Integrated ring wing integrating rolling wing and rotor wing and aircraft based on integrated ring wing

Abstract

The integrated ring wing comprises at least two sets of fusion wings, a driving system and a control system, each fusion wing comprises an upper horizontal wing, a lower horizontal wing, a vertical wing and a flexible connecting section, and the two ends of each flexible connecting section are matched with one end face of the corresponding horizontal wing and one end face of the corresponding vertical wing in shape correspondingly; the horizontal wing and the vertical wing are smoothly connected through the flexible connecting section; the driving system is used for driving the fusion wings to rotate; the control system is used for calculating parameters of the horizontal wing and the vertical wing and adjusting the states thereof. The rotor wing blades adopt a periodic variable-torque disc to control an attack angle, provide lift force and control pitching and rolling; the rolling wing blade adopts an eccentric rotating disc to control the thrust direction and magnitude, and horizontal movement and yawing are controlled. The invention further provides an aircraft using the integrated ring wing. The aircraft has the omni-directional six-degree-of-freedom control capability, is simple and reliable in structure, is suitable for large-size design, and has the advantages of high aerodynamic efficiency, low noise and the like.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to an integrated ring wing integrating a rolling wing and a rotary wing, and an aircraft based on the wing. Background Art

[0002] With the rapid development of UAVs and vertical take-off and landing (VTOL) aircraft, single-rotor helicopters, multi-rotor aircraft and tilt-rotor aircraft have become the main aircraft configurations at present, each of which has different advantages and disadvantages.

[0003] 1. Single-rotor helicopter

[0004] Advantages: Efficient lift generation: The large single rotor provides the main lift, with high efficiency, suitable for long-term hovering and low-speed cruising. Mature technology and industrial chain: After long-term development, the technology is mature, the industrial chain is complete, and the maintenance and operation costs are relatively low.

[0005] Disadvantages: Control complexity: The tail rotor is required to offset the anti-torque of the main rotor, which increases the structural complexity and energy loss. Limited maneuverability: There are certain limitations in horizontal movement and yaw control, and the response speed is slow.

[0006] 2. Multi-rotor aircraft

[0007] Advantages: Simple structure: It is composed of multiple fixed-angle rotors, with simple structure, easy to manufacture and maintain. Flexible control: By adjusting the speed of each rotor, the attitude and position can be precisely controlled, with high maneuverability.

[0008] Disadvantages: Low efficiency: Due to the small size of the rotor and high wingtip speed, the aerodynamic efficiency is low and the flight time is short. High risk failure rate: Multiple motors and rotors increase the failure points, and the failure of a single rotor may cause the aircraft to lose control.

[0009] 3. Tilt-rotor aircraft

[0010] Advantages: It combines the advantages of helicopters and fixed-wing aircraft: it can take off and land vertically, and it can have a high cruising speed and efficiency in level flight. Flexible flight mode: It can switch between vertical and horizontal flight modes according to mission requirements.

[0011] Disadvantages: Complex mechanical structure: The tilt mechanism increases the mechanical complexity and weight, making maintenance difficult. High control difficulty: The flight attitude conversion process between vertical and horizontal flight modes is complex, and the control algorithm requirements are high.

[0012] 4. Rolling Wing Aircraft

[0013] Rolling wing (also known as cycloidal propeller) uses the method of periodic torque change to provide vector thrust, which has the advantages of fast thrust angle control and low thrust noise. However, the development of rolling wing aircraft is currently subject to some limitations:

[0014] High structural load: The rolling wing needs to withstand large centrifugal forces, causing the structural parts and tie rods to work under extreme conditions. Especially in large-size designs, the structural strength is difficult to guarantee.

[0015] Thrust jitter and vibration: Due to the working mode of the rolling wing, thrust jitter and structural vibration are easily generated, affecting the stability and control accuracy of the aircraft.

[0016] Low efficiency and high dead weight: In order to meet the structural strength requirements, the aircraft's own weight is increased, which reduces the aerodynamic efficiency.

