CN115352642B - Unmanned vehicles hybrid power equipment - Google Patents

Abstract

The invention discloses unmanned aerial vehicle hybrid power equipment, which comprises a connecting shell, wherein an internal combustion engine and a brushless permanent magnet motor are arranged on the connecting shell, output shafts of the internal combustion engine and the brushless permanent magnet motor are connected with one-way clutch bearings, and the one-way clutch bearings are connected with a propeller through a driven shaft. The invention relates to the technical field of unmanned aerial vehicles, in particular to unmanned aerial vehicle hybrid power equipment. The most fuel-saving, highest efficiency and lowest emission are achieved, and the storage battery can be charged through the brushless permanent magnet motor. When the brushless permanent magnet motor is used as a power system, the brushless permanent magnet motor can be used as a standby power source when the internal combustion engine is damaged, and can be turned off to be driven by electric power when mute action is required. And the detection of an infrared system can be avoided because the temperature is driven to be reduced by electric power.

Description

Hybrid power equipment for unmanned aerial vehicle

Technical Field

The present invention relates to the technical field of unmanned aerial vehicles, in particular to a hybrid power device for unmanned aerial vehicles.

Background Art

With the vigorous development of the drone industry, the types and application areas of drones have become more extensive; for medium and large fixed-wing or compound-wing drones whose main flight missions are cruising, mapping and logistics transportation, their flight time and endurance are particularly important.

Existing drones have a problem that a single power system cannot meet the diverse usage conditions. For example, when the internal combustion engine fails to work, the drone will fall directly from a high altitude, causing great losses. In addition, in areas where low-pitched flight is required, the drone's generator is noisy and hot, making it difficult to fly covertly.

Summary of the invention

In view of the deficiencies of the prior art, the present invention provides a hybrid power device for an unmanned aerial vehicle, which solves the problems of the unmanned aerial vehicle having a single power source and being difficult to fly concealedly.

To achieve the above object, the present invention is implemented by the following technical solutions: A hybrid power device for an unmanned aircraft, comprising a connecting shell, an internal combustion engine and a brushless permanent magnet motor are mounted on the connecting shell, the output shafts of the internal combustion engine and the brushless permanent magnet motor are both connected to a one-way clutch bearing, and the one-way clutch bearing is connected to a propeller through a passive shaft;

The brushless permanent magnet motor is electrically connected to an electronic speed controller and a battery manager respectively, a charging switch is installed on the connection line between the brushless permanent magnet motor and the battery manager, a discharging switch is installed on the connection line between the electronic speed controller, the brushless permanent magnet motor and the battery manager, and the battery manager is electrically connected to a storage battery;

The system also includes a system controller, which is electrically connected to the internal combustion engine, the charging switch, the discharging switch and the electronic speed controller battery manager respectively.

Preferably, a pulley group is arranged in the connecting shell, and two pulleys of the pulley group are respectively connected to the one-way clutch bearing and the output shaft of the internal combustion engine, and a speed regulator cover is installed on the connecting shell, and the driven shaft passes through the speed regulator cover.

Preferably, the connecting shell is fixedly connected to the brushless permanent magnet motor via a generator connector.

Preferably, the motor shaft of the brushless permanent magnet motor is connected to the passive shaft via a coupling sleeve.

Preferably, the number of the batteries is at least two groups.

Beneficial Effects

The present invention provides a hybrid power device for unmanned aerial vehicles. It has the following beneficial effects: when the hybrid power device for unmanned aerial vehicles adopts an internal combustion engine as a power system, the internal combustion engine can be kept operating under the best performance conditions. The most fuel-efficient, the highest efficiency and the lowest emissions are achieved, and the battery can be charged by a brushless permanent magnet motor. When the brushless permanent magnet motor is used as a power system, it can first be used as a backup power source when the internal combustion engine is damaged, and when silent action is required, the internal combustion engine can be turned off and replaced by electric drive. And because the temperature is reduced by electric drive, it can avoid detection by infrared systems.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG1 is a schematic diagram of a direct-connection structure of the present invention;

FIG. 2 is a schematic diagram of the gearbox structure of the present invention.

FIG3 is a schematic diagram of the structure of the pulley assembly in FIG2 of the present invention;

FIG. 4 is a circuit diagram of FIG. 3 of the present invention.

In the figure: 1, internal combustion engine, 2, brushless permanent magnet motor, 3, one-way clutch bearing, 4, pulley assembly, 5, battery, 6, passive shaft, 7, coupling sleeve, 8, electronic speed controller, 9, connecting shell, 10, generator connector, 11, governor cover, 12, system controller, 121, charging switch, 122, discharge switch, 13, battery manager, 14, propeller.

DETAILED DESCRIPTION

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.

By those skilled in the art, the components in this case are connected in sequence. The specific connection and operation sequence should refer to the following working principle. The detailed connection means are well-known technologies in the art. The following mainly introduces the working principle and process.

