Flap vortex disturbing device and wing assembly comprising flap vortex disturbing device

Abstract

The present invention provides a flap vortex disturbing device and a wing assembly (10) comprising the flap vortex disturbing device, which can disturb vortex generated at the inner and outer side end edges of a flap, thereby suppressing the reduction of lift force and the advance of stall of an aircraft, and a wing assembly (10) comprising the flap vortex disturbing device. The flap vortex interference devices (120 and 140) interfere vortexes of trailing edge flaps (210 and 220) arranged on the trailing edge of a fixed wing (100) when an aircraft flies at a high angle of attack, and the flap vortex interference devices are correspondingly arranged at the inner and outer side end edges (211 and 221) of the trailing edge flaps respectively and are in an obtuse triangle shape. And gaps for air flow to circulate are respectively formed between the flap vortex interference devices (120 and 140) and the inner and outer side end edges (211 and 221) of the trailing edge flap.

Description

Technical Field

[0001] This invention relates to the field of aircraft aerodynamic design, and more specifically to a flap vortex interference device and a wing assembly including the flap vortex interference device. Background Technology

[0002] In the past, when aircraft took off and landed, the flaps were typically extended from the fixed wing and the aircraft flew at high angles of attack. At this time, vortices often formed at the inner and outer edge edges of the flaps, rolling from the lower wing surface to the upper wing surface, producing harmful aerodynamic effects. The deterioration of airflow at the inner and outer edge edges of the flaps may cause airflow separation, reduced lift, and premature stall of the aircraft. Summary of the Invention

[0003] The present invention was made to solve the above-mentioned technical problems, and its purpose is to provide a flap vortex interference device and a wing assembly including the flap vortex interference device, which can interfere with the vortices generated at the inner and outer edge edges of the flap, thereby suppressing the situation of reduced lift and premature aircraft stall.

[0004] The first aspect of the present invention provides a flap vortex interference device that interferes with the vortices of a trailing edge flap provided on the trailing edge of a fixed wing during high angle of attack flight of an aircraft. The flap vortex interference device is respectively provided at the inner and outer end edges of the trailing edge flap and is in the shape of an obtuse triangle. A slit for airflow is formed between the flap vortex interference device and the inner and outer end edges of the trailing edge flap.

[0005] According to the above structure, the flap vortex interference devices are respectively disposed at the inner and outer end edges of the trailing edge flap, and are in the form of obtuse triangles. Slots for airflow are formed between the flap vortex interference devices and the inner and outer end edges of the trailing edge flap. Therefore, when the aircraft flies at high angles of attack, the high-speed jet generated in these slots can impact the airflow separation point area at the inner and outer end edges of the inner and outer flaps, thereby suppressing vortices at this location. This can suppress the decrease in lift and premature stall caused by airflow separation.

[0006] The flap vortex interference device of the second aspect of the present invention is based on the flap vortex interference device of the first aspect of the present invention. The trailing edge flap includes an inner trailing edge flap and an outer trailing edge flap. The flap vortex interference device includes: an inner flap vortex interference device, which protrudes from the connection between the fuselage and the fixed wing corresponding to the inner end edge of the inner trailing edge flap; and

[0007] An outer flap vortex interference device, which protrudes from the trailing edge of the fixed wing corresponding to the outer end edge of the outer trailing edge flap.

[0008] According to the above structure, the trailing edge flap includes two flaps, namely the inner trailing edge flap and the outer trailing edge flap. By setting the inner flap vortex interference device and the outer flap vortex interference device at the inner end edge of the inner trailing edge flap and the outer end edge of the outer trailing edge flap respectively, the flap vortex interference device can be accurately set at the location where the vortex is generated, namely the inner end edge of the inner trailing edge flap and the outer end edge of the outer trailing edge flap, so as to accurately suppress harmful vortices.

[0009] The flap vortex interference device of the third aspect of the present invention is based on the flap vortex interference device of the second aspect of the present invention. The inner flap vortex interference device includes: a first side portion extending outward along the trailing edge of the fixed wing; a second side portion extending along the fuselage towards the trailing edge; and a third side portion connecting the first side portion and the second side portion as the longest side of an obtuse triangle.

