Manned aircraft piloted by small unmanned aerial vehicle

Abstract

The invention discloses a manned aircraft piloted by a small unmanned aerial vehicle, and belongs to the technical field of manned flight equipment. The aircraft comprises a cabin, a large multi-rotor module, a small multi-rotor module, a connecting rod, a universal hinge and an undercarriage, the large multi-rotor module is fixed on the cabin and is mainly used for generating lift force; the small multi-rotor module is connected with the cabin through a connecting rod and a universal hinge, is positioned in front of the cabin, and is mainly used for controlling the flight attitude of the aircraft; a remote controller is arranged in the cabin, and a driver can remotely control the small multi-rotor module through the remote controller. The characteristics of low equipment failure rate and high stability of the small unmanned aerial vehicle are utilized, the overall failure risk of the manned aircraft is reduced, meanwhile, navigation is conducted through the small multi-rotor-wing module in front, the control experience of a driver is enhanced, and the flight safety is improved.

Description

Technical Field

[0001] This invention relates to the field of manned flight equipment technology, and more specifically to a manned aircraft led by a small unmanned aerial vehicle. Background Technology

[0002] With the development of drone technology, multi-rotor aircraft have been widely used in various fields. However, heavy-load manned aircraft pose higher safety risks due to their complex equipment and numerous potential failure points. Small multi-rotor drones, on the other hand, have relatively simple structures, low equipment failure rates, and high stability. Currently, there is a lack of technical solutions that combine the advantages of small drones to reduce the failure risks of manned aircraft and improve the user experience. Summary of the Invention

[0003] The purpose of this invention is to provide a manned aircraft led by a small drone, in order to solve the problems of high failure risk and insufficient control experience of existing heavy-load manned aircraft.

[0004] To achieve the above objectives, the present invention adopts the following technical solution: A manned aircraft led by a small unmanned aerial vehicle includes a cabin, a large multi-rotor module, a small multi-rotor module, connecting rods, and universal hinges.

[0005] The cabin provides seating space for the pilot and is equipped with a remote control, which allows the pilot to remotely operate the small multi-rotor module in front of them.

[0006] The large multi-rotor module is fixed to the cabin and includes multiple large rotors. Its main function is to generate sufficient lift to support the weight of the cabin and pilot. Its distribution ensures balanced lift. The large multi-rotor module has no fewer than four large rotors, symmetrically distributed around the cabin.

[0007] The small multi-rotor module is located at the front of the cabin and is connected to the cabin via connecting rods and universal hinges. Multiple small rotors work together to achieve precise control of the aircraft's flight attitude (such as forward, backward, and yaw). Utilizing the low failure rate of small UAV equipment, the stability of the attitude control section is improved. The small multi-rotor module has no fewer than four small rotors and adopts a multi-rotor UAV structure.

[0008] One end of the connecting rod is fixed to the nacelle, and the other end is connected to the small multirotor module via a universal hinge. The universal hinge allows the small multirotor module to rotate flexibly within a certain range to adapt to different flight attitude adjustment needs, while ensuring the reliability of the connection. The universal hinge enables the small multirotor module to adjust its angle in three-dimensional space.

[0009] Furthermore, it also includes landing gear, which is located at the bottom of the cabin and provides support for the aircraft's takeoff and landing, ensuring stability during ground operations.

[0010] Furthermore, the cabin is fixedly installed on the top of the cabin, facilitating entry and exit for the pilot and passengers, and ensuring high safety and stability.

[0011] Furthermore, the remote controller and the small multi-rotor module communicate wirelessly over a distance of not less than 50 meters. Alternatively, the remote controller and the small multi-rotor module can communicate via a wired connection. The signal line is laid along the connecting rod, with one end electrically connected to the small multi-rotor module and the other end electrically connected to the remote controller. Wired communication avoids interference and offers high security and reliability.

[0012] The beneficial effects of this invention are as follows: Reduced failure risk: By leveraging the low failure rate of small UAV equipment, the critical function of attitude control is handled by a small multi-rotor module, reducing the overall system's failure points and improving flight safety. Enhanced control experience: The pilot controls the navigation through a small multi-rotor module in front, making the control more intuitive. Especially in complex flight environments, the pilot can adjust the flight attitude more promptly, enhancing the driving experience. The structure is rationally designed: the large multi-rotor module is responsible for lift, and the small multi-rotor module is responsible for attitude control. The division of labor is clear. Combined with the connection method of universal hinges and connecting rods, it not only ensures the realization of functions, but also has structural stability. The large multi-rotor module is located on the top of the cabin. During flight, the large multi-rotor module is basically in a horizontal position, which ensures high safety and stability. Attached Figure Description

