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

Abstract

The utility model provides an integrated ring wing integrating a rolling wing and a rotor wing, which comprises a horizontal wing, a vertical wing and a flexible connecting section, the two ends of the flexible connecting section are respectively matched with the shape of one end face of the horizontal wing and the shape of one end face of the vertical wing, so that the horizontal wing and the vertical wing are smoothly connected through the flexible connecting section, the horizontal wing is a rotor wing blade, and the vertical blade is a rolling wing blade. 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 blades control the thrust direction and magnitude through eccentric rotating discs, horizontal thrust is generated, and horizontal movement and yawing are controlled. The utility model 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 utility model relates to the technical field of aerospace, in particular to an integrated annular wing integrating a rolling wing and a rotor and an aircraft based on the wing. Background Art

[0002] With the rapid development of unmanned aerial vehicles and vertical takeoff and landing aircraft (VTOL), single-rotor helicopters, multi-rotor aircraft and tilt-rotor aircraft have become the current main aircraft configurations, each with its own advantages and disadvantages.

[0003] 1. Single-rotor Helicopter

[0004] Advantages: High-efficiency lift generation: A 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 perfect, and the maintenance and operation costs are relatively low.

[0005] Disadvantages: Control complexity: A tail rotor is required to counteract the reaction torque of the main rotor, increasing 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: Composed of multiple rotors with fixed angles, the structure is simple, easy to manufacture and maintain. Flexible control: Precise control of attitude and position can be achieved by adjusting the rotation speed of each rotor, with high maneuverability.

[0008] Disadvantages: Low efficiency: Due to the small rotor size and high tip speed, the aerodynamic efficiency is low and the endurance time is short. High risk of 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: Combining the advantages of helicopters and fixed-wing aircraft: It can take off and land vertically and has a high cruise speed and efficiency during horizontal flight. Flexible flight mode: It can switch between vertical and horizontal flight modes according to mission requirements.

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

[0012] 4. Rolling-wing Aircraft

[0013] The cycloidal rotor (also known as the cycloidal propeller) uses the method of periodic pitch change to provide vector thrust, and has advantages such as fast thrust angle control and low thrust noise. However, the development of cycloidal rotor aircraft is currently restricted by some factors:

[0014] High structural load: The cycloidal rotor needs to bear a large centrifugal force, resulting in structural components and tie rods working under extreme conditions. Especially in large-scale designs, it is difficult to ensure structural strength.

[0015] Thrust jitter and vibration: Due to the working mode of the cycloidal rotor, it is easy to generate thrust jitter and structural vibration, affecting the stability and control accuracy of the aircraft.

[0016] Low efficiency and high dead weight: To meet the requirements of structural strength, the dead weight of the aircraft is increased, reducing the aerodynamic efficiency.

[0017] Although aircraft with separate rotors or cycloidal rotors for propulsion exist, currently, it is not possible to integrate cycloidal rotors and rotors to act on an aircraft simultaneously. This is because:

[0018] (1) To avoid dead weight. Generally, the functions of both cycloidal rotors and rotors on an aircraft overlap: that is, they are used to provide lift. To save flight weight, an aircraft usually only installs one set of lift-providing devices and controls the heading by changing the attitude of the aircraft.

[0019] (2) The control mechanism cannot arbitrarily increase the control degrees of freedom. Adding control degrees of freedom to a single control structure will significantly increase the manufacturing cost. A rotor has three degrees of freedom, and a cycloidal rotor 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) Using an independent cycloidal rotor as a thrust source will greatly waste the efficient aerodynamic advantages of the cycloidal rotor. Since the lift requirement of an aircraft is generally much greater than the thrust requirement, there is a high power-to-weight ratio requirement for the thrust source. Using an independent cycloidal rotor as a thrust source is not an optimal choice. Summary of the Invention

[0021] In view of the above problems, the present invention provides an aircraft that combines cycloidal rotor and rotor flight, aiming to combine the advantages of rotors and cycloidal rotors, overcome their respective disadvantages, enable the cycloidal rotor to have capabilities comparable to those of rotor aircraft, achieve efficient lift generation, omnidirectional attitude and position control, and structural reliability, and open up new ways for the application of cycloidal rotor technology.

