Wing integrated with distributed ducted fan

Abstract

The present invention relates to a wing integrated with a distributed ducted fan. The wing integrated with a distributed ducted fan comprises a distributed ducted fan integrated to an inner section wing of the wing, a nacelle partially surrounding the distributed ducted fan, and a lift equalization device provided at an outboard end of the nacelle in a spanwise direction, wherein the lift equalization device comprises at least one flap and the at least one flap generates a device lift over a device spanwise length of the lift equalization device in the spanwise direction.

Description

Technical Field

[0001] This invention relates to an airfoil integrating a distributed ducted fan, and more particularly to a lift equalization device on the distributed ducted fan of an airfoil. This invention belongs to the field of aircraft wing design. Background Technology

[0002] By integrating the engines into the wing, the nacelle side of the wing can be blended with the wing surface, reducing form drag, friction drag, and interference drag. Under high thrust conditions, the engines exert beneficial interference on the wing, enhancing lift. Furthermore, multiple engines arranged in an array can provide redundancy, improving aircraft safety to some extent.

[0003] The existing airfoil with integrated distributed ducted fans does not meet the lift-to-drag ratio design target.

[0004] The inventors believed that the drag of the wing was still too high and that it was necessary to further reduce the drag of the wing in order to improve the lift-to-drag ratio.

[0005] The downward force exerted by an airfoil on the airflow field is essentially the reaction force of lift, which is also the source of lift. Therefore, the spanwise distribution of the downward force exerted by the airfoil on the airflow field is the same as the spanwise distribution of lift, and the spanwise distribution of downwash velocity is also the same as the spanwise distribution of lift. The downwash velocity causes the lift of the airfoil to deflect rearward, and the resulting drag component is called induced drag. Therefore, the lift distribution affects induced drag.

[0006] According to Prandtl's lift line theory (1918), induced drag is minimized when the spanwise distribution of lift (downwash velocity) is an ideal ellipse. Therefore, the inventors believed that designing the wing so that its spanwise lift distribution curve conforms as closely as possible to an ideal ellipse is a more effective way to reduce induced drag.

[0007] The inventors discovered that on aircraft with conventional wings, the spanwise lift distribution curve can be easily altered by finely adjusting the airfoil to meet design requirements. However, on aircraft with distributed ducted fans mounted on the wings, the following challenges exist:

[0008] 1. The ducted fan nacelle installed on the inner section of the wing generates a large amount of lift, which is reflected in the wing's spanwise lift distribution curve as the lift of the inner section of the wing exceeds the ideal elliptical curve.

[0009] 2. The ducted fan nacelle ends at the mid-span section of the wing, where lift also disappears, leaving a steep step shape on the wing's lift-span distribution curve, generating significant induced drag.

[0010] 3. The inventors discovered that if the stepped shape of the lift distribution curve is counteracted by adjusting the spanwise variation of the wing airfoil, it will lead to wing shape distortion, posing a risk of low structural efficiency or even inability to manufacture. Previous attempts to improve lift distribution by increasing the outer wing twist angle resulted in the outer wing stalling first at high angles of attack, which worsened the stall characteristics, and the wing twist was too large, making the spars impossible to manufacture industrially.

[0011] Therefore, there is still a need for further improvements to the structure of the wing with integrated distributed ducted fans. Summary of the Invention

[0012] The purpose of this invention is to improve the lift distribution curve of an aircraft with an integrated distributed ducted fan nacelle, making it closer to an ideal elliptical curve, thereby reducing induced drag.

[0013] To address the aforementioned problems in the prior art, the inventors provide an airfoil integrating a distributed ducted fan, including a lift equalization device, which fills in the steps on the lift distribution curve, making the lift distribution curve closer to an ideal elliptical curve.

[0014] In the first example of the wing integrated with a distributed ducted fan, the wing integrated with a distributed ducted fan includes: a distributed ducted fan integrated into the inner section of the wing; a nacelle partially surrounding the distributed ducted fan; and a lift equalizer disposed at the outer end of the nacelle in the spanwise direction, wherein the lift equalizer includes at least one blade, and the at least one blade generates device lift along the device spanwise length of the lift equalizer in the spanwise direction.

