Manned multi-rotor aircraft based on direct connection transmission

Abstract

The utility model relates to a manned multi-rotor aircraft based on direct connection transmission, which comprises a fuselage main body, the front part of the fuselage main body is provided with a front wing, the rear part is provided with an empennage, and two sides of the middle part are provided with ailerons; the four groups of lift paddle power assemblies are arranged around the fuselage main body through the front wings and the tail wings respectively; the battery pack is electrically connected with the lift paddle power assembly so as to drive the lift paddle power assembly to operate; the two main rotor assemblies are installed on ailerons on the two sides of the fuselage body correspondingly. The engine is in power connection with the main rotor assembly through the transmission mechanism so as to drive the main rotor assembly to operate. The main rotor assembly of the multi-rotor aircraft is driven by the engine to provide main power for the aircraft, the loading energy of the aircraft can be effectively improved, the lift paddle power assembly can flexibly change the flight attitude of the aircraft, the maneuverability and controllability of the aircraft are enhanced, meanwhile, the engine can charge the battery pack through the generator during operation, and the power generation efficiency is improved. And the endurance mileage of the aircraft can be obviously enhanced.

Description

Technical Field

[0001] The utility model relates to the field of manned aircraft, in particular to a manned multi-rotor aircraft based on direct-connection transmission. 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, and cannot meet the requirements of quickly controlling the flight attitude of rotor manned aircraft, while pure electric tilt-rotor aircraft have fast cruising speed but short cruising range. Utility Model Content

[0003] In order to solve the above problems, the utility model proposes a manned multi-rotor aircraft based on direct-connection transmission, which has a long flight time, a fast cruising speed, a strong load-bearing capacity and flexible take-off and landing.

[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 direct drive, comprising

[0006] The main body of the fuselage has a front wing at the front, a tail wing at the rear, and ailerons on both sides of the middle;

[0007] There are four groups of lift propeller power assemblies, and the four groups of lift propeller power assemblies are arranged around the fuselage body through the front wing and the tail wing respectively;

[0008] A battery pack is installed on the fuselage body, and the battery pack is electrically connected to the lift propeller power assembly to drive the lift propeller power assembly to operate;

[0009] The main rotor assembly has two rotors, which are mounted on the ailerons on both sides of the fuselage.

[0010] The engine is installed on the fuselage body, and the engine is connected to the main rotor assembly through a transmission mechanism to drive the main rotor assembly to operate.

[0011] Preferably, a generator is also provided on the fuselage body, the generator is connected to the output end of the engine and is driven by the engine to generate electricity, and the generator is electrically connected to the battery pack to charge the battery pack.

[0012] Preferably, the generator, battery pack and engine are arranged in the fuselage body and located between the aileron and the tail wing;

[0013] The fuselage body is also provided with seats, which are arranged between the front wing and the aileron.

[0014] Preferably, the aileron is provided with an aileron control surface, the aileron control surface is located at the trailing edge of the outer section of the middle wing of the fuselage body, and the aileron control surfaces on both sides are symmetrically arranged about the central axis of the fuselage body.

[0015] Preferably, two horizontal tail control surfaces are provided on the tail wing, and the horizontal tail control surfaces are located at the trailing edges of both sides of the tail wing, and the horizontal tail control surfaces on both sides are symmetrically arranged about the central axis of the fuselage body.

[0016] Preferably, the transmission mechanism includes two transmission shafts, the engine has an engine output shaft, the engine output shaft is transmission connected to the first ends of the two transmission shafts through a transfer bevel gear set, and the second ends of the transmission shafts are transmission connected to the main rotor assembly through a transmission bevel gear set.

[0017] Preferably, the aileron comprises a fixed part and a rotating part, the fixed part is connected to the fuselage body, the rotating part is rotatably connected to the end of the fixed part away from the fuselage body, and the main rotor assembly is installed on the rotating part;

[0018] The main rotor assembly can be carried by the rotating part so that the axis of the main rotor assembly can stop and be maintained at any angle between horizontal and vertical.

[0019] Preferably, the fuselage body is provided with a tilt actuator, a transmission shaft is installed on the fixed part, and the output end of the tilt actuator is connected to the rotating part through the transmission shaft to drive the rotating part to perform a rotational motion.

[0020] The beneficial effects of using the utility model are:

[0021] The main rotor assembly of this multi-rotor aircraft is driven by an engine to provide the main power for the aircraft. Due to the operating characteristics of the engine, its load-bearing energy can be effectively improved. The lift propeller power assembly arranged at the four corners of the fuselage body can flexibly change the flight attitude of the aircraft and enhance the maneuverability and controllability of the aircraft. The lift propeller power assembly is powered by a battery pack, and the engine can charge the battery pack through a generator during operation, which can significantly enhance the aircraft's cruising range. In addition, since the inclination angle of the main rotor assembly is variable, the aircraft has a fast cruising speed, a strong load-bearing capacity, and flexible take-off and landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 The utility model is a schematic diagram of the whole machine of the manned multi-rotor aircraft based on direct drive in the cruising state.