[0022] According to one aspect of the present utility model, an integrated annular wing combining a rolling wing and a rotor wing is provided, comprising: at least two groups of integrated wings, each group of integrated wings including an upper horizontal wing, a vertical wing, a lower horizontal wing, and a flexible connection section. The two ends of the flexible connection section are respectively adapted to the shapes of one end face of the horizontal wing and one end face of the vertical wing, so that the horizontal wing and the vertical wing are smoothly connected through the flexible connection section. Among them, the horizontal wing is a rotor blade, and the vertical blade is a rolling wing blade.

[0023] Furthermore, the rotor blade is of a symmetric airfoil or an asymmetric airfoil, and the cross-section of the rolling wing blade is of a symmetric airfoil.

[0024] Furthermore, the flexible connection section is a hinge shaft wrapped with a flexible material, and 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 wing blade.

[0025] Furthermore, it further includes a drive shaft for driving the integrated annular wing to rotate axially.

[0026] Furthermore, the rotor blade is connected to a rotor shaft through a hinge, and the drive shaft is connected to the rotor shaft.

[0027] Furthermore, the hinge adopts an axial hinge of a helicopter rotor hinge system.

[0028] Furthermore, it further includes a cyclic pitch disk, which is connected to the root of each rotor blade through a mechanical link for controlling the angle of attack of the rotor blade at each phase.

[0029] Furthermore, an eccentric rotating disk is 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 wing blade through a pull rod, and the pull rod can pull the rolling wing blade to rotate around its own axis, thereby controlling the thrust direction and magnitude of the rolling wing blade.

[0030] Furthermore, the rotation period of the drive shaft is the same as that of the eccentric rotating disk and the cyclic pitch disk.

[0031] According to another aspect of the present utility model, an aircraft is provided, and the above-mentioned integrated annular wings are installed on the left and right sides of the aircraft.

[0032] The beneficial effects of the integrated annular wing combining a rolling wing and a rotor wing provided by the present utility model include:

[0033] (1) Omnidirectional six-degree-of-freedom control: Without structural deformation in a stationary attitude, comprehensive control of the six degrees of freedom of the aircraft is achieved, improving control flexibility, precision, and response speed.

[0034] (2) Low structural load and high reliability: The thrust requirement of the rolling wing is small, reducing the structural load and improving the reliability, which is suitable for the design of large-sized aircraft.

[0035] (3) High aerodynamic efficiency: The lift and thrust share all the power of the power source without dead weight. The rolling wing and the rotor together form an integrated ring wing, which is structurally compact and has high overall aerodynamic efficiency, with a long endurance. Brief Description of the Drawings

[0036] The drawings are used to provide a further understanding of the present invention and constitute a part of the specification. They are used together with the embodiments of the present invention to explain the present invention and do not constitute a limitation to the present invention. In the drawings:

[0037] Figure 1 is a schematic structural diagram of the integrated ring wing according to an embodiment of the present invention;

[0038] Figure 2 is a schematic diagram of the principle of controlling the rolling wing by an eccentric rotating disk in the prior art;

[0039] Figure 3 are the front view and top view of the aircraft according to an embodiment of the present invention;

[0040] Figure 4 is a three-dimensional schematic diagram of the aircraft according to an embodiment of the present invention. Detailed Embodiments

[0041] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. They are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0042] In the present invention, unless otherwise clearly defined and limited, the terms "installed", "connected", "connected", "fixed", etc. 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 directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0043] The preferred embodiments of the present utility model will be described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only for explaining and illustrating the present utility model, and are not used to limit the present utility model.

[0044] An embodiment of the present utility model provides a dual-rotating rolling integrated annular wing 2 that combines a rolling wing and a rotor wing, as Figure 1 , 3 shown, including at least two groups of integrated wings. Each group of integrated wings includes an upper horizontal wing, a vertical wing, a lower horizontal wing, and a flexible connection section. The two ends of the flexible connection section are respectively adapted to the shapes of an end face of the horizontal wing and an end face of the vertical wing, so that the horizontal wing and the vertical wing are smoothly connected through the flexible connection section. Among them, the horizontal wing is a rotor blade, and the vertical blade is a rolling wing blade.

