Trailing edge closure device for an aircraft wing, aircraft wing and method for drag reduction of an aircraft wing

Abstract

The invention relates to a trailing edge closure device for an aircraft wing, comprising a linkage mechanism configured to be hingedly connected to a first hinge point on a rear spar, an actuation element hingedly connected to a flap and connected to the linkage mechanism in such a way that it can actuate the linkage mechanism, and a blocking mechanism hingedly connected to a second hinge point on the rear spar and connected to the linkage mechanism, wherein the flap, when moved from a retracted position to a deployed position, entrains the actuation element to actuate the linkage mechanism, so that the linkage mechanism rotates about the first hinge point and the blocking mechanism rotates about the second hinge point, whereby the blocking mechanism can close a wing fixed trailing edge structure. Thus, after the flap has been lowered, the wing fixed trailing edge can be closed automatically, forming a smooth slot between the flap and the wing fixed trailing edge structure, which prevents the air flowing past the flap leading edge from penetrating into the wing fixed trailing edge structure, which would otherwise cause harmful flow-induced vibrations and turbulent noise. Furthermore, the invention relates to an aircraft wing and to a method for reducing drag on an aircraft wing.

Description

Technical Field

[0001] This invention relates to the field of aircraft, and particularly to aerodynamic design at the trailing edge of an aircraft wing. Specifically, this invention relates to a trailing edge closure device for an aircraft wing. This invention also relates to an aircraft wing including the trailing edge closure device. Furthermore, this invention relates to a method for reducing drag on an aircraft wing. Background Technology

[0002] It is known that aircraft need to reduce their speed and shorten their landing distance as much as possible during landing. This requires high lift to maintain flight. Therefore, aircraft often need to land at large angles of attack. However, conventional wings face two problems at high angles of attack: first, they are limited by the stall angle of attack; second, separation vortices on the upper surface of the wing continuously detach from the trailing edge, generating an unsteady dynamic load on the wing. This unsteady dynamic load causes fluctuations in lift, which is detrimental to aircraft control and leads to structural fatigue of the wing, shortening the aircraft's lifespan.

[0003] To improve aircraft landing performance, the design and application of drag reduction or lift enhancement devices have become important technical approaches. Modern aircraft primarily obtain high usable lift through methods such as increasing wing camber, increasing wing area, and flow control. For example, many aircraft currently use trailing-edge flaps for lift enhancement, mainly because trailing-edge flaps can increase airfoil camber, significantly increasing the effective angle of attack and also increasing the effective airfoil length. Furthermore, the airflow through the slotted channels within slotted flaps can also significantly increase lift.

[0004] Over the decades, lift enhancement systems for large passenger aircraft on the global market have gradually standardized to a design featuring leading-edge slats and single / double-slotted flaps on the trailing edge. In lift enhancement system design, minimizing system complexity while achieving optimal aerodynamic performance is a common goal. Therefore, many aircraft employ fixed-axis deflection flap systems, which are simpler and lighter than rail-mounted Fuller flap mechanisms.

[0005] For example, patent document US8336829B2 discloses a progressive wing trailing edge for an aircraft, the wing trailing edge having flaps that can be adjusted downwards and upwards by positive and negative flap deflection, respectively, thereby sealing the wing profile on the top side by sealing flaps. The wing profile is sealed on the upper side by sealing flaps and on the lower side by ventilated flaps, for using the flaps as control flaps, wherein the flaps are adjusted between negative and small positive flap deflections.

[0006] However, when the flaps are deployed, the fixed trailing edge of the wing is exposed to the airflow field after the flaps are deployed. This causes some of the airflow passing through the leading edge of the flaps to enter the space within the fixed trailing edge of the wing, or the trailing edge cavities, forming vortices. These vortices generate drag, reducing the lift contribution of the flaps, and also cause harmful vibrations and turbulent noise at the fixed trailing edge of the wing. These phenomena will have a significant impact on the structural durability of the aircraft and will significantly affect the aerodynamic performance of the aircraft wing.

[0007] To reduce the increased drag caused by eddies and thus improve aircraft takeoff and landing performance, extensive research has been conducted on active and passive flow control technologies. For example, installing eddy current generators on the upper surface of trailing-edge flaps, slotting the upper surface of trailing-edge flaps for air blowing / drawing, adding plasma actuators, and laying actuators have all achieved certain results. However, these technologies generally have drawbacks such as demanding operating conditions, damage to the original flap structure, the need for additional energy input, and high operating and maintenance costs, limiting their practical engineering applications.

