A simple flap structure with increased lift and slots

Abstract

This application discloses a lift-enhancing slotted simple flap structure, including a control surface component connected to the wing's rear spars. The lift-enhancing slotted simple flap structure also includes a trailing edge channel located at the segment separating the wing from the control surface component. The trailing edge channel allows high-pressure airflow from the lower wing surface to flow into the upper wing surface. This lift-enhancing slotted simple flap structure, through the trailing edge channel, directs high-pressure airflow from the lower wing surface to the upper wing surface, providing energy to the upper wing surface, reducing airflow separation on the upper wing surface, thereby effectively increasing takeoff lift and improving the cruise lift-to-drag ratio.

Description

Technical Field

[0001] This application relates to the field of aircraft lift enhancement devices, and in particular to a simple lift-enhancing slotted flap structure. Background Technology

[0002] To improve aircraft maneuverability, increase lift during low-speed flight, and enhance takeoff and landing performance, a large number of lift-enhancing devices are arranged on the leading and trailing edges of the wings.

[0003] Currently, the most common leading-edge lift enhancement device is the leading-edge slat. At high angles of attack, the possibility of leading-edge stall is high, making leading-edge slats highly advantageous. Trailing-edge lift enhancement devices come in many forms. Most fighter jets and general aviation aircraft currently use simple flaps, allowing the trailing-edge components to rotate via a hinge. Optimal lift enhancement is achieved if the gap between the simple flap and the wing is well-sealed. However, with increasing flap deflection angles, airflow separation occurs at the joints in this simple flap structure, resulting in decreased lift enhancement and increased drag.

[0004] Therefore, how to provide a simple flap structure with increased lift and slots to solve the above-mentioned technical problems is a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] The purpose of this application is to provide a simple flap structure with lift-enhancing slots, which allows high-pressure airflow from the lower wing surface to flow to the upper wing surface through the trailing edge channel, providing energy to the upper wing surface, reducing airflow separation on the upper wing surface, thereby effectively improving takeoff lift and cruise lift-to-drag ratio.

[0006] To achieve the above objectives, this application provides a lift-enhancing slotted simple flap structure, including a control surface component connected to the wing's rear spars. The lift-enhancing slotted simple flap structure also includes a trailing edge channel located at the segment between the wing and the control surface component. The trailing edge channel is used to allow high-pressure airflow from the lower wing surface to flow into the upper wing surface.

[0007] In some embodiments, the upper surface of the trailing edge channel extends along the shape of the wing, and the lower surface is streamlined, forming a specially shaped slit through the trailing edge channel.

[0008] In some embodiments, the trailing edge channel is disposed on the wing rear spars.

[0009] In some embodiments, the wing rear spars are provided with a joint for connecting the control surface component, and the trailing edge flow channel is perforated at the location of the joint to avoid obstruction.

[0010] In some embodiments, the control surface component maintains a complete airfoil shape, with its leading edge in a curved closed state, and an opening is made at the location of the joint to avoid obstruction.

[0011] In some embodiments, the connector includes a suspension connector and a control connector, the suspension connector being connected to the wing rear spars, and the control connector being used to control the movement of the control surface components.

[0012] In some embodiments, the wing rear spars are connected to the trailing edge channel, the upper skin and the lower skin of the wing via a flange strip, and the trailing edge channel aligns with the upper skin and the lower skin of the wing on the wing rear spars.

[0013] In some embodiments, the shape of the trailing edge channel is determined based on aerodynamic simulation analysis and wind tunnel tests of typical structural components.

[0014] In some embodiments, the trailing edge channel is made of fiber-reinforced resin-based composite material, aluminum alloy, or a fiber-reinforced resin-based composite material sandwich structure with aramid paper honeycomb core.

[0015] In some embodiments, the wing rear spars are made of fiber-reinforced resin-based composite material, aluminum alloy, or titanium alloy.

[0016] Compared to the aforementioned background technology, the lift-enhancing slotted simple flap structure provided in this application includes a control surface component and a trailing edge flow channel; the control surface component is connected to the wing rear spars of the wing, and the trailing edge flow channel is located at the segment where the wing and the control surface component are separated, allowing the high-pressure airflow from the lower wing surface to flow into the upper wing surface through the trailing edge flow channel.