[0045] The rotor blade 21 is a horizontal blade, shaped like a long rectangular wing, using a symmetric or asymmetric airfoil. The length and width are determined according to the lift design requirements. For example, the length is 1 meter and the width is 0.2 meter, which can provide a lift of about 100 kgf. The wing surface material is selected as a high-strength composite material to ensure sufficient rigidity and light weight.

[0046] The integrated annular wing further includes a drive shaft 51 for driving the integrated annular wing to rotate axially.

[0047] In one embodiment, the rotor blade is connected to the rotor shaft 24 through a hinge 313. The pitch change disk 31 is arranged above the rotor shaft 24 and is used to control the pitch angle (i.e., the angle of attack) of the rotor blade in each phase, provide the main lift, and control the pitch and roll of the aircraft. The pitch change disk 31 is connected to the root of each rotor blade through a mechanical link 311. The pitch change disk 31 includes an upper and a lower disk, which are driven by a motor or manpower through a rotor control system 61. The upper disk is tilted or displaced using a pull rod 611, and the lower disk rolls accordingly, thereby driving the radial rotation of the rotor blade to periodically change the pitch angle, i.e., the angle of attack, of the rotor blade. The structure and control principle of the pitch change disk belong to the prior art and will not be elaborated here.

[0048] The hinge 313 can adopt a common helicopter rotor hinge system, but only an axial hinge is required, without a conical hinge and a flapping hinge (the horizontal thrust is provided by the rolling wing). The rotor blade is connected to the flexible connection section 23 through a hinge 231.

[0049] The rolling wing blade 22 is a vertical wing surface, located between the upper and lower rotor blades, and is connected to the flexible connection section 23 through a hinge 221. The shape of the rolling wing blade 22 is a rectangular wing with a high aspect ratio. The length can be the same as that of the horizontal wing surface, and 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 50 kgf. The cross-section is a symmetric airfoil, such as NACA0015. The wing surface material is also selected as a high-strength composite material.

[0050] In one embodiment, the eccentric rotating disk 41 may be 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 wing blade through a pull rod 413. The pull rod 413 can pull the rolling wing to rotate around its own axis, that is, change the phase angle (i.e., the angle of attack). Through the rolling wing control system 62 or manual operation, the rotation center can be offset perpendicular to the axial direction of the drive shaft, so as to periodically change the phase angle of the rolling wing blade by adjusting the eccentricity d, control the thrust generated by the rolling wing in the XY direction, and control the horizontal movement and yaw of the aircraft. Figure 2 The schematic diagram of the principle of the eccentric rotating disk is shown. Its structure and control principle are common technologies of the rolling wing aircraft, which belong to the prior art and will not be elaborated here.

[0051] The rotor blade and the rolling wing blade are smoothly connected through a flexible connection section 23, that is, the two ends of the flexible connection section 23 are respectively adapted to the shapes of the end faces of the rotor blade and the rolling wing blade and are fixedly connected, so as to connect the upper rotor blade, the rolling wing blade and the lower rotor blade to form a composite wing rotating along the Z-axis direction. The flexible connection section 23 can generate arbitrary deformations with the rotation of the rotor blade and the rolling wing blade, that is, it can smoothly transition the airfoil and realize the structure of the double-rotating rolling integrated annular wing.

[0052] In one embodiment, two sets of composite wings can be symmetrically placed to form an annular wing. There can also be more than two sets of composite wings, such as 3 sets, 4 sets, etc.

[0053] In one embodiment, the flexible connection section 23 can be a hinge shaft wrapped with a flexible material, such as a hinge shaft wrapped with rubber. The rubber and the hinge shaft can rotate relative to each other. 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 connection section 23 can smoothly transition the horizontal wing surface and the vertical wing surface under different angles of attack, improving the aerodynamic efficiency. Usually, the rotational movement of the rotor blade and the rolling wing blade relative to their axes is a swing, and the angle does not exceed 90 degrees.

[0054] In the integrated annular wing provided by the present utility model, the rotor structure serves as the support structure of the rolling wing and can provide lift, so it does not appear as a dead weight. Moreover, the common rotor structure cannot be directly controlled in the xy direction and needs to indirectly control by changing the attitude of the aircraft through pitch / roll; the common rolling wing structure cannot adjust the attitude and can only control the xy direction. Compared with the common rotor structure, the integrated annular wing of the present utility model only adds a flexible connection section and a vertical wing surface to achieve the function of increasing thrust, so that it can have the flight advantages of both the rolling wing and the rotor at the same time. Through the coordinated work of the rotor and the rolling wing, the aircraft can achieve comprehensive control of six degrees of freedom in space in a stationary attitude:

[0055] (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 body attitude.

