Power system of aircraft and multi-rotor aircraft based on hybrid power

Abstract

The utility model discloses a power system of an aircraft and a multi-rotor aircraft based on hybrid power. The power system comprises a fuselage main body, the main rotor assembly is powered by fuel oil; the power system comprises a controller; the auxiliary rotor assembly is powered by the battery pack; a transmission assembly; and a seat. According to the utility model, when one engine of the aircraft breaks down, the aircraft can still work; through the dynamic power distribution technology of the controller, the aircraft can save electric energy, and energy waste is reduced; fuel oil and a battery pack are used for providing power, so that the multi-rotor aircraft has the performances of large load, sufficient power, stable flight attitude and the like; and the engine for providing kinetic energy for the main rotor assembly can charge the battery pack of the auxiliary rotor assembly, so that the cruising ability and the practical efficiency of the multi-rotor aircraft are remarkably improved.

Description

Technical Field

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

[0002] Multirotor aircraft are increasingly being used due to their excellent maneuverability and controllability. Larger and more powerful multirotor aircraft may provide important solutions for future urban public transportation, emergency services, tourism, and other fields. However, most existing multirotor aircraft have the following shortcomings:

[0003] 1. When one of the engines of an oil-powered multi-rotor aircraft fails, the aircraft will not be able to operate.

[0004] 2. The power system on the aircraft can only provide limited electrical energy, and there are no better measures to save electricity and reduce energy waste.

[0005] 3. Electric-powered multi-rotor aircraft have short flight time, insufficient power, and poor load-bearing capacity, while oil-powered multi-rotor aircraft have poor stability and slow response speed. Electric-powered or oil-powered multi-rotor aircraft cannot simultaneously meet the requirements of large load, sufficient power, stable and agile flight posture for multi-rotor aircraft.

[0006] 4. When the battery pack of an electric multi-rotor aircraft is fully charged, the single flight time is short and there is no other power supply during operation, resulting in low operating efficiency of the aircraft. Utility Model Content

[0007] In order to solve the problems that the oil-powered multi-rotor aircraft cannot operate when one of its engines fails, the multi-rotor aircraft lacks good power-saving measures, the multi-rotor aircraft cannot simultaneously have the performance of large payload, sufficient power, and stable flight attitude, and the battery pack of the electric multi-rotor aircraft has a short flight time and no other power supply, the present invention provides a power system for the aircraft and a multi-rotor aircraft based on hybrid power. The present invention provides the following technical solutions:

[0008] In one aspect, a propulsion system for an aircraft is provided, comprising: a fuselage; a main rotor assembly comprising a first main rotor assembly and a second main rotor assembly, symmetrically located on the left and right sides of the fuselage and coupled to the fuselage; a power system comprising a first engine, a second engine, a first generator, a second generator, a first clutch, a second clutch, a battery pack, a controller, and a motor assembly; an aileron assembly; and a transmission assembly comprising a first transmission assembly and a second transmission assembly. When the first engine fails, the first clutch disengages, allowing the second engine to drive the first and second main rotor assemblies via the first transmission assembly. When the second engine fails, the second clutch disengages, allowing the first engine to drive the first and second main rotor assemblies via the second transmission assembly. The mechanical energy generated by the first and second engines is converted into electrical energy by the first and second generators and transmitted to the controller. Simultaneously, electrical energy generated by the battery pack is also transmitted to the controller. The controller uses dynamic power allocation technology to drive the main rotor assembly and aileron assembly to generate upward lift.

[0009] Preferably, the aileron assembly includes a first aileron assembly, a second aileron assembly, a third aileron assembly, and a fourth aileron assembly. The first to fourth aileron assemblies are symmetrically distributed on the left and right sides of the fuselage body, and the aileron assembly is connected to the motor assembly.

[0010] Preferably, the motor assembly includes a first motor, a second motor, a third motor, and a fourth motor, and the first motor, the second motor, the third motor, and the fourth motor are respectively connected to the first rotor assembly, the second rotor assembly, the third rotor assembly, and the fourth rotor assembly.

