Rotor wing and aircraft

Abstract

The utility model relates to a rotor wing and aircraft, including rotor wing main part, the rotor wing main part along X direction first end endpoint height is higher than second end endpoint height, the rotor wing main part is provided with the runner, the runner passes through the upper surface and lower surface of rotor wing main part along Z direction. The flow channel penetrating through the rotor wing body is formed in the rotor wing of the aircraft, low-speed airflow on the lower surface of the rotor wing is introduced to the upper surface of the rotor wing through the flow channel, the stall attack angle of the rotor wing is delayed, the lift-drag ratio is increased, shock wave resistance generated due to stall of the rotor wing is avoided, the aerodynamic characteristic of the rotor wing is improved, and power consumption of the rotor wing is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft rotors, in particular to a rotor and an aircraft. Background Art

[0002] The rotor includes a main rotor and a tail rotor. The main rotor is the most important power component on the aircraft, providing lift and pulling force during the flight state of the aircraft. The aerodynamic performance of the main rotor directly affects the flight and maneuverability of the aircraft. The aerodynamic force generated by the high-speed rotating main rotor is caused by the pressure difference after the air flow passes through the upper and lower surfaces of the blade. When the aircraft flies horizontally at a certain speed, the leading edge of the rotor enters the transonic region, and local supersonic flow is likely to occur on the upper surface of the blade tip, generating shock wave resistance, and the power required by the rotor increases greatly.

[0003] In the existing rotor, when the attitude amplitude of the aircraft is relatively large, the linear velocity of the rotor, especially the blade tip of the rotor, is relatively large, and it is easy to stall, resulting in the generation of shock wave resistance on the upper surface of the rotor, leading to loss of aerodynamic performance and increasing the power consumption of the rotor. Summary of the Utility Model

[0004] In order to solve the technical problem that when the linear velocity of the above-mentioned rotor is relatively large, shock wave resistance is easily generated on the upper surface of the rotor, increasing the power consumption of the rotor, the utility model provides a rotor and an aircraft.

[0005] To achieve the above object, the utility model provides a rotor, including a rotor main body. The height of the first end point of the rotor main body along the X direction is higher than the height of the second end point. A flow channel is opened on the rotor main body, and the flow channel penetrates the upper surface and the lower surface of the rotor main body along the Z direction.

[0006] Further, the rotor main body includes a first main body part, a gas circulation part and a second main body part. The flow channel is opened on the gas circulation part. The first main body part and the second main body part are connected to both ends of the gas circulation part. The airfoils of the first main body part, the gas circulation part and the second main body part are the same. The upper and lower ports of the flow channel are parallel to the upper and lower surfaces of the first main body part and the second main body part.

[0007] Further, the rotor main body further includes a connecting part. The connecting part is arranged on the second main body part, and the gas circulation part is connected to the second main body part at one end far from the connecting part.

[0008] Further, the junction of the flow channel and the rotor main body is set as an arc surface.

[0009] Further, the cross-sectional size of the flow channel along the Z direction is the same.

[0010] Further, the flow channel extends along the Y direction.

[0011] Further, the flow channel is of an inclined structure.

[0012] Further, in the X direction, the thicknesses at both ends of the rotor main body are different, and the lower end of the flow channel is farther from the end with a lower thickness of the rotor main body than the upper end of the flow channel.

[0013] Further, a plurality of the flow channels are arranged along the X direction.

[0014] Another object of this embodiment is to provide an aircraft, and the aircraft is provided with the above-mentioned rotor.

[0015] The above technical solution of the present utility model has the following advantages compared with the prior art:

[0016] (1) By providing a flow channel penetrating the rotor main body on the aircraft rotor, the flow channel introduces the low-speed air flow on the lower surface of the rotor to the upper surface, delays the stall angle of attack of the rotor, increases the lift-drag ratio, avoids the formation of shock wave drag due to rotor stall, improves the aerodynamic characteristics of the rotor, and reduces the power consumption of the rotor;

[0017] (2) The flow channel is arranged at one end of the rotor away from the connecting part, so that the flow channel is close to the rotor blade tip, and the linear velocity of the blade tip is the fastest, further avoiding the formation of shock wave drag. In addition, the flow channel is set as an inclined structure, and the inclination direction is defined to ensure that the gas flows smoothly in the flow channel, and the flow channel and the rotor main body are connected by an arc surface, further avoiding the generation of resistance, reducing the blade slipstream, and improving the aerodynamic efficiency of the rotor. Description of the Drawings

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the following drawings are only some embodiments of the present utility model. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0019] Figure 1 is a schematic structural diagram of the rotor of the present utility model;

[0020] Figure 2 is a side view of the rotor of the present utility model.

[0021] Description of the reference numerals in the drawings: Rotor main body - 1; First main body part - 11; Gas circulation part - 12; Second main body part - 13; Flow channel - 2; Arc surface - 3. Detailed Embodiments

[0022] To make the above objects, features, and advantages of the present utility model more apparent and understandable, the following provides a detailed description of the specific embodiments of the present utility model with reference to the accompanying drawings of the specification. Apparently, the described embodiments are only a part of the embodiments of the present utility model, rather than all of them. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0023] In the following description, numerous specific details are set forth to facilitate a thorough understanding of the present utility model. However, the present utility model may also be implemented in other ways different from those described herein. Those skilled in the art may make similar generalizations without departing from the connotation of the present utility model. Therefore, the present utility model is not limited by the specific embodiments disclosed below.

