Manned multi-rotor aircraft based on hybrid power

Abstract

The utility model relates to a manned multi-rotor aircraft based on hybrid power. The manned multi-rotor aircraft comprises a fuselage main body, the battery pack is installed on the machine body. The auxiliary rotor assemblies are connected to the fuselage main body; the motor is mounted on the fuselage main body, is connected with the auxiliary rotor wing assembly and is used for driving the auxiliary rotor wing assembly to rotate; the engine is mounted on the fuselage main body; the generator is connected with the output end of the engine, is driven by the engine to generate electricity and is electrically connected with the battery pack; the main rotor assembly is installed on the fuselage main body, the main rotor assembly is in power connection with the engine through the transmission assembly, and the main rotor assembly can be driven by the engine to rotate. The aircraft can be driven through hybrid power, and meanwhile, the endurance time can be prolonged while sufficient power and maneuverability are provided.

Description

Technical Field

[0001] The utility model relates to the technical field of manned aircraft, in particular to a manned multi-rotor aircraft based on hybrid power. Background Art

[0002] At present, multi-rotor aircraft are increasingly widely used due to their good maneuverability and maneuverability. However, among most existing manned multi-rotor aircraft, electric-powered aircraft have short flight time, insufficient power, and poor load-bearing capacity, while oil-powered multi-rotors have poor flight stability and slow response speed, which cannot meet the requirements of quickly controlling the flight attitude of rotor-powered manned aircraft. Utility Model Content

[0003] In order to solve the above problems, the utility model proposes a manned multi-rotor aircraft based on hybrid power, which can be driven by hybrid power and can improve the endurance time while providing sufficient power and maneuverability.

[0004] In order to achieve the above purpose, the technical solution adopted by the utility model is:

[0005] A manned multi-rotor aircraft based on hybrid power, comprising

[0006] The main body of the fuselage;

[0007] A battery pack, mounted on the main body of the fuselage;

[0008] An auxiliary rotor assembly connected to the main fuselage;

[0009] An electric motor is installed on the fuselage body, the electric motor is connected to the auxiliary rotor assembly and is used to drive the auxiliary rotor assembly to rotate;

[0010] The engine, mounted on the main body of the fuselage;

[0011] A generator connected to an output terminal of the engine and driven by the engine to generate electricity, the generator being electrically connected to the battery pack;

[0012] The main rotor assembly is installed on the fuselage body. The main rotor assembly is connected to the engine through a transmission assembly. The main rotor assembly can be driven to rotate by the engine.

[0013] Preferably, there are two groups of main rotor assemblies, and there are also two groups of engines and generators, and each group of engines and generators is respectively connected to a main rotor assembly.

[0014] Preferably, the transmission assembly includes a main drive shaft, and the power ends of the two engines are both power-connected to the main drive shaft.

[0015] Preferably, the output end of the engine is dynamically connected to the transmission assembly via the clutch.

[0016] Preferably, there are four aileron assemblies and they are arranged at the four corners of the fuselage body, two of which are symmetrically arranged at the front of the fuselage body, and the other two are symmetrically arranged at the rear of the fuselage body.

[0017] Preferably, there are two main rotor assemblies, which are respectively arranged between the two left auxiliary rotor assemblies and between the two right auxiliary rotor assemblies.

[0018] Preferably, in a top view, the two left-side auxiliary rotor assemblies of the auxiliary rotor assemblies rotate clockwise, and the two right-side auxiliary rotor assemblies rotate counterclockwise.

[0019] Preferably, in a top-down view, the main rotor assembly on the left side rotates counterclockwise, and the main rotor assembly on the right side rotates clockwise.

[0020] Preferably, the fuselage body includes N seats, where N is an even number, and the seats are arranged symmetrically on the fuselage body.

[0021] The beneficial effects of using the utility model are:

[0022] The multi-rotor aircraft drives the propeller of the aircraft through the main rotor assembly and the auxiliary rotor assembly, wherein the main rotor assembly is driven by the engine, and the auxiliary rotor assembly is driven by the electric motor. The operation of the engine can also charge the battery pack through the generator. In addition, the two engines use the same main drive shaft power setting method. When one engine stops, the clutch of the engine can be cut off, and the two main rotor assemblies can be driven by one engine to achieve dual redundancy in power. The aircraft has a long flight time, a strong load-bearing capacity, and high flight stability and flexibility. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 The utility model is a schematic diagram of the rotor layout of a manned multi-rotor aircraft based on hybrid power.

