CN204489177U - Four rotor unmanned aircrafts - Google Patents

Abstract

The utility model discloses a kind of four rotor unmanned aircrafts, " ten " font suspension body that it is made up of the first suspension and the second suspension, motor, screw propeller, GPS and protective case composition, protective case is provided with above described first suspension and the second suspension intersection location, described protective case edge is provided with GPS, motor is connected at the two ends of described first suspension and the second suspension, described motor output shaft is connected with screw propeller, hydrogen cell is connected with in the below of described first suspension and the second suspension intersection location, described hydrogen cell is electrically connected with motor.The beneficial effects of the utility model are: the cruise duration with overlength, can operation aloft for a long time.

Description

Quadrotor UAV

technical field

The utility model relates to the field of unmanned aerial vehicles, in particular to a four-rotor unmanned aerial vehicle using hydrogen fuel cell micro power.

Background technique

Quadrotor unmanned aerial vehicle is a newly developed unmanned aerial vehicle technology in recent years. Compared with other aircraft, the quadrotor unmanned aerial vehicle has a simple and compact mechanical structure, more flexible actions, lower requirements for take-off and landing environments, and good performance. Excellent operational performance, it can take off, hover and land in a small area. Due to these characteristics, quadrotor aircraft are widely used in many fields such as power line inspection, aerial photography, surveillance, investigation, emergency rescue and so on.

The current quadrotor unmanned aerial vehicles mainly use lithium batteries as power equipment, which has limited power capacity, short battery life, and cannot perform long-endurance tasks, which affects its application in many fields.

Utility model content

The utility model overcomes the shortcomings of the four-rotor unmanned aerial vehicle in the prior art that the lithium battery is used as the power device, and the power supply time is short, and provides a simple structure, easy to carry, stable flight, high degree of full-automatic, low noise, and can be operated in the air. It is a four-rotor unmanned aerial vehicle that operates in a field environment, has a long battery life, and can operate under control for a long time.

In order to achieve the above object, the utility model adopts the following technical solutions:

A four-rotor unmanned aerial vehicle, which is composed of a "cross"-shaped suspension body composed of a first suspension and a second suspension, a motor, a propeller, GPS and a protective cover. A protective cover is provided above the intersecting position of the frames, a GPS is provided on the edge of the protective cover, motors are respectively connected to the two ends of the first suspension and the second suspension, and a propeller is connected to the output shaft of the motor. A hydrogen fuel cell is connected below the intersection of the first suspension and the second suspension, and the hydrogen fuel cell is electrically connected to the motor.

In this technical solution, the hydrogen fuel cell is connected under the intersection position of the first suspension and the second suspension, and the lithium battery power supply method in the prior art is replaced by the hydrogen fuel cell. Due to the increase in the capacity of the hydrogen fuel cell, thereby increasing The endurance time of the aircraft enables the aircraft to operate in the air for a long time.

A further technical solution is that the hydrogen fuel cell is installed below the intersection of the first suspension and the second suspension in a suspended manner.

In this technical solution, the hydrogen fuel cell is installed under the intersection position of the first suspension and the second suspension by means of suspension, so that the whole aircraft can be re-sinked, and the overall wind resistance flight capability of the aircraft can be increased.

A further technical solution is that two ends of the first suspension are provided with supporting legs.

A further technical solution is that two ends of the second suspension are provided with supporting legs.

In the technical solution, the supporting legs are arranged at both ends of the first suspension, and the supporting legs are arranged at both ends of the second suspension, and a support plane is formed by four supporting legs, which is convenient for the stable placement of the aircraft during landing.

A further technical solution is that both the first suspension and the second suspension are made of carbon fiber material.

In this technical solution, because the carbon fiber material has a quality lighter than metal aluminum, but its strength is higher than that of steel, the quality of the first suspension and the second suspension is reduced to reduce the overall weight of the aircraft. The load is reduced and the battery life is increased.

A further technical solution is that the protective cover is hemispherical.

In the technical solution, the protective cover can be set to fly in rainy or humid weather so as to protect the airborne electronic equipment. By setting the protective cover into a hemispherical shape, the wind resistance is reduced, so that the aircraft is less affected by the wind.

A further technical solution is that the GPS is connected with the protective cover through a support frame.

In the technical solution, the GPS is connected to the protective cover through the support frame, thereby increasing the height of the GPS and reducing the influence of the magnetic field on it.

A further technical solution is that the hydrogen fuel cell includes a power supply module, and the power supply module is composed of a battery protection module, a lithium polymer battery, a 5v power supply module, a 12v power supply module and a 28v power supply module electrically connected to each other.

In this technical solution, lithium polymer batteries are provided, which can be used as auxiliary power output under high current conditions.

Compared with the prior art, the beneficial effects of the utility model are:

The utility model is not only easy to carry, has stable flight, high degree of full automation, low noise, and can work in the field environment, but also has super long battery life, and can work in the air for a long time. In power line inspection, emergency rescue, disaster relief survey and other work, ground personnel can obtain aerial perspective images, improve work efficiency and reduce costs.

Description of drawings

Fig. 1 is a schematic structural view of a quadrotor unmanned aerial vehicle according to an embodiment of the present invention.

As shown in Figure 1, the names of the corresponding reference signs are:

1 propeller, 2 first suspension, 3 hydrogen fuel cell, 4 support tripod, 5 second suspension, 6 support frame, 7 GPS, 8 protective cover.

Fig. 2 is a schematic structural diagram of the power supply part of the quadrotor unmanned aerial vehicle according to an embodiment of the present invention.

As shown in Figure 2, the names of the corresponding reference signs are:

31 lithium polymer electromagnetic, 32 5V power supply module, 33 12V power supply module, 34 28V power supply module, 35 battery protection module.