[0024] Secondly, the so-called "one embodiment" or "embodiment" herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation manner of the present utility model. The appearances of "in one embodiment" in different places in this specification do not all refer to the same embodiment, nor are they separate or alternative embodiments that are mutually exclusive of other embodiments.

[0025] The present utility model is described in detail in conjunction with schematic diagrams. When detailing the embodiments of the present utility model, for the convenience of explanation, the cross-sectional views showing the device structure will be enlarged locally out of the general proportion, and the schematic diagrams are only examples and should not limit the protection scope of the present utility model herein. In addition, in actual production, three-dimensional spatial dimensions including length, width, and depth should be included.

[0026] Meanwhile, in the description of the present utility model, it should be noted that the orientation or positional relationships indicated by terms such as "upper, lower, left, right, inner, and outer" are based on the orientation or positional relationships shown in the drawings. This is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or component referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present utility model. In addition, the terms "first, second, or third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0027] Unless otherwise clearly defined and limited in the present utility model, the terms "installation, connection, and coupling" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may also be a mechanical connection, an electrical connection, or a direct connection, or it may be indirectly connected through an intermediate medium, or it may be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0028] Embodiment 1

[0029] The flight of the aircraft is achieved through the high-speed rotation of the rotor. When the rotor blades rotate rapidly, the air flow velocity on the upper surface of the blade is relatively fast, resulting in a lower air pressure, while the air flow velocity on the lower surface of the blade is relatively slow, and the air pressure is higher. This pressure difference will form an upward lift force, enabling the rotorcraft to fly. During the flight of the aircraft, the aerodynamic performance of the rotor directly affects the flight and maneuverability. The aerodynamic performance covers the performance of the aircraft's lift, drag, lift-to-drag ratio, stall angle of attack, etc.; the lift-to-drag ratio refers to the ratio of the lift to the drag, that is, the lift coefficient to the drag coefficient, at the same angle of attack during the flight of the aircraft. The stall angle of attack refers to the angle of attack when the aircraft reaches the maximum lift coefficient. When exceeding this angle, the lift of the wing will drop sharply, causing the aircraft to lose control and enter the stall state. When the rotor enters the stall state, shock waves are generated on the rotor surface, resulting in a loss of starting performance.

[0030] The following refers to Figures 1 to 2 Describe a rotor according to an embodiment of the present invention, including a rotor main body 1. The height of the first end point of the rotor main body 1 along the X direction is higher than the height of the second end point. A flow channel 2 penetrating the upper and lower surfaces is provided on the rotor main body 1 along the Z direction, where the X direction is the radial direction of the rotor blade of the rotor main body 1, the Y direction is the length extension direction of the rotor main body 1, and the Z direction is the height direction of the rotor main body 1. The three directions are perpendicular to each other in pairs; in this embodiment, the rotor main body 1 is connected to the helicopter rotation axis, and the rotor main body 1 rotates clockwise. The height of the left end point of the rotor main body 1 along the X direction is higher than the height of the right end point. When the rotor main body 1 starts to rotate, the air flow passes through the upper and lower surfaces of the rotor main body 1, forming a pressure difference to achieve the flight of the helicopter. During the rotation process, since a flow channel 2 penetrating the upper and lower surfaces is provided on the rotor main body 1 along the Z direction, when the gas flows on the lower surface of the rotor main body 1, part of the gas flows from the flow channel 2 to the upper surface of the rotor main body 1. In addition, since the height of the left end point of the rotor main body 1 along the X direction is higher than the height of the right end point, and the rotor main body 1 rotates clockwise, it is convenient for the gas to flow in the flow channel 2. As a preference, a plurality of flow channels 2 are provided along the X direction, which can further accelerate the flow velocity of the upper surface of the rotor main body 1, increase the pressure difference between the upper and lower surfaces of the rotor main body 1, thereby enhancing the lift, delaying the stall angle of attack, and improving the aerodynamic efficiency of the rotor.

[0031] In one embodiment, refer to Figure 1, the rotor body 1 includes a first body part 11, a gas flow part 12 and a second body part 13. The flow channel 2 is formed on the gas flow part 12. The first body part 11 and the second body part 12 are connected to both ends of the gas flow part 12, so that the flow channel 2 is formed in the middle of the rotor body 1. The airfoils of the first body part 11, the gas flow part 12 and the second body part 13 are the same. The upper and lower ports of the flow channel 2 are parallel to the upper and lower surfaces of the first body part 11 and the second body part 13, ensuring the smoothness of the overall outer surface of the rotor body 1, avoiding resistance to gas flow caused by the surface structure, and avoiding reducing the lift-drag ratio of the rotor body 1.