[0015] In the second example of the wing integrated with a distributed ducted fan, the first example may be included, wherein the lift equalization device is configured such that the lift of the device gradually decreases outward in the spanwise direction.

[0016] In the third example of the wing integrated with the distributed ducted fan, one or more of the first and second examples may be included, wherein the nacelle has a spanwise length in the spanwise direction, and the spanwise starting installation position of the nacelle is the zero spanwise position of the wing, and the spanwise starting installation position of the lift equalizer is 0.7 to 1.5 times the spanwise length of the nacelle from the zero spanwise position.

[0017] In the fourth example of the wing integrated with the distributed ducted fan, one or more of the first to third examples may be included, the nacelle having a nacelle height in the altitude direction, and the initial height installation position of the nacelle being the zero altitude position of the wing, and the distance in the altitude direction between the initial height installation position of the lift equalizer and the zero altitude position is 0.3 to 1.5 times the nacelle height.

[0018] In the fifth example of the wing integrated with a distributed ducted fan, one or more of the first to fourth examples may be optionally included, and the wing integrated with the distributed ducted fan further includes:

[0019] In the sixth example of the wing integrated with a distributed ducted fan, one or more of the first to fifth examples may be included, wherein the nacelle has a spanwise length in the spanwise direction, and the spanwise length of the lift equalizer in the spanwise direction is in the range of 5% to 50% of the nacelle spanwise length.

[0020] In the seventh example of the wing integrated with a distributed ducted fan, one or more of the first to sixth examples may be included, wherein the nacelle has a nacelle flow length in the flow direction, and the lift equalization device has a device flow length in the flow direction that is in the range of 30%-150% of the nacelle flow length.

[0021] In the eighth example of the wing integrated with a distributed ducted fan, one or more of the first to seventh examples may be included, wherein the lift equalization device comprises a single blade, and the dihedral angle of the single blade is greater than -45°.

[0022] In the ninth example of the wing integrated with a distributed ducted fan, one or more of the first to eighth examples may be included, with an end plate provided at the outer end of at least one wing segment.

[0023] In the tenth example of the wing integrated with a distributed ducted fan, one or more of the first to ninth examples may be included, and at least one blade of the lift equalization device has an outward twist angle.

[0024] The wing of the present invention integrates a distributed ducted fan, which generates lift by installing a lift equalization device on the outside of the distributed ducted fan, filling the step on the lift distribution curve of the wing, so that the lift distribution curve is close to an ideal elliptical curve. Attached Figure Description

[0025] To describe embodiments of the above and other features of the present invention, a more detailed description of the invention will be presented with reference to exemplary embodiments of the invention shown in the accompanying drawings. It is to be understood that these drawings depict only exemplary embodiments of the invention and should not be considered as limiting its scope; the invention will be described and explained using the drawings and with the aid of additional features and details. In the drawings:

[0026] Figure 1 This is a perspective view of an airfoil integrating a distributed ducted fan according to an embodiment of the present invention;

[0027] Figure 2 It is based on Figure 1 A front view of wing 2;

[0028] Figure 3 It is based on Figure 1 A top view of wing 2;

[0029] Figure 4 This is a perspective view of a lift equalization device for an airfoil according to another embodiment of the present invention;

[0030] Figure 5 This is a perspective view of a lift equalization device for an airfoil according to yet another embodiment of the present invention;

[0031] Figure 6 yes Figure 5 A front view of the lift equalization device on the wing;

[0032] Figure 7 The diagram schematically illustrates the spanwise lift distribution of an existing wing with integrated distributed ducted fans.

[0033] Figure 8 A schematic diagram illustrating the lift spanwise distribution of an airfoil integrated with a distributed ducted fan according to the present invention; and

[0034] Figure 9 An example curve illustrating the lift spanwise distribution of an airfoil with an integrated distributed ducted fan according to the present invention is shown.