[0017] During the use of this lift-enhancing slotted simple flap structure, the high-pressure airflow from the lower wing surface to the upper wing surface is channeled through the trailing edge flow channel, providing energy to the upper wing surface, reducing airflow separation on the upper wing surface, thereby effectively improving takeoff lift and cruise lift-to-drag ratio. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0019] Figure 1 A schematic diagram of a simple, lift-enhancing slotted flap structure provided in an embodiment of this application. Figure 1 ;

[0020] Figure 2 A schematic diagram of a simple, lift-enhancing slotted flap structure provided in an embodiment of this application. Figure 2 .

[0021] in:

[0022] 1-Wing rear spars, 2-Control surface components, 3-Trail edge flow channel, 4-Connector, 41-Suspension connector, 42-Control connector. Detailed Implementation

[0023] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0024] To enable those skilled in the art to better understand the present application, the present application will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0025] Please refer to Figure 1 , Figure 1 A schematic diagram of a simple, lift-enhancing slotted flap structure provided in an embodiment of this application. Figure 1 .

[0026] In a first specific embodiment, this application provides a lift-enhancing slotted simple flap structure, which serves as a trailing edge lift enhancement device for an aircraft wing; the lift-enhancing slotted simple flap structure includes a control surface component 2 and a trailing edge flow channel 3, the control surface component 2 being connected to the wing rear spars 1 of the wing, and the trailing edge flow channel 3 being located at the segment where the wing and the control surface component 2 are separated.

[0027] In this embodiment, to address the problem of airflow separation at the joint when the flap angle increases in existing simple flap structures, the lift-enhancing slotted simple flap structure provided in this embodiment adds a trailing edge flow channel 3. The trailing edge flow channel 3 is used to allow the high-pressure airflow on the lower wing surface to flow into the upper wing surface, thus solving the problem of decreased lift enhancement and increased drag.

[0028] Specifically, during the use of this lift-enhancing slotted simple flap structure, the high-pressure airflow from the lower wing surface to the upper wing surface is channeled through the trailing edge flow channel, providing energy to the upper wing surface and reducing airflow separation on the upper wing surface, thereby effectively enhancing takeoff lift and improving cruise lift-to-drag ratio.

[0029] In some embodiments, the upper surface of the trailing edge channel 3 extends along the shape of the wing, and the lower surface is streamlined. A special-shaped wing slot is formed through the trailing edge channel 3, and air is drawn in from the lower wing surface through this channel.

[0030] In this embodiment, a lift-enhancing slotted simple flap structure is proposed. Compared with the traditional simple flap structure, in terms of operation, the wing slot at the wing-control surface segment is optimized to increase the streamlined slot, allowing the high-pressure airflow from the lower wing surface to flow to the upper wing surface, providing energy to the upper wing surface, reducing airflow separation on the upper wing surface, thereby effectively improving takeoff lift and cruise lift-to-drag ratio.

[0031] In some embodiments, the trailing edge channel 3 is disposed on the wing rear spars 1.

[0032] In this embodiment, during assembly, the trailing edge flow channel 3 of the lift-enhancing slotted simple flap structure is connected to the wing rear beam 1 via a standard component. The wing rear beam 1 provides connection and support for the trailing edge flow channel 3, ensuring the stable installation of the trailing edge flow channel 3 and guaranteeing the reliable operation of the streamlined slot.

[0033] For example, the wing rear spars 1 is mechanically connected to the trailing edge channel 3, the upper skin and the lower skin of the wing via a slat strip. The trailing edge channel 3 aligns with the upper skin and the lower skin of the wing on the wing rear spars 1, and there should be no large step difference.

[0034] In some embodiments, the wing rear spars 1 is provided with a connector 4 for connecting the control surface component 2, and the trailing edge flow channel 3 has an opening at the position of the connector 4 to avoid obstruction.

[0035] In this embodiment, the control surface component 2 can be a flap, flaperon, aileron, or other control surface structure, and is connected to the wing rear spars 1 via a connector 4. Additionally, the trailing edge flow channel 3 has an opening at the position of the connector 4 on the wing rear spars 1 to avoid obstructing the connector 4.

[0036] In addition, the control surface component 2 maintains a complete airfoil shape, with its leading edge in a curved closed state and an opening at the joint 4 for clearance.

[0037] Please refer to Figure 2 , Figure 2 A schematic diagram of a simple, lift-enhancing slotted flap structure provided in an embodiment of this application. Figure 2 .

