Unmanned aerial vehicle power supply system and unmanned aerial vehicle

Abstract

The unmanned aerial vehicle power supply system comprises a motor power supply link, a standby link, a flight control loop and a propeller motor, the flight control loop comprises a flight control unit and a flight control battery, and the output end of the flight control unit is connected with the motor power supply link and the standby link. The output end of the flight control battery is connected with the input end of the flight control unit and the standby link, the input end of the propeller motor is connected with the motor power supply link and the standby link, and the output end is connected with the flight control unit; when the flight control unit receives that the rotating speed of the propeller motor is lower than a set value, the motor power supply link is controlled to be disconnected, and the standby link is closed. By monitoring the rotating speed of a propeller, disconnecting an original motor power supply link and connecting a standby link, the standby link is connected with an inherent flight control battery, an original battery on the unmanned aerial vehicle is fully utilized, a standby battery is not independently added, and the flight weight is reduced to the maximum extent.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft power supply, and in particular to a power supply system for an unmanned aerial vehicle and an unmanned aerial vehicle. Background Art

[0002] Electric drones are a new concept aircraft that is in rapid development. They have the advantages of maneuverability, quick response, low operating requirements, and green environmental protection. In electric aircraft, a motor power supply link is used to power the propeller motor. If the motor power supply link fails during flight, the propeller speed will be reduced or even stopped, which will seriously affect the flight. A method for protecting the electric propulsion system in the event of a failure is proposed in the prior art. An electric propulsion unit including a battery and multiple motor controllers is set outside the motor power supply link as a backup to avoid propeller stalling. This method requires external batteries and multiple controllers on the basis of the original circuit, which will increase the weight of the aircraft and complicate the control system. If the aircraft is powered by one battery to supply one motor, multiple backup circuits need to be connected externally, which greatly increases the weight of the aircraft and affects the flight of the aircraft. Utility Model Content

[0003] The purpose of this section is to summarize some aspects of the embodiments of the utility model and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this section and the specification abstract and utility model name of this application to avoid blurring the purpose of this section, specification abstract and utility model name, and such simplifications or omissions cannot be used to limit the scope of the utility model.

[0004] In view of the problems existing in the above-mentioned existing UAV power supply system, the present utility model is proposed. The technical problem solved by the present utility model is that the backup circuit for circuit failure in the existing power supply system needs to be equipped with batteries and multiple controllers, which will increase the weight of the aircraft and affect the flight.

[0005] To solve the above technical problems, the utility model provides the following technical solutions: a power supply system for an unmanned aerial vehicle includes a motor power supply link, a backup link, a flight control loop, and a propeller motor. The flight control loop includes a flight control unit and a flight control battery. The output end of the flight control unit is connected to the motor power supply link and the backup link. The output end of the flight control battery is connected to the input end of the flight control unit and the backup link. The input end of the propeller motor is connected to the motor power supply link and the backup link, and the output end is connected to the flight control unit. When the flight control unit receives that the speed of the propeller motor is lower than a set value, the motor power supply link is controlled to be disconnected and the backup link is closed.

[0006] As a preferred solution of the UAV power supply system described in the utility model, the motor power supply link includes a first relay, a battery and an electric regulator, the battery, the first relay and the electric regulator are connected in series, the output end of the electric regulator is connected to the propeller motor, and the input ends of the electric regulator and the first relay are connected to the output end of the flight control unit.

[0007] As a preferred solution of the UAV power supply system described in the utility model, the backup link includes a second relay and a backup point regulator, the second relay and the backup point regulator are connected in series, the input end of the backup point regulator is connected to the flight control battery, and the input end of the second relay is connected to the output end of the flight control unit.

[0008] As a preferred solution of the drone power supply system described in the utility model, wherein: the first relay includes a normally closed contact, which is connected between the battery and the electronic regulator. When the flight control unit receives that the speed of the propeller motor is lower than the set value, the flight control unit controls the normally closed contact of the first relay to disconnect.