[0024] Figure 2 The utility model is a schematic diagram of a power unit of a manned multi-rotor aircraft based on hybrid power.

[0025] Reference numerals include:

[0026] 1-fuselage body, 2-first main rotor assembly, 3-second main rotor assembly, 4-first auxiliary rotor assembly, 5-second auxiliary rotor assembly, 6-third auxiliary rotor assembly, 7-fourth auxiliary rotor assembly, 8-first engine, 9-second engine, 10-electric motor, 11-battery pack, 12-generator, 13-clutch, 14-transmission assembly, 15-bevel gear set. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solution and advantages of the technical solution more clear, the technical solution is further described in detail below in conjunction with specific implementation methods. It should be understood that these descriptions are only exemplary and are not intended to limit the scope of the technical solution.

[0028] In order to solve the problem that in the prior art multi-rotor aircraft, electric-powered aircraft have short flight time, insufficient power, and poor load-bearing capacity, while oil-powered multi-rotor aircraft have poor flight stability and slow response speed, and cannot meet the requirements of quickly controlling the flight attitude of rotor manned aircraft, such as Figure 1 and Figure 2 As shown, this embodiment proposes a manned multi-rotor aircraft based on hybrid power. Specifically, the fuselage body 1 includes N seats, and N is an even number, and the seats are arranged symmetrically on the left and right of the fuselage body 1. In this embodiment, the number of seats is 6.

[0029] like Figure 1 As shown, there are four auxiliary rotor assemblies, which are arranged at the four corners of the fuselage body 1, respectively. Two auxiliary rotor assemblies are arranged on the left and right sides of the front part of the fuselage body 1, respectively, the first auxiliary rotor assembly 4 and the second auxiliary rotor assembly 5, and the first auxiliary rotor assembly 4 and the second auxiliary rotor assembly 5 are arranged symmetrically on the left and right sides, and two auxiliary rotor assemblies are arranged on the left and right sides of the rear part of the fuselage body 1, respectively, the third auxiliary rotor assembly 6 and the fourth auxiliary rotor assembly 7, and the third auxiliary rotor assembly 6 and the fourth auxiliary rotor assembly 7 are arranged symmetrically on the left and right sides. Among them, in the top view, the two auxiliary rotor assemblies on the left side of the auxiliary rotor assembly, namely the second auxiliary rotor assembly 5 and the third auxiliary rotor assembly 6, rotate clockwise, and the two auxiliary rotor assemblies on the right side, namely the second auxiliary rotor assembly 5 and the third auxiliary rotor assembly 6, rotate counterclockwise.

[0030] There are two main rotor assemblies, that is, the second main rotor assembly 3 is arranged between the second auxiliary rotor assembly 5 and the third auxiliary rotor assembly 6 on the left, and the first main rotor assembly 2 is arranged between the first auxiliary rotor assembly 4 and the fourth auxiliary rotor on the right. In a top view, the second main rotor assembly 3 on the left rotates counterclockwise, and the first main rotor assembly 2 on the right rotates clockwise.

[0031] The first engine 8 and the second engine 9 are arranged on the side of the fuselage body 1 , close to the first main rotor assembly 2 and the second main rotor assembly 3 .

[0032] like Figure 2 As shown, Figure 2 The power transmission relationship and the electric energy transmission relationship between the driving components of each main rotor assembly and auxiliary rotor assembly are identified. Specifically, a motor 10 is arranged at each of the first auxiliary rotor assembly 4, the second auxiliary rotor assembly 5, the third auxiliary rotor assembly 6 and the fourth auxiliary rotor assembly 7, and the motor 10 is used to drive the propeller of the corresponding auxiliary rotor assembly to rotate. A battery pack 11 is arranged on the fuselage body 1, and the battery pack 11 supplies power to the above-mentioned motor 10.