[0008] Therefore, in the field of aircraft wings, there has always been a need to reliably reduce vortices inside the slots by setting appropriate structures and related operating methods in order to reduce drag and improve lift-to-drag ratio. Summary of the Invention

[0009] This invention relates to a trailing edge closing device for an aircraft wing. The aircraft wing may include a rear sparsity, a fixed trailing edge structure connected to the rear sparsity, and flaps. The flaps are movable between a retracted position near the fixed trailing edge structure and an extended position away from the fixed trailing edge structure. The trailing edge closing device may include: a linkage mechanism configured to be hinged to a first hinge point on the rear sparsity; an actuating element configured to be hinged to the flaps and connected to the linkage mechanism for actuation; and a blocking mechanism hinged to a second hinge point on the rear sparsity and connected to the linkage mechanism. When the flaps move from the retracted position to the extended position, the flaps can drive the actuating element to actuate the linkage mechanism, causing the linkage mechanism to rotate about the first hinge point and the blocking mechanism to rotate about the second hinge point. This allows the blocking mechanism to close the fixed trailing edge structure to rectify the airflow within the gap between the fixed trailing edge structure and the flaps.

[0010] By using the trailing edge closing device of the present invention, the movement of the flap can be correlated with the movement of the trailing edge closing device, so that the fixed trailing edge structure of the wing can be automatically closed after the flap is deployed, forming a smooth channel between the flap and the fixed trailing edge structure of the wing. This prevents the airflow flowing through the leading edge of the flap from entering the fixed trailing edge structure of the wing and forming harmful flow-induced vibration and turbulent noise, thereby effectively reducing aerodynamic drag, improving the lift-to-drag ratio, and thus improving the safety performance of the aircraft.

[0011] Preferably, the actuating element may include a slider hinged to the flap, the slider may have a through groove, and the linkage mechanism may include a slide rod that can pass through the groove to allow the slider to slide along the slide rod as the flap moves.

[0012] By using a sliding structure consisting of a slider and a slide bar, a compact, simple, and reliable mechanism can be used to achieve the wing fixed trailing edge structure, which closes the wing by driving the blocking mechanism connected to the linkage mechanism as the flap deflects downward.

[0013] In particular, the linkage mechanism may also include a rocker arm member, which may include a first end hinged to a first hinge point and a second end opposite to the first end, wherein the slide rod may be hinged to the second end of the rocker arm member at a position away from the slide block.

[0014] With the help of a rocker arm component hinged to a slide bar, the wing fixed trailing edge structure of the wing can be driven by a simple pivot to close the blocking mechanism.

[0015] Advantageously, the blocking mechanism may include a blocking element and a link, one end of which may be hinged to the rocker arm member at a point between the first and second ends of the rocker arm member, and the other end of which may be hinged to the blocking element. The blocking element may include opposing first and second ends, wherein the first end of the blocking element is hinged to the second hinge point, and the second end of the blocking element may be a free end. When the flap moves from the retracted position to the extended position, the slider may slide on the slide bar so that the rocker arm member may rotate about the first hinge point, thereby driving the blocking element to rotate about the second hinge point via the link. The free end may close the wing fixing trailing edge structure.

[0016] By utilizing the blocking element that is hinged between the linkage and the linkage mechanism, mainly the rocker arm component, the fixed trailing edge structure of the wing can be automatically closed.

[0017] More preferably, the trailing edge closing device may further include an elastic element, wherein one end of the elastic element may be fixed to the second end of the rocker arm member and the other end may be fixed to the slider. When the flap is in the retracted position, the elastic element is in a relaxed state, and when the flap is in the extended position, the elastic element is in a tensioned state.

[0018] By using elastic elements, the flaps can be tensioned during the lowering process, thus allowing for a better design of the motion curve (e.g., motion speed) of the trailing edge closing device as it moves with the flaps.

[0019] For example, when the flap moves from the spread position to other spread positions so that the slider moves away from the slide bar, the elastic coefficient of the elastic element can be designed to keep the blocking mechanism closed and the wing fixed trailing edge structure.

[0020] Due to the action of the elastic element, the blocking mechanism can keep its closed wing fixed trailing edge structure, and will not move away from the wing fixed trailing edge structure as the flaps are further lowered.

[0021] In a specific example, the distance between the first and second ends of the rocker arm component can be close to the distance between the first and second hinge points, the distance from the point on the rocker arm component that is hinged to the link to the first hinge point can be about two-thirds of the distance between the first and second ends of the rocker arm component, and the distance from the point on the link that is hinged to the blocking element to the second hinge point can be about half the distance between the first and second hinge points.

[0022] The trailing edge closure device designed according to the above example dimensions can achieve a compact structure and a reliable and stable motion relationship (the motion relationship between the downward deflection of the flap and the closure of the fixed trailing edge structure of the wing).

[0023] Advantageously, the rocker arm component may include multiple rocker arm portions and a connecting portion for connecting the rocker arm portions. The connecting portion is configured to extend along the width direction of the fixed trailing edge structure of the wing. The connecting portion may include a first connecting crossbar and a second connecting crossbar spaced apart from each other along the length direction of the rocker arm portions. The first connecting crossbar may constitute a pivot for the rocker arm component to pivot about a first hinge point, and the second connecting crossbar may constitute a pivot for the connecting rod to hinge to the rocker arm component.

[0024] By designing a frame structure that extends along the width direction, the mechanical stability and structural strength of the trailing edge closure device can be effectively improved.

[0025] Preferably, the free end may be provided with a flexible part or contain elastic material, and when the flap is in the spread position, it contacts the inner surface of the fixed trailing edge structure of the wing.