[0013] Figure 1 This is a structural schematic diagram of a manned aircraft led by a small unmanned aerial vehicle. The labels in the diagram are as follows: 1-Large multirotor module (fixed to the nacelle): responsible for generating lift; 11-Large rotor: a large multirotor module used to generate lift; 2-Small multirotor module: Located at the front of the cabin, responsible for attitude control; 21-Small rotor: Belongs to the small multirotor module, used to control flight attitude; 3-Pilot: Located inside the cockpit, controlling the aircraft; 4-Cabin: The pilot's seating area, integrating various components; 5-Connecting rod (one end fixed to the nacelle, the other end hinged to the small multirotor module via a universal hinge): connects the nacelle and the small multirotor module; 6-Universal hinge: Enables angle adjustment of small multi-rotor modules; 7-Landing gear: Used for takeoff and landing support; 8-Remote controller: Used by the driver to remotely control the small multi-rotor module. Detailed Implementation

[0014] The specific embodiments of the present invention will be further described below with reference to the accompanying drawings: like Figure 1 As shown, a manned aircraft led by a small unmanned aerial vehicle according to the present invention includes a cabin 4, a large multi-rotor module 1, a small multi-rotor module 2, a connecting rod 5, a universal hinge 6, and a landing gear 7.

[0015] The cabin 4 has a streamlined structure and is equipped with a pilot's seat. The pilot 3 sits in the pilot's seat and is equipped with a remote control 8 in front of him.

[0016] The large multi-rotor module 1 has four large rotors, symmetrically mounted around the upper perimeter of the cabin 4. Each large rotor 11 is driven by an independent motor, which is electrically connected to a battery to provide power and generate lift. The battery is located inside the cabin. The large multi-rotor module 1 is positioned on top of the cabin 4, ensuring both safety and stability.

[0017] The small multi-rotor module 2 is a quadcopter drone structure with four small rotors, connected to the front of the cabin 4 via connecting rod 5 and universal hinge 6. Connecting rod 5 is made of lightweight, high-strength material (carbon fiber or aerospace aluminum alloy), and universal hinge 6 is made of metal, allowing for flexible rotation.

[0018] The remote controller and the small multi-rotor module communicate wirelessly, with a normal communication distance of 60 meters.

[0019] The landing gear 7 is fixed to the bottom of the cabin 4 and features an anti-slip and shock-absorbing design.

[0020] During operation, pilot 3 first checks the status of all components, then starts the power system of the large multi-rotor module 1 to enable the aircraft to take off vertically. During flight, pilot 3 controls the smaller multi-rotor module 2 in front via remote control 8, adjusting its attitude to drive the entire aircraft forward, backward, and yaw maneuvers to complete the flight mission. Upon landing, pilot 3 maneuvers the aircraft to descend slowly, supported by landing gear 7. Throughout the entire process, the large multi-rotor module 1 remains essentially horizontal, and the cabin does not tilt, ensuring safety and stability.

[0021] The above description is merely a preferred embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A manned aircraft led by a small unmanned aerial vehicle, characterized in that, include: The cabin (4) is equipped with a remote controller (8) for remotely controlling the small multi-rotor module (2). A large multi-rotor module (1) is fixed on the cabin (4) and contains multiple large rotors (11), which are mainly used to generate lift; A small multi-rotor module (2), comprising multiple small rotors (21), is located in front of the cabin (4); The connecting rod (5) is fixed at one end to the cabin (4) and the other end is hinged to the small multi-rotor module (2) via a universal hinge (6).

2. The manned aircraft according to claim 1, characterized in that, It also includes landing gear (7), which is located at the bottom of the cabin (4) for support during takeoff and landing.

3. The manned aircraft according to claim 1 or 2, characterized in that, The large multi-rotor module (1) is fixed to the top of the cabin (4).

4. The manned aircraft according to claim 1 or 2, characterized in that, The large multi-rotor module (1) has no fewer than four large rotors (11), which are symmetrically distributed around the cabin (4).

5. The manned aircraft according to claim 1 or 2, characterized in that, The small multi-rotor module (2) has no fewer than four small rotors (21) and adopts a multi-rotor drone structure.

6. The manned aircraft according to claim 1 or 2, characterized in that, The universal hinge (6) enables the small multi-rotor module (2) to adjust its angle in three-dimensional space to adapt to different flight attitude control requirements.

7. The manned aircraft according to claim 1 or 2, characterized in that, The remote controller (8) and the small multi-rotor module (2) communicate wirelessly over a distance of not less than 50 meters.

8. The manned aircraft according to claim 1 or 2, characterized in that, The remote controller (8) and the small multi-rotor module (2) communicate via a wired method. The signal line is laid along the connecting rod (5). One end of the signal line is electrically connected to the small multi-rotor module (2), and the other end of the signal line is electrically connected to the remote controller (8).

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