Multi-ducted aircraft with constant lift and its working method

Abstract

The present invention provides a multi-ducted aircraft with constant lift and its working method. The multi-ducted aircraft with constant lift includes a fuselage and a plurality of ducts. A lift duct body support truss is arranged inside the lift duct, and a gyroscope component is arranged at the central position of the lift duct body support truss. A duct blade is connected to the center of the gyroscope component through a power shaft; the gyroscope component includes an outer steering frame and an inner steering frame. The outer steering frame is connected to the lift duct body support truss through an outer rotating shaft, and the inner steering frame is connected to the outer steering frame through an inner rotating shaft. The included angle between the inner rotating shaft and the outer rotating shaft is 90°. The present invention realizes the separation of the lift surface and the control surface through the position and tension distribution of multiple ducts, which greatly facilitates the control; by adding a gyroscope to the lift duct rotor, the direction and magnitude of the lift can be kept constant in various flight attitudes, improving the lift efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and specifically to a multi-ducted aircraft with constant lift and its working method. Background Art

[0002] A ducted aircraft is an aircraft that incorporates lift components within a duct and has a high lift-to-drag ratio. It is structurally compact, has good maneuverability, a small noise signal signature, and strong adaptability. It is widely used in both military and civilian fields and is one of the research hotspots of current aircraft.

[0003] Conventional ducted aircraft rely on ducted propellers to generate lift and achieve forward flight by tilting the entire duct to generate forward thrust. This causes coupling of lift and forward force, which is not conducive to control and results in waste of lift and reduced efficiency. To balance the counter-torque of the rotor within the duct, multiple sets of rotors or multiple ducts are usually arranged within a single duct body, which increases the structural size and weight. Summary of the Invention

[0004] To solve the problems of the prior art, the present invention provides a multi-ducted aircraft with constant lift and its working method. By distributing the positions and thrusts of multiple ducts, separation of the lift surface and control surface is achieved, greatly facilitating control. By adding gyroscopes to the lift duct rotors, the direction and magnitude of lift can be kept constant in all flight attitudes, improving lift efficiency. Multiple adjustable-angle blades are added to the inner surface of the lift duct body to generate a force biased in the same direction under the action of the rotor downwash, achieving balance of counter-torque. A tail propulsion propeller is added, eliminating the need to tilt the fuselage.

[0005] The present invention provides a multi-ducted aircraft with constant lift, including a fuselage. A lift duct is provided in the center of the fuselage, and several auxiliary ducts are distributed around the lift duct. A lift duct body support truss is provided inside the lift duct. A gyroscope component is provided at the center of the lift duct body support truss. The center of the gyroscope component is connected to a duct propeller through a power shaft. The gyroscope component includes an outer steering frame and an inner steering frame. The outer steering frame is connected to the lift duct body support truss through an outer rotating shaft, and the inner steering frame is connected to the outer steering frame through an inner rotating shaft. The included angle between the inner rotating shaft and the outer rotating shaft is 90°.

[0006] Further improvement: The auxiliary ducts include a front duct, a left duct, and a right duct that are evenly distributed around the circumference of the lift duct.

[0007] Further improvement: A pair of vertical tails are provided on the upper surface of the fuselage, and a thrust propeller is provided behind the fuselage.

[0008] For further improvement, an angle limit block for restricting the rotation angle of the gyroscope component is provided on the lift duct body support truss. The function of the angle limit block is to limit the rotation angle of the fuselage around the rotation axis. The specific limited angle value (the height from the outer steering frame) can be determined according to the actual allowable pitch angle of the aircraft; the limitation in the other direction is restricted by the distance between the inner steering frame and the inner rotating shaft.

[0009] For further improvement, a flow deflector is provided inside the lift duct.

[0010] The present invention also provides a working method for a multi-duct aircraft with constant lift, including the following processes:

[0011] 1) In the vertical flight state, the lift is generated by the lift duct. At this time, the rotor shaft inside the lift duct is perpendicular to the ground. The guide vanes inside the duct adjust the angle according to the reaction torque generated by the rotor. Under the action of the downwash flow, a force along the rotation direction of the rotor is generated around the center of the rotor shaft to achieve the balance of the reaction torque; the thrust propeller at the tail does not work, and the other duct rotors only generate a small amount of lift as auxiliary devices;

[0012] 1.1) For the pitching motion of the aircraft, the front duct increases the rotor speed, the lift increases, and the left and right ducts at the rear reduce the rotor speed, the lift decreases, to maintain the lift balance of the entire aircraft. In this way, a pitching moment is generated relative to the center of gravity of the aircraft, and the fuselage rotates a certain angle around the rotation axis relative to the rotor of the lift duct. The pitching moment will not be transmitted to the center of the rotor of the lift duct, and the lift plane of the rotor remains at the original angle unchanged;

[0013] 1.2) For the rolling motion, the rotor speed of the right duct decreases, the lift decreases, the rotor speed of the left duct increases, the lift increases, a rolling moment is generated relative to the center of gravity of the aircraft, and the fuselage rotates a certain angle around the rotation axis relative to the rotor of the lift duct. The rolling moment will not be transmitted to the rotor of the lift duct, and the lift plane of the rotor remains at the original angle unchanged;

[0014] 1.3) For the yawing motion, by adjusting the angle of the guide vane, the force on the guide vane changes, the reaction torque is unbalanced, and a yawing moment around the center of gravity of the fuselage is generated, thereby changing the heading of the fuselage.

