CN114954903A - A Roller Aircraft Blade With Active Deformation Leading Edge - Google Patents

Abstract

The invention relates to an actively deformed leading edge rolling wing aircraft blade, comprising a blade body of a symmetrical airfoil shape, and the leading edge part of the blade body of the symmetrical airfoil shape is composed of a leading edge flap covering 15% of the chord section and a section of the airfoil section. The other parts are composed and connected in a streamline; the leading edge flap is connected to the blade body through a movable connecting structure installed at the front end of the blade body, and is driven to rotate by a linear servo control system to change the angle between the blade body and the blade body. Through the linear servo control system installed in the main body of the blade, when the blade rotates, the leading edge flap part can be actively rotated according to conditions such as the position of the blade and the direction of the incoming flow, so as to change the shape of the blade and improve the lift of the blade; The leading edge flap part actively rotates, which changes the camber of the blade at the leading edge, improves the stall angle of attack of the blade, the maximum lift coefficient of the blade, improves the dynamic stall of the blade, improves the lift of the blade, mentions the aerodynamic efficiency, reduces the Structural vibration and noise.

Description

A Roller Aircraft Blade With Active Deformation Leading Edge

technical field

The invention belongs to the field of aviation technology, and in particular relates to a rolling wing aircraft blade with an actively deforming leading edge, which is applied to a rolling wing aircraft having a cycloidal propeller with an actively deforming leading edge as a power source.

Background technique

With the development of the UAV industry, especially the rapid development of unsteady aerodynamics, computational fluid dynamics, experimental fluid mechanics technology, material technology and manufacturing technology, electronic equipment and flight control technology, domestic and foreign researchers A lot of research work has been done in the field of aviation, especially on UAVs. Cycloidal propeller is a thrust device whose blade span is parallel to the axis of rotation axis. As a new type of propulsion system, its geometric design is completely different from traditional propellers. Its greatest advantage lies in the omnidirectional vector thrust, which can Generate thrust in any direction 360 degrees in the plane perpendicular to the propeller axis. Aircraft powered by cycloid propellers are called rolling-wing aircraft.

Since the blades of the cycloid propeller generally adopt a symmetrical airfoil, the angle of attack of the blades of the cycloid propeller changes periodically during the flight of the rolling wing aircraft. The pitch oscillation of the blade will lead to the phenomenon of "dynamic stall", which will lose a large amount of lift and seriously affect the aerodynamic performance of the cycloid propeller. Dynamic stalls can also cause structural vibrations that affect the structural strength of the aircraft.

Existing methods for improving dynamic stall generally include vortex generators or active blowing jet devices. Vortex generators and active blowing jet devices are difficult to implement in practical applications due to the complexity of the devices. To sum up, there is an urgent need for a rotorcraft blade, which can improve the dynamic stall of the rotorcraft through the deformation structure.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a rotor blade with an actively deformed leading edge, so as to solve the problem of the dynamic stall phenomenon existing in the rotor. The invention improves the flow quality of the incoming flow by actively changing the shape of the leading edge of the blade, thereby improving the dynamic stall of the rotorcraft, reducing the structural vibration of the rotorcraft, and improving the aerodynamic performance at the same time.

The purpose of this invention is to realize through the following technical solutions:

A rolling wing aircraft blade with an active deformation leading edge, comprising a blade body 1 of a symmetrical airfoil shape, and the leading edge portion of the blade body 1 of the symmetrical airfoil shape is composed of two parts, which are respectively the leading edge covering 15% of the chord section The flaps 4 and other parts of the airfoil section are connected by streamlines;

The leading edge flap 4 is connected to the blade main body 1 through a movable connection structure 3 installed at the front end of the blade main body 1, and is driven to rotate by the linear servo control system 2 installed in the blade main body 1 to change the distance between the blade main body 1 and the blade main body 1. angle.

Further, the blade body 1 is a hollow structure, a linear servo control system 2 and a movable connection structure 3 are installed at the front end thereof, and the linear servo control system 2 is installed inside the blade body 1 .

Further, the movable connecting structure 3 is a link shaft, and the blade body 1 and the leading edge flap 4 are connected through the link shaft.

Furthermore, the linear servo control system 2 is connected by the shaft where the blade is located, so that the leading edge flap 4 can rotate around the connecting shaft.

Furthermore, the maximum angle of rotation is 30°.

Furthermore, when the blade body 1 rotates, the leading edge flap 4 can actively rotate according to the position of the blade body 1 and the direction of the incoming flow to change the shape of the blade body 1 .

Further, the connecting part of the leading edge flap 4 and the blade body 1 is sealed by a material with low friction coefficient, so that the two sides of the blade keep a streamline shape.

Compared with the prior art, the beneficial effects of the present invention are:

1. The present invention uses the linear servo control system installed in the main body of the blade, so that when the blade rotates, the leading edge flap part can be actively rotated according to the position of the blade and the direction of the incoming flow, changing the shape of the blade and improving the lift of the blade. ;

2. Through the active rotation of the leading edge flap part, the curvature of the blade at the leading edge is changed, the stall angle of attack of the blade is increased, the maximum lift coefficient of the blade is increased, the dynamic stall of the blade is improved, the lift of the blade is improved, and the to aerodynamic efficiency. Reduced structural vibration and noise.

Description of drawings

In order to illustrate the technical solutions of the embodiments of the present invention more clearly, the following briefly introduces the accompanying drawings used in the embodiments. It should be understood that the following drawings only show some embodiments of the present invention, and therefore do not It should be regarded as a limitation of the scope, and for those of ordinary skill in the art, other related drawings can also be obtained according to these drawings without any creative effort.