[0010] Based on the above structure, the inward flap vortex interference device is designed as an obtuse triangle to prevent interference between the inward trailing edge flap and the inward flap vortex interference device when the flap deploys backward and downward. Instead, a channel for airflow is formed between the inward flap vortex interference device and the inner edge of the inward trailing edge flap. When the aircraft flies at a high angle of attack, a high-speed jet is generated in the channel. This high-speed jet impacts the airflow separation point area at the inner edge of the inward flap, thereby suppressing vortices at that location. This helps to prevent reduced lift and premature stall caused by airflow separation.

[0011] The flap vortex interference device of the fourth aspect of the present invention is based on the flap vortex interference device of the third aspect of the present invention. If the chord length of the portion of the inner trailing edge flap that extends beyond the trailing edge of the fixed wing when it is deployed from the trailing edge of the fixed wing is set as C, the length of the first side in the wingspan direction is set as H1, and the length of the second side in the chord direction is set as L1, then the ratio of H1 / C is in the range of 30% to 60%, and the ratio of L1 / C is in the range of 30% to 60%.

[0012] According to the above structure, it can be ensured that the energy of the high-speed jet generated by the slot between the inner end edge of the inner trailing edge flap and the inner flap vortex interference device is sufficient to impact the airflow separation point area generated at the inner end edge, thereby suppressing the vortex generated there.

[0013] Moreover, it can also suppress interference between the inner flap vortex interference device and the inner trailing edge flap due to the inner flap vortex interference device being too large.

[0014] The flap vortex interference device of the fifth aspect of the present invention is based on the flap vortex interference device of the second aspect of the present invention. The outer flap vortex interference device includes: a fourth side portion extending inward along the trailing edge of the fixed wing; a fifth side portion extending along the trailing edge of the fixed wing; and a sixth side portion connecting the fourth side portion and the fifth side portion as the longest side of an obtuse triangle.

[0015] Based on the above structure, the outer flap vortex interference device is designed as an obtuse triangle to prevent interference between the outer trailing edge flap and the outer flap vortex interference device when the outer flap deploys backward and downward. Instead, a channel for airflow is formed between the outer flap vortex interference device and the outer edge of the outer trailing edge flap. When the aircraft flies at a high angle of attack, a high-speed jet is generated in the channel. This high-speed jet impacts the airflow separation point area at the outer edge of the outer flap, thereby suppressing vortices at that location. This helps to prevent reduced lift and premature stall caused by airflow separation.

[0016] The flap vortex interference device of the sixth aspect of the present invention is based on the flap vortex interference device of the fifth aspect of the present invention. If the chord length of the portion of the outer trailing edge flap that extends beyond the trailing edge of the fixed wing when it is deployed from the trailing edge of the fixed wing is set as C, the length of the fourth side in the wingspan direction is set as H2, and the length of the fifth side in the chord direction is set as L2, then the ratio of H2 / C is in the range of 30% to 60%, and the ratio of L2 / C is in the range of 30% to 60%.

[0017] Based on the above structure, it can be ensured that the energy of the high-speed jet generated in the slot between the outer edge of the outer trailing edge flap and the vortex interference device of the outer flap is sufficient to impact the airflow separation point area generated at the outer edge, thereby suppressing the vortex generated there.

[0018] Moreover, it can also suppress interference between the outer flap vortex interference device and the outer trailing edge flap due to the outer flap vortex interference device being too large.

[0019] The flap vortex interference device of the seventh aspect of the present invention is based on the flap vortex interference device of any one of the second to sixth aspects of the present invention, wherein the inner flap vortex interference device and the outer flap vortex interference device are formed in the shape of a flat plate and have the same thickness as the skin of the fixed wing.

[0020] According to the above structure, by forming the inner flap vortex interference device and the outer flap vortex interference device into flat plates, it is convenient to form a high-speed jet. Moreover, by forming their thickness to be the same as the thickness of the fixed wing skin, they will not bulge out of the fixed wing skin and cause additional aerodynamic drag.

[0021] The flap vortex interference device of the eighth aspect of the present invention is based on the flap vortex interference device of any one of the second to sixth aspects of the present invention, wherein the inner flap vortex interference device and the outer flap vortex interference device are respectively integrated with the fixed wing.

[0022] According to the above structure, the inner flap vortex interference device and the outer flap vortex interference device are integrated with the fixed wing, thus simplifying the manufacturing process.

