A quick-change structure for drone batteries

Abstract

The present invention relates to a quick-change battery structure for unmanned aerial vehicles. Batteries are installed by sliding in a battery installation space via a guide rail. The upper end of a battery compartment frame is hingedly connected to a hatch cover via a hatch hinge. A locking handle is rotatably mounted on the front end of the battery compartment. Lock holes are provided on both sides of the battery compartment frame. Hatch cover spring lock hooks are provided on the hatch cover corresponding to the lock holes. When the hatch cover and the fuselage are closed, the hatch cover spring lock hooks engage and lock with the lock holes. The present invention has a compact structure. When the battery compartment cover is closed, the hatch cover hinge is hidden inside the fuselage, making the appearance neater and not affecting the aerodynamic shape. The invention has a fault-tolerant design. Even if the locking handle is not fully in place, the locking handle is pressed against the battery compartment cover a second time during the closing process to reset it, thereby ensuring the reliability of battery locking. The installation and replacement of the battery are quick and convenient, and the safety is high.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles (UAVs), relates to UAV battery replacement operations, and particularly relates to a UAV battery quick-change structure. Background Art

[0002] The design of surveying and mapping UAV products is heavy. In order to carry different mission payload equipment, the power matching needs to have a large redundant design. In order to achieve long flight time and range in a single take-off and landing, a large-capacity battery pack module needs to be configured.

[0003] Conventional high-rate power battery cells currently on the market typically use soft-pack lithium batteries. After a certain lifespan, these cells often experience increased internal resistance and even bulging and damage due to prolonged high-rate discharge and heat generation. The cost of using a single high-capacity, high-rate battery pack in large drones is very high, and since it is not compatible with smaller drones of the same family, this further increases the cost of developing and using batteries for large drones.

[0004] Based on the above-mentioned pain point of battery usage cost, the present invention splits the battery module of a large drone into two, and accordingly designs a set of locking and quick-release mechanisms for parallel battery units, thereby reducing the risk and cost of overall failure of the power battery pack, while ensuring that the battery can be easily disassembled and reliably installed. Summary of the Invention

[0005] The object of the present invention is to overcome the shortcomings of the existing technology and provide a quick-change battery structure for unmanned aerial vehicles. The structure is compact. When the battery compartment cover is buckled, the cover hinge is hidden inside the fuselage, which has a neater appearance and does not damage the aerodynamic shape. The structure has a fault-tolerant design. Even if the locking handle is not fully in place, the locking handle is pressed against the battery compartment cover a second time during the buckling process to reset it, thereby ensuring the reliability of battery locking. The installation and replacement of the battery are quick, convenient and safe.

[0006] The present invention solves the technical problem by the following technical solutions:

[0007] A quick-change battery structure for an unmanned aerial vehicle, characterized in that: it includes a hatch and a fuselage, a battery hatch rack is provided in the battery hatch inside the fuselage, the battery hatch rack divides the battery hatch into two battery installation spaces, guide rails are symmetrically installed in the battery installation spaces, batteries are slidably installed between the guide rails, the upper end of the battery hatch rack is hingedly connected to the hatch hatch through a hatch hinge, the hatch hatch can be flipped open and closed along the fuselage, the front end of the battery hatch is rotatably installed with a locking handle through a base, a torsion spring is installed in the base, and the locking handle can be reset by the torsion spring, locking holes are provided on both sides of the battery hatch rack, and hatch cover spring lock hooks are provided on the hatch cover corresponding to the lock holes. When the hatch cover and the fuselage are closed, the hatch cover spring lock hooks are buckled and locked with the lock holes, and a paddle is uniformly provided at the end of the hatch cover spring lock hook, and the paddle extends out of the hatch cover.

[0008] Moreover, locking handle limiters are provided at both ends of the inner side of the hatch cover at positions corresponding to the front end surfaces of the locking handle. When the hatch cover and the fuselage are closed, the locking handle limiters abut against the lower end of the locking handle.

[0009] Moreover, front locking points are symmetrically arranged on the inner side of the front end surface of the locking handle, and side locking points are symmetrically arranged on both sides of the locking handle.

[0010] Moreover, a pressing block is formed at the center of the outer side of the front end surface of the locking handle, and the pressing block is formed with anti-slip grooves.