[0011] Preferably, the transmission assembly includes a first transmission assembly and a second transmission assembly, one end of the first transmission assembly is connected to the first clutch and the other end is connected to the first main rotor assembly, one end of the second transmission assembly is connected to the second clutch and the other end is connected to the second main rotor assembly.

[0012] Preferably, the first engine and the second engine are both piston engines.

[0013] Preferably, the first clutch and the second clutch are made of titanium alloy.

[0014] On the other hand, a hybrid-powered multi-rotor aircraft is provided, which also includes: a seat, arranged inside the cabin of the fuselage main body; the fuselage main body, main rotor assembly, power system, axle rotor assembly, transmission assembly in Example 1, the first engine and the second engine are connected to the battery pack, and the first engine and the second engine that provide kinetic energy to the main rotor assembly can charge the battery pack that drives the axle rotor assembly to work.

[0015] Preferably, 4-6 seats are provided inside the fuselage body 1.

[0016] Preferably, the materials used for the main rotor assembly and the auxiliary rotor assembly are both carbon fiber composite materials.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] The aircraft in this application is powered by fuel and battery packs, so that the multi-rotor aircraft has the performance of large load, sufficient power, and stable flight attitude. When one of the engines of the aircraft fails, the aircraft can still work, and through the dynamic power allocation technology of the controller, the aircraft saves electricity and reduces energy waste. At the same time, the engine that provides kinetic energy to the main rotor assembly can charge the battery pack of the auxiliary rotor assembly, significantly improving the endurance and practical efficiency of the multi-rotor aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is an overall structural diagram of a hybrid-powered multi-rotor aircraft including seats according to an embodiment of the present invention;

[0020] Figure 2 This is a schematic diagram of the connection of the battery pack portion of the power system in an embodiment of the present utility model;

[0021] Figure 3 This is a connection diagram of the part of the power system associated with the main rotor assembly in an embodiment of the present utility model. DETAILED DESCRIPTION

[0022] 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 embodiments described 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 making creative efforts are within the scope of protection of the present invention.

[0023] Example 1:

[0024] like Figure 1-3 As shown, the power system of the aircraft in this embodiment includes:

[0025] Body 1;

[0026] a main rotor assembly 2 connected to the fuselage body 1;

[0027] a power system 3 connected to the main rotor assembly 2 and configured to drive the main rotor assembly 2 to operate;

[0028] The auxiliary rotor assembly 4 is connected to the power system 3 and driven by the power system to operate;

[0029] The transmission assembly 5 is connected to the main rotor assembly 2.

[0030] Specifically, the main rotor assembly includes: a first main rotor assembly 21 and a second main rotor assembly 22. The first main rotor assembly 21 and the second main rotor assembly 22 are symmetrically distributed on the left and right sides of the fuselage body 1 and are both coupled to the power system 3.

[0031] Furthermore, the power system 3 includes: a first engine 31, a second engine 32, a first generator 33, a second generator 34, a first clutch 35, a second clutch 36, a battery pack 37, and an electric motor assembly 38. The first engine 31 and the second engine 32 are respectively connected to the first main rotor assembly 21 and the second main rotor assembly 22, the first generator 33 and the second generator 34 are respectively connected to the first engine 31 and the second engine 32, the battery pack 37 is connected to the first generator 33 and the second generator 34, the first clutch 35 is connected to the first generator 33, the second clutch 36 is connected to the second generator 34, the first clutch 35 and the second clutch 36 are connected to the transmission assembly 5, the battery pack 37 is connected to the electric motor assembly 38, and the battery pack 37 provides kinetic energy for the electric motor assembly 38.

[0032] Furthermore, the aileron assembly 4 includes a first aileron assembly 41, a second aileron assembly 42, a third aileron assembly 43, and a fourth aileron assembly 44. The first to fourth aileron assemblies 41-44 are symmetrically distributed on the left and right sides of the fuselage body 1, and the aileron assembly 4 is connected to the motor assembly 38.