[0032] In one embodiment, the rotor body 1 further includes a connecting part. The connecting part is arranged on the second body part 13. The gas flow part 12 is connected to the second body part 13 at one end far from the connecting part, so that the gas flow part 12 and the flow channel 2 are close to the blade tip position with a relatively high linear velocity of the rotor body 1. In the existing rotor, the chord line of the part near the blade tip is relatively flat, and the angle of attack is relatively small, resulting in an increase in shock wave resistance. If the attitude amplitude of the aircraft is relatively large, the linear velocity of the blade tip part is relatively high, which is likely to cause stall and lead to an increase in shock wave resistance. Therefore, setting the flow channel 2 at the blade tip position with a relatively high linear velocity can further increase the lift, improve the lift-drag ratio of the rotor, and thus improve the aerodynamic efficiency of the rotor.

[0033] In one embodiment, referring to Figure 2 , the junction of the flow channel 2 and the rotor body 1 is set as an arc surface 3 to ensure smoother gas flow. As a preference, the cross-sectional size of the flow channel 2 in the Z direction is the same, and the cross-sectional radii of the upper and lower ends and the middle of the flow channel 2 are the same, avoiding continuous changes in the gas flow velocity in the flow channel 2 and affecting the pressure difference on the surface of the rotor body 1; as a preference, the flow channel 2 extends in the Y direction to increase the lift at different positions of the rotor body 1, and thus improve the aerodynamic efficiency of the rotor.

[0034] In one embodiment, referring to Figure 2 , the flow channel 2 is an inclined structure. In the X direction, the thicknesses at both ends of the rotor body 1 are different. The lower end of the flow channel 2 is farther from the end with a lower thickness of the rotor body 1 than the upper end of the flow channel 2. The existing rotor airfoils mainly include rectangles. The conventional NACA series are a series of airfoils developed by the National Advisory Committee for Aeronautics in the United States. In order to further increase the pressure difference between the upper and lower surfaces of the rotor body, in this embodiment, the two ends of the rotor body 1 are set with different thicknesses. Among them, in the X direction, the thickness of the left end of the rotor body 1 is greater than the thickness of the right end of the rotor body 1, thereby increasing the flow velocity of the air flow on the surface of the rotor body 1. At this time, the flow channel 2 is an inclined structure, and the lower end of the flow channel 2 is farther from the end with a lower thickness of the rotor body 1 than the upper end of the flow channel 2, further ensuring that the air flow flows to the side with a faster flow velocity, further increasing the lift, and reducing the power consumption of the rotor.

[0035] Embodiment Two

[0036] Different from the above embodiments, this embodiment provides an aircraft, which is provided with the above-mentioned rotors, reducing the energy consumption required during the flight of the aircraft and reducing the flight cost.

[0037] Note that the above is only the preferred embodiment of the present invention and the technical principles applied. Those skilled in the art will understand that the present invention is not limited to the specific embodiments here, and various obvious changes, re-adjustments and substitutions can be made by those skilled in the art without departing from the protection scope of the present invention. Therefore, although the present invention has been described in more detail through the above embodiments, the present invention is not limited to the above embodiments only. Without departing from the concept of the present invention, more other equivalent embodiments can be included, and the scope of the present invention is determined by the scope of the appended claims.

Claims

1. A rotor, characterized in that: The invention comprises a rotor body (1), wherein the height of a first end point of the rotor body (1) along the X direction is higher than the height of a second end point, and a flow channel (2) is provided on the rotor body (1), wherein the flow channel (2) penetrates the upper surface and the lower surface of the rotor body (1) along the Z direction.

2. The rotor according to claim 1, characterized in that: The rotor body (1) comprises a first main body portion (11), a gas circulation portion (12) and a second main body portion (13); the flow channel (2) is arranged on the gas circulation portion (12); the first main body portion (11) and the second main body portion (13) are connected at two ends of the gas circulation portion (12); the first main body portion (11), the gas circulation portion (12) and the second main body portion (13) have the same airfoil profile; and the upper and lower ports of the flow channel (2) are parallel to the upper and lower surfaces of the first main body portion (11) and the second main body portion (13).

3. The rotor according to claim 2, characterized in that: The rotor body (1) further comprises a connecting portion, which is arranged on the second body part (13), and the gas circulation part (12) is connected to the second body part (13) at an end away from the connecting portion.

4. The rotor according to claim 1, characterized in that: The intersection of the flow channel (2) and the rotor body (1) is arranged as an arc surface (3).

5. The rotor according to claim 4, characterized in that: The cross-sections of the flow channels (2) along the Z direction are of the same size.

6. The rotor according to claim 1, characterized in that: The flow channel (2) extends along the Y direction.

7. The rotor according to claim 1, characterized in that: The flow channel (2) is an inclined structure.

8. The rotor according to claim 7, characterized in that: In the X direction, the thicknesses of the two ends of the rotor body (1) are different, and the lower end of the flow channel (2) is farther away from the end of the rotor body (1) with a lower thickness than the upper end of the flow channel (2).

9. The rotor according to claim 1, characterized in that: A plurality of flow channels (2) are arranged along the X direction.

10. An aircraft, characterized in that: A rotor comprising the rotor described in any one of claims 1 to 9.

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