[0017] Although there are aircrafts that use either rotors or rolling wings for propulsion, it is not possible to combine rolling wings and rotors on an aircraft. This is because:

[0018] (1) To avoid dead weight. The functions of both rollers and rotors on an aircraft are generally overlapping: they are used to provide lift. In order to save flight weight, an aircraft will generally only be equipped with one set of lift-providing devices, and the heading control is performed by changing the aircraft's attitude.

[0019] (2) The control mechanism cannot increase the control degrees of freedom at will. Increasing the control degrees of freedom on a single control structure will significantly increase the manufacturing cost. The rotor has three degrees of freedom and the roller has two degrees of freedom. It is difficult to operate so many degrees of freedom within an acceptable cost using a single mechanism.

[0020] (3) If an aircraft uses independent rollers for thrust, it will greatly waste the high aerodynamic efficiency of the rollers. Since the lift requirement of an aircraft is generally much greater than the thrust requirement, a higher power-to-weight ratio is required for the thrust source. Independent rollers for thrust are not the best choice. Summary of the invention

[0021] In view of the above problems, the present invention provides an aircraft that integrates rolling wing and rotor flight, aiming to combine the advantages of rotor and rolling wing, overcome their respective shortcomings, make the rolling wing have capabilities comparable to those of rotorcraft, achieve efficient lift generation, omnidirectional attitude and position control and structural reliability, and open up new avenues for the application of rolling wing technology.

[0022] According to one aspect of the present invention, an integrated ring wing integrating a rolling wing and a rotary wing is provided, comprising at least two sets of integrated wings, a drive system and a control system, wherein:

[0023] Each set of fusion wings includes an upper horizontal wing, a vertical wing, a lower horizontal wing and a flexible connection section, and the two ends of the flexible connection section are respectively adapted to the shapes of one end surface of the horizontal wing and one end surface of the vertical wing, so that the horizontal wing and the vertical wing are smoothly connected through the flexible connection section;

[0024] A driving system, used for driving the fusion wing to rotate;

[0025] The control system is used to calculate the parameters of the horizontal wing and the vertical wing and adjust the status of the horizontal wing and the vertical wing.

[0026] Furthermore, the horizontal wing is a rotor blade, and the vertical blade is a rolling blade; the rotor blade is a symmetrical airfoil or an asymmetrical airfoil, and the cross section of the rolling blade is a symmetrical airfoil.

[0027] Furthermore, the flexible connecting section is a hinge shaft wrapped by a flexible material, the flexible material and the hinge shaft can rotate relative to each other, one end of the hinge shaft is connected to the rotor blade, and the other end is connected to the rolling blade.

[0028] Furthermore, the rotor blades are connected to the rotor shaft via hinges, and the drive system is connected to the rotor shaft via a drive shaft.

[0029] Furthermore, the drive shaft is connected to the rotor shaft via a bearing.

[0030] Furthermore, the control system includes a cyclic torque converter plate connected to the root of each rotor blade via a mechanical linkage for controlling the angle of attack of the rotor blade at each phase.

[0031] Furthermore, the control system includes an eccentric rotating disk fixedly connected to the drive shaft, the rotation center of the eccentric rotating disk can move in a direction perpendicular to the axial direction of the drive shaft, and the rotation center is connected to the root of the rolling blade through a pull rod. The pull rod can pull the rolling blade to rotate around the axial direction of the rolling blade itself, thereby controlling the thrust direction and size of the rolling blade.

[0032] Furthermore, the rotation period of the driving shaft is the same as the period of the eccentric rotating disk and the periodic torque converter disk.

