Hybrid power system for unmanned aerial vehicle and working method of hybrid power system

Abstract

The invention discloses a hybrid power system for an unmanned aerial vehicle and a working method of the hybrid power system. The hybrid power system comprises a planetary gear mechanism which comprises an inner gear ring, a planet carrier, a sun gear and a planetary gear assembly arranged on the planet carrier and meshed with the sun gear and the inner gear ring; an output shaft of the engine is in transmission connection with the sun gear; the starting and generating integrated mechanism comprises a stator and a rotor which is arranged on the outer side of the stator and fixedly connected with the inner gear ring, and the stator is arranged on the outer side of a cylinder body of the engine; the invention further discloses a working method of the hybrid power system for the unmanned aerial vehicle, the starting and launching integrated mechanism is arranged on the outer side of the engine, so that the overall structure is simpler and more compact, and the power output stability can be improved.

Description

Technical Field

[0001] This invention relates to the field of hybrid power systems for unmanned aerial vehicles (UAVs), and particularly to a hybrid power system for UAVs and its operating method. Background Technology

[0002] Currently, drones are generally powered by electric, internal combustion engine, or hybrid power systems. However, drones operate in complex environments. Electric systems face significant challenges in high-temperature, high-humidity, and high-altitude areas, as the low-temperature performance and safety of batteries cannot meet usage requirements. Using internal combustion engine systems as a power source limits drone flight altitude, and carbon emissions and air pollution are unavoidable.

[0003] Therefore, it is necessary to improve the power system of drones in the existing technology, so as to make the overall structure more compact and simple, and to improve the adaptability of drones to various working conditions, while also improving the power and economy of drones. Summary of the Invention

[0004] In view of this, the purpose of the present invention is to provide a hybrid power system for unmanned aerial vehicles (UAVs) and its operating method, which can make the overall structure compact and simple, improve the adaptability of UAVs to various operating conditions, and at the same time improve the power and economy of UAVs.

[0005] The hybrid power system for an unmanned aerial vehicle (UAV) of the present invention includes:

[0006] A planetary gear mechanism, comprising an internal gear ring, a planet carrier, a sun gear, and a planetary gear assembly disposed on the planet carrier and meshing with the sun gear and the internal gear ring;

[0007] An engine, wherein the output shaft of the engine is connected to the sun gear drive;

[0008] An integrated starter-generator mechanism includes a stator and a rotor disposed on the outside of the stator and fixedly connected to an internal gear ring, wherein the stator is disposed on the outside of the engine block.

[0009] Furthermore, the planetary gear assembly includes at least three planetary gears, which are disposed on the planet carrier. The center of the planet carrier extends outward to form a power output shaft, which is used to transmit power to external devices.

[0010] Furthermore, the hybrid power system also includes a housing, in which the planetary gear mechanism, engine, and starter-generator integrated mechanism are disposed, and the power output shaft extends out of the housing.

[0011] Furthermore, the housing is provided with a cooling channel, which has a liquid inlet and a liquid outlet, and the cooling channel has a Z-shaped bending structure.

[0012] Furthermore, the integrated starting mechanism also includes several connecting parts, which are evenly arranged along the upper surface of the rotor, and the two ends of the connecting parts are respectively fixedly connected to the rotor and the internal gear ring.

[0013] Furthermore, the integrated starting and starting mechanism also includes a coil winding, which is disposed between the stator and the rotor.

[0014] Furthermore, the engine is a hydrogen fuel cell swivel engine.

[0015] The present invention provides a method for operating a hybrid power system for an unmanned aerial vehicle (UAV), comprising the aforementioned hybrid power system, wherein the hybrid power system includes a pure electric operating mode, and when in the pure electric operating mode:

[0016] When the engine is not working, the stator is energized, which drives the rotor to rotate. The rotor transmits power to the internal gear ring, which in turn transmits power to the planetary gear assembly, and outputs the power to the outside through the power output shaft of the planetary carrier.

[0017] Furthermore, it also includes an engine drive mode, which, when in engine drive mode:

[0018] The engine drives the sun gear to rotate, and the sun gear transmits power to the planetary gear assembly, which outputs power to the outside through the power output shaft of the planetary carrier. At this time, the generator-starting mechanism can receive the output power from the engine, so that the generator-starting mechanism is in the power generation state.

