CN105905274B - The airframe structure of eight rotor wing unmanned aerial vehicles - Google Patents

Abstract

The invention relates to a fuselage structure of an eight-rotor UAV, including a body, a flight control compartment, a battery compartment, an umbrella compartment, several foldable arms, a landing gear, several propellers and a power device for driving the propellers to rotate , the foldable arm and the body can rotate relatively, the foldable arm is connected to the body through a reinforced vertical plate and a carbon fiber card, and the outer end of each foldable arm is connected to two propellers, the flight control The compartment, the battery compartment, and the umbrella compartment are respectively located in the body, and the foldable arm is provided with a pneumatic cooling port. The connectors used on the body are all connected by carbon fiber cards, so as to ensure the strength and avoid metal connections as much as possible. interference with the on-board magnetic compass. The present invention can be used as a fuselage structure of a large-load eight-rotor UAV that is convenient to use and transport. The fuselage uses as few metal connectors as possible, and at the same time, the electronic governor that needs heat dissipation is arranged between the inlet and the outlet. In the air duct.

Description

The fuselage structure of the eight-rotor UAV

technical field

The invention relates to an unmanned aerial vehicle, in particular to a fuselage structure of an eight-rotor unmanned aerial vehicle.

Background technique

Due to the strength and rigidity requirements of the usual large-load drones, in order to facilitate transportation, the arm is disassembled to reduce the space occupied during transportation, and it takes a long time to assemble each flight; at the same time, most drones Carbon fiber board is used as the structural material, and metal materials such as screws and copper columns are used for the connectors, which may easily affect the electromagnetic environment for the operation of airborne electronic equipment; traditional UAVs usually have an external electronic governor for heat dissipation, and use the propeller's downwash The airflow dissipates heat to the electronic governor, and the external placement of wires and electronic equipment has brought some reliability problems, and it also affects the aerodynamic shape of the drone.

Contents of the invention

The purpose of the present invention is to provide a fuselage structure of a large-load eight-rotor UAV that is convenient to use and transport. The fuselage uses as few metal connectors as possible, and at the same time, the electronic governor that needs to dissipate heat is arranged between the inlet and the in the duct between the outlets.

In order to achieve the above object, the present invention has the following technical solutions:

The fuselage structure of an eight-rotor unmanned aerial vehicle of the present invention includes a body, a flight control compartment, a battery compartment, an umbrella compartment, several foldable arms, a landing gear, several propellers and a power device for driving the propellers to rotate , the foldable arm and the body can rotate relatively, the foldable arm is connected to the body through a reinforced vertical plate and a carbon fiber card, and the outer end of each foldable arm is connected to two propellers, the flight control The compartment, the battery compartment and the umbrella compartment are respectively located in the body, and the foldable arm is provided with a pneumatic cooling port, and the connectors used on the body are all connected by carbon fiber cards, so as to ensure the strength and avoid metal connections as much as possible interference with the on-board magnetic compass.

Wherein, the aerodynamic cooling vent includes the inlet of the aerodynamic cooling vent and the outlet of the aerodynamic cooling vent. The speed device is arranged in the air duct between the inlet of the aerodynamic cooling port and the outlet of the aerodynamic cooling port.

Wherein, the propeller is installed on the upper and lower sides of the outer end of the foldable arm.

Wherein, the flight control cabin is arranged behind the center of the body, and the flight control cabin has a flight control cabin cover with a quick-plug connector, no metal connectors, and can be airtight and dustproof.

Wherein, the umbrella compartment is arranged at the front of the center of the body, and the umbrella compartment is provided with a weight-reducing hole and a clamshell made of sandwich composite material.

Wherein, the battery compartment is located on two symmetrical front and rear sides of the body, and the battery compartment is provided with cooling holes and a cooling cover.

Owing to taking above technical scheme, the advantage of the present invention is:

The firm folding mechanism is convenient for use and transportation; the carbon fiber card connection improves the magnetic field environment and increases the reliability of the magnetic compass; it can recover the flow energy of the air flow and actively dissipate heat to improve the reliability of the device.

