An aircraft elevator and an aircraft horizontal tail with a T-shaped microstructure

Abstract

The invention discloses an aircraft elevator and horizontal tail with a T-shaped microstructure, comprising a rudder surface and a T-shaped microstructure connected to the trailing edge of the rudder surface for generating a local vortex at the trailing edge of the rudder surface; the T-shaped microstructure comprises an upper drooping plate, a lower drooping plate, a connecting plate, an upper reinforcing chamfer and a lower reinforcing chamfer, and the material is aviation aluminum; the lower end of the upper drooping plate and the upper end of the lower drooping plate are respectively connected to one end of the connecting plate, and the connecting plate and the upper and lower skins of the rudder surface are connected by gluing; the upper drooping plate and the lower drooping plate protrude from the upper and lower sides of the trailing edge of the rudder surface respectively; the invention generates a local airflow separation vortex by installing a T-shaped microstructure with a scale of 1% of the total length of the tail section at the trailing edge of the rudder surface, thereby increasing the equivalent length of the airfoil flow characteristics, changing the airfoil pressure distribution, and significantly improving the rudder surface control efficiency.

Description

Technical Field

[0001] The invention belongs to the field of aircraft design, in particular to an aircraft elevator and an aircraft horizontal tail with a T-shaped microstructure. Background Art

[0002] The horizontal tail, vertical tail and aileron of modern subsonic aircraft all adopt the structure of stabilizer + control surface. The appearance and main components of a typical subsonic aircraft are shown in Figure 1 The stabilizer is fixedly connected to the aircraft body, while the rudder is generally connected to the stabilizer through a corresponding mounting and driving mechanism and can rotate to a certain angle. For example, the elevator and horizontal tail are shown in the schematic diagram. Figure 2 This structural form provides the aircraft with both stability and maneuverability.

[0003] The aerodynamic efficiency of the existing stabilizer + rudder structure is mainly determined by its shape and size. Under the traditional stabilizer / rudder shape conditions, the control force generated by each 1° rudder deflection angle is fixed. In order to obtain greater control force, the area of ​​the stabilizer and rudder can only be increased at the same time, which increases the area of ​​the entire tail, increases the weight of the aircraft structure, increases resistance, reduces flight performance, and increases the manufacturing cost of the aircraft. Summary of the invention

[0004] The purpose of the present invention is to provide an aircraft elevator and an aircraft horizontal tail with a T-shaped microstructure, which can improve the controllability without increasing the external dimensions of the stabilizer / rudder surface.

[0005] The technical solution to achieve the purpose of the present invention is:

[0006] An aircraft elevator with a T-shaped microstructure comprises a control surface and a T-shaped microstructure connected to the trailing edge of the control surface for generating a local vortex at the trailing edge of the control surface.

[0007] Furthermore, the T-shaped microstructure includes an upper vertical plate, a downward vertical plate, a connecting plate, an upper reinforcing chamfer, and a lower reinforcing chamfer; the lower end of the upper vertical plate and the upper end of the downward vertical plate are respectively connected to one end of the connecting plate, and the connecting plate is adhesively connected to the upper and lower skins of the rudder surface; the upper vertical plate and the downward vertical plate protrude from the upper and lower sides of the trailing edge of the rudder surface respectively; an upper reinforcing chamfer is provided between the upper vertical plate and the connecting plate; a lower reinforcing chamfer is provided between the downward vertical plate and the connecting plate.

[0008] Furthermore, the upper hanging plate and the lower hanging plate have the same height.

[0009] Furthermore, the heights of the upper and lower drooping plates are both 0.5%-1.5% of the total length of the airfoil.

[0010] Furthermore, the upper reinforcement chamfer and the lower reinforcement chamfer are connected to the T-shaped microstructure by welding.

[0011] Furthermore, the T-shaped microstructure material is aviation aluminum.

[0012] Furthermore, the skin of the control surface is made of carbon fiber composite material.

[0013] The utility model relates to an aircraft horizontal tail wing, which comprises an aircraft elevator with a T-shaped microstructure.

[0014] Compared with the prior art, the present invention has the following significant advantages:

[0015] The present invention generates a local airflow separation vortex by installing a T-shaped microstructure with a size of 1% of the total length of the tail section at the trailing edge of the rudder surface, thereby increasing the equivalent length of the airfoil flow characteristics, changing the airfoil pressure distribution, and significantly improving the rudder surface control efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 The figure is a schematic diagram of the main components of a background technology aircraft.

[0017] Figure 2 A schematic diagram of the deflection of the elevator relative to the horizontal tail stabilizer is provided as background technology.

[0018] Figure 3 Side view of the rudder surface with T-shaped microstructure in the embodiment.

[0019] Figure 4 Schematic diagram of the T-shaped microstructure.

[0020] Figure 5 (ab) are the local airflow field diagrams of the T-shaped microstructure and the conventional tail wing respectively.

[0021] Figure 6 (ab) are simulation diagrams showing the effects of the T-shaped microstructure and conventional tail wing on the local space pressure characteristics.

[0022] Figure 7 This is a curve diagram showing the influence of the T-shaped microstructure on the normal force of the rudder surface. DETAILED DESCRIPTION

[0023] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments.

[0024] Combination Figure 3 In this embodiment, an aircraft elevator with a T-shaped microstructure includes a rudder surface and a T-shaped microstructure connected to the trailing edge of the rudder surface for generating a local vortex at the trailing edge of the rudder surface.

