Wing seam flow choking device

Abstract

The utility model belongs to the technical field of airplane structure design, and discloses a wing seam flow choking device which comprises an aileron sealing plate, sealing cloth and an aileron front edge skin, the aileron sealing plate is arranged at the position, right facing an aileron, of the rear portion of a wing, the aileron front edge skin is the skin at the front edge of the aileron, and the sealing cloth is connected between the aileron sealing plate and the aileron front edge skin. And the sealing cloth has redundant length, so that the sealing cloth does not interfere with the rotation of the aileron. The sealing cloth is additionally arranged between the aileron sealing plate and the aileron front edge skin, the aileron sealing plate is designed to be in a straight plate shape instead of a circular arc shape matched with the aileron front edge skin, the dimension shape of the aileron sealing plate and the supporting force on the upper wing face and the lower wing face can be improved, gap fluid channeling between an aileron cabin and an aileron can be eliminated through the design of the sealing cloth, and the sealing effect of the aileron cabin and the aileron is improved. Therefore, the use efficiency of the aileron control mechanism is improved.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft structural design technology, and relates to a wing slot improvement device for aircraft wings, specifically a wing slot flow obstruction device. Background Technology

[0002] An aileron is a small movable surface mounted on the outer trailing edge of the outer wing. It serves as the aircraft's primary control surface; the differential deflection of the left and right ailerons generates a rolling moment that allows the aircraft to perform roll maneuvers. Because the aileron is a movable end face, a certain clearance is unavoidable in the design of the aileron nacelle. This clearance creates a gap between the aileron nacelle and the aileron itself, which can lead to severe flow-induced vibrations within the nacelle structure.

[0003] In domestic aileron nacelle designs, a gap is typically left between the aileron sealing plate and the aileron leading-edge skin in the fuselage structure. Since both the aileron sealing plate and the leading-edge skin are thin-walled structures, this thin-walled cavity structure is greatly affected by airflow. Usually, the aileron sealing plate needs to be designed as a curved thin-walled structure that matches the aileron leading-edge skin. This structural design has a certain impact on the airfoil in order to provide sufficient movement space for the aileron. Even if the theoretical minimum gap is designed, there is still a gap. During flight training, airflow generated by the gap will occur in the aileron nacelle. This high-speed airflow will affect the efficiency of the aileron control mechanism. Utility Model Content

[0004] To address the aforementioned problems, this invention provides a wing slot flow obstruction device that can impede airflow, thereby improving the efficiency of the aileron servo.

[0005] The technical solution of this utility model is as follows:

[0006] A wing slot flow control device includes an aileron sealing plate, a sealing cloth, and an aileron leading edge skin. The aileron sealing plate is located at the rear of the wing, directly opposite the aileron. The aileron leading edge skin is the skin at the leading edge of the aileron. The sealing cloth is connected between the aileron sealing plate and the aileron leading edge skin. The sealing cloth has excess length so that it does not interfere with the rotation of the aileron.

[0007] Furthermore, it also includes a second sealing strip, one end of which is fixed to the leading edge skin of the aileron.

[0008] Furthermore, the end face of the aileron sealing plate is a right-angled C-shaped surface, which includes a vertical straight plate surface and a flat edge surface that is perpendicularly connected to the upper and lower ends of the straight plate surface.

[0009] Furthermore, it also includes Z-shaped profiles, one end of which is installed on the rear straight plate surface of the aileron sealing plate, and the other end of which is connected to the sealing cloth.

[0010] Furthermore, it also includes a pressure strip, one end of which is fixed to the Z-shaped profile.

[0011] Furthermore, the Z-shaped profile, pressure strip one, and pressure strip two are all long strip structures of the same length.

[0012] The beneficial effects of this utility model are as follows:

[0013] This invention proposes adding a sealing cloth between the aileron sealing plate and the aileron leading-edge skin, and designing the aileron sealing plate as a straight plate rather than an arc shape that matches the aileron leading-edge skin. This improves the shape of the aileron sealing plate and its support for the upper and lower wing surfaces. The sealing cloth design eliminates the impact of airflow through the gap between the aileron nacelle and the aileron on the aileron's aerodynamic efficiency. Specifically, this invention can be used in narrow gaps in aircraft wings where airflow needs to be blocked. Due to mechanical movement, gaps are unavoidable in moving parts of the wing structure, and the airflow through these gaps during flight negatively impacts the aileron's aerodynamic efficiency. Adding a sealing cloth between the aileron sealing plate and the aileron leading-edge skin can block the airflow between the aileron nacelle and the aileron, thereby improving the efficiency of the aileron control mechanism. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of a slit flow-blocking device according to the present invention;

[0015] Figure 2 for Figure 1 Enlarged view of a portion;

[0016] Figure 3 This is an exploded view of the wing slot flow-blocking device of this utility model;

[0017] Among them, 1—aileron sealing plate, 2—aileron leading edge skin, 3—sealing cloth, 4—Z-shaped material, 5—pressure strip one, and 6—pressure strip two. Detailed Implementation

[0018] This section describes embodiments of the present invention, used to explain and illustrate the technical solutions of the present invention. Unless otherwise specified, the embodiments and features described herein can be combined with each other.