[0035] The accompanying drawings are drawn roughly to scale; however, the dimensions in the drawings are merely schematic and do not need to be drawn strictly to scale, but are intended to make the illustration clearer. In other embodiments, other relative dimensions may be used.

[0036] Throughout this and all subsequent content, the same features appearing in different figures are indicated by the same or similar reference numerals.

[0037] List of reference numerals in the attached diagram:

[0038] 1. Fuselage

[0039] 2. Wings

[0040] 3 Distributed ducted fans

[0041] 4. Nacelles

[0042] 5. Lift Equalization Device

[0043] 51 Single winglets

[0044] 52 First Wing

[0045] 53 Second Wing

[0046] 54 end plate

[0047] 55. Outer wing twist angle

[0048] A0 Zero-transition position

[0049] A1 Spanning initial installation position of lift equalization device 5

[0050] B0 Zero Height Position

[0051] B1 Height starting installation position of lift equalization device 5

[0052] Hdc Nacelle Height

[0053] Sdc nacelle span

[0054] Szz device spanwise length

[0055] Ldc nacelle flow length

[0056] Lzz device flow length

[0057] Fdc Nacelle Lift

[0058] Fjy wing lift

[0059] Fzz device lift

[0060] Cdc nacelle curve

[0061] Cjy wing curve

[0062] Czz device curve

[0063] Cty Ideal Elliptic Curve

[0064] C1 First Curve

[0065] C2 Second Curve Detailed Implementation

[0066] First, this invention primarily relates to structures related to distributed ducted fan arrays in the field of aircraft wing design. In particular, this invention relates to structures for reducing drag on aircraft wings.

[0067] The term “integrated into” as used in this article is intended to describe a component that is directly connected to another component and is able to remain as a whole, so that forces can be transmitted from one component to another.

[0068] The term “enclosure” as used in this article is intended to describe how one component isolates another component from the external environment in a specified direction, protecting it from the forces of the external environment.

[0069] The directional term “spanning direction” used in this article is intended to describe the direction of wing extension, and “spanning direction outward” is intended to describe the direction of extension from the fuselage to the wingtip.

[0070] The directional term “flow direction” used in this article is intended to describe the direction of motion of the incoming airflow facing the wing.

[0071] The directional terms used herein, such as “top,” “bottom,” “upper,” “lower,” “inner,” “inward,” “outer,” and “outward,” are used to assist in describing the orientation of the invention according to the embodiments illustrated in the figures. Unless otherwise stated, such as “horizontal direction,” “direction of gravity,” etc., the directional terms are not absolute up, down, horizontal, vertical, etc., and should not be construed as limiting the invention to any particular direction.

[0072] The terms “including,” “having,” “comprising,” and variations thereof, as used herein, are intended as open-ended transitional phrases, terms, or words that require the presence of a specified component / step, but also allow for the presence of other components / steps.

[0073] In this invention, unless explicitly stated otherwise, the terms “first,” “second,” etc., are not intended to indicate any difference in order, position, quantity, or importance, but are merely used as labels to distinguish different positions or components.

[0074] The terms “approximately” and “roughly” can be used to include any numerical value that can vary without altering its fundamental function. Generally, the terms “approximately” and “roughly” can refer to plus or minus 10% of the number referred to. When used with ranges, “approximately” and “roughly” also disclose a range defined by the absolute values ​​of two endpoints; for example, “approximately 2 to approximately 4” also discloses a range “from 2 to 4”. All ranges disclosed herein include the endpoints stated and can be combined independently (e.g., the range “from 2 to 4” includes endpoints 2 and 4 as well as all intermediate values).

[0075] The numerical values ​​used herein should be understood to include the same numerical values ​​when reduced to the same number of significant digits, as well as numerical values ​​that differ from those determined by conventional measurement techniques of the type described in this application by an experimental error.

[0076] Finally, the numerical values ​​given in the various embodiments are merely examples and are not intended to limit the scope of the invention.

