KR101858837B1 - System and method of altering leading edge of airfoil - Google Patents

Abstract

A pre-warp deformation system of a flying body is disclosed. The pre-warp deformation system according to an embodiment of the present invention includes an opening extending from a leading edge of a blade to a lower surface of the blade front end; A front edge structure that moves from the inside of the blade to the opening to close the opening and forms an outer shape of a front surface of the blade and a bottom surface of a blade front end; And an opening portion cover which forms a front face of the vane and a front face of the front end of the vane by moving to the opening portion from the lower end of the vane when the front edge structure is inserted into the empty space inside the vane at the opening portion, .

Description

FIELD OF THE INVENTION [0001] The present invention relates to a system and a method for transforming an object,

One embodiment of the present invention relates to a Variable Leading Edge Airfoil (VFR), which is capable of selectively deforming into a supersonic mode and a subsonic mode, .

The blunt frontal shape of the subsonic airfoil generates a vertical shock wave in the supersonic region, which greatly increases the wave drag. On the other hand, a supersonic airfoil with a sharp leading edge shape generates an oblique shock wave at the front edge and has a low drag coefficient, which is suitable for supersonic flow. In this way, it is advantageous to have a sharp frontal shape in the supersonic region.

However, despite the superior performance of supersonic airfoils in the supersonic range, many supersonic fighters, including the recently developed fifth generation fighters, did not use supersonic airfoils. This shows that the sharp frontal shape has high efficiency in the supersonic region, while the subsonic and transonic regions have poor aerodynamic characteristics such as poor stall characteristics and low maximum lift coefficients, which has a negative effect on overall flight performance such as turning ability and take- It is judged as the cause.

Supersonic airfoil is very efficient in supersonic cruise. It shows the problem in applying supersonic airfoil to fighter aircraft. It shows that the frontal shape required to have excellent aerodynamic characteristics is plate in supersonic region and subsonic region. . In order to maintain the required maneuverability in the subsonic and transonic regions and to increase the efficiency of the supersonic cruise by having a low drag coefficient in the supersonic region, an airfoil capable of adapting to the velocity region of the flow is required.

Accordingly, some prior arts disclose a method of forming a blunt or sharp airfoil by inflating or shrinking it by using a soft material. However, since there is a problem that it can not be practically used under extreme conditions, Methods that can be made of materials should be considered.

A related prior art is US Pat. No. 4,706,913 entitled VARIABLE CAMBER LEADING EDGE ASSEMBLY FOR AN AIRFOIL, filed on November 17, 1987.

An object of an embodiment of the present invention is to provide a pre-warp deformation system and a deformation method that can change the frontal shape of a flight wing according to a supersonic mode and a subsonic mode.

According to an aspect of the present invention, there is provided a pre-warp deformation system including: an opening extending from a leading edge of a blade to a lower surface of a blade front end; A front edge structure that moves from the inside of the blade to the opening to close the opening and forms an outer shape of a front surface of the blade and a bottom surface of a blade front end; And an opening portion cover which forms a front face of the vane and a front face of the front end of the vane by moving to the opening portion from the lower end of the vane when the front edge structure is inserted into the empty space inside the vane at the opening portion, .

Advantageously, the front end structure and the opening cover can form different leading edges and can be utilized as different sound speed modes.

Preferably, the fore end structure is bent so as to form a curved shape of a gentle curve at one end, and the blades form a leading edge of the blades, so that the blades can be operated in a subsonic mode, Is formed at an acute angle with an upper surface structure forming the upper surface of the vane, thereby forming a front edge of the acute angle of the vane, and the vane can be operated in the supersonic mode using the front edge of the acute angle vane.

The flap structure may further comprise a flap structure which forms an upper end contour of the vane shear and is connectable with a top surface structure forming the upper surface of the vane.

Preferably, the front-end piston is configured to pull the front-end structure and move it to the inside of the vane or to position it as an opening; A rail for allowing the front piston to move into the interior of the vane; And a rotating unit rotating at least one of the lower surface structure forming the lower end surface of the vane and the opening cover by a predetermined angle.

Preferably, when the frontal structure is positioned at the opening to form the frontal edge of the vane, the frontal structure and the flap structure may be formed with a predetermined angle downward to form the flap.

According to another aspect of the present invention, there is provided a method of modifying a front end of a wing of a vehicle, the method comprising: receiving a mode switching signal for switching to a supersonic mode or a subsonic mode; Converting the wing into a supersonic mode when the wing is operating in a subsonic mode; And switching the wing to a subsonic mode when the wing is operating in a supersonic mode, wherein switching the wing to a supersonic mode comprises closing an opening extending from a front edge of the wing to a lower surface of the front edge of the wing Moving a frontal structure forming a blind front side of the blades and a front side of the blades to an empty space inside the blades; And forming the supersonic airfoil by moving the opening cover to the open aperture to form a front edge of the acute angle vane and a bottom surface of the front edge of the vane, wherein the step of converting the vane to the subsonic mode comprises: The cover slides rearward in the opening to open the opening; And forming a subsonic airfoil by moving a front surface structure from the inside of the vane to the opening to form a front surface and a front surface of the front surface of the vane.

