Generator for hybrid power of multi-rotor unmanned aerial vehicle

Abstract

The invention discloses a generator for hybrid power of a multi-rotor unmanned aerial vehicle, and belongs to the field of multi-rotor unmanned aerial vehicles. The generator comprises an engine, a speed change mechanism, a generator and an electrical system, and is characterized in that the speed change mechanism is an acceleration gear mechanism, an input shaft is connected with an engine crankshaft, an output shaft drives a generator rotor shaft, the transmission ratio is 1 / 3-1 / 5, and the rotating speed of a rotor is increased through the speed increase mechanism; the generator is a permanent magnet generator, a rotor is made of neodymium iron boron strong magnetic materials, and efficient power generation and heat dissipation are achieved by being matched with an integrated cooling fan in an outer rotor. A generator frame and a shell are made of carbon fiber materials, an oil tank body is a carbon fiber shell, and the overall weight is obviously reduced. Through optimization of power transmission, material lightweight and heat dissipation design, the problems of low power-to-weight ratio, large size and overheating of a traditional hybrid power system are solved, and the hybrid power system is suitable for small and medium-sized multi-rotor unmanned aerial vehicles and has the advantages of high energy density, long endurance and compact structure.

Description

Technical Field

[0001] The present invention relates to the field of multi-rotor unmanned aerial vehicles, and particularly to a generator for hybrid power of multi-rotor unmanned aerial vehicles. Background Art

[0002] At present, multi-rotor unmanned aerial vehicles have been widely used in various fields. However, their power systems still face significant technical bottlenecks. Existing unmanned aerial vehicles mostly rely on lithium batteries for power supply, which are difficult to meet the requirements of long-term missions. Although fuel engines have a high energy density, they have problems such as large volume, strong vibration, and low efficiency when directly driving propellers. Existing coupling schemes of internal combustion engines and generators are less applied in the field of unmanned aerial vehicles, mainly limited by problems such as low transmission efficiency, insufficient heat dissipation, and complex structure. To effectively solve the above problems, the present invention proposes a generator for hybrid power of multi-rotor unmanned aerial vehicles.

[0003] Chinese Patent No. CN 220721425 U discloses a generator for large hybrid multi-rotor unmanned aerial vehicles. The utility model provides a generator for large hybrid multi-rotor unmanned aerial vehicles. The series of hollow designs improve the heat dissipation performance while reducing the weight, but the rotational speed is limited within the performance of traditional internal combustion engines, and a higher power-to-weight ratio cannot be obtained. Summary of the Invention

[0004] The present invention provides a generator for hybrid power of multi-rotor unmanned aerial vehicles to solve the problems of low power-to-weight ratio of traditional generators for multi-rotor unmanned aerial vehicles and the influence of the battery capacity of unmanned aerial vehicles on endurance.

[0005] To achieve the above object, the present invention provides the following technical solution: A generator for hybrid power of multi-rotor unmanned aerial vehicles mainly consists of an engine, a speed-changing mechanism, a generator, and an electrical system.

[0006] The speed-changing mechanism is an acceleration gear mechanism, whose input shaft is the crankshaft of the engine, and whose output shaft is the rotor shaft of the generator.

[0007] The generator is a permanent magnet generator.

[0008] Preferably, the generator is an outer rotor type.

[0009] The stator winding is fixed on the casing, and the permanent magnet rotor is fixed on the pinion shaft of the acceleration gear mechanism. A cooling fan is fixed inside the outer rotor. By means of the high rotational speed of the outer rotor, an effective cooling effect can be achieved, further avoiding overheating of the device.

[0010] The electrical system includes a rectifier and a booster.

[0011] The generator frame is a carbon fiber tube, the outer shell is a carbon fiber housing, and the main material of the fuel tank is carbon fiber. Using carbon fiber materials instead of traditional carbon steel to reduce the weight of the entire device and make it more suitable for deployment on hybrid multi-rotor drones.

[0012] The transmission ratio of the acceleration gear mechanism is 1 / 3 to 1 / 5.

[0013] Preferably, the rotor material is neodymium iron boron permanent magnet material. Using permanent magnet materials can have a lighter weight in a smaller volume while meeting the power generation efficiency.

[0014] Preferably, the stator winding of the generator is more than 1000 turns.

[0015] Preferably, the copper wire of the stator winding of the generator is thick copper wire with a diameter of more than 1 mm.