[0026] Using flexible or elastic materials can significantly reduce the impact during the closure process of the fixed trailing edge structure of the wing, and further contribute to the formation of its smooth grooves, as well as reduce wear caused by friction with the fixed trailing edge structure of the wing.

[0027] The present invention also provides an aircraft wing, comprising: a rear sparsity; a fixed trailing edge structure of the wing connected to the rear sparsity; flaps; and a trailing edge closing device as described above, for rectifying the airflow within the gap between the fixed trailing edge structure of the wing and the flaps.

[0028] Finally, the present invention also provides a method for reducing drag on an aircraft wing, which can be used to rectify the airflow within the gap between the fixed trailing edge structure and the flap of an aircraft wing. The aircraft wing may include a rear spars, a fixed trailing edge structure connected to the rear spars, and flaps. The method includes: providing a linkage mechanism that can be hinged to a first hinge point on the rear spars; providing an actuating element that can be hinged to the flaps and connected to the linkage mechanism to actuate them; providing a blocking mechanism that can be hinged to a second hinge point on the rear spars and connected to the linkage mechanism; moving the flaps from a retracted position to a first extended position, thereby driving the actuating element to actuate the linkage mechanism, wherein the linkage mechanism can rotate around the first hinge point and the blocking mechanism can rotate around the second hinge point, thereby causing the blocking mechanism to close the fixed trailing edge structure of the wing. Attached Figure Description

[0029] Figure 1 The illustration schematically shows an aircraft wing according to an embodiment of the present invention, and a portion of the structure of a trailing edge closing device for the aircraft wing, wherein the flaps are in the retracted position;

[0030] Figure 2 Schematic illustration based on Figure 1 The structure of the aircraft wing and a part of the trailing edge closing device for the aircraft wing, wherein the flaps are in the spread position;

[0031] Figure 3 A perspective view of a trailing edge closing device according to an embodiment of the present invention is shown schematically, wherein the flap is in the retracted position;

[0032] Figure 4 Schematic illustration based on Figure 3 A three-dimensional view of the trailing edge closing device, in which the flaps are in the extended position;

[0033] Figure 5 The diagram schematically shows an enlarged detail of an aircraft wing according to the prior art, which shows the fixed trailing edge structure of the wing and the direction of airflow at the flaps and within the flap slots;

[0034] Figure 6 A perspective view and a magnified detailed view of an aircraft wing and trailing edge closing device according to an embodiment of the present invention are schematically shown, wherein the magnified detailed view shows the airflow direction at the fixed trailing edge structure of the wing, the flaps, and within the flap slots.

[0035] Figure 7 A perspective view from above is schematically shown of a trailing edge closing device according to an embodiment of the present invention;

[0036] Figure 8 Schematic illustration based on Figure 7Another perspective view of the rear edge closing device from above;

[0037] Figure 9 A perspective view from below is schematically shown of a trailing edge closing device according to an embodiment of the present invention;

[0038] Figure 10 Schematic illustration based on Figure 9 Another perspective view of the rear edge closing device from below;

[0039] Figure 11 A schematic perspective view of a trailing edge closing device according to an embodiment of the present invention is shown.

[0040] Figure 12 The schematic diagram shows a simplified side view of the rear edge closing device according to an embodiment of the present invention, wherein the flap is in the retracted position;

[0041] Figure 13 Schematic illustration based on Figure 12 A simplified side view of the trailing edge closing mechanism, in which the flaps are in the extended position;

[0042] Figure 14 Schematic illustration based on Figure 13 A simplified side view of the trailing edge closure mechanism, showing an example of the dimensions between the components of the trailing edge closure mechanism.

[0043] List of reference numerals

[0044] 100 Trailing edge closing device;

[0045] 110 sliders;

[0046] 120 sliding bar;

[0047] 130 Rocker arm component;

[0048] 131 (the first end of the rocker arm component);

[0049] 132 (the second end of the rocker arm component);

[0050] 133 Rocker arm section;

[0051] 134 First connecting crossbar;

[0052] 135 Second connecting crossbar;

[0053] 140 linkage;

[0054] 150 blocking element;

[0055] 151 (the first end of the blocking element);

[0056] 152 (the second end of the blocking element);

[0057] 160 First hinge point;

[0058] 170 Second hinge point;

[0059] 180 Elastic element;

[0060] 200 Fixed trailing edge structure for wings;

[0061] 300 rear beam;

[0062] 400 flaps;

[0063] 410 actuator. Detailed Implementation

[0064] 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.

[0065] First, this invention primarily relates to the field of drag reduction for aircraft wings, particularly drag reduction for fixed trailing edge structures. Although this invention is described in conjunction with a fixed-axis deflecting flap, it is understood that the trailing edge closing device for aircraft wings of this invention is not limited to use in conjunction with a fixed-axis deflecting flap, but can be applied to other situations where it is necessary to actively influence the hydrodynamics within the slot structure between the fixed wing and the flap.