[0009] As a preferred solution of the UAV power supply system described in the utility model, the second relay includes a normally open contact, which is installed between the standby electric regulator and the propeller motor. When the flight control unit receives a signal that the speed of the propeller motor is lower than a set value, the flight control unit controls the normally open contact of the second relay to close.

[0010] As a preferred solution of the unmanned aerial vehicle power supply system described in the utility model, there are multiple propeller motors, each of which is connected to a motor power supply link and a backup link, the motor power supply link and the backup link connected to the same propeller motor correspond one to one, multiple motor power supply links are connected in parallel, multiple backup links are connected in parallel, the output end of the flight control unit is connected to the multiple motor power supply links and the backup links, and the input ends of the multiple backup links are connected to the output end of the flight control battery.

[0011] As a preferred solution of the UAV power supply system described in the utility model, wherein: the input end of the flight control unit is connected to the output end of the electric regulator.

[0012] As a preferred solution of the unmanned aerial vehicle power supply system described in the utility model, wherein: the flight control unit includes a propeller speed collection element, a judgment element, a relay switch control element and an electric adjustment control signal sending element, the input end of the propeller speed collection element is connected to the propeller motor, and the output end is connected to the judgment element, the output end of the judgment element is connected to the relay switch control element, the output end of the relay switch control element is connected to the first relay and the second relay, and the output end of the electric adjustment control signal sending element is connected to the electric adjustment and the standby electric adjustment.

[0013] As a preferred solution of the unmanned aerial vehicle power supply system described in the utility model, wherein: the output end of the flight control battery is also connected to the flight equipment subsystem, the third relay is connected between the flight control battery and the flight equipment subsystem, the third relay includes a normally closed contact, and the normally closed contact is connected to the output end of the flight control unit. When the flight control unit detects that the speed of the propeller motor is lower than the set value, the normally closed contact of the third relay is controlled to open.

[0014] Another purpose of this embodiment is to provide a drone, which is equipped with the above-mentioned drone power supply system.

[0015] Beneficial effects of the utility model: The advantages of the drone power supply system constructed by the utility model are as follows:

[0016] (1) By monitoring the propeller speed, the original motor power supply link is disconnected and the backup link is connected. The backup link is connected to the inherent flight control battery, making full use of the original battery on the drone without adding a separate backup battery, thereby maximizing the reduction of flight weight;

[0017] (2) Since the power supply circuit and the backup circuit are connected in series, when a motor power supply link failure occurs, the flight control unit will isolate the battery from the circuit by opening the normally closed contact of the relay. If a battery failure occurs, the impact of the faulty battery on the power supply circuit can be reduced;

[0018] (3) A backup link is set for each propeller motor. The backup link corresponds to the power supply link one by one, so that the faulty motor can be responded to in time to ensure the safe operation of the aircraft;

[0019] (4) When the propeller speed is lower than the set value, the flight control battery will promptly cut off the power supply to the flight equipment subsystem, ensuring the stability of the flight control battery's power supply to the propeller motor and flight control unit, and extending the UAV's flight time in crisis situations. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the following briefly introduces the drawings required for the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative labor. Among them:

[0021] Figure 1 This is a schematic diagram of the structure of the UAV power supply system according to the first embodiment of the utility model;

[0022] Figure 2 This is a flight control unit structure and control flow chart described in the first embodiment of the utility model.

[0023] The components in the attached drawings are marked as follows: flight control unit-1; propeller speed collection element-11; judgment element-12; relay switch control element-13; electric control control signal sending element-14; first relay-21; second relay-22; second relay-23; flight control battery-3; propeller motor-4; battery-5; electric control-6; standby point control-7. DETAILED DESCRIPTION

[0024] In order to make the above-mentioned purposes, features and advantages of the utility model more obvious and easy to understand, the specific implementation methods of the utility model are described in detail below in conjunction with the drawings of the specification. Obviously, the described embodiments are part of the embodiments of the utility model, but not all of them. Based on the embodiments of the utility model, all other embodiments obtained by ordinary persons in the field without creative work should fall within the scope of protection of the utility model.

