CN205060006U - Four -rotor unmanned aerial vehicle - Google Patents

Abstract

A quadrotor unmanned aerial vehicle comprises a fuselage and two flying arms, the middle part of the flying arms is connected to the fuselage by screws, motors are respectively arranged at both ends of the flying arms, and propellers are arranged at the output ends of the motors. The UAV connects the middle parts of the two flying arms to the fuselage with screws, and sets motors and propellers at both ends of each flying arm to form a four-rotor structure. Only two flying arms can form a four-rotor The wing arm is simple in structure, easy to assemble, and the structural stability is obviously improved; the two flying arms are connected to the fuselage by screws, which is convenient for disassembly and assembly, takes up little space after disassembly, and is easy to carry.

Description

A quadcopter drone

technical field

The utility model mainly relates to the technical field of unmanned aerial vehicles, in particular to the technical field of four-rotor unmanned aerial vehicles.

Background technique

Multi-rotor UAV is a relatively flexible UAV aircraft, mainly including four-rotor UAV, six-rotor UAV, eight-rotor UAV and other types, among which quadrotor UAV is the most, The most widely used.

At present, the four-rotor UAV aircraft on the market adopts a star structure, which is mainly composed of a fuselage and four flying arms with motors and propellers. This structure takes up a lot of space, is not suitable for carrying, and is troublesome to disassemble and assemble. Less stable.

Contents of the invention

The utility model provides a four-rotor unmanned aerial vehicle, the structure of the unmanned aerial vehicle is convenient to disassemble, takes up little space after disassembly, is easy to carry, and the structural stability is obviously improved.

The technical scheme adopted in the utility model is:

A quadrotor unmanned aerial vehicle comprises a fuselage and two flying arms, the middle part of the flying arms is connected to the fuselage by screws, motors are respectively arranged at both ends of the flying arms, and propellers are arranged at the output ends of the motors.

The above-mentioned UAV connects the middle parts of the two flying arms to the fuselage through screws, and sets motors and propellers at both ends of each flying arm to form a four-rotor structure. Only two flying arms can form a four-rotor structure. The wing arm of the rotor has a simple structure, is easy to assemble, and has significantly improved structural stability; the two flying arms are connected to the fuselage by screws, which is convenient for disassembly and assembly, takes up little space after disassembly, and is easy to carry.

A recess capable of accommodating the middle part of the other flying arm is provided on the middle part of any flying arm. The middle parts of the two flying arms are fitted together to achieve relative fixation, and then installed on the fuselage, the structure is more stable, and it is ensured that the flying arms are all on the same level, that is, all the propellers are on the same level, ensuring that the UAV performance.

The two flying arms are crossed and fixed in a cross shape. The structure is simple and the product stability is improved.

Corresponding to each motor in the flying arm, an electronic governor is respectively provided. By flexibly adjusting the speed of the motor, the speed of the propeller can be adjusted according to actual needs.

A GPS antenna is set above the fuselage, and a flight control module, a wireless image transmission module, a wireless digital transmission module and a remote control receiving module for receiving remote control signals are set inside the fuselage, and a sensor is mounted on the bottom of the fuselage through screws. . Make full use of the integration space. The sensor mount is equipped with different sensor devices such as cameras with data codes and cameras for operations. The sensor mount is detachable and easy to carry.

The undersides of the two outer sides of the fuselage are symmetrically provided with landing gears, and the two sides of the upper ends of the landing gears are respectively connected under two adjacent flying arms by screws. The landing gear is detachable and easy to carry. It is set on the two flying arms. The structure is stable and the impact resistance is obviously improved.

The landing gear is n-shaped, and the battery is mounted under the landing gear through screws. The battery can be loaded in the battery mount to provide power for the device on the drone. The structure is simple and detachable, and it is easy to carry.

The beneficial effects brought by the utility model are:

The UAV has a simple structure, realizes two flying arms carrying four motors and four propellers, is easy to assemble, and has significantly improved structural stability; it is also easy to disassemble and assemble, takes up little space after disassembly, and is easy to carry.

Description of drawings

Fig. 1 is the top view of the utility model embodiment;

Fig. 2 is the front view of the utility model embodiment;

Fig. 3 is the left view of the utility model embodiment;

Fig. 4 is a schematic diagram of the disassembled structure of the utility model embodiment;

Reference signs:

1. Electronic governor; 2. Motor; 3. Propeller; 4. GPS antenna; 5. Flight control module; 6. Wireless image transmission module; 7. Wireless digital transmission module; 8. Remote control receiving module; 9. Remote control ; 10, battery mounting; 11, sensor mounting; 12, landing gear; 13, flying arm; 14, fuselage; 15, recess.

detailed description

As shown in Figure 1-4, a kind of four-rotor unmanned aerial vehicle comprises fuselage 14 and two flying arms 13, and the middle part of flying arm 13 is connected on the fuselage 14 by screw, is respectively arranged at the two ends of flying arm 13 There is a motor 2, and the output end of the motor 2 is provided with a propeller 3.

The UAV uses the middle parts of the two flying arms 13 to be connected to the fuselage 14 by screws, and the motor 2 and the propeller 3 are respectively arranged at the two ends of each flying arm 13 to form a four-rotor structure. 13 can form a four-rotor wing arm, which has a simple structure and is easy to assemble, and the structural stability is significantly improved; the two flying arms 13 are connected to the fuselage 14 by screws, which is convenient for disassembly and assembly. After disassembly, it takes up little space and is convenient carry.