[0066] Secondly, although this invention describes the spread position of the flap, it should be understood that there can be multiple spread positions (also known as the lowered position) for the flap. The retracted position described in this invention corresponds to the position to which the flap can be deflected that is closest to the fixed trailing edge structure of the wing. Furthermore, the structure of the flap is known in this invention and will not be described in detail.

[0067] Third, when “up” and “down” are described in this invention, they are used with reference to the attitude of an aircraft during normal flight or during testing.

[0068] Fourth, the “rectification” described in this invention refers to the process of reducing vortices by using flaps and a fixed trailing edge structure of a closed wing, which are different from those in the prior art. However, the term “closed” does not require an airtight closure. Any structure and operation method that can reduce vortices or rectify them to a certain extent is within the scope of this invention.

[0069] Finally, it is worth noting that the numerical values ​​given in the various embodiments are merely illustrative and not intended to limit the scope of the invention.

[0070] The trailing edge closing device 100 according to the invention is applicable to an aircraft wing. Here, the aircraft wing mainly includes a rear sparsity, a fixed trailing edge structure 200 connected to the rear sparsity, and flaps 400. Typically, the fixed trailing edge structure 200 is fixed, while the flaps 400 are movable, for example, capable of rotating about a fixed axis (see fixed-axis deflection flap). Figure 3 This shows that its actuator 410 is in the retracted state, while Figure 4 (Actuator 410 is shown in the deployed state). The rear spars can be, for example, the rear spars 300 of the wing, but can also be other fixed structures. It is not required that the rear spars be connected to the fixed trailing edge structure 200 of the wing, as long as there is no relative movement between them. Optionally, the wing of the present invention may also include a fairing located below for protecting the flaps, which preferably moves with the flaps.

[0071] The flap 400 of the present invention can move between a retracted position and an extended position, for example, by rotating about a fixed axis. In the retracted position (e.g., see...), Figure 3 The flap 400 is located near the fixed trailing edge structure 200 of the wing, while in the spread position (see, for example, see...) Figure 4 The flap 400 is located away from the fixed trailing edge structure 200 of the wing. In the retracted position, since the flap 400 and the fixed trailing edge structure 200 form a essentially closed channel, it has virtually no significant impact on the aircraft's flight performance. However, in conventional aircraft, when the flap 400 is in the down position (i.e., when the flap 400 is in the down position), some airflow can enter the fixed trailing edge structure 200. Figure 5 The diagram exemplifies a typical fixed trailing edge and flap structure of a conventional wing (with the flaps down). Solid lines depict laminar flow through the fixed trailing edge structure, while dashed lines depict turbulent or eddy currents entering the fixed trailing edge structure 200. Such turbulence or eddies can cause harmful flow-induced vibrations. These vibrations affect the service life of the aircraft structure and surrounding systems, increasing operating costs. Furthermore, airflow turbulence also significantly impacts the aircraft's aerodynamic characteristics, reducing flight performance.

[0072] To address the aforementioned problems, the present invention provides a trailing edge closure device 100 for an aircraft wing. As previously stated, the term "closure" does not refer to completely closing the fixed trailing edge structure of the wing, but rather to any action that reduces airflow intrusion into the fixed trailing edge structure or flap slots, thereby improving the aircraft's aerodynamic performance (reducing drag and increasing lift-to-drag ratio). In this invention, the trailing edge closure device 100 may contact the fixed trailing edge structure 200, but this is not mandatory; for example, it may be spaced at a certain distance and not completely enclose the internal structure of the trailing edge. For instance, the trailing edge closure device 100 may close the fixed trailing edge structure 200 near its free end or at a location far from its free end. When the trailing edge closure device 100 is closest to the fixed trailing edge structure 200 at a location far from its free end, this reduces the risk of motion interference between the trailing edge closure device 100 and the flaps 400 during their respective movements.

[0073] It is worth noting that, in principle, as long as the trailing edge closing device 100 of the present invention can form a smooth-shaped slot compared to the existing fixed trailing edge structure of the wing, it can improve the lift coefficient of the wing after the flaps are deployed and reduce the aerodynamic drag caused by airflow intrusion. Furthermore, this is at least because the smooth slot between the flap 400 and the fixed trailing edge structure 200 of the wing can prevent airflow passing through the leading edge of the flap 400 from intruding into the fixed trailing edge of the wing, thus preventing harmful flow-induced vibration and turbulent noise. Figure 6 The example illustrates the airflow after forming such a smooth-shaped channel, where essentially only laminar flow is generated between the fixed trailing edge structure 200 of the wing and the flap 400, without substantial turbulence or eddies of significant energy.