[0033] Furthermore, the control system also includes a sensor module, a flight control module, and a feedback adjustment module; wherein,

[0034] Sensor module: including attitude sensor, position sensor and wind speed sensor, used to obtain the status information of the aircraft in real time;

[0035] Flight control module: Calculate the adjustment amount of the rotor blades and roller blades according to the desired pitch, roll and yaw angles; Calculate the required lift and horizontal thrust according to the preset flight mission and real-time data using PID control algorithm or model predictive control algorithm to achieve lift and attitude control, horizontal thrust and yaw control;

[0036] Execution module: receives control instructions from the flight control module and adjusts the corresponding parameters of the rotor and roller through the drive system.

[0037] According to another aspect of the present invention, an aircraft is provided, wherein the integrated ring wing described in any one of the above items is installed on the left and right sides of the aircraft.

[0038] The beneficial effects of the integrated ring wing integrating the rolling wing and the rotary wing provided by the present invention include:

[0039] (1) Omnidirectional six-degree-of-freedom control: Full control of the six degrees of freedom of the aircraft is achieved in a static posture without the need for structural deformation, improving control flexibility, accuracy and response speed.

[0040] (2) Low structural load and high reliability: The rolling wing has a small thrust requirement, which reduces the structural load and improves reliability, making it suitable for the design of large-sized aircraft.

[0041] (3) High aerodynamic efficiency: lift and thrust share the full power of the power source, and there is no dead weight. The rolling wing rotor together forms an integrated ring wing with a compact structure, high overall aerodynamic efficiency, and long endurance. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0043] Figure 1 This is a schematic structural diagram of an integrated ring wing according to an embodiment of the present invention;

[0044] Figure 2 It is a schematic diagram of the principle of the existing eccentric rotating disc controlling the rolling wing;

[0045] Figure 3 It is a structural schematic diagram of a control system of an integrated ring wing according to an embodiment of the present invention;

[0046] Figure 4 A front view and a top view of an aircraft according to an embodiment of the present invention;

[0047] Figure 5 The figure is a three-dimensional schematic diagram of an aircraft according to an embodiment of the present invention. DETAILED DESCRIPTION

[0048] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0049] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0050] The preferred embodiments of the present invention are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0051] The embodiment of the present invention provides a double-rotating integrated ring wing 2 integrating a rolling wing and a rotary wing, such as Figure 1 , 4 As shown, it includes at least two groups of fusion wings, a drive system and a control system, each group of fusion wings includes an upper horizontal wing, a vertical wing, a lower horizontal wing and a flexible connecting section, and the two ends of the flexible connecting section are respectively adapted to the shapes of one end surface of the horizontal wing and one end surface of the vertical wing, so that the horizontal wing and the vertical wing are smoothly connected through the flexible connecting section, wherein the horizontal wing is a rotor blade and the vertical blade is a rolling blade.

[0052] The driving system may be an electric motor or a gas turbine engine, and its main transmission shaft (driving shaft) 51 may be used to drive the fusion wing to rotate along the Z axis.

[0053] The control system is used to calculate the parameters of the horizontal wing and the vertical wing and adjust the status of the horizontal wing and the vertical wing.

[0054] The rotor blade 21 is a horizontal blade in the shape of a long rectangular wing, with a symmetrical or asymmetrical airfoil, and the length and width are determined according to the lift design requirements, for example, a length of 1 meter and a width of 0.2 meters can provide a lift of about 100 kgf. The wing surface material is selected from high-strength composite materials to ensure sufficient rigidity and lightness.

[0055] In one embodiment, the rotor blades are connected to the rotor shaft 24 via hinges 313, and the control system system includes a periodic torque converter 31 and a corresponding servo mechanism 61 disposed above the rotor shaft 24, which are used to control the pitch angle (i.e., angle of attack) of the rotor blades at each phase, provide the main lift, and control the pitch and roll of the aircraft. The periodic torque converter 31 is connected to the root of each rotor blade via a mechanical connecting rod 311. The periodic torque converter 31 includes an upper and lower plate driven by a motor or manpower via a servo mechanism 61, and a pull rod 611 is used to tilt or displace the upper plate, and the lower plate rolls accordingly, thereby driving the rotor blades to rotate radially, thereby achieving periodic changes in the pitch angle, i.e., angle of attack, of the rotor blades. The structure and control principle of the periodic torque converter belong to the prior art and will not be described in detail.