Description of drawings

Fig. 1 is the schematic diagram that machine arm of the present invention expands;

Fig. 2 is the schematic diagram that the arm of the present invention is folded;

Fig. 3 is the enlarged schematic diagram of the arm folding mechanism of the present invention to strengthen the vertical plate and the carbon fiber insert;

Fig. 4 is an enlarged schematic view of the inlet of the pneumatic cooling vent of the present invention.

Fig. 5 is an enlarged schematic diagram of the outlet of the pneumatic cooling vent of the present invention.

Fig. 6 is an enlarged schematic diagram of the quick-plug interface of the flight control cabin cover of the present invention.

In the figure: 1. Body; 2. Flight control compartment; 3. Battery compartment; 4. Umbrella compartment; 5. Foldable arm; 6. Landing gear; 7. Propeller; 8. Reinforced vertical plate; 9. Carbon fiber card; 10. The inlet of the pneumatic cooling port; 11. The outlet of the pneumatic cooling port; 12. The quick-plug connector; 13. The cover plate.

Detailed ways

The following examples are used to illustrate the present invention and uses thereof, but are not intended to limit the protection scope of the present invention.

Referring to Fig. 1-Fig. 6, the fuselage structure of an eight-rotor UAV of the present invention includes a body, a flight control compartment, a battery compartment, an umbrella compartment, several foldable arms, a landing gear, several propellers and a drive The power device for the rotation of the propeller, the foldable arm and the body can rotate relatively, the foldable arm is connected to the body through a reinforced vertical plate and a carbon fiber card, and the outer end of each foldable arm is connected to two a propeller, the flight control compartment, the battery compartment and the umbrella compartment are respectively located in the body, and the foldable arm is provided with an aerodynamic cooling port; the connectors used on the body are all connected by carbon fiber cards to ensure While improving the strength, try to avoid the interference of metal connectors on the airborne magnetic compass.

The aerodynamic radiating vent includes the inlet of the aerodynamic radiating vent and the outlet of the aerodynamic radiating vent, and the inlet and outlet of the aerodynamic radiating vent are arranged front and back on the foldable arm according to the flow direction of the vortex generated by the propeller. It is arranged in the air duct between the inlet of the aerodynamic cooling vent and the outlet of the aerodynamic cooling vent.

The propeller is installed on the upper and lower sides of the outer end of the foldable arm.

The flight control cabin is arranged behind the center of the body, and the flight control cabin has a flight control cabin cover plate with a quick-plug connector, no metal connectors, and can be airtight and dustproof.

The umbrella compartment is arranged at the front of the center of the body, and the umbrella compartment is provided with a weight-reducing hole and a clamshell made of sandwich composite material.

The battery compartment is located on both sides symmetrically front and rear of the body, and has cooling holes and a cooling cover on the battery compartment.

Carbon fiber card connection method: Traditional UAV carbon fiber board connections are usually glued or screwed. The former is prone to cracking under the fatigue stress of the aircraft during flight, while the latter generates interference magnetic fields. The carbon fiber card connection structure is to cut a reserved slot on the carbon fiber board to be connected before assembly, and insert the carbon fiber card after assembly to form an interference fit. This connection structure has been verified by a large number of flight experiments, and it has been proved to be strong, reliable and effective.

The reinforced vertical board is spliced by a plurality of independent reinforced vertical boards, and each independent reinforced vertical board is provided with two protrusions on the top and bottom, and a slot is provided in the protrusion, and the protrusions on the top and The protrusions at the bottom are respectively inserted into the upper and lower plates of the body, and then the carbon fiber cards are inserted into the slots to connect the reinforced vertical plate with the body; the two sides of the reinforced vertical plate are provided with rectangular protrusions and grooves, and two adjacent When the reinforced vertical plate is connected, it is connected by a rectangular protrusion and a groove, and the reinforced vertical plate is connected with the foldable machine arm by inserting the groove on the reinforced vertical plate with the protruding rib on the foldable machine arm.