[0019] Furthermore, it also includes a hybrid mode, which, when in hybrid mode:

[0020] When the engine is running, the starter-generator integrated mechanism is in an electric state. The output power of the engine and the starter-generator integrated mechanism is coupled through the planetary gear mechanism and finally output to the outside through the power output shaft of the planetary carrier.

[0021] The beneficial effects of the present invention are as follows: The hybrid power system and its working method for UAVs of the present invention, by setting an integrated starter-generator mechanism and setting the stator on the outer wall of the engine cylinder, can make the structure compact, shorten the axial length of the hybrid power system, and facilitate the layout. At the same time, through the synergistic effect of the planetary gear mechanism, the integrated starter-generator mechanism and the engine, three working modes can be realized, thereby improving the UAV's ability to adapt to various working conditions. Attached Figure Description

[0022] The present invention will be further described below with reference to the accompanying drawings and embodiments:

[0023] Figure 1 This is a schematic diagram of the hybrid power system of the present invention;

[0024] Figure 2 for Figure 1 A sectional view;

[0025] Figure 3 for Figure 1 A schematic diagram of the structure when the shell is concealed.

[0026] Figure label:

[0027] 1. Planetary gear mechanism; 2. Housing; 3. Planetary gear assembly; 4. Planetary carrier; 5. Power take-off shaft; 6. Internal gear ring; 7. Engine; 8. Starter-start mechanism; 9. Stator; 10. Rotor; 11. Coil winding; 12. Sun gear; 13. Swashplate; 14. Connecting rod; 15. Connecting component. Detailed Implementation

[0028] like Figure 1-3 As shown: The hybrid power system for an unmanned aerial vehicle in this embodiment includes:

[0029] The planetary gear mechanism 1 includes an internal gear ring 6, a planet carrier 4, a sun gear 12, and a planetary gear assembly 3 disposed on the planet carrier 4 and meshing with the sun gear 12 and the internal gear ring 6; the planetary gear assembly 3 generally includes several planetary gears and is evenly arranged along the axial direction of the sun gear 12.

[0030] Engine 7, the output shaft of engine 7 is connected to the sun gear 12 for transmission; the power of engine 7 can be transmitted to planetary gear assembly 3 through sun gear 12.

[0031] The starter-generator integrated mechanism 8 includes a stator 9 and a rotor 10 disposed on the outside of the stator 9 and fixedly connected to the internal gear ring 6. The stator 9 is disposed on the outside of the cylinder block of the engine 7.

[0032] Specifically, in use, the integrated starter-generator mechanism 8 can function as an electric motor to output power or receive output power from the engine 7 and generate electricity. Since the rotor 10 is fixed to the internal gear ring 6, the integrated starter-generator mechanism 8 can switch between electric motor and generator operating modes by adjusting the drive source of the rotor 10. When the stator 9 is energized, the stator 9 drives the rotor 10 to rotate, and the rotor 10 performs work externally, which is the electric motor mode. When the engine 7 drives the rotor 10 to rotate through the planetary gear mechanism 1, the magnetic field changes, thereby generating current in the stator 9. The coil on the stator 9 is connected to the rectifier and filter circuit through wires. The rectifier and filter circuit is connected to the AC / DC conversion circuit through a relay. The AC / DC conversion circuit is connected to the input terminal of the capacitor bank, thereby realizing energy storage. At the same time, the stored electrical energy can be output externally. The current conversion and output method is an application of existing technology, which will not be elaborated here, in order to realize energy recovery. Thus, the integrated starter-generator mechanism 8, the planetary gear mechanism 1, and the engine 7 can realize three operating modes of the hybrid power system, which can adapt to the needs of the UAV in all operating conditions.

[0033] In this embodiment, the planetary gear assembly 3 includes at least three planetary gears, which are respectively disposed on the planetary carrier 4. A power output shaft 5 extends outward from the center of the planetary carrier 4, and the power output shaft 5 is used to transmit power to external devices. The external devices are generally drones, but can also be other devices. The power of the hybrid power system is output to the outside through the planetary carrier 4, and the power output shaft 5 extends outward from the center of the planetary carrier 4 to facilitate connection with external devices.

