Multi-redundant whole-machine power supply device for unmanned aerial vehicle and unmanned aerial vehicle

Abstract

The utility model discloses a kind of multi-redundancy whole machine power supply device for unmanned plane and unmanned plane, including four independent battery unit B1, B2, B3, B4 and parallel bus, the positive pole of battery unit B1 is connected with the negative pole of battery unit B2, forms first series branch, the positive pole of battery unit B3 is connected with the negative pole of battery unit B4, forms second series branch, the positive pole input end of parallel bus is simultaneously connected with the positive pole of B1 in first series branch and the positive pole of B3 in second series branch, the negative pole input end of parallel bus is simultaneously connected with the negative pole of B2 in first series branch and the negative pole of B4 in second series branch;Parallel bus is also connected with the main power output port for supplying power to unmanned plane whole machine. The utility model solves the problem that existing technology exists electric unmanned plane and causes whole machine power failure crash risk due to single battery fault.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicles (UAVs), and in particular to a multi-redundant power supply device for UAVs and the UAV itself. Background Technology

[0002] Currently, in the field of electric tandem rotor helicopter drones, especially medium and large models, the power supply system generally adopts a relatively simple design, which involves a single battery directly connected to the drone's main power input interface for power supply. This power supply method is representative of the industry; for example, the related products (such as power management systems, drone power supply modules, or power distribution boards) of major manufacturers such as DJI Technology Co., Ltd. and XAG Technology Co., Ltd. are mostly based on this single battery power supply solution.

[0003] The core of this existing technical solution lies in its reliance on a single power source, resulting in a simple and straightforward structure. However, this simplicity introduces a significant and critical flaw: when this single power source experiences any unexpected malfunction during operation (such as internal short circuit, open circuit, voltage drop, or complete failure), the entire drone's power supply will be instantly interrupted or a voltage drop will occur that prevents it from maintaining normal flight. Since the drone relies entirely on electricity to drive its flight control system, rotor motors, and payload, the direct consequence of this power outage is that the drone inevitably loses power and control, leading to a very high risk of crashing. This single point of failure mode seriously threatens flight safety, mission success rate, and equipment asset security, especially for medium to large-sized drones performing important missions or operating in high-value areas, where the consequences are even more severe, becoming a critical pain point that existing technologies urgently need to address.

[0004] In view of this, this technical solution proposes a multi-redundant power supply device and drone for unmanned aerial vehicles (UAVs). By adopting a two-series-two-parallel battery pack topology (specifically using four 6S batteries), an inherent power supply redundancy mechanism is constructed. When any battery fails, thanks to the unique design combining parallel and series connections, the remaining battery pack can seamlessly continue to maintain the operating voltage and current levels required by the system. This ensures that even in the event of a single battery failure, the power supply system does not experience power outages or voltage drops, and the entire drone can still maintain normal operation. This completely eliminates the inherent risk of drone crashes associated with single-battery power supply solutions, significantly improving the reliability and safety of the UAV power supply system and enhancing fault tolerance. Utility Model Content

[0005] The present invention aims to at least partially solve one of the technical problems in related technologies. Therefore, the main objective of this invention is to provide a multi-redundant power supply device for unmanned aerial vehicles (UAVs) and the UAV itself, thereby addressing the risk of power outages and crashes in existing electric UAVs due to the failure of a single battery.

[0006] To achieve the above objectives, this utility model provides a multi-redundant power supply device for unmanned aerial vehicles (UAVs) and the UAV itself, comprising four independent battery units B1, B2, B3, and B4 and a parallel bus.

[0007] The positive terminal of battery cell B1 is connected to the negative terminal of battery cell B2, forming a first series branch.

[0008] The positive terminal of battery cell B3 is connected to the negative terminal of battery cell B4, forming a second series branch.

[0009] The positive input terminal of the parallel bus is simultaneously connected to the positive terminal of B1 in the first series branch and the positive terminal of B3 in the second series branch, and the negative input terminal of the parallel bus is simultaneously connected to the negative terminal of B2 in the first series branch and the negative terminal of B4 in the second series branch.

[0010] The parallel bus is also connected to a main power output port for supplying power to the entire drone.

[0011] As a further embodiment of this utility model, the battery units B1, B2, B3, and B4 are all 6S lithium batteries, and the nominal voltage of each battery is 22.2V.

[0012] As a further embodiment of this utility model, the parallel bus is integrated with an anti-backflow circuit, which includes a diode disposed at the output end of each series branch. The anode of the diode is connected to the positive terminal of the series branch, and the cathode is connected to the positive terminal of the parallel bus.