[0016] In summary, compared with the prior art, the beneficial effects of the present invention are as follows: The generator in the present invention uses an acceleration gear mechanism to increase the speed of the rotor to a higher speed compared to traditional internal combustion engines, and uses a permanent magnet material as the rotor to obtain a higher power-to-weight ratio, while reducing the volume, making the present invention more suitable for small and medium-sized multi-rotor drones. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is a perspective view of a generator for hybrid power of a multi-rotor drone according to the present invention.

[0018] Figure 2 is a perspective view of the speed increasing device described in the present invention.

[0019] In the figure: 1. Gasoline engine with weight reduction design; 2. Transmission mechanism; 3. Neodymium iron boron permanent magnet generator; 4. Carbon fiber fuel tank; 5. Carbon fiber frame; 6. Electrical system; 7. Output part; 8. Crankshaft; 9. Large gear; 10. Small gear; 11. Rotor shaft; 12. Forced cooling fan; 13. Stator. DETAILED DESCRIPTION OF THE INVENTION

[0020] The following specifically describes the present invention with reference to the accompanying drawings and embodiments, as Figure 1As shown in the figure, a generator for a multi-rotor UAV hybrid power system is characterized by including a gasoline engine 1 with a weight reduction design, a speed-changing mechanism 2, a neodymium iron boron permanent magnet generator 3, a carbon fiber fuel tank 4, a carbon fiber frame 5, an electrical system 6, and an output part 7. The gasoline engine 1 with a weight reduction design is fixed on the carbon fiber frame 5 with shock absorbers. The input end of the speed increasing and speed changing mechanism 2 is connected to the output end of the generator, and the output end of the speed increasing and speed changing mechanism 2 is connected to the neodymium iron boron permanent magnet generator 3. The neodymium iron boron permanent magnet generator 3 is connected to the electrical system 6 with a rectifier bridge and a booster through wires, and then to the output part 7. The carbon fiber fuel tank 4 is installed on the top of the carbon fiber frame 5 to provide gasoline for the gasoline engine 1 with a weight reduction design.

[0021] As Figure 2 shown in the figure, the output end of the crankshaft 8 is connected to a large gear 9, and the large gear 9 is connected to a small gear 10 to form a speed increasing gear train with a transmission ratio of 1 / 3 to 1 / 5. The small gear 10 and the forced cooling fan 12 are installed on the rotor shaft 11 and are on the same axis as the stator 13.

[0022] During use, open the fuel tank valve and the choke plate on the gasoline engine, start the engine through the start switch on the panel or connect to an additional electrical control. After that, the rotor shaft 11 of the neodymium iron boron permanent magnet generator 3 rotates at a high speed to generate electricity. The electrical system 6 completes rectification and boosting to obtain direct current, and the panel on the output part 7 provides a direct current output port.

Claims

1. A hybrid power generator for a multi-rotor drone, mainly composed of an engine, a speed change mechanism, a generator and an electrical system, characterized in that: The speed change mechanism is an acceleration gear mechanism, the input shaft of which is the crankshaft of the engine, and the output shaft of which is the rotor shaft of the generator.

2. A hybrid power generator for a multi-rotor UAV according to claim 1, characterized in that: The generator is a permanent magnet generator and the rotor material is NdFeB strong magnet.

3. A hybrid power generator for a multi-rotor UAV according to claim 1, characterized in that: The transmission ratio of the acceleration gear mechanism is 1 / 3~1 / 5.

4. A hybrid power generator for a multi-rotor UAV according to claim 1, characterized in that: The stator winding of the generator has more than 1000 turns.

5. The hybrid power generator for a multi-rotor UAV according to claim 1, characterized in that: The copper wire of the stator winding of the generator is a thick copper wire with a diameter of more than 1 mm.

6. A hybrid power generator for a multi-rotor UAV according to claim 1, characterized in that: The generator is of outer rotor type, the stator winding is fixed on the casing, and the permanent magnet rotor is fixed on the pinion shaft of the acceleration gear mechanism.

7. A hybrid power generator for a multi-rotor UAV according to claim 6, characterized in that: A cooling fan is fixed inside the outer rotor.

8. The hybrid power generator for a multi-rotor UAV according to claim 1, characterized in that: The frame is a carbon fiber tube, the outer shell is a carbon fiber shell, and the main body of the fuel tank is carbon fiber.

9. The hybrid power generator for a multi-rotor UAV according to claim 1, characterized in that: Its electrical system includes a rectifier and a booster.

Images