[0077] In one non-limiting example, the wing 2 of the present invention includes a distributed ducted fan 3 on the inner section of the wing near the fuselage 1.

[0078] The distributed ducted fan 3 can be installed above the wing 2, and the lower surface of the nacelle 4 of the distributed ducted fan 3 can be connected face-to-face with the upper surface of the wing 2. There can be more than one distributed ducted fan 3 on each side of the wing 2, and multiple fans can be set according to actual lift requirements, such as two, three or more.

[0079] In a non-limiting example, the wing 2 of the present invention includes a nacelle 4 that partially surrounds a distributed ducted fan 3. Specifically, the nacelle 4 is open in the flow direction of the wing 2 and surrounds the distributed ducted fan 3 in the spanwise and height directions.

[0080] Preferably, each of the multiple distributed ducted fans 3 is housed in a corresponding nacelle 4, and the nacelles 4 are connected to each other as a whole on the wing 2.

[0081] In a non-limiting example, the wing 2 of the present invention includes a lift equalization device 5, which is disposed at the outer end of the nacelle 4 in the spanwise direction. Since the distributed ducted fan 3 and the corresponding nacelle 4 are disposed above the wing 2, the lift equalization device 5 is also disposed above the wing 2.

[0082] The lift equalization device 5 may include at least one blade 51, and the at least one blade 51 can generate device lift Fzz along the device spanwise length Szz in the spanwise direction of the lift equalization device 5. Multiple blades 51 may be provided according to actual lift requirements, and the device lift Fzz of the lift equalization device 5 may be set according to actual lift requirements.

[0083] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0084] Figure 1 A perspective view of a wing 2 integrated with a distributed ducted fan 3 according to an embodiment of the present invention is shown schematically.

[0085] In this embodiment, the distributed ducted fan 3 is preferably provided with a row of five fans arranged in an array, and the nacelle 4 is an integral nacelle with a long strip shape in the presentation direction and a generally wavy upper surface corresponding to the fans.

[0086] In this embodiment, the lift equalization device 5 includes a single blade 51, which is curved upwards. It can be understood that the specific shape of the blade of the lift equalization device 5 can be set according to the actual lift requirements.

[0087] Figure 2 Schematic illustration based on Figure 1 Front view of wing 2.

[0088] First, refer to Figure 2 Describe the installation position of the lift equalization device 5 in the spanwise direction.

[0089] like Figure 2 As shown, the nacelle 4 has a spanwise length Sdc in the spanwise direction, and the initial spanwise mounting position of the nacelle 4 is the zero spanwise position A0 of the wing 2, where the zero spanwise position A0 is close to the outer periphery of the fuselage 1. In this example, the zero spanwise position A0 is close to the fuselage 1. It can be understood that the initial spanwise mounting position of the nacelle 4 is not limited to this, and it can also be set at other positions on the wing 2 as needed.

[0090] In this example, the spanwise starting installation position A1 of the lift equalization device 5 is located at the outer end of the spanwise direction of the nacelle 4. Specifically, the distance between the spanwise starting installation position A1 of the lift equalization device 5 and the zero spanwise position A0 is the spanwise length Sdc of the nacelle 4.

[0091] However, it is understandable that, based on actual needs and the goal of making the nacelle 4's shape and the lift distribution curve conform as closely as possible to an ideal elliptical curve, the distance in the spanwise direction between the initial spanwise installation position A1 of the lift equalization device 5 and the zero spanwise position A0 can be 0.7 to 1.5 times the spanwise length Sdc of the nacelle, preferably 0.9 to 1 times. Specifically, the initial spanwise installation position A1 of the lift equalization device 5 can be oriented towards... Figure 2 It moves slightly inward and is located on the generally wavy upper surface of the top wall of the nacelle 4 of the fan 3, which extends outward.

[0092] Secondly, refer to Figure 2 Describe the installation position of the lift equalization device 5 in the height direction.