[0013] As a further improvement of this invention, the anti-backflow circuit also includes an overcurrent protection device, which is a surface-mount self-resetting fuse connected in series between each series branch and the parallel bus.

[0014] An electric tandem dual-rotor helicopter drone includes a multi-redundant power supply device for the drone and the drone itself. The main power output port is electrically connected to the drone's motor controller and flight control system.

[0015] The beneficial effects of this utility model are as follows:

[0016] This technical solution addresses the fatal flaw of existing electric drones, where a single battery failure can cause the entire drone to lose power and crash. It constructs a redundant architecture of two series and two parallel using four independent battery units B1, B2, B3, and B4. Specifically, B1 and B2 are connected in series to form the first series branch, and B3 and B4 are connected in series to form the second series branch. The positive terminals (connected to the positive terminals of B1 / B3) and the negative terminals (connected to the negative terminals of B2 / B4) of the two series branches are then connected in parallel via a parallel bus and output to the main power output port. When any single battery in B1-B4 fails (such as a 22.2V 6S lithium battery), the remaining three batteries can still maintain the rated voltage of 44.4V at the main power output port through the parallel bus. At the same time, the diodes at the output of each series branch (anode connected to the positive terminal of the branch / cathode connected to the bus) block the backflow of fault current, and the series-connected surface-mount self-resetting fuses disconnect and isolate the faulty branch in case of overcurrent. With this dual protection, the UAV motor controller and flight control system are guaranteed to receive stable power continuously, completely eliminating the risk of rotor stoppage or attitude loss of tandem twin-rotor helicopters due to power interruption. Attached Figure Description

[0017] To more clearly illustrate the technical solutions of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the technical solutions of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the circuit structure of the power supply device in this utility model.

[0019] [Explanation of Markings on Main Components / Assemblies]

[0020] label name label name 1 Battery cell B1 11 First series branch 2 Battery cell B2 12 Second series branch 3 Battery cell B3 5 Parallel bus 4 Battery cell B4 50 Main power output port Detailed Implementation

[0021] as follows:

[0022] Please see the appendix Figure 1 ,

[0023] The main structure includes four independent battery units B1, B2, B3, and B4, and a parallel bus. The positive terminal of battery unit B1 is connected to the negative terminal of battery unit B2 to form a first series branch. The positive terminal of battery unit B3 is connected to the negative terminal of battery unit B4 to form a second series branch. The positive input terminal of the parallel bus is connected to the positive terminals of B1 in the first series branch and B3 in the second series branch. The negative input terminal of the parallel bus is connected to the negative terminals of B2 in the first series branch and B4 in the second series branch. The parallel bus is also connected to a main power output port for powering the entire UAV.

[0024] The working principle is as follows:

[0025] This technical solution utilizes four independent battery units B1, B2, B3, and B4 to construct a two-series, two-parallel redundant circuit structure. Specifically, the positive terminal of battery unit B1 is connected to the negative terminal of battery unit B2 to form the first series branch, and the positive terminal of battery unit B3 is connected to the negative terminal of battery unit B4 to form the second series branch. The positive input terminals (connecting the positive terminals of battery units B1 and B3) and the negative input terminals (connecting the negative terminals of battery units B2 and B4) of the two series branches are then connected in parallel via a parallel bus and output to the main power output port. This structure fundamentally solves the fatal flaw of existing single-battery power supply schemes, where the entire drone crashes due to the failure of any single battery (such as a short circuit / open circuit). When any single battery among battery units B1-B4 fails, the remaining three batteries automatically maintain the rated voltage of the main power output port via the parallel bus (for example, a 22.2V 6S lithium battery can still maintain a working voltage of 44.4V), ensuring continuous power supply to the drone's motor controller and flight control system. A reverse current protection circuit can also be set up. This circuit (diodes at the output of the series branch and surface-mount self-resetting fuse) further blocks the reverse current from the faulty branch, which not only eliminates the risk of crash but also improves the fault tolerance of the power supply system. It is particularly suitable for the safety redundancy requirements of medium and large UAVs such as electric tandem rotor helicopters.

[0026] In a preferred embodiment of this utility model, battery units B1, B2, B3, and B4 are all 6S lithium batteries, and the nominal voltage of each battery is 22.2V.

