A foldable quadrotor unmanned aerial vehicle combining the characteristics of multi-rotor and fixed-wing

Abstract

This utility model discloses a foldable quadcopter drone combining the characteristics of multi-rotor and fixed-wing aircraft, relating to the field of drone technology. The key technical features are: the drone adopts a design that integrates quadcopter arms and main wings, and is equipped with swastika-shaped folding canard rudders. Through differential coordinated control of the canard rudders and motors, the drone can achieve level flight / hovering modes with overall tilting during flight, providing diverse mission capabilities. The device combines the advantages of multi-rotor and fixed-wing aircraft, enabling level flight and hovering without additional power unit dead weight. Furthermore, its folding mechanism ensures launch compatibility, adapting to tube-launch requirements and improving deployment flexibility.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to a foldable quadcopter UAV that combines the characteristics of multi-rotor and fixed-wing. Background Technology

[0002] Traditional multi-rotor drones suffer from slow flight speed and short range, while fixed-wing drones require runways or catapults; conventional compound-wing drones are difficult to fold to adapt to cannon firing requirements, and the rotor power kit is dead weight during level flight, providing no value.

[0003] It is evident that existing technologies lack unmanned aerial vehicle (UAV) systems that can achieve high-speed horizontal flight, vertical take-off and landing, hovering flight, and are suitable for tube-launch. Utility Model Content

[0004] The purpose of this invention is to provide a foldable quadcopter drone that combines the characteristics of multi-rotor and fixed-wing drones to solve the aforementioned technical problems.

[0005] The above-mentioned technical objective of this utility model is achieved through the following technical solution: a foldable quadcopter drone that combines the characteristics of multi-rotor and fixed-wing, wherein the main body of the drone adopts a quadcopter as the basic power mode, and the fuselage is formed by extending from the center of the quadcopter along the power axis direction. The fuselage is connected to four arms, and the four arms are equipped with main wings.

[0006] The present invention is further configured such that: the fuselage is divided into two sections according to the arrangement of the equipment, namely the nose section and the fuselage section;

[0007] The nose section is used to install and carry various airborne equipment and is equipped with canard rudders on the outside.

[0008] The fuselage compartment is mainly used to carry equipment including batteries, data link antennas, and GNSS antennas.

[0009] The fuselage compartment is equipped with a metal mounting frame at the rear, which is connected to a wing folding mechanism. The wing folding mechanism is connected to a main wing, and a power unit is installed in the middle section of each main wing.

[0010] The present invention is further configured such that: the skin of the nose section is a large opening, and the nose section is equipped with equipment including mission payload, data link, flight control computer, and servo motors.

[0011] The present invention is further configured such that the power equipment includes a motor and an ESC, and the wiring runs from inside the main wing, bypasses the wing folding mechanism, and enters the fuselage.

[0012] The present invention is further configured such that: the canard rudder is located on the outside of the nose section skin and is integrated with the skin when there is no rudder movement; the canard rudder is connected to a rudder hinge, and the rudder hinge is connected to a servo motor; the servo motor shaft is coaxial with the canard rudder surface shaft.

[0013] In summary, this utility model has the following beneficial effects:

[0014] This invention employs a quadcopter arm integrated with the main wing, and is equipped with a swastika-shaped folding canard rudder. Through differential coordinated control of the canard rudder and motors, the UAV can achieve level flight / hovering modes with overall tilting during flight, providing diverse mission capabilities through dual-mode flight. The device combines the advantages of multi-rotor and fixed-wing systems, enabling level flight and hovering without the dead weight of an additional power unit.

[0015] Furthermore, its folding mechanism ensures launch compatibility, adapts to tube-type launch requirements, and improves deployment flexibility.

[0016] The device adopts a modular design, which facilitates subsequent maintenance and upgrades. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the folded state of the drone in this embodiment of the utility model;

[0018] Figure 2 This is a schematic diagram of the UAV in the deployed state in an embodiment of this utility model;

[0019] Figure 3 This is a structural diagram of the internal structure of the fuselage in an embodiment of this utility model;

[0020] Figure 4 This is a detailed drawing of the wing folding mechanism in an embodiment of this utility model;

[0021] Figure 5 This is a detailed drawing of the canard rudder folding mechanism in an embodiment of this utility model.

[0022] In the diagram: 1. Canard rudder; 101. Control surface; 2. Fuselage; 201. Nose compartment; 202. Fuselage compartment; 3. Arm; 4. Power plant; 5. Main wing; 6. Skin; 7. Wing folding structure; 8. Metal mounting frame; 9. Servo; 10. Rudder hinge. Detailed Implementation

[0023] The following is in conjunction with the appendix Figure 1-5 The present invention will be described in further detail below.

[0024] Example: A foldable quadcopter drone combining the characteristics of multi-rotor and fixed-wing aircraft, such as... Figure 1-5As shown, the main body of the unmanned aerial vehicle adopts four rotors as the basic power configuration. A fuselage extends from the center of the four rotors along the direction of the power axis, the fuselage is connected with four arms, and main wings are arranged on the four arms.