[0056] (2)Z direction movement. The lift provided by the rotor system realizes the ascent and descent of the aircraft by adjusting the total pitch of the rotor blades.

[0057] (3)Attitude control (Pitch, Roll, Yaw). Pitch and Roll: By means of the cyclic pitch control disk of the rotor system, pitch and roll torques are generated to control the attitude of the aircraft. Yaw: Through the asymmetric thrust of the rolling wing system, a yaw torque is generated to achieve yaw control.

[0058] The working principles and control processes of the rotor blades and rolling wing blades are specifically described below.

[0059] 1. Control of rotor blades

[0060] The integral annular wing rotates along the Z-axis driven by the drive shaft 51, that is, the rotor 21 rotates around the Z-axis. At the same time, the cyclic pitch control disk 31 adjusts the angle of attack change of the rotor blade 21 during rotation in real time through mechanical or electric control methods to achieve periodic lift adjustment. The functions it plays in the present invention are as follows:

[0061] Lift generation: The adjustment of the angle of attack of the rotor at each phase enables the rotor to generate stable lift during rotation to support the vertical hovering and ascent / descent of the aircraft.

[0062] Attitude control (pitch and roll): By periodically changing the angle of attack of the rotor at different phases, a differential lift distribution is generated to produce pitch and roll torques, thereby achieving precise control of the aircraft attitude.

[0063] During the rotation of the rotor, due to the aerodynamic action, a lift (L) perpendicular to the wing surface is generated, and its magnitude is determined by the following formula:

[0064]

[0065] where: ρ is the air density, V is the relative velocity of the wing surface, S is the wing area, and CL is the lift coefficient, which depends on the airfoil and the angle of attack.

[0066] By adjusting the angle of attack change of each rotor blade within one rotation through the cyclic pitch control disk, the periodic change of lift is achieved, and pitch and roll torques are generated:

[0067] Pitch control (Pitch): Increase the angle of attack in the first half of the rotor rotation and decrease the angle of attack in the second half to generate a torque along the transverse axis of the fuselage.

[0068] Roll control: Increase the angle of attack when the rotor is in the left half cycle and decrease the angle of attack in the right half cycle to generate a moment along the longitudinal axis of the airframe.

[0069] 2. Control of the rolling wing blades

[0070] The overall annular wing rotates along the Z-axis driven by the drive shaft 51. Since the rolling wing and the rotor jointly form an integral annular wing, the rolling wing blades 22 rotate synchronously with the rotor blades 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. The functions it plays in the present utility model are as follows:

[0071] Horizontal thrust generation: During the rotation of the rolling wing, through the adjustment of the eccentric rotating disk, the direction of the force received is changed, so that the generated thrust has a component in the horizontal direction (XY plane) to achieve horizontal movement.

[0072] Yaw control (Yaw): By adjusting the direction and magnitude of the rolling wing thrust, a yaw moment is generated to achieve precise control of the yaw of the aircraft.

[0073] 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 generated thrust are controllable.

[0074] (1) Generation of thrust: During the rotation of the rolling wing blades, they are affected by aerodynamic forces to generate horizontal thrust (T), and its magnitude is determined by the following formula:

[0075]

[0076] Where: CD is the drag coefficient, which depends on the airfoil and the angle of attack.

[0077] Control of the thrust direction: By adjusting the eccentricity (d) and phase angle (θ) of the eccentric rotating disk, the movement trajectory of the rolling wing blades is changed to control the thrust direction (Ф):

[0078]

[0079] Where: R is the rotation radius of the rolling wing.

[0080] Yaw control (Yaw): By introducing asymmetry into the trajectory of the rolling wing blades, a moment around the vertical axis of the airframe is generated to achieve yaw control.

[0081] In one embodiment, in order to generate lift or thrust in a specified direction, both the horizontal wing and the vertical wing need to perform side moment (i.e., swing) movements with the rotation of the overall wing for one cycle. The drive shaft 51 drives the integral annular wing to rotate one circle, and the eccentric rotating disk 41 and the periodic moment disk 31 also just rotate one circle, that is, they are linked and have the same period.

