A structure and method for generating lift

Abstract

The application discloses a structure for generating lift force, which comprises a shaft rotatably or fixedly installed on a machine body, one or more revolute bodies fixedly or rotatably installed on the shaft, and a power device for driving the revolute bodies to rotate around the shaft; and a rotary rotor is installed on the outer edge of the revolute body, and the rotary rotor rotates with the revolute body and generates lift force by windward rotation. The structure for generating lift force has the advantages of good aerodynamic performance, high lift force generation efficiency, vertical lift function, forced landing function and structure self-stabilization function.

Description

Technical Field

[0001] This invention relates to takeoff devices, and more particularly to a structure and method for generating lift. Background Technology

[0002] Existing aircraft include fixed-wing aircraft, helicopters, gyroplanes, rotorcraft, and light air vehicles.

[0003] The lift of a fixed-wing aircraft mainly comes from its wings. When the aircraft's engine fails, it will glide to make an emergency landing. However, fixed-wing aircraft generally need a runway to land, and runways are only available in a few fixed locations. Landing in other places increases the risk.

[0004] Helicopters generate lift from their rotating rotors. Compared to the rotors of autogyros, helicopters have lower aerodynamic efficiency and are more difficult to land without power.

[0005] Autogyros generate lift from their rotating rotors, but they need to have forward speed like airplanes to generate lift. Autogyros cannot take off and land vertically or fly vertically, which greatly limits their functions and applications.

[0006] Rotorcraft are generally multi-rotor aircraft with low lift generation efficiency and no ability to make forced landings. They rely on sensors, chips, and algorithms to maintain the self-stability of the aircraft. Once the sensors, chips, algorithms, motors, or rotors fail, it is extremely dangerous.

[0007] Light air vehicles are large and easily affected by atmospheric airflow. Summary of the Invention

[0008] The technical problem to be solved by the present invention is to provide a structure and method for generating lift, which has good aerodynamic performance, high lift generation efficiency, vertical lifting function, forced landing function and structural self-stabilization function.

[0009] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is as follows: A structure for generating lift includes a shaft rotatably mounted on a fuselage, with one or more orbiting bodies circumferentially fixed to the shaft; or, the shaft is fixedly mounted on the fuselage, with one or more orbiting bodies rotatably mounted to the shaft; a power unit drives the orbiting bodies to rotate about the axis of the shaft; a self-rotating rotor is mounted on the outer edge of the orbiting body, the self-rotating rotor revolves with the orbiting body and rotates in the wind to generate lift.

[0010] One or more rotating rotors are installed on the orbital body; when multiple rotating rotors are installed, the rotating rotors are symmetrically arranged on the rotation circumference of the outer edge of the orbital body.

[0011] The rotation direction of the self-rotating rotor is the same as the rotation direction of the orbiting body.

[0012] When the shaft is fixedly mounted on the fuselage, the power unit is an aviation or aerospace propulsion device, which is installed on the orbiting body to drive the orbiting body to rotate.

[0013] When the shaft is rotatably mounted on the machine body, the power unit is an engine. The engine is mounted on the machine body and transmits power to the shaft directly or through a mechanical transmission mechanism, driving the revolution body to rotate.

[0014] The autorotor adjusts the angle between its rotor disk and the revolution plane via a pitch adjustment device.

[0015] The pitch adjustment device is a servo motor, actuator, or actuator, which drives the electric autorotator to pitch.

[0016] The orbiting body and the eccentric rotor are provided with space for the blades of the eccentric rotor to flap.

[0017] A method to generate lift, 1) When the orbiting body rotates under the drive of the power unit, the autorotor on it revolves. When the pitch adjustment device is operated to make the rotor disk of the autorotor have a certain angle with the orbital plane, the autorotor rotates in the wind and generates lift. The magnitude of the lift can be controlled by adjusting the pitch angle of the power unit and the autorotor. 2) When the power unit fails, the entire device falls. The autorotor continues to rotate against the falling wind and generates lift. When the lift and drag are balanced, the aircraft descends at a constant speed. Furthermore, by adjusting the autorotor's rotor disk angle to a depression angle, the autorotor will drive the orbital body to rotate, thereby improving the aircraft's stability. When approaching the ground, the rotational energy of the orbital body can be converted into lift by adjusting the autorotor's rotor disk angle to a pitch angle, reducing the impact during landing. The entire process can achieve a vertical forced landing.

[0018] This invention provides a structure and method for generating lift, which has the following technical effects: 1) Compared with fixed-wing aircraft, this invention can realize the vertical take-off and landing and hovering functions of aircraft.

[0019] 2) Compared to helicopters, the autorotor used in this invention has better aerodynamic efficiency and is easier to make a forced landing without power.