Quick-plug connector cover of the flight control cabin: The flight control cabin of the UAV is usually airtight for dust and static prevention. The traditional UAV cabin cover is usually fixed with screws and other metal parts, which is troublesome to disassemble and easy to produce. magnetic interference. The quick-plug joint of the present invention utilizes the tenacious and deformable characteristics of carbon fiber materials, without any metal material, to realize disassembly and assembly of the flight control hatch cover conveniently and durablely.

As shown in Figure 6, the quick-insert joint includes two insert arms, insert arm seats, and a fixed frame. There is a notch on the insert arm, and the fixed frame is fixed on the body. When installing, insert the insert arm For the fixed frame, use the notch of the plug arm to press the cover of the flight control compartment, and the plug arm seat is fixed on one side of the fixed frame to form a stable plug structure.

Claims (6)

1. A fuselage structure of an eight-rotor unmanned aerial vehicle, characterized in that: comprising a body, a flight control compartment, a battery compartment, an umbrella compartment, several foldable arms, an undercarriage, several propellers and driving the propellers to rotate The power device, the landing gear is connected to the bottom of the body, the power device is connected to the battery in the battery compartment, the foldable arm and the body can rotate relatively, and the foldable arm and the body are strengthened by a vertical plate It is connected with a carbon fiber card, and the outer end of each foldable arm is connected to two propellers. The flight control compartment, battery compartment, and umbrella compartment are respectively arranged in the body, and the foldable arm is provided with a pneumatic cooling port. , the connectors used on the body are all connected by carbon fiber cards to ensure the strength while avoiding the interference of the metal connectors on the airborne magnetic compass; The reinforced vertical board is spliced by a plurality of independent reinforced vertical boards, and each independent reinforced vertical board is provided with two protrusions on the top and bottom, and a slot is provided in the protrusion, and the protrusions on the top and The protrusions at the bottom are respectively inserted into the upper and lower plates of the body, and then the carbon fiber cards are inserted into the slots to connect the reinforced vertical plate with the body; the two sides of the reinforced vertical plate are provided with rectangular protrusions and grooves, and two adjacent The reinforced vertical plate is connected through rectangular protrusions and grooves, and the reinforced vertical plate is connected to the foldable machine arm through the groove on the reinforced vertical plate and the raised rib on the foldable machine arm; The flight control cabin is provided with a cover plate of the quick-plug connector on the flight control cabin. The quick-plug connector includes two insert arms, insert arm seats, and a fixed frame. The insert arm is provided with a notch, and the fixed frame Fixed on the body, when installing, insert the insert arm into the fixed frame, use the notch to press the cover of the flight control compartment, and the insert arm seat is fixed on one side of the fixed frame to form a stable insertion structure. 2. The fuselage structure of an eight-rotor UAV as claimed in claim 1, wherein the aerodynamic heat dissipation port includes an aerodynamic heat dissipation port inlet and an aerodynamic heat dissipation port outlet, and the aerodynamic heat dissipation port inlet and aerodynamic heat dissipation port The mouth and outlet are arranged front and back on the foldable arm according to the flow direction of the vortex generated by the propeller, and the electronic governor that needs to dissipate heat is arranged in the air duct between the inlet of the aerodynamic heat dissipation port and the outlet of the aerodynamic heat dissipation port. 3. The fuselage structure of an eight-rotor UAV as claimed in claim 1, wherein the propeller is installed on the upper and lower sides of the outer end of the foldable arm. 4. The fuselage structure of an eight-rotor UAV as claimed in claim 1, wherein the flight control cabin is located behind the center of the fuselage, and the flight control cabin is equipped with a flight control unit with a quick-plug connector. The warehouse cover has no metal connectors and can be airtight and dustproof. 5. The fuselage structure of an eight-rotor UAV as claimed in claim 1, characterized in that: the umbrella compartment is arranged in front of the center of the fuselage, and the umbrella compartment is provided with a weight-reducing hole and a sandwich compound Material flap. 6. The fuselage structure of an eight-rotor UAV as claimed in claim 1, wherein the battery compartment is located on both sides of the front and rear symmetry of the fuselage, and the battery compartment is provided with a heat dissipation hole and a heat dissipation cover plate .