[0023] Figure 2 The utility model is a schematic diagram of the whole machine of the manned multi-rotor aircraft based on direct drive in a hovering state.

[0024] Figure 3 The utility model is a schematic diagram of the internal power system and transmission structure of a manned multi-rotor aircraft based on direct drive.

[0025] Reference numerals include:

[0026] 1-fuselage body, 2-electric motor, 3-lift propeller power assembly, 4-seat, 5-tilt actuator, 501-transmission shaft, 6-engine, 7-engine output shaft, 8-transfer bevel gear set, 9-transmission bevel gear set, 10-main rotor assembly, 11-speed sensor, 12-aileron control surface, 13-horizontal tail control surface, 14-battery pack, 15-generator. 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 manned 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 the rotor manned aircraft, such as Figure 1-Figure 3 As shown, this embodiment proposes a manned multi-rotor aircraft based on direct transmission. Specifically, this aircraft includes a fuselage body 1, a canard is arranged at the front of the fuselage body 1, a tail is arranged at the rear, and ailerons are arranged on the left and right sides of the middle of the fuselage body 1, and the total extended length of the ailerons is slightly larger than the canard and the tail. In this embodiment, the canard, the tail and the two ailerons are arranged symmetrically with the central axis of the fuselage body 1 as the center of symmetry. The lift propeller power assembly 3 is symmetrically arranged at the ends of the canard and the tail away from the fuselage body 1, wherein the electric motor 2 in the lift propeller power assembly 3 serves as a power device for driving the propeller to rotate.

[0029] In order to improve the maneuverability of the aircraft, the aileron includes a fixed part and a rotating part. The fixed part is connected to the fuselage body 1, and the rotating part is rotatably connected to the end of the fixed part away from the fuselage body 1. The main rotor assembly 10 is installed on the rotating part; the main rotor assembly 10 can be carried by the rotating part so that the axis of the main rotor assembly 10 can stay and maintain at any angle between horizontal and vertical. In this embodiment, the main rotor assembly 10 is installed in the middle of the rotating part, such as Figure 1 As shown, when the axis of the main rotor assembly 10 is in a horizontal state, the propeller of the main rotor assembly 10 faces the front of the fuselage body 1, and the aircraft is in a cruising state. Figure 2As shown, when the main rotor assembly 10 is driven by the rotating part to be in a vertical state, the axis of the main rotor assembly 10 is perpendicular to the axis of the lift propeller power assembly 3, and the aircraft is in a hovering state.

[0030] Preferably, the fuselage body 1 is provided with a tilt actuator 5, a transmission shaft 501 is installed on the fixed part, and the output end of the tilt actuator 5 is connected to the rotating part through the transmission shaft 501 to drive the rotating part to perform a rotation action.

[0031] Control surfaces are arranged on the ailerons and the tail wing to quickly control the flight attitude of the aircraft. Specifically, the ailerons are provided with aileron control surfaces 12, which are located at the trailing edge of the outer section of the wing in the middle of the fuselage body 1, and the aileron control surfaces 12 on both sides are arranged symmetrically about the central axis of the fuselage body 1. Two horizontal tail control surfaces 13 are arranged on the tail wing, which are located at the trailing edges of both sides of the tail wing, and the horizontal tail control surfaces 13 on both sides are arranged symmetrically about the central axis of the fuselage body 1.

[0032] Preferably, a generator 15 is also provided on the fuselage body 1, and the generator 15 is connected to the output end of the engine 6 and driven by the engine 6 to generate electricity. The generator 15 is electrically connected to the battery pack 14 to charge the battery pack 14. When the engine 6 is running, the engine 6 can drive the two lift propeller power assemblies 3 to operate simultaneously through the transmission mechanism. At the same time, in order to charge the battery pack 14, in this embodiment, the power output end of the generator 15 is also provided with a tail output shaft on the other side of the engine output shaft 7, and the tail output shaft is connected to the input end of the generator 15. Therefore, when the engine 6 is running, the generator 15 can generate electricity, and the electric energy generated by the generator 15 is output to the battery pack 14 to supply power to the battery pack 14.

[0033] Preferably, in order to balance the front and rear weights of the aircraft, the generator 15, the battery pack 14 and the engine 6 are arranged on the fuselage body 1 and between the aileron and the tail wing. The fuselage body 1 also has seats 4, which are arranged between the front wing and the aileron. In this embodiment, there are three seats 4 arranged in an inverted triangular shape.