[0023] A ninth aspect of the present invention provides a wing assembly connected to a fuselage, including a fixed wing and a trailing edge flap disposed at the trailing edge of the fixed wing, including a flap vortex interference device according to any one of the first to eighth aspects, wherein the trailing edge flap includes an inner trailing edge flap and an outer trailing edge flap, and the flap vortex interference device includes an inner flap vortex interference device and an outer flap vortex interference device, wherein the inner flap vortex interference device is correspondingly disposed at the inner end edge of the inner trailing edge flap, and the outer flap vortex interference device is correspondingly disposed at the outer end edge of the outer trailing edge flap, wherein a slot for airflow is formed between the inner flap vortex interference device and the inner end edge of the inner trailing edge flap, and between the outer flap vortex interference device and the outer end edge of the outer trailing edge flap.

[0024] Based on the above structure, by installing flap vortex interference devices at the locations where vortices are generated on the flaps—namely, the inner edge of the inner trailing edge flap and the outer edge of the outer trailing edge flap—and forming airflow channels, high-speed jets generated in these channels can impact the airflow separation points at the inner and outer edges of the flaps during high angle-of-attack flight, thereby suppressing vortices at these locations. This helps to prevent reduced lift and premature aircraft stall caused by airflow separation. Attached Figure Description

[0025] Figure 1 This is a partial top view schematically showing the installation location of the flap vortex interference device provided on the inner trailing edge flap and the outer trailing edge flap according to the first embodiment of the present invention.

[0026] Figure 2 This is a partial top view schematically showing the flap turbine interference device at the inner end edge of the inner trailing edge flap in the high-speed cruise configuration of the aircraft of this embodiment.

[0027] Figure 3 This is a partial top view schematically showing the flap turbine interference device at the inner edge of the outer trailing edge flap in the low-speed cruise configuration of the aircraft of this embodiment.

[0028] Figure 4This is a partial top view schematically showing the flap turbine interference device at the inner end edge of the inner trailing edge flap in the high-speed cruise configuration of the aircraft of this embodiment.

[0029] Figure 5 This is a partial top view schematically showing the flap turbine interference device at the inner edge of the outer trailing edge flap in the low-speed cruise configuration of the aircraft of this embodiment.

[0030] Figure 6 This is a coordinate graph showing the improvement in stall characteristics achieved by the flap vortex interference device of this embodiment.

[0031] Symbol Explanation

[0032] 10. Wing assembly; 100 fixed-wing aircraft; 110 Inner wing angle; 111 First inner wing edge; 112 Second inner wing edge; 120 Inner flap vortex interference device; 121 First side; 122 Second side; 123 Third side; 130° outer wing angle; 131 First outer wing edge; 132 Second outer wing edge; 140 Outer flap vortex interference device; 141. Fourth side; 142 Fifth side; 143. The sixth side; 200 flaps; 210 Inner trailing edge flap; 211 The inner end edge of the inner trailing edge flap; 220 Outer trailing edge flap; 221 The outer edge of the outer trailing edge flap; 300 fuselage. Detailed Implementation

[0033] The present invention will be further described below with reference to specific embodiments and accompanying drawings, but this should not be construed as limiting the scope of protection of the present invention.

[0034] First, this invention primarily relates to the field of aircraft aerodynamic design, and more particularly to interference measures for mitigating lift reduction caused by vortices generated at the trailing edge of the flaps during high angle-of-attack flight. Although the flap vortex interference device described in this invention is located at the junction of the trailing edge of the fixed wing and the fuselage, or at the trailing edge of the fixed wing, those skilled in the art should understand that the flap vortex interference device of this invention can also be applied to other specific locations on the aircraft besides the inner and outer trailing edge of the flaps, as long as lift can be reduced at those specific locations.

[0035] Secondly, descriptions involving orientation, such as terms like "inner side," "outer side," and "trailing edge," are all based on the aircraft's orientation during normal flight. For example, "inner side" and "outer side" refer to the side closer to the fuselage in the wingspan direction and the side farther from the fuselage in the wingspan direction, respectively; "leading edge" refers to the edge of the wing closer to the nose; and "trailing edge" refers to the edge of the wing closer to the tail.

[0036] Finally, it is worth noting that the number of "flap vortex interference devices" (2) in each of the accompanying drawings is merely an example and is not intended to limit the scope of the invention.

[0037] For ease of explanation, the following will be... Figures 2 to 5 The wingspan direction of the aircraft is set as the X direction, the side closer to the fuselage in the wingspan direction is set as the X2 side, and the side farther from the fuselage is set as the X1 side. The chord direction of the wing is set as the Y direction, the front side in the chord direction is set as the Y1 side, and the rear side is set as the Y2 side.