[0074] According to the present invention, when the flap 400 moves from the retracted position to the extended position, the trailing edge closing device 100 can close the fixed trailing edge structure 200 of the wing (for example, comparable to...). Figure 2 and Figure 1The trailing edge closure device 100 is used to straighten the airflow within the gap between the trailing edge and the flap 400, thereby reducing drag on the aircraft wing and improving the lift-to-drag ratio. This closure occurs with or in response to the movement of the flap 400. In other words, the movement of the flap 400 from its retracted position to its extended position actuates the trailing edge closure device 100 of the present invention, enabling it to close the fixed trailing edge structure 200 of the wing without the need for an additional actuation mechanism. It can be understood that the movement of the flap 400 and the closure of the fixed trailing edge structure 200 of the wing are directly kinematically related or mutually linked. Preferably, the trailing edge closure device 100 can close the fixed trailing edge structure 200 of the wing under the driving action of the flap 400 itself, before the flap 400 is lowered to a typical first latch position (which may be referred to as the first extended position) (e.g., a downward deflection angle of 7-10°).

[0075] The trailing edge closing device 100 of the present invention includes a plurality of mechanisms and elements. First, the trailing edge closing device 100 may include a linkage mechanism configured to be hinged to a first hinge point 160 on a rear spar (e.g., a fixed wing rear spar 300), thereby pivotable relative to the first hinge point 160. The linkage mechanism may include a plurality of elements or components. Second, the trailing edge closing device 100 may include an actuating element configured to be hinged to a flap 400, thereby pivotable relative to the flap 400 (the flap 400 itself is movable, for example, rotating about a fixed axis). The actuating element can be connected to the linkage mechanism so that it can actuate the linkage mechanism. More specifically, when the flap 400 moves from a retracted position to an extended position, the flap 400 can drive the actuating element to actuate the linkage mechanism so that the linkage mechanism can rotate about the first hinge point 160.

[0076] Furthermore, the rear edge closing device 100 of the present invention may also include a blocking mechanism, which on the one hand can be hinged to the second hinge point 170 on the rear beam, and on the other hand can be connected to a linkage mechanism. For example... Figure 12-13 As shown, the second hinge position can be spaced vertically from the first hinge position. For example, the linear distance between the second hinge position and the first hinge position can be approximately the distance between the first end 131 and the second end of the rocker arm member 130, or the length of the rocker arm member 130 (shown in the side view). In some embodiments, the blocking mechanism can be hinged to the rear beam, such as a fixed wing rear beam 300 or an integral extension of the rear beam 300 or other structure fixedly connected to the rear beam 300. This hinge can be achieved, for example, by a pivot disposed between the rear beam and the blocking mechanism, such as... Figure 11 As clearly shown in the image.

[0077] The blocking mechanism is connected to the linkage mechanism such that when the linkage mechanism rotates about the first hinge point 160 (as mentioned above, due to the rotation caused by the actuation of the linkage mechanism by the actuating element when the flap 400 moves from the retracted position to the extended position), the blocking mechanism can rotate about the second hinge point 170. This allows the blocking mechanism to close the fixed trailing edge structure 200 of the wing, forming a relatively smooth channel, thereby rectifying the airflow in the channel between the fixed trailing edge structure 200 of the wing and the flap 400.

[0078] Therefore, for the present invention, the motion path of the trailing edge closing device 100 is basically as follows: the flap 400 drives the actuating element to move, the actuating element actuates the linkage mechanism to rotate around the first hinge point 160, and this rotation of the linkage mechanism in turn drives the blocking mechanism to rotate around the second hinge point 170, and this rotation of the blocking mechanism enables the wing fixed trailing edge structure 200 to close. It is worth noting that the blocking mechanism can constitute the main mechanism for closing the wing fixed trailing edge structure 200, while other mechanisms or elements can be mainly used for motion transmission.

[0079] The actuating element of the trailing edge closing device 100 may include a slider 110 hinged to the flap 400, i.e., the slider 110 is pivotable relative to the flap 400. The slider 110 may have a through groove for receiving a slide rod 120 of the linkage mechanism, allowing the slide rod 120 to pass through the groove. When the flap 400 of the present invention moves between a retracted position and an extended position, the slider 110 can slide along the slide rod 120 as the flap 400 moves. Of course, the present invention is not limited to the specific structure of the actuating element and the connection form between the actuating element and the linkage mechanism; it can be any structure capable of causing the movement of the flap 400 to drive the linkage mechanism to rotate about the first hinge point 160, such as a rack and pinion or other linkage mechanism.

[0080] In addition to the slide bar 120, the linkage mechanism also includes a rocker arm member 130, which connects the first hinge point 160 (e.g., a first hinge) to the slide bar 120 or other elements actuable by an actuating element. Figure 7-8 as well as Figure 12-13As shown, the rocker arm member 130 may include a first end 131 hinged to a first hinge point 160 and a second end opposite to the first end 131. Preferably, the first end 131 and the second end are the two ends of the rocker arm member 130, but the invention is not limited thereto. A slide bar 120 may be hinged to the second end of the rocker arm member 130 at a position away from the slider 110. The other end of the slide bar 120 may preferably be a free end. The slider 110 of the actuating element may move, particularly slide, between the first end and the second end of the slide bar 120. In some embodiments, the length of the rocker arm member 130 between the first end 131 and the second end may be one-half to one-third of the length of the slide bar 120. It will be understood that the specific dimensions may be determined based on the geometry of the actual flap-rotating rocker arm mechanism. The following provides examples of recommended geometric proportions for mechanism design.