[0034] like Figure 3 As shown, the transmission mechanism includes two transmission shafts 501, the engine output shaft 7 of the engine 6 is transmission-connected to the first ends of the two transmission shafts 501 through the transfer bevel gear set 8, and the second ends of the transmission shafts 501 are transmission-connected to the main rotor assembly 10 through the transmission bevel gear set 9. The engine output shaft 7 can drive two passive transmission bevel gears through an active transmission bevel gear to form a transfer bevel gear set 8, so that the power is divided into two and transmitted to the two lift propeller power assemblies 3. The transmission is carried out between the transmission shaft 501 and the lift propeller power assembly 3 through the transmission bevel gear set 9.

[0035] The transmission mechanism uses the engine output shaft 7 and the transmission shaft 501 for transmission, which is beneficial to the location of the engine 6 and the adjustment of the center of gravity of the aircraft. The transmission bevel gear set 9 uses bevel gears to change the rotation direction by 90 degrees, which is beneficial to the continuity of the power transmission of the transmission system during the tilting process and the stability of the aircraft flight. It has the advantages of high power density and continuous and stable transmission.

[0036] If the engine 6 stops, the battery and four lift propeller power assemblies 3 provide lift for landing. During the descent process, the main rotors in the main rotor assembly 10 are turned to negative pitch to maintain the speed and maintain the kinetic energy of the main rotors. At a certain height before landing, the two main rotor assemblies 10 are turned to positive pitch to convert the kinetic energy of the main rotor assembly 10 into lift to achieve drifting and reduce the landing speed of the aircraft to a safe range. The speed of the propellers in the main rotor assembly 10 can be obtained through the speed sensor 11.

[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 manned multi-rotor aircraft based on direct drive, characterized in that: include The main body of the fuselage has a front wing at the front, a tail wing at the rear, and ailerons on both sides of the middle; There are four groups of lift propeller power assemblies, and the four groups of lift propeller power assemblies are arranged around the fuselage body through the front wing and the tail wing respectively; A battery pack is installed on the fuselage body, and the battery pack is electrically connected to the lift propeller power assembly to drive the lift propeller power assembly to operate; The main rotor assembly has two rotors, which are mounted on the ailerons on both sides of the fuselage. The engine is installed on the fuselage body, and the engine is connected to the main rotor assembly through a transmission mechanism to drive the main rotor assembly to operate.

2. The manned multi-rotor aircraft based on direct transmission according to claim 1, characterized in that: A generator is also provided on the fuselage body, which is connected to the output end of the engine and driven by the engine to generate electricity. The generator is electrically connected to the battery pack to charge the battery pack.

3. The manned multi-rotor aircraft based on direct transmission according to claim 2, characterized in that: The generator, battery pack and engine are arranged in the main body of the fuselage and located between the aileron and the tail wing; The fuselage body is also provided with seats, which are arranged between the front wing and the aileron.

4. The manned multi-rotor aircraft based on direct transmission according to claim 1, characterized in that: The ailerons are provided with aileron control surfaces, which are located at the trailing edge of the outer section of the wing in the middle of the fuselage body, and the aileron control surfaces on both sides are symmetrically arranged with respect to the central axis of the fuselage body.

5. The manned multi-rotor aircraft based on direct transmission according to claim 1, characterized in that: The tail wing is provided with two horizontal tail control surfaces, which are located at the trailing edges of both sides of the tail wing, and the horizontal tail control surfaces on both sides are symmetrically arranged with respect to the central axis of the fuselage body.

6. The manned multi-rotor aircraft based on direct transmission according to claim 1, characterized in that: The transmission mechanism includes two transmission shafts, and the engine has an engine output shaft, which is transmission-connected to the first ends of the two transmission shafts through a transfer bevel gear set, and the second ends of the transmission shafts are transmission-connected to the main rotor assembly through a transmission bevel gear set.

7. The manned multi-rotor aircraft based on direct transmission according to any one of claims 1 to 6, characterized in that: The aileron comprises a fixed part and a rotating part, wherein the fixed part is connected to the fuselage body, the rotating part is rotatably connected to the end of the fixed part away from the fuselage body, and the main rotor assembly is installed on the rotating part; The main rotor assembly can be carried by the rotating part so that the axis of the main rotor assembly can stop and be maintained at any angle between horizontal and vertical.

8. The manned multi-rotor aircraft based on direct transmission according to claim 7, characterized in that: The fuselage body is provided with a tilt actuator, the fixed part is provided with a transmission shaft, and the output end of the tilt actuator is connected to the rotating part through the transmission shaft to drive the rotating part to perform a rotation action.

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