[0038] It should be noted that, Figure 2 , Figure 4 The high-speed cruise configuration of the aircraft shown refers to the configuration when the flaps are retracted and the fixed wings are in high-speed flight. Figure 3 , Figure 5 The low-speed cruise configuration of the aircraft shown refers to the configuration when the flaps are deployed from the fixed wings during takeoff and landing, and the aircraft flies at low speed.

[0039] This invention provides a flap vortex interference device and a wing assembly including the flap vortex interference device, used to interfere with vortices on trailing-edge flaps located on the trailing edge of a fixed wing during high angle-of-attack flight, suppressing airflow separation, reduced lift, and premature aircraft stall caused by the vortices. Here, the term "flap vortex" refers to vortices generated at the inner or outer end edge of the trailing-edge flap, rising from the lower wing surface to the upper wing surface. The term "interference" refers to various methods to reduce or eliminate the effect or influence of vortices, including but not limited to blocking, obstructing, breaking, disrupting, and damaging them.

[0040] like Figure 1As shown, the wing assembly 10 of the present invention is connected to the fuselage 300 and includes: a fixed wing 100 connected to the fuselage 300 along the wingspan direction; and a trailing edge flap 200 disposed at the trailing edge of the fixed wing 100 in a manner that can be retracted or deployed from the trailing edge of the fixed wing 100.

[0041] The trailing edge flap 200 includes an inner trailing edge flap 210 and an outer trailing edge flap 220, the inner trailing edge flap 210 having an inner end edge 211 (see reference). Figure 2 The outer trailing edge flap 220 has an outer end edge 221 (see reference). Figure 3 ).

[0042] The wing assembly 10 also includes a flap vortex interference device, which includes: an inner flap vortex interference device 120, which is correspondingly disposed at the inner end edge 211 of the inner trailing edge flap; and an outer flap vortex interference device 140, which is correspondingly disposed at the outer end edge 221 of the outer trailing edge flap.

[0043] The term "corresponding configuration" here refers to the fact that when the trailing edge flap 200 of the aircraft wing is deployed from the fixed wing 100 at a high angle of attack, there is no interference between the inner flap vortex interference device 120 and the inner end edge 211 of the inner trailing edge flap, and a channel capable of generating a high-speed jet is formed between them. This high-speed jet can impact the airflow separation point area at the inner end edge, thereby suppressing the vortex generated there. Similarly, there is no interference between the outer flap vortex interference device 140 and the outer end edge 221 of the outer trailing edge flap 220, and a channel capable of generating a high-speed jet is formed between them. This high-speed jet can impact the airflow separation point area at the outer end edge, thereby suppressing the vortex generated there.

[0044] Thus, by setting the inner flap vortex interference device 120 and the outer wing vortex interference device 140 at the locations where vortices are generated, namely the inner end edge 211 of the inner trailing edge flap and the outer end edge 221 of the outer trailing edge flap, respectively, the vortices can be accurately and effectively suppressed, and the airflow separation, reduced lift, and premature stall caused by the vortices can be reliably suppressed.

[0045] like Figures 2 to 5As shown, the inner flap vortex interference device 120 protrudes from the connection point between the fixed wing 100 and the fuselage 300, i.e., at the inner wing angle 110, while the outer flap vortex interference device 140 protrudes from the outer wing angle 130 at the trailing edge of the fixed wing 100. The term "protrusion" includes both the case where the inner flap vortex interference device 120 and the outer flap vortex interference device 140 are integrally formed with the fixed wing 100 and protrude from the inner wing angle 110 and the outer wing angle 130, and the case where the inner flap vortex interference device 120 and the outer flap vortex interference device 140 are separate from the fixed wing 100, connected to each other, and protruding from the inner wing angle 110 and the outer wing angle 130. Preferably, the inner flap vortex interference device 120 and the outer flap vortex interference device 140 are integrally formed with the fixed wing 100 and protrude from the inner wing angle 110 and the outer wing angle 130, which simplifies the manufacturing process.

[0046] like Figure 2 , Figure 3 As shown, the inner flap vortex interference device 120 is an obtuse triangle, and its maximum angle is the same as the inner wing angle 110, preferably 92 degrees. Figure 4 , Figure 5 As shown, the outer flap vortex interference device 140 is an obtuse triangle, and its maximum angle is the same as the outer wing angle 130, preferably 108 degrees. The maximum angles of the inner flap vortex interference device 120 and the outer flap vortex interference device 140 are merely examples and are not intended to limit the scope of the invention.