[0093] like Figure 2 As shown, the nacelle 4 has a nacelle height Hdc in the vertical direction, and the initial installation position of the nacelle 4 is the zero-height position B0 of the wing 2, where the zero-height position B0 is close to the upper surface of the wing 2. In this example, the zero-height position B0 is in close contact with the wing 2. Therefore, the lower surface of the nacelle 4 of the distributed ducted fan 3 is in face-to-face contact with the upper surface of the wing 2. It can be understood that the initial installation position of the nacelle 4 is not limited to this, and it can also be set at other positions on the wing 2 as needed.

[0094] In this example, the initial height installation position B1 of the lift equalization device 5 is located above the outer end of the nacelle 4, near the top. Specifically, the distance between the initial height installation position B1 of the lift equalization device 5 and the zero height position B0 is 0.9 times the nacelle height Hdc.

[0095] However, it is understood that, based on actual needs and considering the shape and structural stress of the nacelle 4, the distance in the height direction between the initial installation position B1 of the lift equalization device 5 and the zero-height position B0 can be 0.3 to 1.5 times the nacelle height Hdc, preferably 0.8 to 1 times. Specifically, this initial installation position B1 of the lift equalization device 5 can be oriented towards... Figure 2 It moves slightly up and down and is located in the middle or top of the side wall of the nacelle 4 of the fan 3 that extends outward.

[0096] Then, refer to Figure 2 Describe the length of the lift equalization device 5 in the spanwise direction.

[0097] like Figure 2 As shown, the nacelle 4 has a nacelle spanning length Sdc in the spanning direction, and the lift equalization device 5 has a device spanning length Szz in the spanning direction that is approximately 10% of the nacelle spanning length Sdc.

[0098] It is understood that the spanwise length Szz of the device can be within the range of 5%-50% of the spanwise length Sdc of the nacelle, preferably within the range of 10%-20%, so that the overall lift spanwise distribution curve of the wing 2 in the spanwise direction conforms to the ideal elliptical curve as much as possible.

[0099] Then, refer to Figure 2 Describe the dihedral angle Γ of the lift equalization device 5.

[0100] like Figure 2 As shown, the lift equalization device 5 includes a single blade 51 with an anhedral angle Γ of 15°. The anhedral angle Γ is preferably greater than -45°, and more preferably greater than 0°, to avoid excessive interference with the airflow of the wing 2.

[0101] Figure 3 Schematic illustration based on Figure 1 A top view of wing 2. (Refer to...) Figure 3 Describe the length of the lift equalization device 5 in the flow direction.

[0102] like Figure 3 As shown, the nacelle 4 has a nacelle flow length Ldc in the flow direction, and the lift equalization device 5 has a device flow length Lzz in the flow direction that is approximately 50% of the nacelle flow length Ldc.

[0103] It is understood that the flow length Lzz of the device can be within the range of 30%-150% of the flow length Ldc of the nacelle, preferably within the range of 50%-100%, to generate the required lift, so that the overall lift spanwise distribution curve of the wing 2 in the wingspan direction conforms as closely as possible to the ideal elliptical curve.

[0104] Preferably, in this practical example, as the spanwise direction moves outward, the flow length (chord length) Lzz of the device gradually decreases, which reduces the area of ​​the lift equalization device 5 and the lift gradually decreases, so that the overall lift spanwise distribution curve of the wing 2 in the spanwise direction conforms as closely as possible to the ideal elliptical curve.

[0105] Preferably, in this example, the individual winglets 51 of the lift equalization device 5 have an outer wing twist angle portion 55, specifically, the sweep angle gradually increases in the extension direction to further improve the lift distribution, and the winglet shape design conforms to the outer end twist angle of the wing 2.

[0106] Figure 4 A perspective view of a lift equalization device 5 for a wing 2 according to another embodiment of the present invention is shown schematically.

[0107] In this embodiment, the lift equalization device 5 includes a single winglet 51, which is flat in shape, and has an end plate 54 at the outer end in the spanwise direction to reduce the wingtip vortex of the lift equalization device itself and further reduce drag.