[0056] The hinge 313 may adopt a common helicopter rotor hinge system, but only an axial hinge is required, without a taper hinge and a flap hinge (horizontal thrust is provided by the rolling wing). The rotor blade is connected to the flexible connection section 23 via the hinge 231 .

[0057] The rolling blade 22 is a vertical wing surface, located between the upper and lower rotor blades, and connected to the flexible connection section 23 through a hinge 221. The rolling blade 22 is in the shape of a rectangular wing with a high aspect ratio, and the length can be the same as the horizontal wing surface. The length and width can also be determined according to the thrust design requirements, for example, 1×0.2 meters, which can provide a thrust of about 50kgf, and the cross section is a symmetrical airfoil, such as NACA0015. The wing surface material is also selected from high-strength composite materials.

[0058] In one embodiment, the control structure includes an eccentric rotating disk 41 and an execution structure 62 fixedly connected to the drive shaft 51. The rotation center of the eccentric rotating disk is connected to the root hinge 412 of each rolling blade through a pull rod 413. The pull rod 413 can pull the rolling blade to rotate around the rolling blade's own axis, that is, change the phase angle (i.e., angle of attack). Through the actuator 62 or manual operation, the rotation center can be offset perpendicular to the axial direction of the drive shaft 51, so that the phase angle of the rolling blade is periodically changed by adjusting the eccentric distance d, and the rolling blade is controlled to generate thrust along the XY direction, thereby controlling the horizontal movement and yaw of the aircraft. Figure 2 The figure shows a schematic diagram of the principle of an eccentric rotating disk, and its structure and control principle are common technologies of rolling-wing aircraft, which belong to the existing technology and will not be described in detail.

[0059] The rotor blade and the rolling blade are smoothly connected by the flexible connecting section 23, that is, the two ends of the flexible connecting section 23 are respectively adapted to the shapes of the rotor blade end surface and the rolling blade end surface and are fixedly connected, so that the upper rotor blade, the rolling blade and the lower rotor blade are connected to form a fusion wing that rotates along the Z-axis direction. The flexible connecting section 23 can produce any deformation as the rotor blade and the rolling blade rotate, that is, it can smoothly transition the airfoil to realize the structure of the double-rotation-rolling integrated ring wing.

[0060] In one embodiment, two groups of fusion wings can be symmetrically placed to form an annular wing. The fusion wings can also be more than two groups, such as 3 groups, 4 groups, etc.

[0061] In one embodiment, the flexible connecting section 23 can be a hinge shaft wrapped with a flexible material, such as a hinge shaft wrapped with rubber, and the rubber and the hinge shaft can rotate relative to each other, and one end of the hinge shaft is connected to the horizontal rotor 21, and the other end is connected to the vertical rolling wing 22. The flexible connecting section 23 can smoothly transition between the horizontal wing surface and the vertical wing surface at different angles of attack, thereby improving aerodynamic efficiency. Generally, the rotational motion of the rotor blades and rolling wing blades relative to their axes is a swing, and the angle does not exceed 90 degrees.

[0062] In the integrated ring wing provided by the present invention, the rotor structure plays the role of the supporting structure of the rolling wing and can provide lift, so it does not appear as dead weight. In addition, the commonly used rotor structure cannot be directly controlled in the xy direction, and it is necessary to change the aircraft's attitude through pitch / roll before it can be indirectly controlled; the commonly used rolling wing structure cannot adjust the attitude and can only control the xy direction. Compared with the commonly used rotor structure, the integrated ring wing of the present invention only adds a flexible connection section and a vertical wing surface to increase the thrust, so that it can have the flight advantages of both rolling wings and rotors. Through the coordinated work of the rotor and rolling wings, the aircraft can achieve comprehensive control of the six degrees of freedom in space in a static attitude:

[0063] (1) X / Y direction movement. The horizontal thrust provided by the rolling wing system can directly control the movement of the aircraft in the horizontal direction without changing the aircraft's posture.