[0025] The fuselage is divided into two sections according to the arrangement of equipment, namely a nose section and a fuselage section; the nose section is configured to mount and carry various airborne equipment, and canard control surfaces are mounted on the outside of the nose section. The canard control surfaces are located outside the skin of the nose section, and are integrated with the skin when there is no control deflection; the canard control surfaces are connected to control hinges, which are connected to steering gears; the steering gear shaft is coaxial with the control surface shaft of the canard control surface.

[0026] The fuselage section is mainly configured to carry equipment including batteries, data link antennas and GNSS antennas; a metal mounting frame is arranged at the tail of the fuselage section, the metal mounting frame is connected with a main wing folding mechanism, the main wing folding mechanism is connected with the main wings, and a power device is installed in the middle section of each main wing. The power device comprises a motor and an electronic speed controller, and wiring is routed from the inside of the main wing, bypasses the wing folding mechanism and enters the fuselage.

[0027] The skin of the nose section is a large hatch, and equipment including mission payload, data link, flight control computer and steering gear is installed inside the nose section.

[0028] The nose section supports overall refitting after integration with the mission payload and airborne equipment.

[0029] The folding process of the main wings in the above unmanned aerial vehicle is as follows: the main wings fold 90° backward around the root axis, and are restrained by the wall of the launch tube, and automatically unfold and lock after exiting the tube. An elastic unfolding actuation mechanism with a torsion spring and a locking pin is arranged at the root rotating shaft.

[0030] The folding process of the canard control surfaces is as follows: the canard control surfaces fold in a "卍" shape around the chordwise axis near the root, and are restrained by the tube wall, and automatically unfold and lock after exiting the tube. The canard control surface skin has a streamlined spindle-shaped bulge at the folding axis, which can accommodate a folding actuation mechanism with a torsion spring and a locking pin.

[0031] Working principle: When the device is in use, the unmanned aerial vehicle is initially in a folded state, the tail is embedded into the piston, and the unmanned aerial vehicle and the piston are loaded together into a launch tube with a square cross-section. The gas generator provides the initial launch air pressure to push the piston, which in turn pushes the unmanned aerial vehicle, so that the unmanned aerial vehicle obtains kinetic energy and exits the tube. After exiting the tube, the canard control surfaces of the unmanned aerial vehicle get rid of the constraint of the tube wall, unfold and lock. The piston separates from the unmanned aerial vehicle under resistance. The main wings of the unmanned aerial vehicle get rid of the constraints of the tube wall and the piston, unfold and lock.

[0032] After launching, it enters the level flight mode: the fuselage pitches down, the canard control surfaces and the motors work in differential coordination to control and stabilize the aircraft attitude, after the power device is started, it accelerates with large throttle, and the unmanned aerial vehicle enters the level flight state.

[0033] When hovering is required: After gradually reducing the fuselage pitch angle to 90° at high speed, decelerate and switch to the quadcopter's conventional control mode.

[0034] This specific embodiment is merely an explanation of the present utility model and is not intended to limit the present utility model. After reading this specification, those skilled in the art can make modifications to this embodiment without contributing any inventive step, but as long as they are within the scope of the claims of the present utility model, they are protected by patent law.

Claims

1. A foldable quadcopter drone that combines the characteristics of both multi-copters and fixed-wing aircraft, characterized in that: The main body of the drone uses a quadcopter as its basic power source. The fuselage extends from the center of the quadcopter along the power axis, and the fuselage is connected to four arms, with main wings installed on the four arms.

2. The foldable quadcopter UAV combining the characteristics of multi-rotor and fixed-wing as described in claim 1, characterized in that: The fuselage is divided into two sections according to the arrangement of the equipment: the nose section and the fuselage section. The nose section is used to install and carry airborne equipment and is equipped with canard rudders on the outside. The fuselage compartment is mainly used to carry equipment including batteries, data link antennas, and GNSS antennas. The fuselage compartment is equipped with a metal mounting frame at the rear, which is connected to a wing folding mechanism. The wing folding mechanism is connected to a main wing, and a power unit is installed in the middle section of each main wing.

3. A foldable quadcopter UAV combining the characteristics of multi-rotor and fixed-wing as described in claim 2, characterized in that: The nose section is covered by a large hatch, and the nose section contains equipment including mission payloads, data links, flight control computers, and servos.

4. A foldable quadcopter UAV combining the characteristics of multi-rotor and fixed-wing as described in claim 2, characterized in that: The power unit includes a motor and an ESC, which are routed from inside the main wing, bypassing the wing folding mechanism, and into the fuselage.

5. A foldable quadcopter UAV combining the characteristics of multi-rotor and fixed-wing as described in claim 2, characterized in that: The canard rudder is located on the outside of the nose section skin and is integrated with the skin when there is no rudder movement; the canard rudder is connected to a rudder hinge, and the rudder hinge is connected to a servo motor; the axis of the servo motor is coaxial with the axis of the canard rudder surface.

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