixing groove (302), so that the fixing interface (30) is connected to the connecting interface (50).

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