[0064] (2) Z-direction movement: The lift provided by the rotor system is used to adjust the rotor pitch to achieve the ascent and descent of the aircraft.

[0065] (3) Attitude control (Pitch, Roll, Yaw). Pitch and Roll (Pitch, Roll): The pitch and roll torques are generated through the cyclic torque converter of the rotor system to control the attitude of the aircraft. Yaw: The yaw torque is generated through the asymmetric thrust of the rolling wing system to achieve yaw control.

[0066] The working principle and control process of the rotor blades and roller blades are explained in detail below.

[0067] 1. Rotor Blade Control

[0068] The integral annular wing is driven by the drive shaft 51 to rotate along the Z axis, that is, the rotor 21 rotates around the Z axis, and at the same time, the periodic torque converter 31 adjusts the angle of attack of the rotor blade 21 in real time during the rotation process through mechanical or electrical control to achieve periodic lift regulation. In the present invention, it plays the following roles:

[0069] Lift generation: The angle of attack of the rotor is adjusted at each phase, so that the rotor generates stable lift during rotation, supporting the vertical hovering, ascent and descent of the aircraft.

[0070] Attitude control (pitch and roll): By periodically changing the angle of attack of the rotor at different phases, differentiated lift distribution is generated, pitch and roll moments are generated, and precise control of the aircraft's attitude is achieved.

[0071] During the rotation of the rotor, due to the action of aerodynamic force, a lift (L) perpendicular to the wing surface is generated, and its magnitude is determined by the following formula:

[0072]

[0073] Where: ρ is the air density, V is the relative velocity of the airfoil, S is the wing area, and CL is the lift coefficient, which depends on the airfoil and the angle of attack.

[0074] The angle of attack of each rotor blade is adjusted within one rotation by a periodic torque converter to achieve periodic changes in lift and generate pitch and roll moments:

[0075] Pitch control: Increase the angle of attack in the first half of the rotor and reduce it in the second half, generating a torque along the lateral axis of the fuselage.

[0076] Roll control: Increase the angle of attack when the rotor is in the left half of the circle, and reduce the angle of attack in the right half of the circle, generating a torque along the longitudinal axis of the fuselage.

[0077] 2. Roller blade control

[0078] The integral annular wing is driven by the drive shaft 51 to rotate along the Z axis. Since the rolling wing and the rotor are combined into an integral annular wing, the rolling wing blade 22 rotates synchronously with the rotor blade along the Z axis. The eccentric rotating disk 41 changes the thrust direction and magnitude of the rolling wing by adjusting the eccentricity and angle. In the present invention, it plays the following roles:

[0079] Horizontal thrust generation: During the rotation of the roller, the direction of the force is changed by adjusting the eccentric rotating disk, so that the thrust generated has a component in the horizontal direction (XY plane), achieving horizontal movement.

[0080] Yaw control: By adjusting the direction and magnitude of the rolling wing thrust, a yaw moment is generated to achieve precise control of the aircraft's yaw.

[0081] The rolling wing generates horizontal thrust through the rotating vertical wing surface, and its principle is similar to that of a cycloidal propeller. During the rotation of the rolling wing, due to the action of the eccentric rotating disk, the trajectory is non-circular, and the direction and magnitude of the thrust generated are controllable.

[0082] (1) Thrust generation: During the rotation of the rolling blade, the rolling blade is acted upon by aerodynamic forces, generating horizontal thrust (T), the magnitude of which is determined by the following formula:

[0083]

[0084] Where: CD is the drag coefficient, which depends on the airfoil and angle of attack.

[0085] Control of thrust direction: By adjusting the eccentricity (d) and phase angle (θ) of the eccentric rotating disk, the motion trajectory of the rolling blade is changed and the thrust direction (Ф) is controlled:

[0086]

[0087] Where: R is the rolling radius.