[0019] In the description of this utility model, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating directions or positional relationships, are based on the orientation or positional relationships in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description. They do not indicate or imply that the device or device referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting this utility model. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include more than one of those features. In the description of this utility model, unless otherwise stated, "a plurality of" means two or more.

[0020] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integrated connection; they can refer to a mechanical connection or a point connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0021] Example 1:

[0022] A wing slot flow control device includes an aileron sealing plate 1, a sealing cloth 3, and an aileron leading edge skin 2. The aileron sealing plate 1 is located at the rear of the wing, directly opposite the aileron. The aileron leading edge skin 2 is the skin at the leading edge of the aileron. The sealing cloth 3 is connected between the aileron sealing plate 1 and the aileron leading edge skin 2. The sealing cloth 3 has excess length so that it does not interfere with the rotation of the aileron.

[0023] It also includes pressure strip 2 6, one end of the sealing cloth 3 is fixed to the aileron leading edge skin 2 by pressure strip 2 6.

[0024] The end face of the aileron sealing plate 1 is a right-angled C-shaped surface, which includes a vertical straight plate surface and a flat edge surface that is perpendicularly connected to the upper and lower ends of the straight plate surface.

[0025] It also includes Z-shaped profile 4, one end of which is installed on the rear straight plate surface of the aileron sealing plate 1, and the other end of Z-shaped profile 4 is connected to the sealing cloth 3.

[0026] It also includes pressure strip 5, one end of sealing cloth 3 is fixed to Z profile 4 by pressure strip 5.

[0027] Z-shaped profile 4, pressure strip 1 5, and pressure strip 2 6 are long strip structures of the same length.

[0028] Example 2:

[0029] This utility model provides a wing gap blocking device, which uses a threaded bracket nut and bolts to fix sealing cloth, Z-shaped material, and pressure strips, one end of which is fixed to the aileron sealing plate and the other end to the aileron leading edge skin. This utility model is composed of 1 aileron sealing plate (originally curved surface, this model is changed to right-angled C-shaped surface), 2 aileron leading edge skin, 3 sealing cloth, 4 Z-shaped material, 5 pressure strip 1, and 6 pressure strip 2. The 3 sealing cloths are fixed between the 1 aileron sealing plate and the 2 aileron leading edge skins by the bracket nut connection to block the gap between the aileron wing gaps.

[0030] Specific steps: as follows Figure 1 As shown, this utility model discloses a wing gap flow obstruction device, mainly composed of a wing sealing plate, a wing leading edge skin, a sealing cloth, a Z-shaped profile, a pressure strip 1, and a pressure strip 2. First, the support plate nuts are evenly distributed and installed on one bent edge of the 4Z-shaped profile. Then, one end of the sealing cloth 3 is laid flat on this side of the 4Z-shaped profile. After pressing the sealing cloth 3 flat and adhering it with the pressure strip 1, it is fixed to the 4Z-shaped profile with bolts. The other bent edge of the 4Z-shaped profile is fixed to the wing sealing plate 1 with rivets. The wing leading edge skin 2 is divided into two arc-shaped curved skin sections. The two sections are connected by the support plate nuts to connect the curved edges of the skin. The other end of the sealing cloth 3 is laid flat on the curved edge of the wing leading edge skin 2. After pressing the other end of the sealing cloth 3 flat and adhering it with the pressure strip 2, it is fixed to the curved edge of the wing leading edge skin 2 with bolts. The wing gap flow obstruction device is thus assembled.

[0031] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of this utility model, but the protection scope of this utility model is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in this utility model, and these modifications or substitutions should be covered within the protection scope of this utility model.

Claims

1. A slatted flow-blocking device, characterized in that, It includes an aileron sealing plate (1), sealing cloth (3) and aileron leading edge skin (2). The aileron sealing plate (1) is located behind the wing directly opposite the aileron. The aileron leading edge skin (2) is the skin at the leading edge of the aileron. The sealing cloth (3) connects the aileron sealing plate (1) and the aileron leading edge skin (2). The sealing cloth (3) has extra length so that the sealing cloth (3) will not interfere with the rotation of the aileron.

2. The slit flow obstruction device according to claim 1, characterized in that, It also includes a second pressure strip (6), one end of the sealing cloth (3) is fixed to the leading edge skin (2) of the aileron through the second pressure strip (6).

3. The slit flow obstruction device according to claim 2, characterized in that, The end face of the aileron sealing plate (1) is a right-angled C-shaped surface, which includes a vertical straight plate surface and a flat edge surface that is perpendicularly connected to the upper and lower ends of the straight plate surface.

4. The slit flow obstruction device according to claim 3, characterized in that, It also includes Z-shaped material (4), one end of which is installed on the rear straight plate surface of the aileron sealing plate (1), and the other end of which is connected to the sealing cloth (3).

5. The slit flow obstruction device according to claim 4, characterized in that, It also includes a pressure strip (5), one end of the sealing cloth (3) is fixed to the Z-shaped material (4) by the pressure strip (5).

6. A slit flow-blocking device according to claim 5, characterized in that, Z-shaped material (4), pressure strip one (5) and pressure strip two (6) are long strip structures of the same length.

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