[0081] Preferably, the blocking mechanism may include at least a blocking element 150 and a connecting rod 140, wherein the connecting rod 140 is mainly used to connect the blocking element 150 to the linkage mechanism, preferably to the rocker arm member 130 of the linkage mechanism. For example, one end of the connecting rod 140 may be hinged to the rocker arm member 130 at a certain point between the first end 131 and the second end (e.g., the distance from the first end 131 is about two-thirds to three-quarters of the distance between the first end 131 and the second end, i.e., closer to the second end of the rocker arm member 130), while the other end of the connecting rod 140 may be hinged to the blocking element 150 (e.g., it may be significantly closer to its first end 151 than the free end of the blocking element 150, such as a distance from the first end 151 that is less than 25%, less than 20%, less than 15%, less than 10% of the total length of the blocking element 150, etc.). Therefore, the link 140 can rotate both around the linkage mechanism and around the blocking element 150, but the link 140 constitutes a linkage element between the blocking element 150 and the linkage mechanism. In some embodiments, the length of the link 140 is less than the distance between the first hinge point 160 and the second hinge point 170, for example, only one-third to one-half of it.

[0082] Advantageously, the blocking element 150 includes a first end 151 and an opposing second end 152, wherein the first end 151 can be hinged to a second hinge point 170, and its second end 152 is preferably a free end. The blocking element 150, particularly its second end 152, is used to close the fixed trailing edge structure 200 of the wing. If direct contact with the fixed trailing edge structure 200 is required, the free end of the blocking element 150 is preferably provided with a flexible portion or contains an elastic material to reduce direct impact on the fixed trailing edge structure 200 and reduce the risk of wear. Furthermore, it is preferable that when the flap 400 is in the retracted position, the deployed blocking element 150 can form part of the wing's aerodynamic surface to shape the aircraft's aerodynamic profile.

[0083] As previously described, in these embodiments, when the flap 400 moves from the retracted position to the extended position (see...) Figure 12-13 (The flap 400 rotates clockwise), and the slider 110 slides along the slide rod 120, allowing the rocker arm member 130 to rotate around the first hinge point 160 (the rocker arm member 130 rotates counterclockwise). This, via the connecting rod 140 of the blocking mechanism, drives the blocking element 150 to rotate around the second hinge point 170 (the blocking element 150 also rotates counterclockwise). The free end of the blocking element 150 can close the fixed trailing edge structure 200 of the wing. By closing the blocking element 150, for example in the form of a baffle, the trailing edge hatch opening of the wing is sealed, preventing airflow from entering the slot and causing harmful structural vibrations, as well as structural fatigue and reduced durability caused by harmful vibrations.

[0084] In a more preferred embodiment, the trailing edge closing device 100 may further include an elastic element 180. One end of the elastic element 180 may be fixed to the second end of the rocker arm member 130, while the opposite end may be fixed to the slider 110 (e.g., see [reference needed]). Figure 9-10 Since both ends are fixed to the linkage mechanism and the slider 110 respectively, the elastic element 180 can be configured (e.g., but not limited to the design of the elastic coefficient, position, size, etc.) so that when the flap 400 is in the retracted position, the elastic element 180 is in a relaxed state, and when the flap 400 is in the extended position, the elastic element 180 is in a tensioned state. Preferably, the elastic coefficient (stiffness) of the elastic element 180 can be designed such that during the further lowering of the flap 400 (e.g., from the above extended position to a lower extended position in the figure or other lowering positions (e.g., the second or third lowering positions), at which time the slider 110 can extend along the slide bar 120 toward its free end), the blocking mechanism, mainly the blocking element 150, will always be in a closed position relative to the wing fixed trailing edge structure 200, maintaining a smooth groove forming the wing fixed trailing edge structure 200.

[0085] Advantageously, the elastic element 180 can be arranged along the slide bar 120, for example, the elastic element 180 is configured as a spring surrounding the slide bar 120 and extending along its length, such as a coil spring (see...). Figure 10 In some embodiments, the spring constant of the helical spring can be determined based on the specific dimensions of each component in the closed trailing edge device, the hinge torque (which can be determined by factors such as flight conditions, structural dimensions, airfoil geometry, and wing stiffness). For example, when the hinge torque is 10 kN / m, in the mechanism model established in this patent, the spring force is approximately 2 kN, and the spring constant can be taken as 0.1 kN / mm.

[0086] exist Figure 14A specific embodiment of the trailing edge closure device 100 is shown, but the dimensions of the various mechanisms and components of the trailing edge closure device 100 of the present invention are not limited to the values ​​shown, and the specific values ​​are related to the design dimensions of the wing fixed trailing edge structure 200, flaps 400, and other components of the aircraft wing itself. Furthermore, Figure 14 The proportional relationships between the various mechanisms and elements of the trailing edge closing device 100 shown are preferred, but are also exemplary.

[0087] Although the forms of the main mechanisms and elements of the trailing edge closure device 100 are shown in the side view, it should be understood that at least some of the aforementioned mechanisms and elements of the trailing edge closure device 100 may have an extension (referred to as the width direction) along the width direction of the wing fixed trailing edge structure 200 of the wing.