[0082] The drive shaft 51 can be the main drive shaft of an electric motor or a gas turbine engine. In one embodiment, the drive shaft 51 is connected to the rotor shaft 24 through bearings (the outer ring of the bearing is connected to the drive shaft, and the inner ring of the bearing is connected to the rotor shaft), 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 wing blades to rotate along the Z-axis, so that the rotor blades and the rolling wing blades of the integrated annular wing rotate synchronously and share the available power of the drive system.

[0083] In one embodiment, the structural parameters and material selection of the aircraft are as follows:

[0084] (1) Rotor blade parameters:

[0085] Length (L1): Determined according to the lift design requirements, such as 1 meter can be taken; at this time, a rotor surface with a diameter of 2 meters can be obtained

[0086] Width (W1): Such as 0.2 meters.

[0087] Airfoil: An airfoil with a high lift coefficient is adopted, such as NACA2412, etc.

[0088] Material: Carbon fiber composite material, with high strength and lightweight characteristics.

[0089] (2) Rolling wing blade parameters:

[0090] Length (L2): Determined according to the thrust design requirements, such as 1 meter.

[0091] Width (W2): 0.2 meters can be taken.

[0092] Airfoil: A symmetric airfoil, suitable for two-way stress. Such as NACA0015, etc.

[0093] Material: Also choose carbon fiber composite material.

[0094] (3) Flexible connector 23:

[0095] Material: High-strength elastomer or composite material.

[0096] Connection method: Hinge mechanisms 221 and 231 are adopted, which are convenient for installation and maintenance.

[0097] (4) Transmission system material:

[0098] Main drive shaft 51, rotor shaft 24: High-strength alloy steel, with the surface heat-treated and anti-corrosion treated.

[0099] The present utility model also provides an aircraft. One integrated annular wing 2 of the above embodiment is installed on each of the left and right sides of the aircraft 1. Such as Figure 3 、4 As shown in the figure. Among them Figure 3 The upper part of the figure is the front view of the aircraft, and the lower part is the top view when the integrated wing of the aircraft rotates.

[0100] Those of ordinary skill in the art can understand that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope defined by the claims of the present invention.

Claims

1. An integrated annular wing integrating a rolling wing and a rotor, characterized in that, It includes at least two sets of blended wings. Each set of blended wings includes an upper horizontal wing, a vertical wing, a lower horizontal wing, and a flexible connection section. The two ends of the flexible connection section are respectively adapted to the shapes of one end face of the horizontal wing and one end face of the vertical wing, so that the horizontal wing and the vertical wing are smoothly connected through the flexible connection section. Among them, the horizontal wing is a rotor blade, and the vertical blade is a cyclorotor blade.

2. The integrated annular wing according to claim 1, characterized in that The rotor blade is of a symmetric airfoil or an asymmetric airfoil, and the cross-section of the cyclorotor blade is of a symmetric airfoil.

3. The integrated annular wing according to claim 1, characterized in that, The flexible connection section is a hinge shaft wrapped with 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 cyclorotor blade.

4. The integrated annular wing according to claim 1, wherein, It further includes a drive shaft for driving the integrated annular wing to rotate axially.

5. The integrated annular wing according to claim 4, wherein, The rotor blade is connected to the rotor shaft through a hinge, and the drive shaft is connected to the rotor shaft.

6. The integrated annular wing according to claim 5, characterized in that, The hinge adopts an axial hinge of a helicopter rotor hinge system.

7. The integrated annular wing according to claim 1, characterized in that, It further includes a pitch change disk, which is connected to the root of each rotor blade through a mechanical link for controlling the angle of attack of the rotor blade at each phase.

8. The integrated annular wing according to claim 7, characterized in that, An eccentric rotating disk is 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 cyclorotor blade through a pull rod. The pull rod can pull the cyclorotor blade to rotate around its own axis, thereby controlling the thrust direction and magnitude of the cyclorotor blade.

9. The integrated annular wing according to claim 8, characterized in that, The rotation period of the drive shaft is the same as the periods of the eccentric rotating disk and the pitch change disk.

10. An aircraft, characterized in that, The integrated annular wings described in any one of claims 1-9 are installed on the left and right sides of the aircraft.

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