[0033] In the part of the first main rotor assembly 2 and the second main rotor assembly 3, the first main rotor assembly 2 and the second main rotor assembly 3 are driven by the first engine 8 and the second engine 9. Specifically, taking the first engine 8 as an example, the output end of the first engine 8 is connected to the generator 12, and the generator 12 is connected to the battery pack 11, so the engine can drive the generator 12 to run and generate electrical energy to charge the battery pack 11. The first engine 8 is connected to the input end of the transmission assembly 14 through the clutch 13, and the output end of the transmission assembly 14 is connected to the first main rotor assembly 2 through a set of bevel gear sets 15. Similarly, the second engine 9 can drive the second main rotor assembly 3 to rotate. The transmission assembly 14 includes a main drive shaft, and the power ends of the first engine 8 and the second engine 9 are both connected to the main drive shaft power.

[0034] Therefore, when the clutch 13 is in the engaged state, the first engine 8 and the second engine 9 jointly output power to drive the main drive shaft to rotate, and respectively drive the first main rotor assembly 2 and the second main rotor assembly 3 to rotate through the bevel gear sets 15 at both ends of the main drive shaft.

[0035] If any one of the first engine 8 and the second engine 9 fails to shut down, the clutch 13 connected thereto is disconnected, and the other engine can drive the two first main rotor assemblies 2 and the second main rotor assemblies 3 through the transmission assembly 14 and the bevel gear set 15, thereby achieving dual power redundancy.

[0036] The present invention provides power for the aircraft by carrying two piston engines to drive the main rotor propellers, which can effectively improve its load-bearing capacity; the auxiliary rotor assembly driven by four electric motors 10 can flexibly change the flight attitude of the aircraft and enhance the maneuverability and controllability of the aircraft; the design that the engine can charge the battery pack can significantly improve the endurance of the aircraft.

[0037] The above contents are only preferred embodiments of the present invention. For ordinary technicians in this field, many changes can be made in the specific implementation methods and application scopes based on the ideas of the present technical content. As long as these changes do not deviate from the concept of the present invention, they all fall within the scope of protection of this patent.

Claims

1. A hybrid powered manned multi-rotor aircraft, characterized in that: include The main body of the fuselage; A battery pack, mounted on the main body of the fuselage; An auxiliary rotor assembly connected to the main fuselage; An electric motor is installed on the fuselage body, the electric motor is connected to the auxiliary rotor assembly and is used to drive the auxiliary rotor assembly to rotate; The engine, mounted on the main body of the fuselage; A generator connected to an output terminal of the engine and driven by the engine to generate electricity, the generator being electrically connected to the battery pack; The main rotor assembly is installed on the fuselage body. The main rotor assembly is connected to the engine through a transmission assembly. The main rotor assembly can be driven to rotate by the engine.

2. The hybrid-powered manned multi-rotor aircraft according to claim 1, characterized in that: There are two groups of main rotor assemblies, and there are also two groups of engines and generators. Each group of engines and generators is respectively connected to a main rotor assembly.

3. The hybrid-powered manned multi-rotor aircraft according to claim 2, characterized in that: The transmission assembly comprises a main drive shaft, and the power ends of the two engines are both connected to the main drive shaft in power.

4. The hybrid-powered manned multi-rotor aircraft according to claim 3, characterized in that: The output end of the engine is dynamically connected to the transmission assembly via a clutch.

5. The hybrid-powered manned multi-rotor aircraft according to claim 1, characterized in that: There are four aileron assemblies which are arranged at the four corners of the fuselage body, two of which are respectively located at the front of the fuselage body and are arranged symmetrically on the left and right, and the other two of which are respectively located at the rear of the fuselage body and are arranged symmetrically on the left and right.

6. The hybrid-powered manned multi-rotor aircraft according to claim 5, characterized in that: There are two main rotor assemblies, which are respectively arranged between the two auxiliary rotor assemblies on the left side and between the two auxiliary rotor assemblies on the right side.

7. The hybrid-powered manned multi-rotor aircraft according to claim 6, characterized in that: In a top-down state, the two left-side auxiliary rotor assemblies of the auxiliary rotor assemblies rotate clockwise, and the two right-side auxiliary rotor assemblies rotate counterclockwise.

8. The hybrid-powered manned multi-rotor aircraft according to claim 6, characterized in that: When viewed from above, the main rotor assembly on the left side rotates counterclockwise, and the main rotor assembly on the right side rotates clockwise.

9. The hybrid-powered manned multi-rotor aircraft according to claim 6, characterized in that: The fuselage body includes N seats, where N is an even number, and the seats are arranged symmetrically on the fuselage body.

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