[0108] Figure 5 A perspective view of the lift equalization device 5 of the wing 2 according to another embodiment of the present invention is shown schematically. Figure 6 Schematic illustration based on Figure 5 A front view of the lift equalization device 5 of the wing 2.

[0109] The lift equalization device 5 includes a first winglet 52 and a second winglet 53 located above the first winglet in the height direction, and the dihedral angle Γ of the first winglet 52 is -15°. When the lift equalization device 5 has two or more winglets, the dihedral angle Γ is measured with the lowermost winglet as a reference, and as mentioned above, the dihedral angle Γ is preferably greater than -45°, more preferably greater than 0°, to avoid excessive interference with the airflow of the wing 2.

[0110] Figure 7The diagram schematically illustrates the spanwise lift distribution curve of an existing wing integrated with a distributed ducted fan. In the diagram, the horizontal axis represents the position of the wing along the spanwise direction, and is shown from left to right from the fuselage to the wingtip, but specific values ​​are not labeled. The vertical axis represents the total lift of the wing, increasing in the direction of the arrow, but no specific value is indicated. Wing 2 generates wing lift Fjy, represented by the wing curve Cjy on the spanwise lift distribution curve of wing 2; the nacelle 4 of the ducted fan 3 generates nacelle lift Fdc, represented by the nacelle curve Cdc with an outer contour on the spanwise lift distribution curve of wing 2.

[0111] On the inner section of wing 2, the nacelle 4 of the ducted fan 3 will generate nacelle lift Fdc. When superimposed with the wing lift Fjy generated by wing 2, the total lift of the inner section of wing 2 is shown on the spanwise lift distribution curve of wing 2 as exceeding the ideal elliptic curve Cty.

[0112] The nacelle 4 ends at the mid-section of the wing 2, and the nacelle lift Fdc also disappears, leaving a steep step shape on the lift spanwise distribution curve of the wing 2. Specifically, a steep step shape is formed from the transition from the nacelle curve Cdc to the wing curve Cjy. This step shape will generate a large induced drag.

[0113] Figure 8 The diagram schematically illustrates the spanwise lift distribution curve of an airfoil integrated with a distributed ducted fan according to the present invention. In the diagram, the horizontal axis represents the position on the airfoil in the spanwise direction, and is shown from left to right from the fuselage to the wingtip, but specific values ​​are not indicated. The vertical axis represents the total lift of the airfoil, and increases in the direction of the arrow, but specific values ​​are not indicated. The lift equalization device 5 generates device lift Fzz, which is represented by the device curve Czz with an outer contour on the spanwise lift distribution curve of the airfoil 2.

[0114] The lifting force equalization device 5 provides a device curve Czz with lifting force Fzz, which effectively eliminates the step shape of the lifting force distribution curve, making the lifting force distribution curve close to the ideal elliptical curve Cty.

[0115] Figure 9 An example lift spanwise distribution curve of an airfoil with an integrated distributed ducted fan according to the present invention is schematically shown. In the figure, the horizontal axis represents the position on the airfoil in the spanwise direction, and is shown from left to right from the fuselage to the wingtip, but no specific values ​​are indicated. The vertical axis represents the total lift of the airfoil, and increases in the direction of the arrow, but no specific value is indicated. The lift spanwise distribution curve of the airfoil 2 without the application of the lift equalization device 5 is represented by the first curve C1, and the lift spanwise distribution curve of the airfoil 2 with the application of the lift equalization device 5 is represented by the second curve C2.

[0116] Preferably, the lift equalizer 5 is configured such that the lift Fzz gradually decreases outward along the spanwise direction, which is suitable for filling the step shape on the lift distribution curve of the wing after superimposing the nacelle lift Fdc and the wing lift Fjy. Compared with the first curve C1 without the application of the lift equalizer 5, the second curve C2 with the application of the lift equalizer 5 is more in line with the ideal elliptic curve Cty.