[0088] In such Figure 7-8 In the illustrated embodiment, the rocker arm member 130 of the linkage mechanism can be configured as a frame or bracket. For example, the rocker arm member 130 may include a plurality of rocker arm portions 133 (i.e., the length constituting the rocker arm member 130 in the side view) and a (lateral) connecting portion for connecting these rocker arm portions 133, the connecting portion being configured to extend along the width direction of the wing fixed trailing edge structure 200 of the wing. Advantageously, the connecting portion may include a first connecting crossbar 134 and a second connecting crossbar 135 spaced apart from each other along the length direction of the rocker arm portions 133. Preferably, the first connecting crossbar 134 may constitute a pivot for the rocker arm member 130 to pivot about a first hinge point 160, while the second connecting crossbar 135 may constitute a pivot for the link 140 to hinge to the rocker arm member 130. Furthermore, the connecting portion may also include connecting crossbars connecting the rocker arm portions 133 at other points to improve structural strength.

[0089] Advantageously, multiple sets, particularly two sets, of linkage mechanisms can be arranged along the width direction of the fixed trailing edge structure 200 of the wing, such as two sets of rocker arm members 130 and corresponding multiple sets, such as two sets of slide rods 120. Therefore, the trailing edge closing device 100 may also include corresponding multiple, such as two actuating elements, such as two sliders 110, configured to connect to the flap 400. In this case, the links 140 for connecting the blocking element 150 and the rocker arm members 130 of the linkage mechanism can also be provided in multiple sets. However, it is preferred that the blocking mechanism includes only one blocking element 150, i.e., even if multiple sets of links 140 are provided, these links 140 are hinged to a common blocking element 150. The blocking element 150 is preferably constructed as a flat (large) baffle, but this construction is not limiting. More preferably, the above two sets of mechanisms or elements can be arranged symmetrically on both sides of the flap support, with reference to the flap support.

[0090] In this invention, the trailing edge closing device 100 is connected to the flap 400, and the downward deflection of the flap 400 provides the driving force for the trailing edge closing device 100, realizing the linkage of the mechanism. The part of the trailing edge closing device 100 exposed outside the wing shape is enveloped by the fairing of the flap bracket, and remains within the fairing of the flap bracket throughout the entire movement process.

[0091] Furthermore, the present invention also provides a drag reduction method for an aircraft wing, which reduces drag by rectifying the airflow within the duct between the fixed trailing edge structure 200 and the flap 400 of the aircraft wing. The drag reduction method includes: providing a linkage mechanism hinged to a first hinge point 160 on a rear beam; providing an actuating element hinged to the flap 400 and connected to the linkage mechanism to actuate it; and providing a blocking mechanism hinged to a second hinge point 170 on the rear beam and connected to the linkage mechanism. After the aforementioned mechanism or element has been provided, the drag reduction method of the present invention includes the following operation: moving the flap 400 from the retracted position to the extended position (e.g., a first lowered latch), thereby driving the actuating element to actuate the linkage mechanism (e.g., slider 110 drives slide bar 120, slide bar 120 drives the linkage mechanism), wherein the linkage mechanism rotates about the first hinge point 160, and the blocking mechanism rotates about the second hinge point 170, thereby allowing the blocking mechanism (e.g., blocking element 150 in the form of a baffle) to close the wing fixed trailing edge structure 200 of the wing.

[0092] Furthermore, when the flap 400 moves from the aforementioned extended position to other extended positions (e.g., the second or third lowered locking positions), due to the action of the elastic element 180, the blocking mechanism can maintain the wing fixed trailing edge structure 200 of its closed wing, and will not move away from the wing fixed trailing edge structure 200 due to the further lowering of the flap 400.

[0093] Although various embodiments of the invention have been described with reference to fixed-axis deflection flap systems in the accompanying drawings, it should be understood that embodiments within the scope of the invention can be applied to other typical applications of wing trailing edges with similar structures and / or functions.

[0094] 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 apparatus and methods. This document is intended to be exemplary and is not exhaustive or limiting.

[0095] 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 trailing edge closing device for an aircraft wing, the aircraft wing including a rear spars, a fixed trailing edge structure (200) connected to the rear spars, and flaps (400), the flaps (400) being movable between a retracted position near the fixed trailing edge structure (200) and an extended position away from the fixed trailing edge structure (200), characterized in that, The trailing edge closing device (100) includes: A linkage mechanism configured to be hinged to a first hinge point (160) on the rear beam; An actuating element configured to be hinged to the flap (400) and connected to the linkage mechanism to be actuated thereon; A blocking mechanism, which is hinged to a second hinge point (170) on the rear beam and connected to the linkage mechanism; When the flap (400) moves from the retracted position to the extended position, the flap (400) drives the actuating element to actuate the linkage mechanism, so that the linkage mechanism rotates around the first hinge point (160) and the blocking mechanism rotates around the second hinge point (170). Thus, the blocking mechanism can close the fixed trailing edge structure (200) of the wing to rectify the airflow in the gap between the fixed trailing edge structure (200) of the wing and the flap (400).