[0025] In the following description, many specific details are set forth to facilitate a full understanding of the present invention, but the present invention may also be implemented in other ways different from those described herein, and those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0026] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure or characteristic that may be included in at least one implementation of the present invention. The term "in one embodiment" that appears in different places in this specification does not necessarily refer to the same embodiment, nor does it refer to a separate or selective embodiment that is mutually exclusive with other embodiments.

[0027] The utility model is described in detail with reference to the schematic diagram. When describing the embodiments of the utility model, for the sake of convenience, the cross-sectional diagrams showing the device structure will not be partially enlarged according to the general proportion, and the schematic diagrams are only examples, which should not limit the scope of protection of the utility model. In addition, in actual production, the three-dimensional dimensions of length, width and depth should be included.

[0028] At the same time, in the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "upper, lower, inner and outer" are based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or component referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first, second or third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0029] In the present utility model, unless otherwise clearly specified and limited, the terms "install, connect, connect" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection or an integrated connection; it can also be a mechanical connection, an electrical connection or a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two original components. For ordinary technicians in this field, the specific meanings of the above terms in the utility model can be understood according to specific circumstances.

[0030] Example 1

[0031] Reference Figure 1 and 2 The embodiment provides a power supply system for a drone, including a motor power supply link, a backup link, a flight control loop, and a propeller motor 4, wherein the flight control loop includes a flight control unit 1 and a flight control battery 3, the output end of the flight control unit 1 is connected to the motor power supply link and the backup link, and controls the opening and closing of the motor power supply link and the backup link, the output end of the flight control battery 3 is connected to the input end of the flight control unit 1 and the backup link, and supplies power to the flight control unit 1 and the backup link, the input end of the propeller motor 4 is connected to the motor power supply link and the backup link, the motor power supply link and the backup link supply power to the propeller motor 4, and the output end of the propeller motor 4 is connected to the flight control unit 1, and the speed data of the propeller is transmitted to the flight control unit, in the normal operating state of the drone, the motor power supply link is closed, the backup link is disconnected, and the motor power supply link supplies power to the propeller motor 4, when the flight control unit 1 receives that the speed of the propeller motor 4 is lower than the set value, the motor power supply link is controlled to be disconnected, the backup link is closed, and the backup link is connected to the output end of the flight control battery 3, and the propeller motor 4 is supplied with power by the flight control battery 3, thereby ensuring the smooth operation of the drone.

[0032] In this embodiment, the motor power supply link includes a first relay 21, a battery 5 and an electric regulator 6, which are connected in series. The output end of the electric regulator 6 is connected to the propeller motor 4, and the battery 5 supplies power to the power supply link. The input end of the electric regulator 6 is connected to the output end of the flight control unit 1. The flight control unit 1 transmits the propeller motion data to the electric regulator 6, and controls the operation of the propeller motor 4 through the electric regulator 6. The input end of the first relay 21 is also connected to the output end of the flight control unit 1. The flight control unit 1 controls the switch of the first relay 21, thereby changing the power supply link of the propeller motor 4.

[0033] Furthermore, the backup link includes a second relay 22 and a backup point adjustment 7, which are connected in series. The input end of the backup point adjustment 7 is connected to the flight control battery 3, and the input end of the second relay 22 is connected to the output end of the flight control unit 1. The flight control unit 1 controls the switch of the second relay 22.

[0034] It should be noted that the first relay 21 includes a normally closed contact, and the second relay 22 includes a normally open contact. When the propeller operates normally, the normally closed contact of the first relay 21 is in a closed state, and the normally open contact of the second relay 22 is in an open state. A power supply loop is formed between the motor power supply link and the propeller motor 4, and the connection between the backup link and the propeller motor 4 is disconnected. The propeller motor 4 is powered by the battery 5 in the motor power supply link, and the flight control unit 1 controls the operation of the propeller motor 4 through the electric regulator 6; when the input end of the flight control unit 1 receives that the speed of the propeller is lower than the set value, the flight control unit 1 controls the normally closed contact of the first relay 21 to be disconnected, and controls the normally open contact of the second relay 22 to be closed, so that a power supply loop is formed between the backup link and the propeller motor 4, and the connection between the motor power supply link and the propeller motor 4 is disconnected. Since the backup link is connected to the output end of the flight control battery 3, the propeller motor 4 is powered by the flight control battery 3 at this time to maintain the stable operation of the drone.

