All-moving foldable high-lift wing for multi-rotor aircraft

Abstract

The invention discloses a full-motion foldable high lift wing for a multi-rotor aircraft, which comprises a rotor power device and a fuselage for mounting airborne equipment and connecting the rotor power device, and further comprises a pair of independent controllable high lift wings, the high-lift wings are mounted on the fuselage; when the full-moving foldable high-lift wing for the multi-rotor aircraft flies, a flight control algorithm controls the tilting angle of the high-lift wing according to the attitude and the flight speed of the aircraft, so that the high-lift wing is in a proper attack angle state, and proper lift force can be provided for the aircraft. The flying speed can be increased, the cruising ability is improved, and transportation and storage are convenient.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more specifically to a fully movable foldable lift-enhancing wing for multi-rotor aircraft. Background Technology

[0002] Existing multirotor aircraft rely on the thrust generated by the rotor to overcome gravity and provide flight propulsion. During flight, the rotor must consistently provide a vertical component of the force to overcome gravity, consuming a significant portion of the multirotor's energy. Furthermore, because the rotor thrust is primarily used to overcome gravity, the available power for flight is relatively insufficient, resulting in slow flight speeds. Existing multirotor aircraft are also limited by battery technology and power source, leading to short endurance and slow speeds. Existing wing moment control relies on ailerons, flaps, and other mechanisms, requiring additional hinges and control surfaces on the wing, increasing structural complexity and weight.

[0003] Therefore, a fully movable foldable lift-enhancing wing for multi-rotor aircraft is proposed, which can improve flight speed, enhance endurance, and facilitate transportation and storage. Summary of the Invention

[0004] In view of the technical problems existing in the background art, the present invention provides a fully movable foldable lift-enhancing wing for multi-rotor aircraft that can improve flight speed, enhance endurance, and facilitate transportation and storage. To achieve the above objectives, the present invention provides the following technical solution: A fully movable foldable lift-enhancing wing for a multi-rotor aircraft, the fully movable foldable lift-enhancing wing comprising two foldable wings; the two foldable wings are symmetrically mounted on both sides of the multi-rotor aircraft; each foldable wing includes a servo mechanism and a wing, the servo mechanism being mounted on the multi-rotor aircraft; The wing includes a wing body and a wing adapter; the wing adapter is connected to a servo mechanism, and a wing latch is installed on the wing adapter; the wing body and the wing adapter are connected by a wing hinge. When the wing body is deployed, the wing body rotates around the wing hinge until it is parallel to the wing adapter. The wing latch locks the wing body. During flight, the wing is driven by the servo mechanism to change the tilt angle according to the flight speed and attitude, providing lift and torque for the multi-rotor aircraft.

[0005] Preferably, the servo mechanism includes a servo motor, a coupling, a bearing, and a bearing housing; the servo motor and the bearing housing are both fixedly mounted on the multi-rotor aircraft, and the servo disk on the servo motor is fixedly connected to the coupling; the bearing is mounted on the bearing housing; the wing adapter is fixedly connected to the coupling through the wing shaft passing through the bearing.

[0006] There are two wing hinges and two wing latches.

[0007] When an aircraft is in flight, adjusting the angle of attack of the lift-enhancing wings to a suitable angle can provide lift, reduce energy consumption, and increase range. Simultaneously, the lift provided by the lift-enhancing wings overcomes some of the gravity, allowing more rotor thrust to be distributed in the horizontal direction, thereby increasing the aircraft's speed. Aircraft equipped with foldable lift-enhancing wings possess both the vertical takeoff and landing and hovering capabilities of rotorcraft and the high-speed cruise capabilities of fixed-wing aircraft.

[0008] The wing as a whole can rotate in a vector direction, enabling full-motion control of the wing. It has no ailerons, flaps, or other control surfaces, and no complex control mechanisms, which can effectively reduce weight and aerodynamic drag.

[0009] The beneficial effects of this invention are: 1. The flight control program of the multi-rotor aircraft controls the lift-enhancing wings to rotate to a suitable angle according to the flight speed and the aircraft attitude, so as to provide lift and roll torque for the aircraft, thereby reducing flight energy consumption, increasing endurance, and providing redundant control torque, which improves the maximum flight speed of the multi-rotor platform; 2. The wings can rotate as a whole, and the lift of the wings can be controlled by individually controlling the angle of attack of the wings. At the same time, the wings can provide additional lateral and longitudinal stability, making the fuselage less prone to swaying, especially when the wind speed fluctuates. 3. Foldable lift-enhancing wings can fold the wing body to fit snugly against the fuselage, allowing the folded multi-rotor aircraft to be stored in narrow spaces, facilitating storage and transportation; 4. The airfoil adopts a self-developed high lift-to-drag ratio airfoil, which has good aerodynamic characteristics. Attached Figure Description

[0010] Figure 1 This is a schematic diagram of the structure of the fully movable foldable lift-enhancing wing of the present invention; Figure 2 This is a schematic diagram of the installation of a fully movable foldable lift-enhancing wing on a multi-rotor aircraft. Figure 3 This is a schematic diagram of the installation of the servo mechanism in this invention; Figure 4 This is a schematic diagram of a multi-rotor aircraft (in flight mode). Figure 5 This is a structural diagram of a multi-rotor aircraft (folded). Figure 6 A structural schematic diagram of the airfoil used for the cross-section of an all-moving, foldable, lift-enhancing airfoil; Figure 7 Flow distribution diagram on the surface of a fully movable, foldable, lift-enhancing wing; Figure 8 This is a lift distribution diagram for a fully movable, foldable, height-enhancing wing. Figure 9A wing modeled for the traditional low-speed airfoil NACA 4412; In the diagram, 1-foldable lift-enhancing wing, 11-servo mechanism, 111-servo motor, 1111-servo disc, 112-coupling, 113-bearing, 114-bearing housing, 12-wing, 121-wing adapter, 1211-wing shaft, 122-lock, 123-wing hinge, 124-wing body, 2-quadcopter. Detailed Implementation

[0011] Combination Figures 1-9 The present invention provides an all-moving foldable lift-enhancing wing for a multi-rotor aircraft, which is mounted on the multi-rotor aircraft to provide aerodynamic force and torque during flight. In this embodiment, the foldable lift-enhancing wing 1 is mounted on a quadcopter 2.

