CN220842106U

CN220842106U - Aircraft

Info

Publication number: CN220842106U
Application number: CN202322846793.6U
Authority: CN
Inventors: 彭云; 张志奇; 万明全; 邓子涵; 张进; 徐勇; 涂良辉; 曾志峰
Original assignee: Nanchang Hangkong University
Current assignee: Nanchang Hangkong University
Priority date: 2023-10-24
Filing date: 2023-10-24
Publication date: 2024-04-26
Anticipated expiration: 2033-10-24

Abstract

The utility model discloses an aircraft, which comprises a base and a main body part arranged on the base, wherein the base is a bearing structure part of the aircraft, the main body part comprises a disc structure arranged on the base and a deflection connecting rod mechanism arranged on the periphery of the disc structure, the disc structure is used for placing components, a rotor wing driving structure is arranged on the deflection connecting rod mechanism, and the deflection connecting rod mechanism can realize tilting of the rotor wing driving structure to change the pulling force direction by 90 degrees. The aircraft solves the technical problem that the traditional quadrotor unmanned aerial vehicle can only fly in the air but cannot move after landing on the ground, and can integrate the flying power device and the ground moving power device into a whole, thereby reducing the dead weight of the aircraft.

Description

Aircraft

Technical Field

The utility model relates to the technical field of aircraft manufacturing, in particular to an aircraft.

Background

Unmanned aerial vehicle's application in various fields such as civilian, for military use, search and rescue at present is more and more frequent, unmanned aerial vehicle's technique also constantly updates the iteration, traditional rotor unmanned aerial vehicle can only fly the reconnaissance in the air in the application of reconnaissance, and can not fall the back and remove the reconnaissance on ground, and hover for a long time can cause the duration of aircraft not enough, along with the environmental condition requirement of application is more and more complicated, continuous improvement to energy-conserving duration, a tractor serves several purposes requirement, but the small-size aircraft that can ground motion and air flight appears, but adopts ground motion power device and flight power device separation design mostly, leads to the dead weight of aircraft to increasing.

Disclosure of Invention

The utility model aims to solve the technical problems, and provides an aircraft, which deflects a rotor arm by 90 degrees through a connecting rod deflection mechanism, wherein four rotors respectively rotate to generate forward, backward, leftward and rightward driving forces, or the rotors which are mutually 90 degrees rotate at different rotating speeds to generate lateral combined driving forces so as to drive the aircraft to move on the ground, so that the technical problem that a traditional four-rotor unmanned aerial vehicle can only fly in the air and cannot move after landing on the ground is solved, a flying power device and a ground moving power device can be integrated, and the dead weight of the aircraft is reduced.

In order to achieve the above purpose, the present utility model adopts the following technical scheme:

The utility model provides an aircraft, which comprises a base and a main body part arranged on the base, wherein the base is a bearing structure part of the aircraft, the main body part comprises a disc structure arranged on the base and a deflection connecting rod mechanism arranged on the periphery of the disc structure, the disc structure is used for placing components, a rotor wing driving structure is arranged on the deflection connecting rod mechanism, and the deflection connecting rod mechanism can realize tilting of the rotor wing driving structure to change the pulling force direction by 90 degrees.

Further, the rotor driving structure is a power device of the aircraft, the rotor driving structure comprises a motor and a rotor, and the motor is used for driving the rotor to rotate.

Further, the number of the components is a plurality of, and the components are respectively a receiver, a flight control device, a battery and an electric regulator.

Further, the bottom of base is equipped with the universal wheel, through the universal wheel realizes the omnidirectional rotation.

Further, the rotor driving structure is arranged at one end of the deflection connecting rod mechanism, and a camera is arranged at one end of the deflection connecting rod mechanism away from the rotor driving structure.

Further, the deflection link mechanism comprises a first link, an acting cylinder and a second link, wherein the acting cylinders and the second link are arranged on two opposite sides of the first link, one end, away from the first link, of the second link is a fulcrum end, and the crank arm is rotated through the expansion and contraction of the acting cylinder, so that the rotor wing deflects around the fulcrum end, and the tension direction is changed.

Further, the deflection link mechanism is connected to the rotor driving structure by a motor.

In summary, the beneficial effects of the utility model are as follows:

According to the aircraft disclosed by the utility model, the rotor arm is deflected by 90 degrees through the deflection connecting rod mechanism, so that the ground movement power device and the flight power device of the four-axis unmanned aerial vehicle are integrated, the movement field of the traditional four-axis aircraft is expanded from the air to the ground, the switching between the air flight and the ground movement is realized through the connecting rod deflection mechanism, the two movement modes share one set of power, and the conversion structure is simple.