[0020] 3) Compared with autogyros, this invention can achieve vertical take-off and landing and hovering of the aircraft, and the difficulty of unpowered forced landing is low. It can also achieve vertical forced landing, while the forced landing of autogyros requires a certain forward speed and forward flight distance; and it does not require a pre-spin mechanism, while autogyros are generally equipped with a pre-spin mechanism.

[0021] 4) Compared with the lift structure of rotorcraft, the present invention generates lift more efficiently, has excellent forced landing capability, and has the stabilizing characteristics of a gyroscope when the orbiting body rotates, thus achieving a simple and reliable attitude self-stabilization function.

[0022] 5) Compared with the lift structure of light air vehicles, the present invention has better wind resistance. Attached Figure Description

[0023] The present invention will be further described below with reference to the accompanying drawings and embodiments: Figure 1 This is a schematic diagram of the structure of the present invention.

[0024] Figure 2 This is a schematic diagram showing the tilt angle between the self-rotating rotor disk and the revolution plane of the present invention.

[0025] Figure 3 This is a schematic diagram of the self-rotating rotor disk of the present invention with no elevation angle to the revolution plane.

[0026] Figure 4 This is a schematic diagram illustrating the aerodynamic changes of the forward propeller blades of the self-rotating rotor when the incoming flow velocity changes in this invention.

[0027] Figure 5 This is a schematic diagram illustrating the aerodynamic changes of the backward propeller blades of the rotating rotor when the incoming flow velocity changes in this invention.

[0028] In the diagram: 1. Autorotor; 2. Turbojet engine; 3. Pitch adjustment device; 4. Revolutionary body; 5. Shaft. Detailed Implementation

[0029] like Figure 1 As shown, a structure and method for generating lift includes a shaft 5, which is rotatably mounted on the fuselage or other location of an aircraft. A circumferentially distributed orbital bodies 4 are mounted on the shaft 5, the number of which can be set according to actual needs. A turbojet engine 2 is mounted on each orbital body 4, driving the orbital body 4 to rotate. A spin rotor 1 is mounted on the outer edge of each orbital body 4; when the orbital body 4 rotates, the spin rotor 1 rotates against the wind, thereby generating lift. Figure 1 As shown, when viewed from above, the rotation direction of the orbital body 4 is clockwise. Therefore, the rotation direction of the autorotor 1 should also be clockwise, that is, the front end of the autorotor blade airfoil faces clockwise.

[0030] In addition, the autorotor 1 is mounted on the orbital body 4 via a pitch adjustment device 3. The pitch adjustment device 3 can control the angle between the rotor disk of the autorotor 1 and the orbital plane. The pitch adjustment device 3 uses an existing servo motor. The autorotor is fixed on the servo motor arm. When the servo motor is rotated, the servo motor arm rotates, and the angle between the rotor disk of the autorotor 1 and the orbital plane changes. At this time, the rotation axis is the output axis of the servo motor.

[0031] like Figure 1 As shown, the orbital body 4 should meet the needs of the rotor blades of the autorotor 1 to flap, and prevent the rotor blades of the autorotor 1 from colliding with the orbital body 4. This can be achieved by lowering the orbital body on the side closer to the shaft and raising it on the side closer to the autorotor; or by maintaining a suitable distance between the autorotor and the orbital body through a connecting piece.

[0032] like Figure 2-3 As shown, the ellipse (dashed line) in the figure represents the rotor disk angle of the autorotor 1. Figure 3 The disc of the autorotor 1 is aligned with the orbital plane. Figure 2 The autorotor 1 at point a tilts to the upper right, and the autorotor 1 at point b tilts to the upper left.

[0033] When the orbiting body 4 rotates under the drive of the turbojet engine 2, its autorotor 1 revolves. When the pitch adjustment device 3 is operated to make the rotor disk of the autorotor 1 have a certain angle with the orbital plane, such as... Figure 2-3 As shown, the autorotor 1 rotates against the wind and generates lift. The magnitude of the lift can be controlled by adjusting the throttle of the turbojet engine 2 and the pitch angle of the autorotor 1. The orbiting body 4 exhibits the stabilizing characteristics of a gyroscope during its rotation, thus achieving attitude self-stabilization.

[0034] The rotation direction of a spin rotor should be the same as the rotation direction of the orbiting body. A spin rotor that revolves is equivalent to a spin rotor in a ring-shaped airflow. Compared to a spin rotor in a straight airflow, the speed of the advancing blade increases and the speed of the retreating blade decreases.

[0035] Analyzing autorotors from the perspective of blade element theory, for the advancing blade, increasing the incoming flow velocity leads to a greater resultant velocity of the autorotation speed and the incoming flow velocity, as well as a larger angle of attack. This results in an increase in the aerodynamic resultant force dR and its angle with the rotor shaft, leading to increased lift and driving torque. Figure 4 As shown. Figure 4 In the figure, ΩR represents the rotor tip velocity in m / s; V represents the rotor tip velocity. 来流 : Incoming flow velocity; V 合1 V 合2 dL1, dL2: Lift; dD1, dD2: Drag; dR1, dR2: Resultant force of lift and drag (1 in the symbol indicates before the change, 2 indicates after the increase of the incoming flow speed).