[0047] The fact that the maximum angle of the inner flap vortex interference device 120 is smaller than the maximum angle of the outer flap vortex interference device 140 is merely an example and is not intended to limit the scope of the invention.

[0048] like Figure 2 As shown, the inner wing angle 110 is composed of a first inner wing edge 111 and a second inner wing edge 112. The first inner wing edge 111 extends from the fuselage 300 along the trailing edge of the fixed wing 100 toward the X1 side (i.e., the outer side), and the second inner wing edge 112 extends along the connection between the fuselage 300 and the inner end edge 211 of the inner trailing edge flap toward the Y2 side (i.e., the trailing edge side).

[0049] An inner flap vortex interference device 120 is provided corresponding to the inner wing angle 110, including a first side portion 121 extending along the first inner wing edge 111, a second side portion 122 extending along the second inner wing edge 112, and a third side portion 123 connecting the first side portion 121 and the second side portion 122.

[0050] like Figure 5As shown, the outer wing angle 130 is composed of a first outer wing edge 131 and a second outer wing edge 132. The first outer wing edge 131 extends from the fixed wing 100 along its trailing edge toward the X2 side (i.e., the inner side), and the second outer wing edge 132 extends from the fixed wing 100 along its trailing edge toward the Y2 side (i.e., the trailing edge side).

[0051] A vortex interference device 140 for the outer flap is provided at the outer wing angle 130, including a fourth side 141 extending along the first outer wing edge 131, a fifth side 142 extending along the second outer wing edge 132, and a sixth side 143 connecting the fourth side 141 and the fifth side 142.

[0052] The third side 123 of the inner flap vortex interference device 120 and the sixth side 143 of the outer flap vortex interference device 140 are preferably straight, but they can also be formed into various curved shapes with small curvatures. When formed into a straight shape, when the inner trailing edge flap 210 unfolds from the trailing edge of the fixed wing 100, the cross-section of the slot formed between the inner flap vortex interference device 120 and the inner trailing edge flap 210 gradually decreases, forming a contracting flow channel, which can generate a high-speed, concentrated, and stable jet. This high-speed jet can impact the airflow separation point area at the inner end edge of the inner flap, thereby suppressing the vortex at this point and delaying airflow separation to the maximum extent, resulting in the best effect. Similarly, when the outer trailing edge flap 220 unfolds from the trailing edge of the fixed wing 100, the cross-section of the slot formed between the outer flap vortex interference device 140 and the outer trailing edge flap 220 gradually decreases, forming a contracting flow channel that can generate a high-speed, concentrated, and stable jet. This high-speed jet can impact the airflow separation point area at the outer edge of the outer flap, thereby suppressing the vortex at this point and delaying separation to the maximum extent, achieving the best effect.

[0053] Although not illustrated, regarding the inner flap vortex interference device 120, if it is as follows... Figure 3 The dimension (i.e. chord length) of the portion of the inner trailing edge flap 210 that extends out from the trailing edge of the fixed wing 100 in the Y direction is set as C, the dimension of the first side 121 in the Y direction is set as H1, and the dimension of the second side 122 in the X direction is set as L1. The ratio of H1 / C to L1 / C is preferably in the range of 30% to 60%.

[0054] For the outer flap vortex interference device 140, the dimension in the Y direction of the fourth side 141 is set as H2, and the dimension in the X direction of the fifth side is set as L2. The ratio range of H2 / C and L2 / C is preferably 30% to 60%.

[0055] Thus, convergent slots are formed between the inner flap vortex interference device 120 and the inner end edge 211 of the inner trailing edge flap, and between the outer flap vortex interference device 140 and the outer end edge 221 of the outer trailing edge flap. When the ratio of H1 / C to L1 / C is in the range of 30% to 60% as described above, and the ratio of H2 / C to L2 / C is preferably in the range of 30% to 60%, a high-speed jet can be generated through the slots. This high-speed jet can impact the airflow separation point area at the vortex generation location, namely the inner end edge of the inner trailing edge flap and the outer end edge of the outer trailing edge flap, thereby suppressing airflow separation at this location. As a result, the decrease in lift and premature aircraft stall caused by airflow separation can be suppressed.