[0088] Yaw control: Yaw control is achieved by introducing asymmetry in the trajectory of the rolling blades to generate a torque around the vertical axis of the fuselage.

[0089] In one embodiment, in order to generate lift or thrust in a specified direction, the horizontal wing and the vertical wing both need to perform a lateral moment (i.e., swinging) motion with a period of one rotation of the whole wing. When the drive shaft 51 drives the integrated ring wing to rotate one circle, the eccentric rotating disk 41 and the periodic torque converter disk 31 also rotate one circle, that is, they are linked and have the same period.

[0090] In one embodiment, the drive shaft 51 is connected to the rotor shaft 24 through a bearing (the drive shaft is connected to the outer ring of the bearing, and the rotor shaft is connected to the inner ring of the bearing), thereby driving the rotor shaft and the rotor blades to rotate along the Z axis. At the same time, the drive shaft 51 is fixedly connected to the eccentric rotating disk, driving the rotation center and the rolling blades to rotate along the Z axis, so that the rotor blades and the rolling blades of the integrated ring wing rotate synchronously, sharing the available power of the drive system.

[0091] In one embodiment, the structural parameters and material selection of the aircraft are as follows:

[0092] (1) Rotor blade parameters:

[0093] Length (L1): Determined by lift design requirements, such as 1 meter; in this case, a 2-meter diameter rotor surface can be obtained

[0094] Width (W1): such as 0.2 meters.

[0095] Airfoil: Use airfoils with high lift coefficient, such as NACA2412.

[0096] Material: Carbon fiber composite material, with high strength and light weight.

[0097] (2) Roller blade parameters:

[0098] Length (L2): Determined by thrust design requirements, such as 1 meter.

[0099] Width (W2): 0.2 meters is recommended.

[0100] Airfoil: Symmetrical airfoil, suitable for bidirectional force. Such as NACA0015, etc.

[0101] Material: Carbon fiber composite material is also used.

[0102] (3) Flexible connector 23:

[0103] Material: High strength elastomer or composite material.

[0104] Connection method: hinge mechanisms 221 and 231 are used to facilitate installation and maintenance.

[0105] (4) Transmission system materials:

[0106] Main transmission shaft 51, rotor shaft 24: high-strength alloy steel, with surface subjected to heat treatment and anti-corrosion treatment.

[0107] Control system such as Figure 3 As shown, it is responsible for the attitude and motion control of the aircraft, and also includes sensors, flight control modules, execution modules, and feedback adjustment modules.

[0108] Sensor module: including attitude sensors (accelerometer, gyroscope), position sensors (GPS, lidar) and wind speed sensors, etc., to obtain real-time status information of the aircraft.

[0109] Flight control module: runs control algorithms, processes sensor data, and calculates control instructions. Algorithms include: Attitude control algorithm: calculates the adjustment amount of the rotor and roller according to the desired pitch, roll, and yaw angles. Position control algorithm: According to the preset flight mission and real-time data, such as the desired spatial position (X, Y, Z), the PID control algorithm or model predictive control (MPC) algorithm is used to calculate the required lift and horizontal thrust, that is, the required rotor and roller adjustment amount, such as the rotor angle of attack and pitch angle of the rotor blades, which are used to achieve lift and attitude control, and the roller blade eccentricity and phase angle, which are used to control the trajectory of the roller blades to achieve horizontal thrust and yaw control.

[0110] Execution module: includes the periodic torque disc 31 and its servo mechanism 61, the eccentric rotating disc 41 and its actuator 62, which is used to receive control instructions sent by the flight control module and adjust the corresponding states of the rotor and the roller through the periodic torque disc 31 and the eccentric rotating disc 41.

[0111] In one embodiment, the control system also includes a feedback adjustment module: used to continuously monitor the status of the aircraft, continuously adjust the control instructions through the branch control module according to the feedback information, and adjust the status of the rotor and roller through the execution module to ensure that the aircraft flies according to the expected trajectory and attitude.