[0038] In some embodiments, connector 4 includes a suspension connector 41 and a control connector 42.

[0039] In this embodiment, the connector 4 is a structure that connects the wing (wing rear spars 1) and the control surface (control surface component 2). The control surface component 2 is connected to the wing rear spars 1 through the suspension connector 41, and the movement of the control surface component 2 is controlled by the control connector 42.

[0040] In some embodiments, the shape of the trailing edge channel 3 is determined based on aerodynamic simulation analysis and wind tunnel tests of typical structural components.

[0041] In some embodiments, the trailing edge channel 3 is made of fiber-reinforced resin-based composite material, aluminum alloy, or fiber-reinforced resin-based composite material with aramid paper honeycomb core structure, and needs to have a certain rigidity.

[0042] In some embodiments, the wing rear spars 1 are made of fiber-reinforced resin-based composite material, aluminum alloy, or titanium alloy, possessing high rigidity and strength.

[0043] In summary, to improve the takeoff lift of an aircraft without increasing structural weight, and to achieve lift enhancement on a simple flap structure, this embodiment proposes a lift-enhancing slotted simple flap structure. Compared to traditional simple flap structures, this lift-enhancing slotted simple flap structure utilizes the wing slots at the wing-control surface segment to increase streamlined gaps, allowing high-pressure airflow from the lower wing surface to flow to the upper wing surface, providing energy to the upper wing surface, reducing airflow separation on the upper wing surface, and increasing the maximum lift-to-drag ratio by more than 1.5, thereby effectively improving takeoff lift and cruise lift-to-drag ratio.

[0044] It should be noted that many of the components mentioned in this application are general standard parts or components known to those skilled in the art, and their structures and principles can be learned by those skilled in the art through technical manuals or conventional experimental methods.

[0045] It should be noted that in this specification, relational terms such as first and second are used only to distinguish one entity from several other entities, and do not necessarily require or imply any such actual relationship or order between these entities.

[0046] The above provides a detailed description of the lift-enhancing slotted simple flap structure provided in this application. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are merely for the purpose of helping to understand the method and core ideas of this application. It should be noted that those skilled in the art can make various improvements and modifications to this application without departing from its principles, and these improvements and modifications also fall within the protection scope of the claims of this application.

Claims

1. A high-lift slotted plain flap configuration comprising a control surface part (2) connected to a wing rear spar (1) of a wing, characterized in that The high-lift slotted simple flap structure further comprises a trailing edge flow channel (3) located at the section of the wing and the control surface component (2), which is used to make the high-pressure airflow of the lower wing surface flow into the upper wing surface; The upper surface of the trailing edge flow channel (3) extends along the wing profile, and the lower surface is streamlined, forming a specially shaped wing slot through the trailing edge flow channel (3); The trailing edge flow channel (3) is arranged on the wing rear spar (1); The profile of the trailing edge flow channel (3) is determined according to aerodynamic simulation analysis and typical structural component wind tunnel test; The wing rear spar (1) is provided with a joint (4) connected to the control surface component (2), and the trailing edge flow channel (3) is opened and avoided at the position of the joint (4); The wing rear spar (1) is connected with the trailing edge flow channel (3), the upper skin and the lower skin of the wing through a trailing edge strip, and the trailing edge flow channel (3) and the upper skin and the lower skin of the wing are matched on the wing rear spar (1).

2. The high-lift slotted plain flap configuration of claim 1, wherein, The control surface component (2) maintains the completed wing shape, and the control surface leading edge is in a curved closed state, and is opened and avoided at the position of the joint (4).

3. The high-lift slotted plain flap configuration of claim 1, wherein, The joint (4) comprises a suspension joint (41) and a control joint (42), which is connected with the wing rear spar (1) through the suspension joint (41) and controls the movement of the control surface component (2) through the control joint (42).

4. The high-lift slotted plain flap configuration of claim 1, wherein, The trailing edge flow channel (3) adopts a fiber-reinforced resin-based composite material or an aluminum alloy or a fiber-reinforced resin-based composite material and aramid paper honeycomb sandwich structure.

5. The high-lift slotted plain flap configuration of claim 1, wherein, The wing rear spar (1) is made of a fiber-reinforced resin-based composite material or an aluminum alloy or a titanium alloy.

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