[0117] After applying the lift equalization device 5 according to this application, the lift spanwise distribution of the wing 2 is improved, and during the cruise phase of the aircraft, the lift-to-drag ratio is increased by more than 10%, meeting the design target, and thus the range is increased by more than 9%.

[0118] In order to make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention have been clearly and completely described above in conjunction with the specific embodiments and accompanying drawings.

[0119] Although various embodiments have been described above, it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of them, and are presented by way of example rather than limitation. It will be apparent to those skilled in the art that the disclosed subject matter may be implemented in other specific forms without departing from its spirit and essential characteristics.

[0120] In this process, various elements important to the present invention or elements conducive to further development of the present invention will be mentioned in the specific examples. However, some of these elements may also be used to further develop the present invention when departing from the content and other features of the corresponding examples. Therefore, the embodiments described above are considered exemplary in all respects and not restrictive, and are not intended to limit the present invention in any way.

[0121] Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this invention. This disclosure also includes various modifications and equivalent variations. In addition, various combinations and methods, further including only one element, one or more or less other combinations and methods, also fall within the scope and concept of this disclosure.

Claims

1. A wing integrating a distributed ducted fan, the wing integrating the distributed ducted fan (2) comprising: Distributed ducted fan (3), the distributed ducted fan (3) is integrated into the inner section of the wing (2); Nacelle (4), which partially surrounds the distributed ducted fan (3); as well as A lift equalization device (5) is provided at the outer end of the nacelle (4) in the spanwise direction, wherein the lift equalization device (5) includes at least one blade, and the at least one blade generates device lift (Fzz) in the device spanwise length (Szz) of the lift equalization device (5) in the spanwise direction. The lift equalization device (5) is configured such that the lift of the device gradually decreases outward in the spanwise direction, so that the overall lift spanwise distribution curve of the wing (2) in the spanwise direction conforms as much as possible to the ideal elliptical curve.

2. The wing integrating a distributed ducted fan according to claim 1, characterized in that, The nacelle (4) has a spanwise length (Sdc) in the spanwise direction, and the spanwise starting installation position of the nacelle (4) is the zero spanwise position (A0) of the wing (2), and The distance between the spanwise starting installation position (A1) of the lift equalization device (5) and the zero spanwise position (A0) in the spanwise direction is 0.7 to 1.5 times the spanwise length (Sdc) of the nacelle.

3. The wing integrating a distributed ducted fan according to claim 1, characterized in that, The nacelle (4) has a nacelle height (Hdc) in the vertical direction, and the initial height installation position of the nacelle (4) is the zero-altitude position (B0) of the wing (2), and The distance between the initial height installation position (B1) of the lift equalization device (5) and the zero height position (B0) in the height direction is 0.3 to 1.5 times the nacelle height (Hdc).

4. The wing integrating a distributed ducted fan according to claim 1, characterized in that, The nacelle (4) has a nacelle spanning length (Sdc) in the spanning direction, and The spanwise length (Szz) of the lifting equalization device (5) in the spanwise direction is within 5%-50% of the spanwise length (Sdc) of the nacelle.

5. The wing integrating a distributed ducted fan according to claim 1, characterized in that, The nacelle (4) has a nacelle flow length (Ldc) in the flow direction, and The lift equalization device (5) has a device flow length (Lzz) in the flow direction that is 30%-150% of the nacelle flow length (Ldc).

6. The wing integrating a distributed ducted fan according to claim 1, characterized in that, The lift equalization device (5) includes a single winglet (51), and The dihedral angle (Γ) of the individual blade (51) is greater than -45°.

7. The wing integrating a distributed ducted fan according to claim 1, characterized in that, The lift equalization device (5) includes a first winglet (52) and a second winglet (53) located above the first winglet in the height direction, and The dihedral angle Γ of the first winglet (52) is greater than -45°.

8. The wing integrating a distributed ducted fan according to claim 1, characterized in that, An end plate (54) is provided at the outer end of at least one winglet.

9. The wing integrating a distributed ducted fan according to claim 1, characterized in that, At least one wing of the lift equalization device (5) has an external twist angle (55).

Images