[0025] The present invention installs a T-shaped microstructure 2 on the trailing edge of the conventional rudder surface 1. Figure 3 .

[0026] Combination Figure 4 The main components of the T-shaped microstructure 2 are an upper vertical plate 21, a lower vertical plate 22, a connecting plate 23, an upper reinforcing chamfer, and a lower reinforcing chamfer. The lower end of the upper vertical plate 21 and the upper end of the lower vertical plate 22 are respectively connected to one end of the connecting plate 23, and the vertical plate and the lower vertical plate protrude from the upper and lower sides of the trailing edge of the rudder surface respectively; the connecting plate 23 is mainly used to connect the upper vertical plate 21 and the lower vertical plate 22 to the rudder surface 1, and the connecting plate 23 extends into the rudder surface 1. The connecting plate and the upper and lower skins of the rudder surface are connected by gluing. The material of the T-shaped microstructure is aviation aluminum, and the T-shaped microstructure is formed by welding; an upper reinforcing chamfer is provided between the upper vertical plate and the connecting plate, and a lower reinforcing chamfer is provided between the lower vertical plate and the connecting plate. The upper reinforcing chamfer and the lower reinforcing chamfer are connected to the T-shaped microstructure by welding. The rudder surface skin is made of carbon fiber composite material and is connected to the connecting plate by gluing.

[0027] The upper drooping plate 21 and the lower drooping plate 22 have the same height, which is about 1% of the total length of the airfoil, and are used to generate a local vortex at the trailing edge of the rudder surface 1. Numerical simulation shows that the upper and lower drooping plate heights can produce similar aerodynamic effects within the range of 0.5%-1.5% of the total length of the airfoil, but the aerodynamic efficiency decreases when the height is less than 1%, and the drag cost increases when the height is greater than 1%, and the comprehensive efficiency is optimal when the height is 1%.

[0028] According to the above-mentioned aircraft elevator with T-shaped microstructure, the present invention also proposes an aircraft horizontal tail, including the aircraft elevator with T-shaped microstructure adopting the above-mentioned structure.

[0029] The local airflow field and spatial pressure distribution in the trailing edge area of ​​the rudder surface with T-shaped microstructure rear fin and conventional rear fin were obtained by numerical calculation method. Figure 5 (ab) and Figure 6 (ab). Figure 6 (a) Positive pressure is generated in area A and its vicinity, and the absolute value of negative pressure in area B increases, and the area expands. From the comparison of flow field characteristics, it can be seen that the T-shaped microstructure prevents local airflow from flowing smoothly, and a local separation zone is generated in its vicinity, especially in the rear. The direction of the airflow outside the local separation zone has changed, which is approximately equivalent to flowing over a rudder with an increased length. From the pressure distribution, it can be seen that after the rudder surface is deflected, the T-shaped microstructure blocks the airflow on the windward side, generates positive pressure and transmits it to the nearby area; at the same time, due to the increase in the equivalent curvature of the rudder surface, the absolute value of the negative pressure at the front edge of the rudder surface on the leeward side increases, and the area expands. The overall result is that the pressure difference on both sides of the rudder surface is enlarged, generating a greater control force.

[0030] The influence of microstructure tail and conventional tail on the normal force of the control surface obtained by numerical calculation method is shown in Figure 7 . Combined Figure 6(a) It can be seen that the pressure difference on both sides of the control surface is increased due to the microstructure, so that the control force (normal force) is increased at different angles of attack α, and it increases by 24% when the commonly used tail angle of attack α = 0°. According to this conversion, the horizontal tail area can be reduced by 24%, reducing the weight of the tail, reducing the aircraft manufacturing cost and improving the flight performance.

Claims

1. An aircraft elevator with a T-shaped microstructure, characterized in that: It includes a rudder surface and a T-shaped microstructure connected to the trailing edge of the rudder surface for generating a local vortex at the trailing edge of the rudder surface; The T-shaped microstructure comprises an upper drooping plate, a lower drooping plate, a connecting plate, an upper reinforcing chamfer, and a lower reinforcing chamfer; the lower end of the upper drooping plate and the upper end of the lower drooping plate are respectively connected to one end of the connecting plate, and the connecting plate is connected to the upper and lower skins of the rudder surface by gluing; the upper drooping plate and the lower drooping plate protrude from the upper and lower sides of the trailing edge of the rudder surface respectively; an upper reinforcing chamfer is provided between the upper drooping plate and the connecting plate; a lower reinforcing chamfer is provided between the lower drooping plate and the connecting plate; The height of the upper droop plate and the lower droop plate are both 0.5%-1.5% of the total length of the airfoil.

2. The aircraft elevator with a T-shaped microstructure according to claim 1, characterized in that: The upper hanging plate and the lower hanging plate have the same height.

3. The aircraft elevator with a T-shaped microstructure according to claim 1, characterized in that: The upper reinforcement chamfer and the lower reinforcement chamfer are connected to the T-shaped microstructure by welding.

4. The aircraft elevator with a T-shaped microstructure according to claim 1, characterized in that: The T-shaped microstructure material is aviation aluminum.

5. The aircraft elevator with a T-shaped microstructure according to claim 1, characterized in that: The skin of the rudder surface is made of carbon fiber composite material.

6. An aircraft horizontal tail, characterized in that: It comprises an aircraft elevator with a T-shaped microstructure as described in any one of claims 1-5.

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