Embodiment 1

As can be seen from Figures 2-3, a hybrid power device for an unmanned aerial vehicle includes a connecting shell 9, on which an internal combustion engine 1 and a brushless permanent magnet motor 2 are installed, and the output shafts of the internal combustion engine 1 and the brushless permanent magnet motor 2 are both connected to a one-way clutch bearing 3, and the one-way clutch bearing 3 is connected to a propeller 14 through a passive shaft 6.

The brushless permanent magnet motor 2 is electrically connected to a battery 5;

In the specific implementation process, it is worth pointing out that this structure belongs to the direct connection mode, and there are two working modes, specifically:

Working mode 1, the internal combustion engine drives the propeller 14 to rotate. The working principle is: the internal combustion engine 1 works, driving the brushless permanent magnet motor 2 and the one-way clutch 3 to rotate. As the rotor of the brushless permanent magnet motor 2 rotates, the brushless permanent magnet motor 2 generates electricity and charges the battery 5; the one-way clutch bearing 3 drives the propeller 14 to rotate through the passive shaft 6. The propeller 4 rotates to generate thrust to push the unmanned aerial vehicle.

In this state, the brushless permanent magnet motor 2 acts as a generator and the internal combustion engine 1 acts as a power machine.

Working mode 2, when the brushless permanent magnet motor 2 is used as the motor, the working principle is: the permanent magnet brushless motor 2 is powered on and rotates to drive the single steering clutch 3 and the propeller 4 to rotate, but due to the existence of the steering clutch 3, the internal combustion engine 1 will not be driven during operation.

Embodiment 2

As can be seen from Figures 1-3, a hybrid power device for an unmanned aerial vehicle includes a connecting shell 9, on which an internal combustion engine 1 and a brushless permanent magnet motor 2 are installed, a pulley group 4 is arranged in the connecting shell 9, and two pulleys of the pulley group 4 are respectively connected to a one-way clutch bearing 3 and an output shaft of the internal combustion engine 1, the connecting shell 9 is connected to the brushless permanent magnet motor 2 through a generator connector 10, and the motor shaft of the brushless permanent magnet motor 2 is connected to a passive shaft 6 through a coupling sleeve 7; the one-way clutch bearing 3 is connected to a propeller 14 through the passive shaft 6.

A speed regulator cover 11 is mounted on the connecting shell 9 , and the driven shaft 6 passes through the speed regulator cover 11 .

The pulley set 4 can be a synchronous pulley or a grooved pulley. The diameters of the two pulleys are different and adjustable, so that the speed regulation effect can be achieved.

The connection mode with the pulley set 4 is a gearbox type connection, and the specific working mode is: when driven by the engine 1, the pulley set 4 drives the one-way clutch bearing 3, and the one-way clutch bearing 3 drives the passive shaft 6. The passive shaft 6 drives the propeller 14 and the brushless permanent magnet motor 2 at the same time. The brushless permanent magnet motor 2 now acts as a generator and charges the battery 5.

When the brushless permanent magnet motor 2 is used as a motor to drive the propeller 14 , the pulley assembly 4 will not be driven to rotate under the action of the one-way clutch bearing 3 .

It should be noted that during operation, the battery manager 13 controls the charging current to change the load torque of the internal combustion engine 1 , thereby achieving the effect of controlling the rotation speed of the internal combustion engine 1 .

The reason for adopting hybrid power is that since the internal combustion engine has the highest efficiency and the lowest emissions at a rated throttle opening, maintaining the rated throttle is beneficial to the operation of the internal combustion engine.

It should be further explained that the optimal torque of the internal combustion engine is different at different speeds. For example, when the UAV needs to reduce thrust during navigation, the internal combustion engine 1 will slow down, and the maximum torque will increase. In order to keep the throttle unchanged and consume excess torque, the brushless permanent magnet motor 2 can generate electricity to increase current, and multiple groups of batteries 5 can be charged at the same time. Conversely, when the UAV needs to increase thrust, the speed of the internal combustion engine 1 increases, the maximum torque decreases accordingly, and then the residual torque decreases, the power generation decreases, and the number of charged batteries needs to be reduced. Each group of batteries 5 is connected in parallel, and the voltage of each group is the same, but the charging current can be the same or different charging currents can be designed as needed.

Specifically, when the internal combustion engine 1 speeds up and slows down, causing a decrease or increase in torque, the charging current is controlled by the battery manager 13. The brushless permanent magnet generator 2 charges the battery system, and the number of batteries 5 to be charged is determined by the system controller 12 according to the residual torque of the internal combustion engine 1;

When the internal combustion engine 1 is used as the power system, the internal combustion engine can be kept working under the best performance conditions to achieve the most fuel-efficient, highest efficiency and lowest emissions, and the battery 5 can be charged through the brushless permanent magnet motor 2 .

When the brushless permanent magnet motor 2 is used as a motor, the battery 5 is discharged. The brushless permanent magnet motor 2 is powered by the electronic speed controller 8 to drive the propeller 14. The power system can power the brushless permanent magnet generator 2 by one or more groups of batteries 5 according to power requirements.