[0056] If the above ratio is less than 30%, the gaps formed between the inner flap vortex interference device and the inner edge of the inner flap, and between the outer flap vortex interference device and the outer edge of the outer flap, are too wide. The airflow energy is lost during diffusion and cannot form a high-speed jet. Therefore, it is insufficient to impact the airflow separation point area at the inner edge of the inner flap and the outer edge of the outer flap to suppress airflow separation. As a result, it is impossible to suppress the situation of reduced lift and premature aircraft stall caused by airflow separation.

[0057] On the other hand, if the ratio is greater than 60%, when both the inner trailing edge flap 210 and the outer trailing edge flap 220 are retracted relative to the fixed wing 100, interference may occur between the inner flap vortex interference device 120 and the inner end edge 211 of the inner trailing edge flap, and between the outer flap vortex interference device 140 and the outer end edge 221 of the outer trailing edge flap 220, which may affect the lift of the flaps during high-speed cruise of the aircraft.

[0058] Although not illustrated, both the inner flap vortex interference device 120 and the outer flap vortex interference device 140 are flat and have the same thickness as the skin of the fixed wing 100. Therefore, when the inner trailing edge flap 210 or the outer trailing edge flap 220 is retracted relative to the fixed wing 100, the inner trailing edge flap 210 and the outer trailing edge flap 220 will not protrude from the fixed wing 100 and cause additional aerodynamic drag.

[0059] Previously, the vortices generated at the inner edge of the inner trailing edge flap and the outer edge of the outer trailing edge flap, flowing from the lower wing surface to the upper wing surface, would produce harmful aerodynamic effects, causing airflow separation, reducing the airflow speed and increasing the pressure on the upper wing surface, decreasing the pressure difference between the upper and lower wing surfaces, reducing lift, and causing the aircraft to stall earlier.

[0060] According to the flap vortex interference device and the wing assembly including the flap vortex interference device of the present invention, by correspondingly providing the inner flap vortex interference device 120 and the outer flap vortex interference device 140 at the vortex generation location, namely the inner end edge 211 of the inner trailing edge flap and the outer end edge 221 of the outer trailing edge flap, when the aircraft is flying at a high angle of attack and the inner trailing edge flap 210 and the outer trailing edge flap 220 are deployed from the trailing edge of the fixed wing 100, gaps for airflow are formed between the inner flap vortex interference device 120 and the inner end edge 211 of the inner trailing edge flap, and between the outer flap vortex interference device 140 and the outer end edge 221 of the outer trailing edge flap. These gaps generate high-speed jets, which impact the airflow separation point area at these end edges, thereby suppressing airflow separation at this location and suppressing the situation where the lift is reduced and the aircraft stalls prematurely due to airflow separation.

[0061] in, Figure 6 The coordinate graph can show in detail the effect of delaying aircraft stall. For example... Figure 6 As shown, the horizontal axis AOA (Angle of Attack) represents the angle of attack of the aircraft during flight, and the vertical axis CL (Lift coefficient) represents the lift coefficient. The solid line represents the lift coefficient of the flaps corresponding to conventional aircraft flying at high angles of attack, and the dashed line represents the lift coefficient of the flaps of the aircraft of this invention flying at high angles of attack. As shown by the solid line in the figure, in conventional aircraft, the CL of the flaps reaches its maximum value when the angle of attack of the wing reaches AOA1 (the conventional stall critical angle of attack). After that, the aircraft stalls, and the lift of the wing continues to decrease.

[0062] In this invention, after the wing's angle of attack reaches AOA1, the lift of the aircraft does not decrease sharply but remains at its maximum value, continuing flight until the wing's angle of attack reaches AOA2 (the stall critical angle of attack of this invention). At this point, the aircraft stalls, and the wing's lift begins to decrease sharply, AOA2 - AOA1 = 2°. Therefore, it can be seen that the flap vortex interference device and the wing assembly including the flap vortex interference device according to this invention can delay the aircraft's stall critical angle of attack by 2°, thus delaying the aircraft's stall and improving its stall characteristics.

[0063] Furthermore, since the inner flap vortex interference device 120 and the outer flap vortex interference device 140 protrude from the inner wing angle 110 of the fixed wing 100 and the outer wing angle 130 of the fuselage 300, respectively, the lifting area of ​​the fixed wing can be increased compared to the previous case without protrusion, thereby increasing lift. In this way, the lift loss caused by airflow separation can be compensated, further delaying the aircraft's stall.