[0012] The foldable lift-enhancing wing 1 includes a servo mechanism 11 and a wing 12. The servo mechanism 11 is mounted on the quadcopter 2, and the wing 12 is connected to the servo mechanism 11. The servo mechanism 11 includes a servo motor 111, a coupling 112, a bearing 113, and a bearing housing 114. The servo motor 111 is fixedly mounted on the fuselage of the quadcopter 2. The servo disc 1111 on the servo motor 111 is fixedly connected to the coupling 112. The bearing housing 114 is fixedly mounted on the fuselage of the quadcopter 2, and the bearing 113 is mounted on the bearing housing 114.

[0013] The wing 12 includes a wing adapter 121, a latch 122, a hinge 123, and a wing body 124. The wing adapter 121 is fixed to the coupling 112 through the wing shaft 1211 passing through the bearing 113. The wing adapter 121 is connected to the wing body 124 through the hinge 123.

[0014] Servo motor 111 drives wing 12 to rotate. By controlling the wing's angle of attack, the lift of the wing is controlled. Other drones increase lift by adjusting the propeller pitch, which essentially means trading power for higher energy consumption. However, increasing lift through the wing is achieved through aerodynamics, without increasing energy consumption too much. On the other hand, the wing can provide additional lateral and longitudinal stability, especially when the wind speed fluctuates, making the fuselage less prone to swaying. Adjusting the propeller pitch, on the other hand, relies more on motor correction, which can easily cause the drone to experience slight turbulence in complex airflow.

[0015] Hinges 123 are installed below the wing adapter 121 and the wing body 124. The wing body 124 can rotate around the hinges 123. When the foldable wing 1 is unfolded, the wing body 124 rotates around the hinges 123 until it is horizontal with the wing adapter 121 and the latches 122 are fastened. To ensure the overall strength of the foldable wing, there are two hinges 123 and two latches 122. By unlocking the latches 122 and rotating the wing body 124 around the hinges 123 until it is nearly perpendicular to the wing adapter 121, the foldable wing 1 can be in a folded state. Please see Figure 3 , Figure 4 When the pair of symmetrically mounted foldable wings 1 on the quadcopter 2 are deployed, the tilt angle of the foldable wings 1 is controlled according to the flight speed and attitude during flight, so as to provide aerodynamic lift and torque for the quadcopter 2. Please see Figure 5 When the pair of symmetrically mounted foldable wings 1 on the quadcopter 2 are folded, the quadcopter 2 becomes long and narrow, which is convenient for storage and transportation.

[0016] Please see Figure 6 The wing is made using a self-developed airfoil; the surface flow distribution of the self-developed wing is shown in [the image / description]. Figure 7 The wings possess excellent dynamic performance. Figure 8 It is evident that the lift distribution of the wing is elliptical, exhibiting excellent pressure distribution characteristics, compared to the wing modeled by the traditional low-speed airfoil naca4412 (see...). Figure 9 With the same lift, the lift-to-drag ratio is increased by 30.65%.

[0017] like Figures 1-9 As shown, the working principle and process of this invention are as follows: When the foldable wing 1 is unfolded, the wing body 124 rotates around the hinge 123 until it is level with the wing adapter 121 and the latch 122 is fastened, ready for flight.

[0018] When the latch 122 is released and the wing body 124 is rotated around the hinge 123 until it is nearly perpendicular to the wing adapter 121, the foldable wing 1 can be put into a folded state. like Figure 4 As shown, during flight, the tilt angle of the foldable wing 1 is controlled according to the flight speed and attitude to provide aerodynamic lift and torque for the quadcopter 2.

Claims

1. A fully movable, foldable, lift-enhancing wing for a multi-rotor aircraft, characterized in that: The fully movable foldable lift-enhancing wing consists of two foldable wings; the two foldable wings are symmetrically mounted on both sides of the multi-rotor aircraft; each foldable wing includes a servo mechanism and a wing, and the servo mechanism is mounted on the multi-rotor aircraft. The wing includes a wing body and a wing adapter; the wing adapter is connected to a servo mechanism, and a wing latch is installed on the wing adapter; the wing body and the wing adapter are connected by a wing hinge. When the wing body is deployed, it rotates around the wing hinge until it is parallel to the wing adapter. The wing latch locks the wing body. During flight, the wing is driven by a servo mechanism to change its tilt angle according to the flight speed and attitude, providing lift and torque for the multi-rotor aircraft.

2. The all-moving foldable lift-enhancing wing for a multi-rotor aircraft according to claim 1, characterized in that: The servo mechanism includes a servo motor, a coupling, a bearing, and a bearing housing; the servo motor and the bearing housing are both fixedly mounted on the multi-rotor aircraft, and the servo disk on the servo motor is fixedly connected to the coupling; the bearing is mounted on the bearing housing; the wing adapter is fixedly connected to the coupling through the wing shaft passing through the bearing.

3. The all-moving foldable lift-enhancing wing for a multi-rotor aircraft according to claim 2, characterized in that: There are two wing hinges and two wing latches.

Images