[0112] The present invention also provides an aircraft, wherein an integrated ring wing 2 of the above embodiment is installed on each of the left and right sides of the aircraft 1. Figure 4 , 5 As shown, Figure 4 The upper part is a front view of the aircraft, and the lower part is a top view of the aircraft when the integrated wing is rotating.

[0113] Those skilled in the art will appreciate that the foregoing embodiments are merely intended to illustrate the technical solutions of the present invention rather than to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art will appreciate that the technical solutions described in the foregoing embodiments may be modified or some or all of the technical features may be replaced by equivalents. Such modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope defined by the claims of the present invention.

Claims

1. An integrated ring wing integrating a rolling wing and a rotary wing, characterized in that: It includes at least two sets of fusion wings, a drive system and a control system, wherein: Each set of fusion wings includes an upper horizontal wing, a vertical wing, a lower horizontal wing and a flexible connection section, and the two ends of the flexible connection section are respectively adapted to the shapes of one end surface of the horizontal wing and one end surface of the vertical wing, so that the horizontal wing and the vertical wing are smoothly connected through the flexible connection section; A driving system, used for driving the fusion wing to rotate; The control system is used to calculate the parameters of the horizontal wing and the vertical wing and adjust the status of the horizontal wing and the vertical wing.

2. The one-piece ring wing according to claim 1, characterized in that: The horizontal wing is a rotor blade, and the vertical blade is a rolling blade; the rotor blade is a symmetrical airfoil or an asymmetrical airfoil, and the cross section of the rolling blade is a symmetrical airfoil.

3. The one-piece ring wing according to claim 1, characterized in that: The flexible connecting section is a hinge shaft wrapped by a flexible material. The flexible material and the hinge shaft can rotate relatively. One end of the hinge shaft is connected to the rotor blade, and the other end is connected to the rolling blade.

4. The one-piece ring wing according to claim 1, characterized in that: The rotor blades are connected to the rotor shaft through hinges, and the drive system is connected to the rotor shaft through a drive shaft.

5. The one-piece ring wing according to claim 1, characterized in that: The drive shaft is connected to the rotor shaft through bearings.

6. The one-piece ring wing according to claim 1, characterized in that: The control system consists of a cyclic torque converter connected to the root of each rotor blade by a mechanical linkage to control the angle of attack of the rotor blade at each phase.

7. The one-piece ring wing according to claim 1, characterized in that: The control system includes an eccentric rotating disk fixedly connected to the drive shaft. The rotation center of the eccentric rotating disk can move in a direction perpendicular to the axial direction of the drive shaft. The rotation center is connected to the root of the rolling blade through a pull rod. The pull rod can pull the rolling blade to rotate around the axial direction of the rolling blade itself, thereby controlling the thrust direction and size of the rolling blade.

8. The one-piece ring wing according to claim 7, characterized in that: The rotation period of the drive shaft is the same as that of the eccentric rotating disk and the periodic torque converter disk.

9. The one-piece ring wing according to claim 1, characterized in that: The control system also includes a sensor module, a flight control module, and a feedback adjustment module; among which, Sensor module: including attitude sensor, position sensor and wind speed sensor, used to obtain the status information of the aircraft in real time; Flight control module: Calculate the adjustment amount of the rotor blades and roller blades according to the desired pitch, roll and yaw angles; Calculate the required lift and horizontal thrust according to the preset flight mission and real-time data using PID control algorithm or model predictive control algorithm to achieve lift and attitude control, horizontal thrust and yaw control; Execution module: receives control instructions from the flight control module and adjusts the corresponding parameters of the rotor and roller through the periodic torque converter and the eccentric rotating disk.

10. An aircraft, characterized in that: The integrated ring wing according to any one of claims 1 to 9 is installed on the left and right sides of the aircraft.

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