[0034] In this embodiment, the hybrid power system further includes a housing 2, within which the planetary gear mechanism 1, the engine 7, and the integrated starter-start mechanism 8 are disposed, and the power output shaft 5 extends out of the housing 2. The housing 2 is provided to form a support.

[0035] In this embodiment, the housing 2 is provided with a cooling channel, which has an inlet and an outlet, and the cooling channel has a Z-shaped bend structure. The Z-shaped bend structure of the cooling channel creates an asymmetrical turning design, generating turbulence when the cooling medium flows through it, thereby improving the mixing and heat exchange efficiency of the cooling medium. Adding arcs at the corners of the cooling channel reduces flow resistance and increases flow efficiency compared to right-angle turns, further enhancing heat dissipation. The cooling medium can be selected according to usage requirements. Since the starter-generator integrated mechanism 8 is located on the outside of the engine 7, the heat dissipation effect on the starter-generator integrated mechanism 8 is improved.

[0036] In this embodiment, the integrated starting and stopping mechanism 8 further includes several connecting members 15. These connecting members 15 are evenly arranged along the upper surface of the rotor 10, and both ends of each connecting member 15 are fixedly connected to the rotor 10 and the internal gear ring 6, respectively. The connecting members 15 are generally steel bars, such as… Figure 2 As shown, relative to Figure 2 In the vertical direction, the two ends of the connector 15 are respectively connected to the upper surface of the rotor 10 and the lower surface of the internal gear ring 6.

[0037] In this embodiment, the integrated starting and starting mechanism 8 further includes a coil winding 11, which is disposed between the stator 9 and the rotor 10.

[0038] In this embodiment, the engine 7 is a hydrogen fuel cell swivel engine 7. The engine 7 includes a cylinder block, several cylinders arranged in a circular array parallel to the central axis of the cylinder block, a piston inside the cylinder, a connecting rod 14 cooperating with the piston, and a swashplate 13 connected to the connecting rod 14, etc. The specific structure of the engine 7 is an application of existing technology and will not be described in detail here. The engine 7 of this structure uses hydrogen as the main fuel and, with the help of exhaust gas treatment, can achieve near-zero carbon emission operation.

[0039] The method for operating a hybrid power system for a drone in this embodiment includes the hybrid power system for the drone, which includes a pure electric operating mode. When in pure electric operating mode:

[0040] When the engine 7 is not operating, the sun gear 12 does not rotate, the stator 9 is energized, driving the rotor 10 to rotate. The rotor 10 transmits power to the internal gear ring 6, which in turn transmits power to the planetary gear assembly 3, and outputs power externally through the power output shaft 5 of the planetary carrier 4. This mode can be used when the UAV is operating at low speeds. In this mode, the rotor 10 transmits power to the internal gear ring 6 through the connector 15, which in turn transmits power to the planetary gear assembly 3, and outputs power externally through the planetary carrier 4.

[0041] This embodiment also includes an engine drive mode. When in engine drive mode:

[0042] The engine 7 drives the sun gear 12 to rotate, and the sun gear 12 transmits power to the planetary gear assembly 3 and outputs it to the outside through the power output shaft 5 of the planet carrier 4. At this time, the generator-starting integrated mechanism 8 can receive the output power from the engine 7, so that the generator-starting integrated mechanism 8 is in the power generation state.

[0043] Specifically, when in engine-driven mode, the starter-generator integrated mechanism 8 can act as the starter motor for the engine 7. When the engine 7 begins to output power, the starter-generator integrated mechanism 8 can be in a non-working state or a power generation state. The engine 7 transmits power to the planetary gear assembly 3 through the sun gear 12 and outputs power through the planet carrier 4. At this time, the rotor 10 is kept stationary by the motor controller (generally a combination of CPU and peripheral circuits), that is, the internal gear ring 6 does not rotate. When the engine 7 outputs residual power, the rotor 10 can be driven to rotate, thereby causing the stator 9 to generate current, which can be stored and utilized to improve the energy utilization rate of the hybrid power system.