Detailed ways

Below in conjunction with accompanying drawing, the utility model is further elaborated.

A kind of quadrotor unmanned aerial vehicle as shown in Figure 1, it is made up of " cross " shape suspension body, motor, propeller 1, GPS7 and protective cover 8 that first suspension 2 and second suspension 5 form, in A protective cover 8 is provided above the intersecting position of the first suspension 2 and the second suspension 5, and the edge of the protective cover 8 is provided with a GPS7, and at both ends of the first suspension 2 and the second suspension 5 Motors are respectively connected, and the output shaft of the motor is connected with a propeller 1, and a hydrogen fuel cell 3 is connected below the intersection position of the first suspension 2 and the second suspension 5, and the hydrogen fuel cell 3 adopts a suspended The method is installed below the intersection position of the first suspension 2 and the second suspension 5. By adopting the installation method of suspension, the center of gravity of the aircraft is lowered and the wind resistance is improved. The hydrogen fuel cell 3 is electrically connected with the motor. The hydrogen fuel cell 3 is used to provide power for the rotation of the motor. Since the hydrogen fuel cell 3 has a large electric capacity, the working time of the motor is prolonged, thereby increasing the cruising time of the aircraft.

According to an embodiment of the utility model, the two ends of the first suspension 2 are provided with supporting legs 4, and the two ends of the second suspension 5 are provided with supporting legs 4, and there are four supporting legs 4, They are arranged at the two ends of the first suspension 2 and the second suspension 5 respectively, and the specific position of the supporting foot 4 is on the first suspension 2 or the second suspension 5 close to the motor.

According to an embodiment of the present utility model, the first suspension 2 and the second suspension 5 are tubes with a hollow inside, and are made of carbon fiber material. By using the first suspension 2 and the second suspension 5 as It is made of structure and materials, thereby reducing the overall weight of the aircraft, thereby improving the endurance time of the aircraft.

According to an embodiment of the present utility model, described protective cover 8 is hemispherical, has reduced the air resistance in the flight process by hemispherical shape, and described GPS7 is connected with protective cover 8 through support frame 6, and GPS7 adopts above-mentioned structure from using The height of the GPS7 setting is increased to avoid the influence of the electromagnetic field on the GPS7.

As shown in Figure 2, the power supply structure of a four-rotor unmanned aerial vehicle, the hydrogen fuel cell 3 includes a power supply module, and the power supply module is composed of a battery protection module 35 and a lithium polymer battery 31 electrically connected to each other. , 5v power supply module 32, 12v power supply module 33 and 28v power supply module 34 components.

Its function is to avoid insufficient output current of the hydrogen fuel cell 3 when the unmanned aerial vehicle performs high-power maneuvers. Therefore, the lithium polymer battery 31 is used as a part, and the power module uses lithium polymer as appropriate according to the current demand of the electrical device. The battery 31 serves as a compensating power source.

References in this specification to "one embodiment", "another embodiment", "embodiment", etc. refer to the specific features, structures or characteristics described in conjunction with the embodiment included in the general description of this application. In at least one embodiment of . The appearance of the same expression in multiple places in the specification does not necessarily refer to the same embodiment. Furthermore, when a specific feature, structure or characteristic is described in combination with any embodiment, it should be claimed that realizing such feature, structure or characteristic in combination with other embodiments also falls within the scope of the present invention.

Although the utility model has been described herein with reference to a number of illustrative embodiments of the utility model, it should be understood that those skilled in the art can devise many other modifications and implementations which will fall within the scope of this application. within the scope and spirit of the principles disclosed. More specifically, within the scope of the disclosure, drawings and claims of the present application, various modifications and improvements can be made to the components and/or layout of the subject combination layout. In addition to modifications and improvements in component parts and/or layout, other uses will be apparent to those skilled in the art.

Claims (8)

1. A four-rotor unmanned aerial vehicle, which is composed of a "cross"-shaped suspension body, a motor, a propeller (1), a GPS (7) and a protection Cover (8), a protective cover (8) is provided above the intersection position of the first suspension (2) and the second suspension (5), and a GPS (7) is provided on the edge of the protective cover (8) , motors are respectively connected to both ends of the first suspension (2) and the second suspension (5), and the output shaft of the motor is connected to a propeller (1), characterized in that: A hydrogen fuel cell (3) is connected below the intersecting position of the frame (2) and the second suspension (5), and the hydrogen fuel cell (3) is electrically connected with the motor. 2. The four-rotor unmanned aerial vehicle according to claim 1, characterized in that the hydrogen fuel cell (3) is mounted on the intersecting position of the first suspension (2) and the second suspension (5) in a suspended manner. below. 3. The quadrotor unmanned aerial vehicle according to claim 1 or 2, characterized in that two ends of the first suspension (2) are provided with supporting legs (4). 4. The quadrotor unmanned aerial vehicle according to claim 1 or 2, characterized in that two ends of the second suspension (5) are provided with supporting legs (4). 5. The quadrotor unmanned aerial vehicle according to claim 1, characterized in that the first suspension (2) and the second suspension (5) are made of carbon fiber material. 6. The quadrotor unmanned aerial vehicle according to claim 1, characterized in that the protective cover (8) is hemispherical. 7. The quadrotor unmanned aerial vehicle according to claim 1, characterized in that the GPS (7) is connected to the protective cover (8) through a support frame (6). 8. The four-rotor unmanned aerial vehicle according to claim 1, characterized in that the hydrogen fuel cell (3) includes a power supply module, and the power supply module is composed of a battery protection module (35) electrically connected to each other, lithium It consists of a polymer battery (31), a 5v power supply module (32), a 12v power supply module (33) and a 28v power supply module (34).