Drawings

FIG. 1 is a schematic structural view of an aircraft of the present utility model;

FIG. 2 is a schematic structural view of the aircraft of FIG. 1 from another perspective;

FIG. 3 is a schematic structural view of the deflection link mechanism of the aircraft shown in FIG. 1;

FIG. 4 is a schematic view of the structure at A of the deflection link mechanism shown in FIG. 3;

FIG. 5 is a schematic view of the structure of the deflection link mechanism shown in FIG. 3 at B;

FIG. 6 is a schematic view of the deflection link mechanism of FIG. 3 in another state;

FIG. 7 is a schematic view of the deflection link mechanism of FIG. 3 in a further state;

FIG. 8 is a schematic view of the deflection link mechanism of FIG. 3 in a further state;

FIG. 9 is a tension diagram of the rotor drive structure of the aircraft shown in FIG. 1;

In the figure: universal wheel 1, base 2, rotor drive structure 3, disc structure 4, deflection link mechanism 5, camera 6, action section of thick bamboo 11, fulcrum end 12, motor 13.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions in the embodiments of the present utility model will be clearly and completely described below, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Referring to fig. 1-9, the present utility model provides an aircraft, including a base 2 and a main body portion disposed on the base, where the base is a load-bearing structure portion of the aircraft, and the main body portion includes a disc structure 4 disposed on the base and a deflection link mechanism 5 disposed on a peripheral side of the disc structure, where the disc structure is used for placing components, and the deflection link mechanism is provided with a rotor driving structure 3, and the deflection link mechanism can implement tilting of the rotor driving structure, so that a tensile direction of the rotor driving structure is changed by 90 degrees.

In one embodiment, the rotor driving structure is a power device of the aircraft, and the rotor driving structure includes a motor and a rotor, and the motor is used for driving the rotor to rotate.

In one embodiment, the number of the components is a plurality of the components, and the plurality of the components are a receiver, a flight control, a battery and an electric regulator respectively.

In one embodiment, the bottom end of the base is provided with a universal wheel 1, and the universal wheel is used for realizing omnidirectional rotation.

In one embodiment, the rotor driving structure is disposed at one end of the deflection link mechanism, and a camera 6 is disposed at one end of the deflection link mechanism away from the rotor driving structure.

In one embodiment, the deflection link mechanism comprises a first link, an acting cylinder 11 and a second link, wherein the acting cylinders 11 and the second link are arranged on two opposite sides of the first link, one end, far away from the first link, of the second link is a fulcrum end 12, the 7-shaped crank arm is rotated through the expansion and contraction of the acting cylinder, and the rotor is deflected around the fulcrum end to change the pulling force direction.

In one embodiment, the deflection linkage is coupled to the rotor drive structure by a motor 13.

The aircraft of the utility model lands on the ground when no aerial reconnaissance/shooting is needed or when further reconnaissance/shooting is needed, and can freely move on the ground to more conveniently execute tasks. Compared with hovering, the method is more energy-saving and can increase the time for executing the task; the unmanned aerial vehicle can also be used as a small unmanned aerial vehicle, and when the unmanned aerial vehicle moves on the ground and encounters an insurmountable obstacle, the unmanned aerial vehicle is switched to the quadrotor unmanned aerial vehicle to fly over the obstacle. The specific tension implementation is shown in fig. 9, and the arrow indicates the rotor tension direction. The front, back, left, right or lateral movement of the unmanned aerial vehicle is realized by controlling the rotation speed of each rotor wing or the rotation speeds of the rotor wings which are 90 degrees mutually.

Finally, it should be noted that the above embodiments are only for illustrating the technical solution of the present utility model and not for limiting the scope of the present utility model, and although the present utility model has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions can be made to the technical solution of the present utility model without departing from the spirit and scope of the technical solution of the present utility model.

Claims

1. An aircraft, characterized in that: including the base with locate main part on the base, the base is the bearing structure part of aircraft, main part is including locating disc structure on the base with locate the deflection link mechanism of disc structure week side, disc structure is used for placing components and parts, be equipped with rotor driving structure on the deflection link mechanism, deflection link mechanism can realize rotor driving structure's tilting, makes its pulling force direction take place 90 degrees changes.

2. An aircraft according to claim 1, wherein: the rotor driving structure is a power device of the aircraft, and comprises a motor and a rotor, wherein the motor is used for driving the rotor to rotate.

3. An aircraft according to claim 2, wherein: the number of the components is multiple, and the components are respectively a receiver, a flight control device, a battery and an electric regulator.

4. An aircraft according to claim 3, wherein: the bottom of base is equipped with the universal wheel, through the universal wheel realizes the omnidirectional rotation.

5. An aircraft according to claim 4, wherein: the rotor driving structure is arranged at one end of the deflection connecting rod mechanism, and a camera is arranged at one end of the deflection connecting rod mechanism away from the rotor driving structure.

6. An aircraft according to claim 5, wherein: the deflection link mechanism comprises a first link, an action cylinder and a second link, wherein the action cylinders and the second link are arranged on two opposite sides of the first link, one end, far away from the first link, of the second link is a fulcrum end, the crank arm is rotated through the expansion and contraction of the action cylinder, and the rotor wing deflects around the fulcrum end to change the tension direction.

7. An aircraft according to claim 6, wherein: the deflection link mechanism is connected with the rotor driving structure through a motor.