A recess 15 capable of accommodating the middle of another flying arm 13 is provided at the middle of any flying arm 13 . The middle parts of the two flying arms 13 are fitted to each other to achieve relative fixation, and then installed on the fuselage 14, the structure is more stable, and it is ensured that the flying arms 13 are all located on the same horizontal plane, that is, each propeller 3 is located on the same horizontal plane, Guaranteed drone performance.

Two flying arms 13 are crossed and fixed in a cross shape. The structure is simple and the product stability is improved.

Corresponding to each motor 2, an electronic governor 1 is respectively provided in the flying arm 13 . By flexibly adjusting the rotational speed of the motor 2, the rotational speed of the propeller 3 can be adjusted according to actual needs.

A GPS antenna 4 is arranged on the top of the fuselage 14, and a flight control module 5, a wireless image transmission module 6, a wireless digital transmission module 7 and a remote control receiving module 8 for receiving signals from the remote controller 9 are arranged in the fuselage 14. The sensor mounting 11 is connected to the bottom of the 14 by screws. Make full use of the integrated space, the sensor mount 11 is equipped with different sensor devices such as a data code camera and a video camera to carry out operations, and the sensor mount 11 is detachable and easy to carry.

Underneath the two outer sides of the fuselage 14 are symmetrically provided with landing gears 12, and the two sides of the upper end of the landing gears 12 are respectively connected under two adjacent flying arms 13 by screws. The undercarriage 12 is detachable and easy to carry. It is arranged on the two flying arms 13. The structure is stable and the impact resistance is obviously improved.

The undercarriage 12 is n-shaped, and the battery mount 10 is connected with a screw under the undercarriage 12 . The battery can be loaded in the battery mount 10, the structure is simple and detachable, and it is easy to carry.

The specific implementation steps for the application of the quadrotor UAV are as follows:

(1) First, the electronic governor 1 is correspondingly embedded in the flight arm 13, the GPS antenna 4 is installed and fixed on the fuselage 14, and the flight control module 5, wireless image transmission module 6, wireless digital transmission module 7, remote control The receiving module 8 is installed and fixed in the fuselage 14;

(2) 4 propellers 3 are respectively installed on the output terminals of 4 motors 2, 4 motors 2 are installed on 2 flying arms 13, and electronic governor 1 is connected with motor 2 signal;

(3) The middle recesses 15 of the two flying arms 13 are fixed in a cross shape to the recesses 15, and installed under the fuselage 14;

(4) The sensor mounting 11 is installed below the middle part of the two flying arms 13;

(5) 2 landing gears 12 are installed and fixed on the flight arm 13, so that the 2 landing gears 12 are arranged symmetrically below the two outer sides of the fuselage 14;

(6) Install two battery mounts 10 under the landing gear 12 respectively;

(7) Mount the two batteries on the two battery mounts 10 respectively;

(8) mount the sensor on the sensor mount 11 of the fuselage 14 mainboard;

(9) Take off after debugging the UAV;

(10) After the operation is completed, the UAV lands and powers off;

(11) the sensor is unloaded from the sensor mount 11 of the fuselage 14;

(12) 2 batteries are unloaded from the battery mount 10;

(13) 2 battery mounts 10 devices are unloaded from the flight arm 13;

(14) Sensor mounting 11 is unloaded from flying arm 13;

(15) 2 flying arms 13 are unloaded from the fuselage 14;

(16) 4 motors 2 and 4 propellers 3 are unloaded from 2 flying arms 13;

(17) All accessories are placed in the carrying device, and a flight operation is completed.

The above detailed description is a specific description for one of the feasible embodiments of the present utility model. This embodiment is not intended to limit the patent scope of the present utility model. Any equivalent implementation or change that does not deviate from the utility model shall include within the patent scope of this case.

Claims (7)

1. four rotor wing unmanned aerial vehicles, is characterized in that: comprise fuselage and two flight arms, the middle part of described flight arm is connected on described fuselage by screw, is respectively arranged with motor, is provided with screw propeller at the mouth of described motor at the two ends of described flight arm.

2. four rotor wing unmanned aerial vehicles according to claim 1, is characterized in that: the recess offering the middle part that can hold the arm that to fly described in another on the middle part of arbitrary described flight arm.

3. four rotor wing unmanned aerial vehicles according to claim 1 and 2, is characterized in that: described two flight arms are that square crossing is fixed.

4. four rotor wing unmanned aerial vehicles according to claim 3, is characterized in that: in described flight arm, corresponding each described motor is respectively equipped with electronic governor.

5. four rotor wing unmanned aerial vehicles according to claim 4, it is characterized in that: above described fuselage, be provided with gps antenna, in described fuselage, be provided with the remote control reception module of flight control modules, wireless image transmission module, wireless digital transmission module and reception remote controller signal, below described fuselage, be connected with sensor carry by screw.

6. four rotor wing unmanned aerial vehicles according to claim 5, is characterized in that: the below outside two of described fuselage is arranged with alighting gear, under the both sides, upper end of alighting gear are connected to respectively by screw the arm that to fly described in adjacent two.

7. four rotor wing unmanned aerial vehicles according to claim 6, is characterized in that: described alighting gear is N-shaped, are connected with battery carry in the below of described alighting gear by screw.