When the brushless permanent magnet motor 2 is used as a power system, it can first be used as a backup power source when the internal combustion engine 1 is damaged, and when silent operation is required, the internal combustion engine can be turned off and electric drive can be used instead. Moreover, since the temperature is lowered by electric drive, it can avoid detection by infrared systems.

The circuit control system includes the following:

The brushless permanent magnet motor 2 is electrically connected to the electronic speed controller 8 and the battery manager 13, respectively. A charging switch 121 is installed on the connection line between the brushless permanent magnet motor 2 and the battery manager 13. A discharge switch 122 is installed on the connection line between the electronic speed controller 8, the brushless permanent magnet motor 2 and the battery manager 13. The battery manager 13 is electrically connected to the storage battery 5. In this case, only two groups of storage batteries 5 are shown for reference. However, the number of battery groups in the pick-up battery system can exceed two groups.

The system controller 12 is also included, and the system controller is electrically connected to the internal combustion engine 1, the charging switch 121, the discharging switch 122, the electronic speed controller 8 and the battery manager 13. A switch is provided on the connection line between the system controller 12 and the electronic speed controller 8.

The system controller 8 is used to control the charging of the battery 5 and the operation of the permanent magnet brushless synchronous generator 2 .

When the internal combustion engine 1 is running and the battery 5 needs to be charged, the system controller 12 closes the charging switch 121 and opens the discharging switch 122. When the internal combustion engine 1 is running and the battery 5 does not need to be charged, the system controller 12 opens both the charging switch 121 and the discharging switch 122.

When the internal combustion engine 1 stops running and the unmanned aerial vehicle needs power, the system controller 8 will disconnect the charging switch 121 and close the discharging switch 122. The battery 5 supplies power to the electronic speed controller 6 through the battery manager 13 to drive the permanent magnet brushless motor 2 to work.

The system controller 8 monitors the internal combustion engine 1 , and when the internal combustion engine 1 is rotating, the discharge switch 122 cannot be closed.

The storage battery 5 can be used to power other subsystems on the unmanned aerial vehicle.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims (5)

1. An unmanned aircraft hybrid power plant, characterized by: the motor comprises a connecting shell (9), wherein an internal combustion engine (1) and a brushless permanent magnet motor (2) are arranged on the connecting shell (9), output shafts of the internal combustion engine (1) and the brushless permanent magnet motor (2) are connected with one-way clutch bearings (3), and the one-way clutch bearings (3) are connected with a propeller (14) through a driven shaft (6);

The brushless permanent magnet motor (2) is respectively and electrically connected with an electronic speed controller (8) and a battery manager (13), a charging switch (121) is arranged on a connecting line of the brushless permanent magnet motor (2) and the battery manager (13), a discharging switch (122) is arranged on a connecting line of the electronic speed controller (8) and the brushless permanent magnet motor (2) and the battery manager (13), and the battery manager (13) is electrically connected with a storage battery (5);

the brushless permanent magnet motor (2) provides two working modes, including being used as a generator and being used as a motor drive;

When the brushless permanent magnet motor (2) works as a generator, the internal combustion engine (1) drives the brushless permanent magnet motor (2) and the one-way clutch bearing (3) to rotate, and as the rotor of the brushless permanent magnet motor (2) rotates, the brushless permanent magnet motor (2) generates electric power and charges a storage battery, and the one-way clutch bearing (3) drives the propeller (14) to rotate through the driven shaft;

When the brushless permanent magnet motor (2) is used as a motor for driving, the permanent magnet brushless motor (2) is electrified to rotate to drive the one-way clutch bearing (3) and the propeller (4) to rotate, and the internal combustion engine (1) is not driven during operation due to the existence of the one-way clutch bearing (3);

The system also comprises a system controller (12), wherein the system controller (12) is electrically connected with the internal combustion engine (1), the charging switch (121), the discharging switch (122), the electronic speed controller (8) and the battery manager (13) respectively; the system controller (12) is used for determining the number of the charged storage batteries; the device is used for controlling the charging of a storage battery and the action of the brushless permanent magnet motor (2); for monitoring the internal combustion engine (1) and the discharge switch cannot be closed during rotation thereof.

2. An unmanned aircraft hybrid power plant according to claim 1, wherein: the connecting shell (9) is internally provided with a belt pulley group (4), two belt pulleys of the belt pulley group (4) are respectively connected with the one-way clutch bearing (3) and an output shaft of the internal combustion engine (1), the connecting shell (9) is provided with a speed regulator cover (11), and the driven shaft (6) penetrates through the speed regulator cover (11).

3. An unmanned aircraft hybrid power plant according to claim 2, wherein: the connecting shell (9) is fixedly connected with the brushless permanent magnet motor (2) through a generator connector (10).

4. An unmanned aircraft hybrid power plant according to claim 2, wherein: the motor shaft of the brushless permanent magnet motor (2) is connected with the driven shaft (6) through the connecting shaft sleeve (7).

5. An unmanned aircraft hybrid power plant according to claim 1, wherein: the number of the storage batteries (5) is at least two.