[0035] It should be noted that the first relay 21 is connected between the battery 5 and the electric speed controller 6, and the second relay 22 is installed between the standby electric speed controller 7 and the propeller motor 4. When the speed of the propeller is lower than the set value, the normally closed contact of the first relay 21 is disconnected, and the normally open contact of the second relay 22 is closed, so that the battery 5 is isolated from the flight circuit, and the power supply can be directly isolated, and the power supply to the faulty circuit is stopped or the impact of the faulty battery on the flight circuit is reduced. The standby electric speed controller 7 in the standby link transmits the control data transmitted from the flight control unit 1 to the electric speed controller 6 to the standby electric speed controller 7, and the movement of the propeller motor 4 is controlled by the standby electric speed controller 7.

[0036] In the present embodiment, there are multiple propeller motors 4, each propeller motor 4 is connected to a motor power supply link and a backup link, forming multiple motor power supply links and backup links, the multiple motor power supply links are connected in parallel, the multiple backup links are connected in parallel, and are all connected to the flight control unit 1. Since each motor power supply link and the backup link supplies power to one propeller motor 4, the number of the two is the same, and there is a one-to-one correspondence according to the connected propeller motors 4. When the propeller speed collected by the flight control unit 1 is lower than the set value, the normally closed contact of the first relay 21 is controlled to open, and the normally open contact of the second relay 22 in the backup link connected to the same propeller motor 4 is closed. The propeller motor 4 is powered by the backup link. Since most existing drones adopt a direct supply method of one battery corresponding to one motor, this solution provides a corresponding backup link for each supply battery, which can respond to and handle the failure of each motor in a timely manner.

[0037] In this embodiment, the input end of the flight control unit 1 is connected to the output end of the electric speed regulator 6. The electric speed regulator 6 can not only receive the control data of the speed of the propeller motor provided by the flight control unit 1, but also obtain the movement status of the propeller motor in real time. The input end of the flight control unit 1 is connected to the output end of the electric speed regulator 6, and the motion data of the propeller can be directly obtained from the electric speed regulator 6.

[0038] In this embodiment, refer to Figure 2The flight control unit 1 includes a propeller speed acquisition element 11, a judgment element 12, a relay switch control element 13 and an electric adjustment control signal sending element 14. The four elements are connected in sequence. The propeller speed acquisition element 11 is used to obtain the speed of the propeller motor 4 in real time and transmit the speed data to the judgment element 12. The judgment element 12 judges whether the speed is lower than the set value. The relay switch control element 13 can control the switch of the relay 2 in the motor power supply link and the backup link. When the propeller speed acquisition element 11 detects that the speed of the propeller motor 4 is lower than the set value, the judgment element 12 transmits an electrical signal to the relay switch control element 13. The relay switch control element 13 controls the relay 2 in the motor power supply link to open, isolates the motor power supply link from the propeller motor 4, and controls the relay 2 in the backup link to close, connecting the backup link to the propeller motor 4. The electric adjustment control signal sending element 14 sends the electric adjustment control signal to the running electric adjustment 6 or the backup electric adjustment 7. The principle is: when the propeller motor 4 operates normally, the propeller speed acquisition element 11 monitors the speed of the motor in real time, the judgment element 12 compares the speed with the set value, the motor power supply link provides power support for the propeller motor, and the electric control signal sending element 14 sends the electric control signal to the electric control 6 to control the operation of the propeller motor. When the judgment element 12 detects that the speed of the propeller motor 4 is lower than the set value, the relay switch control element 13 sends a signal to control the normally closed contact of the first relay 21 to open, and controls the normally open contact of the second relay 22 to close, so as to connect the flight control battery 3 with the propeller motor 4 to provide power support for it, thereby ensuring the smooth operation of the aircraft. The electric control signal sending element 14 sends the electric control signal to the standby electric control 7, and the standby electric control 7 controls the operation of the propeller motor according to the control information. After a circuit failure, the electric control information that should have been transmitted to the power supply circuit is transmitted to the standby electric control, and the electric control information does not change, thereby further ensuring the stable operation of the aircraft.