[0015] 2) In the forward flight state, the thrust propeller generates thrust, enabling the aircraft to obtain forward force. Since the duct rotor is inside the duct, it is less affected by the forward flight speed; in this state, for the pitching, rolling and yawing motions of the aircraft, the principle is similar to that in step 1) of the vertical flight state.

[0016] The beneficial effects of the present invention are as follows:

[0017] 1. Efficiency improvement: The ducted rotor has higher aerodynamic efficiency compared to the isolated rotor, and the magnitude and direction of the lift are kept constant by adding a gyroscope, further improving the efficiency.

[0018] 2. Good maneuverability: The pitch and roll motions are achieved through the combination of auxiliary ducts, which are independent of the lift duct, making the operation simple; the yaw motion only requires adjusting the angle of the guide vane, with simple operation and easy implementation.

[0019] 3. Low noise: The entire aircraft uses ducted rotors, resulting in lower noise compared to isolated rotors.

[0020] 4. High mobility: The independent control mechanism of the aircraft includes three auxiliary ducts, guide vanes, a lift duct, and a tail propulsion propeller, making it easy to achieve maneuverable flight.

[0021] 5. High safety: Except for the tail propulsion propeller, the rotating components are contained within the fuselage, reducing the probability of collision accidents. Brief Description of the Drawings

[0022] Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0023] Figure 2 It is a structural diagram of the lift duct.

[0024] Figure 3 It is a structural diagram of the gyroscope component. Detailed Description of the Invention

[0025] The present invention will be further described below with reference to the accompanying drawings.

[0026] The present invention provides a multi-ducted aircraft with constant lift, and the structure is as Figure 1 shown, including a fuselage, a lift duct 6 is arranged in the center of the fuselage, and several auxiliary ducts are distributed around the lift duct. A lift duct body support truss 9 is arranged in the lift duct, and a gyroscope component is arranged at the center position of the lift duct body support truss. The center of the gyroscope component is connected to a duct blade through a power shaft; the gyroscope component includes an outer steering frame 10 and an inner steering frame 11, wherein the outer steering frame 10 is connected to the lift duct body support truss 9 through an outer rotating shaft 13, and the inner steering frame 11 is connected to the outer steering frame 10 through an inner rotating shaft 14, and the included angle between the inner rotating shaft and the outer rotating shaft is 90°.

[0027] Further improvement, the auxiliary ducts include a front duct 7, a left duct 1, and a right duct 5 that are equally spaced around the circumference of the lift duct.

[0028] Further improvement, a pair of vertical tails are arranged on the upper surface of the fuselage, including a left vertical tail 2 and a right vertical tail 4, and a thrust propeller 3 is arranged at the rear of the fuselage.

[0029] For further improvement, an angle limiting block 12 for limiting the rotation angle of the gyroscope component is provided on the lift duct body support truss. The function of the angle limiting block is to limit the rotation angle of the fuselage around the rotation axis. The specific limited angle value (the height from the outer steering frame) can be determined according to the actual allowable pitch angle of the aircraft; the limitation in the other direction is achieved by the distance between the inner steering frame and the inner rotation axis.

[0030] For further improvement, a flow guiding vane 8 is provided inside the lift duct.

[0031] The present invention also provides a working method for a multi-duct aircraft with constant lift, including the following processes:

[0032] 1) In the vertical flight state, the lift is generated by the lift duct. At this time, the rotor shaft inside the lift duct is perpendicular to the ground. The flow guiding vanes inside the duct adjust the angle according to the reaction torque generated by the rotor. Under the action of the downwash flow, a force that rotates clockwise (or counterclockwise, determined by the rotation direction of the rotor) around the center of the rotor shaft is generated to achieve the balance of the reaction torque; the thrust propeller at the tail does not work, and the other duct rotors only generate a small amount of lift as auxiliary devices;

[0033] 1.1) For the pitching motion of the aircraft (taking the entire aircraft raising its head as an example), the front duct increases the rotor speed, and the lift increases. The left and right ducts at the rear reduce the rotor speed, and the lift decreases to maintain the lift balance of the entire aircraft. In this way, a pitching moment is generated relative to the center of gravity of the aircraft, and the fuselage rotates a certain angle around the rotation axis of the rotor of the lift duct. The pitching moment will not be transmitted to the center of the rotor of the lift duct, and the lift plane of the rotor remains at the original angle unchanged;