[0011] The advantages and beneficial effects of the present invention are:

[0012] 1. The quick-change battery structure for drones of the present invention is characterized in that the battery compartment frame divides the battery compartment into two battery installation spaces, and guide rails are symmetrically installed in the battery installation spaces, and the batteries are slidably installed between the guide rails. The upper end of the battery compartment frame is hingedly connected to the hatch through a hatch hinge, and the hatch can be flipped open and closed along the fuselage through the hatch hinge. A locking handle is rotatably installed at the front end of the battery compartment, and the locking handle can be reset by a torsion spring. Lock holes are provided on both sides of the battery compartment frame, and hatch spring lock hooks are provided on the hatch corresponding to the lock holes. When the hatch and the fuselage are closed, the hatch spring lock hooks are buckled and locked with the lock holes. A paddle is uniformly formed at the end of the hatch spring lock hook, and the paddle extends out of the hatch to facilitate the hatch to be opened by flipping. The present invention disassembles the battery module of a large drone into two, and through the quick-change structure, reduces the risk and cost of overall failure of the power battery pack, while ensuring that the battery is easy to disassemble and reliably installed.

[0013] 2. The quick-change battery structure for the drone of the present invention is compact. When the battery compartment cover is closed, the cover hinge is hidden inside the fuselage, making the appearance neater and not destroying the aerodynamic shape.

[0014] 3. In the UAV battery quick-change structure of the present invention, locking handle limiters are provided at the positions of the front end surfaces of the locking handle at both ends of the inner side of the hatch. When the hatch and the fuselage are closed, the locking handle limiters abut against the lower end of the locking handle, which has a fault-tolerant design. Even if the locking handle is not fully in place, the locking handle limiters abut against the locking handle a second time during the closing process of the battery hatch to reset it, thereby ensuring the reliability of battery locking.

[0015] 4. The UAV battery quick-change structure of the present invention has front locking points symmetrically provided on the inner side of the front end surface of the locking handle, and side locking points symmetrically provided on both sides of the locking handle, which can limit the battery and prevent the battery from falling out of the electromagnetic compartment.

[0016] 5. The drone battery quick-change structure of the present invention has a pressing block at the center of the outer side of the front end surface of the locking handle. The pressing block is provided with anti-slip grooves. When the battery is installed, the locking handle needs to be rotated and pressed down to make room for the battery. The pressing block facilitates the rotation operation of the locking handle, and the anti-slip grooves can prevent the locking handle from rebounding due to hand slippage and causing damage to the battery. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a structural schematic diagram of the present invention;

[0018] Figure 2 This is a schematic diagram of the hatch cover of the present invention being opened and the locking handle being pressed down;

[0019] Figure 3 This is a schematic diagram of the battery installation of the present invention;

[0020] Figure 4 This is a schematic diagram of the battery installation and locking state of the present invention;

[0021] Figure 5 This is a schematic diagram of the hatch cover closing process of the present invention;

[0022] Figure 6 A schematic diagram of the hatch cover of the present invention being closed;

[0023] Figure 7 It is a schematic diagram of the principle of opening the hatch cover of the present invention.

[0024] Description of Reference Numerals

[0025] 1- hatch cover, 2- locking handle limiter, 3- hatch cover spring lock hook, 4- fuselage, 5- lock hole, 6- battery compartment, 7- battery compartment frame, 8- locking handle, 9- down pressure block, 10- front locking point, 11- guide rail, 12- hatch cover hinge, 13- paddle, 14- battery, 15- side locking point, 16- hinge base. DETAILED DESCRIPTION

[0026] The present invention will be further described in detail below through specific examples. The following examples are only illustrative and not restrictive, and the scope of protection of the present invention cannot be limited thereto.

[0027] like Figure 1 , a quick-change battery structure for an unmanned aerial vehicle, the innovation of which lies in: comprising a hatch 1 and a fuselage 4, a battery compartment rack 7 is provided in the battery compartment 6 on the inner side of the fuselage 4, the battery compartment rack 7 divides the battery compartment 6 into two battery installation spaces, and guide rails 11 are symmetrically installed in the battery installation spaces, and batteries 14 are slidably installed between the guide rails 11, and the upper end of the battery compartment rack 7 is hingedly connected to the hatch 1 through a hatch hinge 12, and the hatch 1 can be flipped open and closed along the fuselage 4, and a locking handle 8 is installed on the front end of the battery compartment 6 through rotation of the base, and a torsion spring is installed in the base, and the locking handle can be reset by the torsion spring. Lock holes 5 are provided on both sides of the battery compartment rack 7, and hatch spring lock hooks 3 are provided on the hatch 1 corresponding to the lock holes 5. When the hatch 1 and the fuselage 4 are closed, the hatch spring lock hooks 3 are buckled and locked with the lock holes 5, and a paddle 13 is uniformly formed at the end of the hatch spring lock hook 3, and the paddle 13 extends out of the hatch 1.