[0044] This embodiment also includes a hybrid mode. When in hybrid mode:

[0045] When the engine 7 is working, the starter-generator integrated mechanism 8 is in an electric state. The output power of the engine 7 and the starter-generator integrated mechanism 8 is coupled through the planetary gear mechanism 1 and finally output to the outside through the power output shaft 5 of the planetary carrier 4.

[0046] Specifically, in this mode, based on the output power requirements of the UAV, the engine 7, the starter-generator integrated mechanism 8, and the planetary gear mechanism 1 work together to ensure that the engine 7 is always in a high-efficiency operating range, reducing hydrogen consumption. The speed or torque of the starter-generator integrated mechanism 8 can be precisely controlled by the control system (generally a combination of CPU and peripheral circuits), and the output speed and torque of the planetary carrier 4 can be infinitely adjusted to optimize the operating point of the engine 7.

[0047] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A hybrid power system for an unmanned aerial vehicle (UAV), characterized in that: include: A planetary gear mechanism, comprising an internal gear ring, a planet carrier, a sun gear, and a planetary gear assembly disposed on the planet carrier and meshing with the sun gear and the internal gear ring; An engine, wherein the output shaft of the engine is connected to the sun gear drive; An integrated starter-generator mechanism includes a stator and a rotor disposed on the outside of the stator and fixedly connected to an internal gear ring, wherein the stator is disposed on the outside of the engine block.

2. The hybrid power system for an unmanned aerial vehicle according to claim 1, characterized in that: The planetary gear assembly includes at least three planetary gears, which are disposed on the planet carrier. The center of the planet carrier extends outward to form a power output shaft, which is used to transmit power to external devices.

3. The hybrid power system for an unmanned aerial vehicle according to claim 2, characterized in that: The hybrid power system also includes a housing, in which the planetary gear mechanism, engine and starter-generator integrated mechanism are disposed, and the power output shaft extends out of the housing.

4. The hybrid power system for an unmanned aerial vehicle according to claim 3, characterized in that: The housing is provided with a cooling channel, which has a liquid inlet and a liquid outlet, and the cooling channel has a Z-shaped bending structure.

5. The hybrid power system for an unmanned aerial vehicle according to claim 1, characterized in that: The integrated starting and starting mechanism also includes several connecting parts, which are evenly arranged along the upper surface of the rotor, and the two ends of the connecting parts are fixedly connected to the rotor and the internal gear ring, respectively.

6. The hybrid power system for an unmanned aerial vehicle according to claim 1, characterized in that: The integrated starting and starting mechanism also includes a coil winding, which is disposed between the stator and the rotor.

7. The hybrid power system for an unmanned aerial vehicle according to claim 1, characterized in that: The engine is a hydrogen fuel cell oscillating engine.

8. A method for operating a hybrid power system for an unmanned aerial vehicle (UAV), characterized in that: Including the hybrid power system for an unmanned aerial vehicle as described in any one of claims 1-7, the hybrid power system includes a pure electric operating mode, wherein when in pure electric operating mode: When the engine is not working, the stator is energized, which drives the rotor to rotate. The rotor transmits power to the internal gear ring, which in turn transmits power to the planetary gear assembly, and outputs the power to the outside through the power output shaft of the planetary carrier.

9. The hybrid power system for an unmanned aerial vehicle according to claim 8, characterized in that: It also includes engine drive mode, when in engine drive mode: The engine drives the sun gear to rotate, and the sun gear transmits power to the planetary gear assembly, which outputs power to the outside through the power output shaft of the planetary carrier. At this time, the generator-starting mechanism can receive the output power from the engine, so that the generator-starting mechanism is in the power generation state.

10. The hybrid power system for an unmanned aerial vehicle according to claim 8, characterized in that: It also includes a hybrid mode, when in hybrid mode: When the engine is running, the starter-generator integrated mechanism is in an electric state. The output power of the engine and the starter-generator integrated mechanism is coupled through the planetary gear mechanism and finally output to the outside through the power output shaft of the planetary carrier.

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