FIG. 1 is a structural diagram of a rolling wing aircraft blade with an active deformation leading edge of the present invention.

In the figure, 1. Blade body 2. Linear servo control system 3. Movable connecting structure 4. Leading edge flap.

Detailed ways

Below in conjunction with embodiment, the present invention is further described:

The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention, but not to limit the present invention. In addition, it should be noted that, for the convenience of description, the drawings only show some but not all structures related to the present invention.

It should be noted that like numerals and letters refer to like items in the following figures, so once an item is defined in one figure, it does not require further definition and explanation in subsequent figures. Meanwhile, in the description of the present invention, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

As shown in FIG. 1 , the rolling wing aircraft blade with active deformation leading edge of the present invention includes a blade body 1 with a symmetrical airfoil shape, and the leading edge portion of the blade body 1 with a symmetrical airfoil shape is composed of two parts, each covering 15% The leading edge flap 4 of the chord section and other parts of the airfoil section are connected by a streamline.

The leading edge flap 4 is connected to the blade main body 1 through a movable connection structure 3 installed at the front end of the blade main body 1, and is driven to rotate by the linear servo control system 2 installed in the blade main body 1 to change the distance between the blade main body 1 and the blade main body 1. angle. The included angle between the leading edge flap 4 and the blade body 1 depends on the size of the blade body 1, the distance between the blade body 1 and the rotation axis (the central axis when it rotates, not shown in the figure), and the incoming flow nature, etc.

Specifically, the movable connection structure 3 is processed on the blade body 1 or fixed by welding.

Specifically, the linear servo control system 2 is installed at the front end of the blade body 1 . When the blade body 1 rotates, the leading edge flaps 4 can actively rotate according to conditions such as the position of the blade body 1 and the direction of the incoming flow, and change the shape of the blade body 1 to improve the lift of the blade. At the same time, through the active rotation of the leading edge flap 4, the curvature of the blade body 1 at the leading edge is changed, the stall angle of attack of the blade is increased, the maximum lift coefficient of the blade is increased, the dynamic stall of the blade is improved, and the The lift of the blade improves aerodynamic efficiency and reduces structural vibration and noise.

The connection between the leading edge flap 4 and other parts of the airfoil section is sealed with a low friction coefficient sealing material.

Example 1

An actively deforming leading edge rolling wing aircraft blade, comprising a blade body 1 of a symmetrical airfoil, the leading edge portion of the blade body 1 consists of a leading edge flap 4 covering 15% of the chord section and other parts of the airfoil section Composition, the two parts are connected in a streamline.

The blade body 1 is a hollow structure, and a linear servo control system 2 and a movable connection structure 3 are installed at the front end thereof, and the linear servo control system 2 is installed inside the blade body 1 by bolts.

The blade body 1 and the leading edge flap 4 are connected by a link shaft. The leading edge flap 4 is driven by a linear servo control system 2, and the linear servo control system 2 is connected by the shaft where the blade is located, so that it can rotate around the link shaft, and the maximum angle of rotation is 30°.

The connecting part of the leading edge flap 4 and the blade body 1 is sealed by a material with low friction coefficient, so that the two sides of the blade keep a streamline shape.

Note that the above are only preferred embodiments of the present invention and applied technical principles. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the protection scope of the present invention. Therefore, although the present invention has been described in detail through the above embodiments, the present invention is not limited to the above embodiments, and can also include more other equivalent embodiments without departing from the concept of the present invention. The scope is determined by the scope of the appended claims.

Claims (7)

1. A rolling wing aircraft blade with an actively deformed leading edge, comprising: the blade comprises a blade main body (1) with a symmetrical airfoil shape, wherein the leading edge part of the blade main body (1) with the symmetrical airfoil shape consists of two parts, namely a leading edge flap (4) covering 15% of chord section and other parts of airfoil section, and the two parts are connected by a streamline;

the leading edge flap (4) is connected with the blade main body (1) through a movable connecting structure (3) arranged at the front end of the blade main body (1) and is driven to rotate by a linear servo control system (2) arranged in the blade main body (1) so as to change an included angle between the leading edge flap and the blade main body (1).

2. The rotorcraft blade with an actively deformed leading edge of claim 1, wherein: the blade body (1) is of a hollow structure, a linear servo control system (2) and a movable connecting structure (3) are installed at the front end of the blade body, and the linear servo control system (2) is installed inside the blade body (1).

3. The rotorcraft blade with an actively deformed leading edge of claim 2, wherein: the movable connecting structure (3) is a connecting shaft, and the blade main body (1) is connected with the leading edge flap (4) through the connecting shaft.

4. A rolling wing aircraft blade with an actively deformed leading edge according to claim 3, wherein: the linear servo control system (2) is connected through a shaft where the blade is located, so that the leading edge flap (4) can rotate around the connecting shaft.

5. The rotorcraft blade with an actively deformed leading edge of claim 4, wherein: the maximum angle of rotation is 30 °.

6. The rotorcraft blade with an actively deformed leading edge of claim 4, wherein: when the blade main body (1) rotates, the leading edge flap (4) can actively rotate according to the position of the blade main body (1) and the direction of incoming flow, so that the shape of the blade main body (1) is changed.

7. The rotorcraft blade with an actively deformed leading edge of claim 1, wherein: the connecting part of the leading edge flap (4) and the blade main body (1) is sealed by a material with low friction coefficient, so that two side surfaces of the blade keep streamline.

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