[0039] It should be noted that, in actual application, the propeller speed acquisition element 11 can be a data receiver, which obtains the speed data by obtaining the feedback of the electric regulator 6 connected to the propeller motor 4; the propeller speed acquisition element 11 can also be a small propeller speed measuring device installed on the propeller motor 4, which uses a camera, laser or other means to measure the speed of the propeller connected to the propeller motor 4.

[0040] In this embodiment, the output end of the flight control battery 3 is also connected to the flight equipment subsystem. The flight control unit 1 also includes systems that are strongly related to the UAV when it is flying in the air and will affect the flight of the aircraft when it is cut off, such as navigation system, data transmission system, flight control system, etc., to ensure the flight of the UAV in the event of a fault. The flight equipment subsystem is a system that is not strongly related to the UAV when it is flying and will not affect the flight of the aircraft when it is cut off, such as lighting, navigation lights, landing lights, taxi lights, hub motors, water jet propulsion, etc., as well as additional functional equipment. A third relay 23 is set between the subsystems, and the third relay 23 includes a normally closed contact. When the UAV is operating normally, the flight equipment subsystem is powered by the flight control battery 3, and the normally closed contact of the third relay 23 is closed and connected to the output end of the flight control unit 1. When the propeller speed acquisition element 11 detects that the speed of the propeller motor 4 is lower than the set value, the relay switch control element 13 opens the normally closed contact of the third relay 23, disconnects the flight equipment subsystem from the flight control battery 3, and prolongs the power supply time of the flight control battery 3 to the flight control system 1 and the propeller motor 4, saving energy consumption.

[0041] The working principle of the power supply system of this embodiment is as follows: during the flight of the UAV, when a power supply circuit of a propeller motor 4 fails, the speed of the propeller motor 4 will be reduced, affecting the normal flight of the UAV. The propeller speed acquisition component 11 collects the speed data of the propeller motor 4 in real time, and transmits the collected data to the judgment component 12. The judgment component 12 determines whether the collected speed is lower than the set value. If it is not lower than the set value, the electric adjustment control signal sending component 14 transmits the electric adjustment control information to the electric adjustment 6 to control the speed of the propeller motor 4. If the collected speed is lower than the set value, the electric adjustment control signal sending component 14 will send the electric adjustment control information to the electric adjustment 6 to control the speed of the propeller motor 4. If the speed is lower than the set value, the flight control unit 1 will open the normally closed contacts of the first and third relays connecting the electric regulator 6 and the flight equipment subsystem, disconnect the battery 5 and the flight equipment subsystem from the circuit, and close the normally open contact of the second relay 22 at the same time, and the flight control battery 3 will supply power to the propeller motor 4 through the backup electric regulator 7, and the electric regulator control signal sending element 14 will transmit the electric regulator control signal transmitted to the original electric regulator 6 to the corresponding backup electric regulator 7, that is, the motor control strategy is transferred from the faulty electric regulator to the backup electric regulator, thereby controlling the motor speed to ensure a smooth return or forced landing of the aircraft.

[0042] Example 2

[0043] Different from the above-mentioned embodiment, this embodiment provides a UAV, which is equipped with the above-mentioned UAV power supply system to ensure that when the propeller speed of the UAV has problems, the backup link is cut in to ensure the smooth flight and landing of the UAV, and the UAV with this power supply system does not need to add additional power supply batteries, which can reduce the overall weight of the UAV and ensure the flight effect.