2. The trailing edge closing device as described in claim 1, characterized in that, The actuating element includes a slider (110) hinged to the flap (400), the slider (110) having a through groove, and the linkage mechanism includes a slide rod (120) that can pass through the groove to allow the slider (110) to slide along the slide rod (120) as the flap (400) moves.

3. The trailing edge closing device as described in claim 2, characterized in that, The linkage mechanism further includes a rocker arm component (130), which includes a first end (131) hinged to the first hinge point (160) and a second end (132) opposite to the first end (131), wherein the slide rod (120) is hinged to the second end of the rocker arm component (130) at a position away from the slider (110).

4. The trailing edge closing device as described in claim 3, characterized in that, The blocking mechanism includes a blocking element (150) and a connecting rod (140). One end of the connecting rod (140) is hinged to the rocker arm member (130) at a point between the first end (131) and the second end (132) of the rocker arm member (130). The other end of the connecting rod (140) is hinged to the blocking element (150). The blocking element (150) includes a first end (151) and a second end (152) opposite to each other, wherein the first end (151) of the blocking element (150) is hinged to the second hinge position. Point (170), and the second end (152) of the blocking element (150) is a free end. When the flap (400) moves from the retracted position to the extended position, the slider (110) slides on the slide bar (120) so that the rocker arm member (130) rotates around the first hinge point (160), thereby driving the blocking element (150) to rotate around the second hinge point (170) via the connecting rod (140). The free end can close the fixed trailing edge structure (200) of the wing.

5. The trailing edge closing device as described in claim 4, characterized in that, The trailing edge closing device (100) further includes an elastic element (180), wherein one end of the elastic element (180) is fixed to the second end of the rocker arm member (130), and the other end is fixed to the slider (110). When the flap (400) is in the retracted position, the elastic element (180) is in a relaxed state, and when the flap (400) is in the extended position, the elastic element (180) is in a tensioned state.

6. The trailing edge closing device as described in claim 5, characterized in that, When the flap (400) moves from the spread position to another spread position so that the slider (110) moves away from the slide bar (120), the elastic coefficient of the elastic element (180) is designed to keep the blocking mechanism closed on the fixed trailing edge structure (200) of the wing.

7. The trailing edge closing device as described in any one of claims 4-6, characterized in that, The distance between the first end (131) and the second end (132) of the rocker arm component (130) is close to the distance between the first hinge point (160) and the second hinge point (170). The distance from the first hinge point (160) to the hinge point on the rocker arm component (130) that is hinged to the connecting rod (140) is about two-thirds of the distance between the first end (131) and the second end (132) of the rocker arm component (130). The distance from the second hinge point (170) to the hinge point on the connecting rod (140) that is hinged to the blocking element (150) is about half the distance between the first hinge point (160) and the second hinge point (170).

8. The trailing edge closing device as described in any one of claims 4-6, characterized in that, The rocker arm component (130) includes a plurality of rocker arm portions (133) and a connecting portion for connecting the rocker arm portions (133). The connecting portion is configured to extend along the width direction of the fixed trailing edge structure (200) of the wing. The connecting portion includes a first connecting crossbar (134) and a second connecting crossbar (135) spaced apart from each other along the length direction of the rocker arm portions (133). The first connecting crossbar (134) constitutes a pivot for the rocker arm component (130) to pivot about the first hinge point (160). The second connecting crossbar (135) constitutes a pivot for the connecting rod (140) to be hinged to the rocker arm component (130).

9. The trailing edge closing device as described in any one of claims 4-6, characterized in that, The free end is provided with a flexible part or contains elastic material, and when the flap (400) is in the spread position, it contacts the inner surface of the fixed trailing edge structure (200) of the wing.

10. An aircraft wing, characterized in that, The aircraft wings include: Rear beam; A fixed trailing edge structure (200) for the wing connected to the rear beam; Flaps (400); The trailing edge closing device as described in any one of claims 1-9 is used to rectify the airflow in the gap between the fixed trailing edge structure (200) of the wing and the flap (400).

11. A method for reducing drag on an aircraft wing, wherein the method rectifyes the airflow within the duct between the fixed trailing edge structure (200) and the flap (400) of the aircraft wing, wherein, The aircraft wing includes a rear spars, a fixed trailing edge structure (200) connected to the rear spars, and flaps (400), characterized in that the method includes: A linkage mechanism is provided such that the linkage mechanism is hinged to a first hinge point (160) on the rear beam; An actuating element is provided, which is hinged to the flap (400) and connected to the linkage mechanism to be actuated thereon; A blocking mechanism is provided, which is hinged to a second hinge point (170) on the rear beam and connected to the linkage mechanism; The flap (400) is moved from the retracted position to the first extended position, thereby driving the actuating element to actuate the linkage mechanism, wherein the linkage mechanism rotates about the first hinge point (160) and the blocking mechanism rotates about the second hinge point (170), thereby causing the blocking mechanism to close the fixed trailing edge structure (200) of the wing.

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