[0033] Furthermore, the motor assembly 38 includes a first motor 381, a second motor 382, a third motor 383, and a fourth motor 384. The first motor 381, the second motor 382, the third motor 383, and the fourth motor 384 are respectively connected to the first aileron assembly 41, the second aileron assembly 42, the third aileron assembly 43, and the fourth aileron assembly 44. Multiple sets of aileron assemblies can make the aircraft more flexible when flying in the air.

[0034] Furthermore, the transmission assembly 5 includes a first transmission assembly 51 and a second transmission assembly 52. One end of the first transmission assembly 51 is connected to the first clutch 35 and the other end is connected to the first main rotor assembly 21. One end of the second transmission assembly 52 is connected to the second clutch 36 and the other end is connected to the second main rotor assembly 22.

[0035] On this basis, the first engine 31 and the second engine 32 are both piston engines.

[0036] In addition, the first clutch 35 and the second clutch 36 are both made of titanium alloy and can withstand high temperature and high stress.

[0037] In this embodiment, when the first engine 31 fails, the first clutch 35 is disengaged, and the second engine 32 drives the first main rotor assembly 21 and the second main rotor assembly 22 via the first transmission assembly 51. When the second engine 32 fails, the second clutch 36 is disengaged, and the first engine 31 drives the first main rotor assembly 21 and the second main rotor assembly 22 via the second transmission assembly 52. This achieves dual power redundancy.

[0038] Therefore, when one of the engines of the multi-rotor aircraft fails, the main rotor assembly is driven by another engine through the transmission assembly, and the multi-rotor aircraft can still operate safely and smoothly.

[0039] Example 2:

[0040] like Figure 1-3 As shown, the power system in this embodiment includes the fuselage body 1, main rotor assembly 2, power system 3, auxiliary rotor assembly 4, and transmission assembly 5 in Example 1, wherein the power system 3 also includes a controller 39, one end of the controller 39 is connected to the first generator 31 and the second generator 32, and the other end is connected to the battery pack 37.

[0041] In this embodiment, the mechanical energy generated by the first engine 31 and the second engine 32 is converted into electrical energy through the first generator 33 and the second generator 34 and transmitted to the controller 39. At the same time, the electrical energy generated by the battery pack 37 is also transmitted to the controller 39. The controller 39 drives the main rotor assembly 2 and the auxiliary rotor assembly 4 to generate upward lift through dynamic power distribution technology. The total lift generated by the main rotor assembly 2 and the auxiliary rotor assembly 4 overcomes the gravity of the aircraft and ensures the vertical take-off and landing process of the aircraft.

[0042] During the above process, the controller dynamically allocates power to the main rotor assembly and the auxiliary rotor assembly, rationally utilizing the limited electrical energy provided by the power system on the aircraft, reducing power waste and increasing flight time and mileage.

[0043] Example 3:

[0044] This embodiment provides a multi-rotor aircraft based on hybrid power, such as Figure 1-3 As shown, it includes: a seat 6, the fuselage body 1, the main rotor assembly 2, the power system 3, the aileron assembly 4, and the transmission assembly 5 in Example 1, the seat 6 is arranged inside the fuselage body 1, the first engine 31 and the second engine 32 are connected to the battery pack 37, and the first engine 31 and the second engine 32 that provide kinetic energy to the main rotor assembly 2 can charge the battery pack 37 that drives the aileron assembly 4 to work.

[0045] During operation, the first engine 31 and the second engine 32 use fuel combustion to provide mechanical energy to the main rotor assembly 2, while the battery pack 37 provides mechanical energy to the auxiliary rotor assembly 4 through the motor assembly 38. The main rotor assembly 2 and the auxiliary rotor assembly 4 operate simultaneously, driving the multirotor aircraft to fly smoothly.

[0046] Furthermore, 4-6 seats are provided inside the fuselage body 1, and the manned multi-rotor aircraft that can accommodate a large number of people can provide better support for urban smart transportation and smart tourism.