[0044] It should be noted that the above embodiments are only used to illustrate the technical solution of the utility model rather than to limit it. Although the utility model has been described in detail with reference to the preferred embodiments, ordinary technicians in the field should understand that the technical solution of the utility model can be modified or replaced by equivalents without departing from the spirit and scope of the technical solution of the utility model, which should be included in the scope of the claims of the utility model.

Claims

1. A UAV power supply system, characterized in that: Including motor power supply link, backup link, flight control loop, propeller motor (4), The flight control loop comprises a flight control unit (1) and a flight control battery (3), the output end of the flight control unit (1) is connected to the motor power supply link and the backup link, the output end of the flight control battery (3) is connected to the input end of the flight control unit (1) and the backup link, the input end of the propeller motor (4) is connected to the motor power supply link and the backup link, and the output end is connected to the flight control unit (1); When the flight control unit (1) receives information that the rotation speed of the propeller motor (4) is lower than a set value, it controls the motor power supply link to be disconnected and the standby link to be closed.

2. The UAV power supply system according to claim 1, characterized in that: The motor power supply link comprises a first relay (21), a battery (5) and an electric regulator (6); the battery (5), the first relay (21) and the electric regulator (6) are connected in series; the output end of the electric regulator (6) is connected to the propeller motor (4); and the input ends of the electric regulator (6) and the first relay (21) are connected to the output end of the flight control unit (1).

3. The UAV power supply system according to claim 2, characterized in that: The backup link comprises a second relay (22) and a backup point regulator (7), wherein the second relay (22) and the backup point regulator (7) are connected in series, an input end of the backup point regulator (7) is connected to the flight control battery (3), and an input end of the second relay (22) is connected to an output end of the flight control unit (1).

4. The UAV power supply system according to claim 2, characterized in that: The first relay (21) comprises a normally closed contact connected between the battery (5) and the electric regulator (6); when the flight control unit (1) receives that the rotation speed of the propeller motor (4) is lower than a set value, the flight control unit (1) controls the normally closed contact of the first relay (21) to be disconnected.

5. The UAV power supply system according to claim 3, characterized in that: The second relay (22) comprises a normally open contact, which is installed between the standby point adjustment (7) and the propeller motor (4). When the flight control unit (1) receives that the rotation speed of the propeller motor (4) is lower than a set value, the flight control unit (1) controls the normally open contact of the second relay (22) to close.

6. The UAV power supply system according to claim 1, characterized in that: There are a plurality of propeller motors (4), each of which is connected to a motor power supply link and a backup link. The motor power supply link and the backup link connected to the same propeller motor (4) correspond to each other one by one. The plurality of motor power supply links are connected in parallel, and the plurality of backup links are connected in parallel. The output end of the flight control unit (1) is connected to the plurality of motor power supply links and the backup links, and the input ends of the plurality of backup links are connected to the output end of the flight control battery (3).

7. The UAV power supply system according to claim 2, characterized in that: The input end of the flight control unit (1) is connected to the output end of the electric regulator (6).

8. The UAV power supply system according to claim 3, characterized in that: The flight control unit (1) comprises a propeller speed acquisition element (11), a judgment element (12), a relay switch control element (13) and an electric control signal sending element (14); the input end of the propeller speed acquisition element (11) is connected to the propeller motor (4), and the output end is connected to the judgment element (12); the output end of the judgment element (12) is connected to the relay switch control element (13); the output end of the relay switch control element (13) is connected to the first relay (21) and the second relay (22); the output end of the electric control signal sending element (14) is connected to the electric control (6) and the standby point control (7).

9. The UAV power supply system according to claim 4, characterized in that: The output end of the flight control battery (3) is also connected to a flight equipment subsystem, and the third relay (23) is connected between the flight control battery (3) and the flight equipment subsystem. The third relay (23) comprises a normally closed contact, and the normally closed contact is connected to the output end of the flight control unit (1). When the flight control unit (1) detects that the rotation speed of the propeller motor (4) is lower than a set value, the normally closed contact of the third relay (23) is controlled to open.

10. A drone, characterized in that: The UAV is provided with a UAV power supply system as described in any one of claims 1-9.

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