[0064] Although various embodiments of the invention have been described in the accompanying drawings with reference to flap vortex interference devices, it should be understood that the embodiments within the scope of the invention can be applied to other applications on aircraft with similar structures and / or functions that require interference with lift reduction caused by vortices.

[0065] The foregoing description has already given many features and advantages, including various alternative implementations, as well as details of the structure and function of the device. This document is intended to be exemplary and is not exhaustive or limiting.

[0066] It will be apparent to those skilled in the art that various modifications can be made within the full scope indicated by the broad superordinate meaning of the terms expressed in the appended claims, particularly in terms of structure, materials, elements, components, shapes, dimensions, and arrangements of components, including combinations of these aspects within the scope of the principles described herein. Such various modifications are intended to be included herein, provided they do not depart from the spirit and scope of the appended claims.

Claims

1. A flap vortex interference device, characterized in that, To interfere with the vortices of the trailing edge flaps located on the trailing edge of the fixed wing during high angle-of-attack flight. The flap vortex interference devices are respectively disposed at the inner and outer end edges of the trailing edge flap, and are in the shape of obtuse triangles. A slit is formed between the flap vortex interference device and the inner and outer edge edges of the trailing edge flap to allow airflow.

2. The flap vortex interference device as described in claim 1, characterized in that, The trailing edge flap includes an inner trailing edge flap and an outer trailing edge flap. The flap vortex interference device includes: An inward flap vortex interference device, the inward flap vortex interference device protruding from the connection between the fuselage and the fixed wing corresponding to the inner end edge of the inward trailing edge flap; and An outer flap vortex interference device, which protrudes from the trailing edge of the fixed wing corresponding to the outer end edge of the outer trailing edge flap.

3. The flap vortex interference device as described in claim 2, characterized in that, The inner flap vortex interference device includes: The first side extends outward along the trailing edge of the fixed wing; The second side extends along the fuselage towards the rear edge; and The third side, which serves as the longest side of the obtuse triangle, connects the first side and the second side.

4. The flap vortex interference device as described in claim 3, characterized in that, If the chord length of the portion of the inner trailing edge flap that extends beyond the trailing edge of the fixed wing when it unfolds from the trailing edge of the fixed wing is set as C, the length of the first side in the wingspan direction is set as H1, and the length of the second side in the chord direction is set as L1, then the ratio of H1 / C is in the range of 30% to 60%, and the ratio of L1 / C is in the range of 30% to 60%.

5. The flap vortex interference device as described in claim 2, characterized in that, The outer flap vortex interference device includes: The fourth side extends inward along the trailing edge of the fixed wing; The fifth side extends along the fixed wing toward the rearward edge; and The sixth side, which serves as the longest side of the obtuse triangle, connects the fourth side and the fifth side.

6. The flap vortex interference device as described in claim 5, characterized in that, If the chord length of the portion of the outer trailing edge flap that extends beyond the trailing edge of the fixed wing when it unfolds from the trailing edge of the fixed wing is set as C, the length of the fourth side in the wingspan direction is set as H2, and the length of the fifth side in the chord direction is set as L2, then the ratio of H2 / C ranges from 30% to 60%, and the ratio of L2 / C also ranges from 30% to 60%.

7. The flap vortex interference device as described in any one of claims 2 to 6, characterized in that, The inner flap vortex interference device and the outer flap vortex interference device are formed in the shape of flat plates and have the same thickness as the skin of the fixed wing.

8. The flap vortex interference device as described in any one of claims 2 to 6, characterized in that, The inner flap vortex interference device and the outer flap vortex interference device are respectively integrated with the fixed wing.

9. A wing assembly connected to a fuselage, comprising a fixed wing and a trailing edge flap disposed at the trailing edge of the fixed wing, characterized in that, Including the flap vortex interference device as described in any one of claims 1 to 8, The trailing edge flap includes an inner trailing edge flap and an outer trailing edge flap. The flap vortex interference device includes an inner flap vortex interference device and an outer flap vortex interference device. The inner flap vortex interference device is correspondingly disposed at the inner end edge of the inner trailing edge flap. The outer flap vortex interference device is correspondingly disposed at the outer end edge of the outer trailing edge flap. A slit for airflow is formed between the inner flap vortex interference device and the inner edge of the inner trailing edge flap, and between the outer flap vortex interference device and the outer edge of the outer trailing edge flap.

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