[0047] In addition, the materials used for the main rotor assembly 2 and the auxiliary rotor assembly 4 are both carbon fiber composite materials, which can provide good strength and rigidity while also keeping the rotor lightweight.

[0048] Providing power to the main rotor assembly through fuel and to the auxiliary rotor assembly through the battery pack can enable the multi-rotor aircraft to have the performance of large load, sufficient power, and stable flight attitude; the first engine and the second engine that provide kinetic energy to the main rotor assembly can charge the battery pack of the auxiliary rotor assembly, which significantly improves the endurance of the multi-rotor aircraft and improves the practical efficiency of the multi-rotor aircraft.

[0049] It should be noted that the technical features in the above two embodiments can be combined in any way, and the technical solutions formed by the combination all belong to the scope of protection of this application. In this article, terms such as "including", "comprising" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or equipment including a series of elements includes not only those elements, but also includes other elements that are not explicitly listed, or also includes elements inherent to such process, method, article or equipment. In the absence of further restrictions, the elements defined by the sentence "including a..." do not exclude the presence of other identical elements in the process, method, article or equipment including the elements.

[0050] Although the embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A power system for an aircraft, characterized in that: include: fuselage body; a main rotor assembly connected to the fuselage main body, the main rotor assembly comprising a first main rotor assembly and a second main rotor assembly, wherein the first main rotor assembly and the second main rotor assembly are symmetrically distributed on the left and right sides of the fuselage main body; a power system connected to the main rotor assembly and configured to drive the main rotor assembly to operate; an aileron assembly connected to the power system, and driven by the power system to operate the aileron assembly; A transmission assembly is connected to the main rotor assembly.

2. The power system according to claim 1, wherein: The power system includes: a first engine, a second engine, a first generator, a second generator, a first clutch, a second clutch, a battery pack, and an electric motor assembly. The first engine and the second engine are respectively connected to the first main rotor assembly and the second main rotor assembly, the first generator and the second generator are respectively connected to the first engine and the second engine, the battery pack is connected to the first generator and the second generator, the first clutch and the second clutch are respectively connected to the first generator and the second generator, the first clutch and the second clutch are connected to the transmission assembly, and the battery pack is connected to the electric motor assembly.

3. The power system according to claim 2, wherein: The aileron assembly includes a first aileron assembly, a second aileron assembly, a third aileron assembly, and a fourth aileron assembly. The first to fourth aileron assemblies are symmetrically distributed on the left and right sides of the fuselage body, and the aileron assembly is connected to the motor assembly.

4. The power system according to claim 3, wherein: The motor assembly includes a first motor, a second motor, a third motor, and a fourth motor. The first motor, the second motor, the third motor, and the fourth motor are respectively connected to the first rotor assembly, the second rotor assembly, the third rotor assembly, and the fourth rotor assembly.

5. The power system according to claim 4, characterized in that: The transmission assembly includes a first transmission assembly and a second transmission assembly. One end of the first transmission assembly is connected to the first clutch and the other end is connected to the first main rotor assembly. One end of the second transmission assembly is connected to the second clutch and the other end is connected to the second main rotor assembly.

6. The power system according to claim 2, wherein: The power system further includes a controller, one end of which is connected to the first generator and the second generator, and the other end of which is connected to the battery pack.

7. The power system according to claim 2, wherein: The first clutch and the second clutch are both made of titanium alloy.

8. A hybrid-powered multi-rotor aircraft, characterized in that: include: A seat and a power system according to any one of claims 2 to 7, wherein the seat is arranged inside the fuselage body, and the first engine and the second engine are connected to the battery pack.

9. The multi-rotor aircraft according to claim 8, wherein: 4-6 seats are arranged inside the fuselage body.

10. The multi-rotor aircraft according to claim 8, wherein: The materials used for the main rotor assembly and the auxiliary rotor assembly are both carbon fiber composite materials.

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