[0028] Locking handle limiters 2 are provided at the two ends of the inner side of the hatch 1 corresponding to the front end surface of the locking handle 8. When the hatch 1 and the fuselage 4 are closed, the locking handle limiter 2 abuts against the lower end of the locking handle 8. When the hatch 1 and the fuselage are closed, the locking handle limiter abuts against the lower end of the locking handle, which has a fault-tolerant design. Even if the locking handle is not fully in place, the locking handle limiter abuts against the locking handle a second time during the closing process of the battery hatch to reset it, thereby ensuring the reliability of battery locking.

[0029] The front end surface of the locking handle 8 is symmetrically provided with a front locking point 10, and the locking handle 8 is symmetrically provided with side locking points 15 on both sides, which can limit the battery and prevent the battery from escaping from the electromagnetic compartment.

[0030] A pressing block 9 is provided at the center of the outer side of the front end surface of the locking handle 8. The pressing block 9 is provided with anti-slip grooves. When the battery is installed, the locking handle needs to be rotated and pressed down to make room for the battery. The pressing block facilitates the rotation operation of the locking handle, and the anti-slip grooves can prevent the locking handle from rebounding due to slipping of the hand and causing damage to the battery.

[0031] The working principle of the present invention is:

[0032] The hatch opening principle is as follows Figure 7 As shown, two hinge seats are symmetrically fixedly installed at both ends of the inner side of the fuselage, and the hinge seats are hingedly connected to the hatch hinge, and the lower end of the hatch hinge is connected to the hatch;

[0033] After the hatch is opened, press the pressing block to rotate the locking handle downward to leave space for battery insertion. Figure 2 ; Insert the battery horizontally along the guide rails toward the battery compartment. Figure 3 ; Loosen the locking handle to make it rebound and reset. At this time, the battery cannot be removed from the battery compartment due to the restriction of the front locking point and the side locking point of the locking handle. Figure 4 ;

[0034] After the battery is installed, the hatch cover is folded down. When it is close to the closed position, the hatch cover spring lock hook installed on the hatch cover rotates clockwise under the action of the lock hole. At the same time, the locking handle limiter gradually approaches the locking handle and presses against the locking handle through the inclined surface. Figure 5 Until the hatch is completely closed, the hatch spring lock hook rebounds counterclockwise under the force of the tension spring to lock the lock hole on the front face of the battery compartment, and the locking handle limiter holds the locking handle in place to ensure reliable locking of the battery. Figure 6 .

[0035] Although the embodiments and drawings of the present invention are disclosed for illustrative purposes, those skilled in the art will understand that various substitutions, changes and modifications are possible without departing from the spirit and scope of the present invention and the appended claims. Therefore, the scope of the present invention is not limited to the contents disclosed in the embodiments and drawings.

Claims

1. A quick-change battery structure for a drone, characterized by: The invention comprises a hatch (1) and a fuselage (4), wherein a battery compartment (6) inside the fuselage (4) is provided with a battery compartment frame (7), wherein the battery compartment frame (7) divides the battery compartment (6) into two battery installation spaces, wherein guide rails (11) are symmetrically installed in the battery installation spaces, and batteries (14) are slidably installed between the guide rails (11), and the upper end of the battery compartment frame (7) is hingedly connected to the hatch (1) through a hatch hinge (12), and the hatch (1) can be flipped open and closed along the fuselage (4), and the battery compartment (6) is symmetrically installed in the battery installation spaces, wherein the guide rails (11) are symmetrically installed in the battery installation spaces, and the batteries (14) are slidably installed between the guide rails (11), and the upper end of the battery compartment frame (7) is hingedly connected to the hatch (1) through a hatch hinge (12), and the hatch (1) can be flipped open and closed along the fuselage (4). The front end of the battery compartment frame (7) is provided with a locking handle (8) which is rotated by the base. A torsion spring is installed in the base. The locking handle (8) can be reset by the torsion spring. Lock holes (5) are provided on both sides of the battery compartment frame (7). A hatch cover spring lock hook (3) is provided on the hatch cover (1) corresponding to the lock hole (5). When the hatch cover (1) and the fuselage (4) are closed, the hatch cover spring lock hook (3) and the lock hole (5) are locked. A paddle (13) is integrally formed at the end of the hatch cover spring lock hook (3). The paddle (13) extends out of the hatch cover (1). Locking handle limiters (2) are provided at the positions of the front end of the locking handle (8) at both ends of the inner side of the hatch cover (1); when the hatch cover (1) and the fuselage (4) are closed, the locking handle limiters (2) abut against the lower end of the locking handle (8); A front locking point (10) is symmetrically provided on the inner side of the front end surface of the locking handle (8), and side locking points (15) are symmetrically provided on both sides of the locking handle (8); A lower pressing block (9) is integrally formed at the center of the outer side of the front end surface of the locking handle (8), and the lower pressing block (9) is provided with anti-slip grooves.

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