[0036] For the retreating blade, when the incoming flow velocity decreases, the combined aerodynamic velocity increases while the angle of attack decreases. Therefore, the magnitude of the resultant aerodynamic force dR requires further analysis and calculation. The slope of the lift curve before airfoil stall is approximately a constant, with a value of about 0.1 / degree or 5.73 / radian. This is based on the blade element lift calculation formula. Where: d is the differential symbol, Let b be the air density, b be the airfoil chord length, and V be the airfoil density. 合 The velocity is the resultant velocity of the airfoil velocity and the incoming flow velocity. Let dL1 be the lift coefficient and R be the rotor radius. Calculations show that dL1 is greater than dL2. That is, the lift of the retreating blade increases, such as... Figure 5 As shown. Figure 5 In the figure, ΩR represents the rotor tip velocity in m / s; V represents the rotor tip velocity. 来流 : Incoming flow velocity; V 合1 V 合2 dL1, dL2: Lift; dD1, dD2: Drag; dR1, dR2: Resultant force of lift and drag (2 in the symbol indicates before the change, 1 indicates after the flow velocity is reduced).

[0037] If the rotation direction of the autorotor mounted on the orbiting body is opposite to the orbital direction, similarly, for the advancing blade, lift and driving torque decrease; for the retreating blade, lift decreases. Therefore, it is better to have the autorotor rotate in the same direction as the orbiting body.

[0038] In the event of a power plant failure, the aircraft descends. The autorotor continues to rotate against the descent winds, generating lift. Once lift and drag balance, the aircraft descends at a constant speed. Adjusting the autorotor's disk angle to a depression angle causes the autorotor to rotate the orbital body, thus improving stability. Upon approaching the ground, adjusting the autorotor's disk angle to a pitch angle converts the rotational energy of the orbital body into lift, reducing the impact upon landing. This entire process allows for a vertical forced landing.

Claims

1. A structure for generating lift, characterized in that: The device includes a shaft, which is rotatably mounted on the fuselage, and one or more orbiting bodies are circumferentially fixed on the shaft; or, the shaft is fixedly mounted on the fuselage, and one or more orbiting bodies are rotatably mounted on the shaft; a power unit drives the orbiting bodies to rotate around the axis of the shaft; a self-rotating rotor is installed on the outer edge of the orbiting body, and the self-rotating rotor revolves with the orbiting body and rotates in the wind to generate lift. The autorotor adjusts the angle between its rotor disk and the revolution plane via a pitch adjustment device. The pitch adjustment device is a servo motor, which electrically drives the autorotor to pitch.

2. The structure for generating lift according to claim 1, characterized in that: One or more rotating rotors are installed on the orbital body; when multiple rotating rotors are installed, the rotating rotors are symmetrically arranged on the rotation circumference of the outer edge of the orbital body.

3. The structure for generating lift according to claim 1, characterized in that: The rotation direction of the self-rotating rotor is the same as the rotation direction of the orbiting body.

4. The structure for generating lift according to claim 1, characterized in that: When the shaft is fixedly mounted on the fuselage, the power unit is an aviation or aerospace propulsion device, which is installed on the orbiting body to drive the orbiting body to rotate.

5. The structure for generating lift according to claim 1, characterized in that: When the shaft is rotatably mounted on the machine body, the power unit is an engine. The engine is mounted on the machine body and transmits power to the shaft directly or through a mechanical transmission mechanism, driving the revolution body to rotate.

6. The structure for generating lift according to claim 1, characterized in that: The orbiting body and the eccentric rotor are provided with space for the blades of the eccentric rotor to flap.

7. A method for generating lift using a structure according to any one of claims 1-6, characterized in that: 1) When the orbiting body rotates under the drive of the power unit, the autorotor on it revolves. When the pitch adjustment device is operated to make the rotor disk of the autorotor have a certain angle with the orbital plane, the autorotor rotates in the wind and generates lift. The magnitude of the lift can be controlled by adjusting the pitch angle of the power unit and the autorotor. 2) When the power unit fails, the entire device falls. The autorotor continues to rotate against the falling wind and generates lift. When the lift and drag are balanced, the aircraft descends at a constant speed. Furthermore, by adjusting the autorotor's rotor disk angle to a depression angle, the autorotor will drive the orbital body to rotate, thereby improving the aircraft's stability. When approaching the ground, by adjusting the autorotor's rotor disk angle to a pitch angle, the rotational energy of the orbital body is converted into lift from the autorotor, reducing the impact during landing. The entire process can achieve a vertical forced landing.

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