[0027] In this technical solution, battery cells B1, B2, B3, and B4 use 6S lithium batteries with a nominal voltage of 22.2V, ensuring sufficient energy density and discharge capacity for each battery. When connected in series in the first series branch (B1-B2) and the second series branch (B3-B4), each branch can stably output 44.4V. If any single battery (e.g., B1) fails, the remaining three batteries, connected in parallel, can still maintain the rated operating voltage of 44.4V at the main power output port. This is because the unfailed series branches (e.g., B3-B4) maintain a complete voltage output, and the anti-reverse current circuit isolates the faulty branch, ensuring a continuous and safe voltage supply to the UAV motor controller and flight control system.

[0028] In a preferred embodiment of this utility model, an anti-backflow circuit is integrated on the parallel bus. The anti-backflow circuit includes a diode disposed at the output end of each series branch. The anode of the diode is connected to the positive terminal of the series branch, and the cathode is connected to the positive terminal of the parallel bus.

[0029] This solution sets up a diode at the output end of each series branch (anode connected to the positive terminal of B1 or B3, cathode connected to the positive terminal of the parallel bus). Utilizing the unidirectional conduction characteristic of the diode, when a series branch (such as B1-B2) experiences voltage abnormality due to a single battery failure, the forced current can only flow from the normal branch to the positive terminal of the parallel bus, blocking the reverse flow of the faulty branch current into the normal branch, preventing the fault from escalating and maintaining the stability of the main power output port voltage.

[0030] In a preferred embodiment of this utility model, the anti-reverse current circuit further includes an overcurrent protection device, which is a surface-mount self-resetting fuse connected in series between each series branch and the parallel bus.

[0031] Specifically, a surface-mount resettable fuse is connected in series between each series branch (such as B1-B2, B3-B4) and the positive terminal of the parallel bus. When an overcurrent occurs in a branch due to a battery fault (such as a short circuit), the fuse of that branch immediately disconnects to isolate the fault, preventing abnormal current from flowing into the parallel bus and avoiding affecting the power supply of another normal branch. After the fault is cleared, the fuse automatically resumes conduction, forming a double protection with the diode to ensure that the main power output port continuously and stably supplies power to the UAV system.

[0032] A drone includes a multi-redundant power supply device for the drone and the drone itself, wherein the main power output port is electrically connected to the drone's motor controller and flight control system.

[0033] This technical solution directly connects the main power output port to the UAV motor controller and flight control system, enabling the tandem dual-rotor helicopter to maintain a stable 44.4V voltage output through redundant branches even when any single battery unit (B1-B4) fails. This ensures continuous power supply to the dual-rotor power system and flight control core, completely eliminating the risk of rotor stoppage or attitude loss due to power interruption.

[0034] The above are merely preferred embodiments of the present utility model and do not limit the patent scope of the present utility model. Any equivalent structural transformations made using the contents of the present utility model specification and drawings under the concept of the present utility model, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present utility model.

Claims

1. A multi-redundant power supply device for unmanned aerial vehicles (UAVs), characterized in that, include Four independent battery cells B1, B2, B3, B4 and a parallel bus, The positive terminal of battery cell B1 is connected to the negative terminal of battery cell B2, forming a first series branch. The positive terminal of battery cell B3 is connected to the negative terminal of battery cell B4, forming a second series branch. The positive input terminal of the parallel bus is simultaneously connected to the positive terminal of B1 in the first series branch and the positive terminal of B3 in the second series branch. The negative input terminal of the parallel bus is simultaneously connected to the negative terminal of B2 in the first series branch and the negative terminal of B4 in the second series branch. The parallel bus supplies power to the entire UAV through the main power output port.

2. The multi-redundant power supply device for unmanned aerial vehicles according to claim 1, characterized in that, The battery cells B1, B2, B3, and B4 are all 6S lithium batteries, and each battery has a nominal voltage of 22.2V.

3. The multi-redundant power supply device for unmanned aerial vehicles according to claim 1, characterized in that, The parallel bus integrates an anti-backflow circuit, which includes a diode at the output of each series branch. The anode of the diode is connected to the positive terminal of the series branch, and the cathode is connected to the positive terminal of the parallel bus.

4. The multi-redundant power supply device for unmanned aerial vehicles according to claim 3, characterized in that, The anti-backflow circuit also includes an overcurrent protection device, which is a surface-mount self-resetting fuse connected in series between each series branch and the parallel bus.

5. An unmanned aerial vehicle (UAV), characterized in that: The device includes a multi-redundant power supply unit for a drone as described in any one of claims 1-4, wherein the main power output port is electrically connected to the drone's motor controller and flight control system.

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