[0034] 1.2) For the rolling motion (taking the aircraft rotating towards the right duct as an example), the rotor speed of the right duct decreases, and the lift decreases. The rotor speed of the left duct increases, and the lift increases, generating a rolling moment relative to the center of gravity of the aircraft. The fuselage rotates a certain angle around the rotation axis of the rotor of the lift duct. The rolling moment will not be transmitted to the rotor of the lift duct, and the lift plane of the rotor remains at the original angle unchanged;

[0035] 1.3) For the yawing motion, by adjusting the angle of the flow guiding vane, the force on the flow guiding vane is changed, the reaction torque is unbalanced, generating a yawing moment around the center of gravity of the fuselage, thereby changing the heading of the fuselage.

[0036] 2) In the forward flight state, the thrust propeller generates thrust, enabling the aircraft to obtain forward force. Since the duct rotor is inside the duct, it is less affected by the forward flight speed; for the pitching, rolling and yawing motions of the aircraft in this state, the principle is similar to that in step 1) in the vertical flight state.

[0037] The specific application ways of the present invention are numerous. The above description is only the preferred embodiment of the present invention. It should be noted that for those of ordinary skill in the art, several improvements can be made without departing from the principle of the present invention, and these improvements should also be regarded as the protection scope of the present invention.

Claims

1. A multi-ducted aircraft with a constant lift, comprising a fuselage, a lift duct is arranged in the center of the fuselage, and a number of auxiliary ducts are distributed around the lift duct, characterized in that: A lift duct is provided with a support truss for the lift duct body. A gyroscope component is arranged at the central position of the support truss for the lift duct body. The center of the gyroscope component is connected with a duct propeller through a power shaft. The gyroscope component includes an outer steering frame and an inner steering frame. The outer steering frame is connected with the support truss for the lift duct body through an outer rotating shaft. The inner steering frame is connected with the outer steering frame through an inner rotating shaft. The included angle between the inner rotating shaft and the outer rotating shaft is 90°. The auxiliary ducts include a front duct, a left duct and a right duct which are evenly distributed around the circumference of the lift duct. A pair of vertical tails are arranged on the upper surface of the fuselage, and a thrust propeller is arranged at the rear of the fuselage.

2. The multi-ducted aircraft with constant lift according to claim 1, wherein: Angle limiting blocks for limiting the rotation angle of the gyroscope component are arranged on the support truss for the lift duct body.

3. The multi-ducted aircraft with constant lift according to claim 1, characterized in that: Flow guiding vanes are arranged in the lift duct.

4. A working method of a multi-ducted aircraft with constant lift, using the multi-ducted aircraft with constant lift described in claim 1, characterized in that It includes the following processes: 1) In the vertical flight state, lift is generated by the lift duct. At this time, the rotor shaft in the lift duct is perpendicular to the ground. The flow guiding vanes in the duct body adjust the angle according to the reverse torque generated by the rotor. Under the action of the downwash flow, a force along the rotation direction of the rotor is generated simultaneously around the center of the rotor shaft to achieve the balance of the reverse torque. The thrust propeller at the tail does not work, and the rotors of the other ducts only generate a small amount of lift as auxiliary devices. 1.1) For the pitching motion of the aircraft, the rotor speed of the front duct is increased, the lift is increased, and the rotor speeds of the left and right ducts at the rear are decreased, and the lift is decreased to maintain the lift balance of the entire aircraft. In this way, a pitching moment will be generated relative to the center of gravity of the aircraft. The fuselage rotates a certain angle around the rotating shaft relative to the rotor of the lift duct, and the pitching moment will not be transmitted to the center of the rotor of the lift duct. The lift plane of the rotor remains at the original angle unchanged. 1.2) For the rolling motion, the rotor speed of the right duct is decreased, the lift is decreased, the rotor speed of the left duct is increased, the lift is increased, and a rolling moment is generated relative to the center of gravity of the aircraft. The fuselage rotates a certain angle around the rotating shaft relative to the rotor of the lift duct, and the rolling moment will not be transmitted to the rotor of the lift duct. The lift plane of the rotor remains at the original angle unchanged. 1.3) For the yawing motion, by adjusting the angle of the flow guiding vane, the force on the flow guiding vane is changed, the reverse torque is unbalanced, and a yawing moment around the center of gravity of the fuselage is generated, thereby changing the heading of the fuselage. 2) In the forward flight state, the thrust propeller generates thrust, enabling the aircraft to obtain forward force. Since the duct rotor is in the duct body, it is less affected by the forward flight speed. For the pitching, rolling and yawing motions of the aircraft in this state, the principle is similar to that in step 1) in the vertical flight state.

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