According to an embodiment of the present invention, it is possible to provide a pre-warp deformation system and a deformation method of a flight capable of switching to a supersonic mode or a subsonic mode according to whether a flying situation is a supersonic region or a subsonic region.

According to an embodiment of the present invention, it is possible to provide a pre-warp deformation system and a deformation method capable of forming wings of a flying object by using a material made of a rigid material.

According to an embodiment of the present invention, it is possible to provide a pre-warp deformation system and a deformation method that do not seriously affect flight when deformation during flight.

FIG. 1A is a view showing a subsonic mode shape of an airfoil to which a pre-warp deformation system according to an embodiment of the present invention is applied, FIG. 1B is a view showing a supersonic mode shape, Fig.
FIG. 2A is a view showing a subsonic mode shape of an airfoil to which a pre-warp deformation system according to another embodiment of the present invention is applied, and FIG. 2B is a view showing a supersonic mode shape.
FIG. 3A is a view showing a subsonic mode shape of an airfoil to which a pre-warp deformation system according to another embodiment of the present invention is applied, and FIG. 3B is a view showing a supersonic mode shape.
4 is a view illustrating an embodiment in which a front flap is formed in an airfoil to which a pre-warp deformation system according to another embodiment of the present invention is applied.
5 is a flowchart illustrating a pre-warp deformation method of a wing including a pre-warp deformation system according to an embodiment of the present invention.
6 is a view illustrating a process of deforming an airfoil to which a pre-warp deformation system according to another embodiment of the present invention is applied from a subsonic mode to a supersonic mode.

While the invention is susceptible to various modifications and alternative forms, specific embodiments thereof are shown by way of example in the drawings and will herein be described in detail. It is to be understood, however, that the invention is not to be limited to the specific embodiments, but includes all changes, equivalents, and alternatives falling within the spirit and scope of the invention. Like reference numerals are used for like elements in describing each drawing.

The terms first, second, A, B, etc. may be used to describe various elements, but the elements should not be limited by the terms. The terms are used only for the purpose of distinguishing one component from another. For example, without departing from the scope of the present invention, the first component may be referred to as a second component, and similarly, the second component may also be referred to as a first component. And / or < / RTI > includes any combination of a plurality of related listed items or any of a plurality of related listed items.

It is to be understood that when an element is referred to as being "connected" or "connected" to another element, it may be directly connected or connected to the other element, . On the other hand, when an element is referred to as being "directly connected" or "directly connected" to another element, it should be understood that there are no other elements in between.

The terminology used in this application is used only to describe a specific embodiment and is not intended to limit the invention. The singular expressions include plural expressions unless the context clearly indicates otherwise. In the present application, the terms "comprises" or "having" and the like are used to specify that there is a feature, a number, a step, an operation, an element, a component or a combination thereof described in the specification, But do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, or combinations thereof.

Unless defined otherwise, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. Terms such as those defined in commonly used dictionaries are to be interpreted as having a meaning consistent with the contextual meaning of the related art and are to be interpreted as either ideal or overly formal in the sense of the present application Do not.

Hereinafter, preferred embodiments according to the present invention will be described in detail with reference to the accompanying drawings.

FIG. 1A is a view showing a subsonic mode shape of an airfoil to which a pre-warp deformation system according to an embodiment of the present invention is applied, FIG. 1B is a view showing a supersonic mode shape, Fig.

Referring to FIGS. 1A to 1C, a pre-warp deformation system 100 according to an embodiment of the present invention includes an opening 20, an anterior defense structure 110, and an opening cover 120.

The opening 20 extends from the leading edge of the blade 10 to the lower surface of the front end of the blade 10. [ FIG. 1C is a view showing the position and shape of the opening 20 as a shape omitting the front-end structure 110. FIG. Referring to FIG. 1C, it can be seen that the opening 20 can be formed by the separation of the upper surface structure 150 and the opening cover 120, which will be described later.

The front opening structure 20 can be positioned by moving from the inside to the front opening structure 20. The front structure 110 moves from the inside of the vane 10 to the opening 20 to block the opening 20, (10) and the front end of the blade (10).

The opening cover 120 moves to the opening 20 from the rear surface of the lower end of the vane 10 when the front edge structure 110 is inserted into the empty space inside the vane 10 from the opening 20, So that the front edge of the blade 10 and the lower surface of the front edge of the blade 10 are formed.

Here, the front edge structure 110 and the opening cover 120 can form different front edge shapes, and they can be utilized as different sound speed modes.

More specifically, the front end structure 110 is bent so as to form a gentle curved shape at one end, and the blunt shape forms the front end of the wing 10, so that the air vehicle can be operated in the subsonic mode, The cover 120 is connected to the upper surface structure 150 of the vane 10 at an acute angle, thereby forming a sharp front edge, and the aircraft can be operated in a supersonic mode.

FIG. 2A is a view showing a subsonic mode shape of an airfoil to which a pre-warp deformation system according to another embodiment of the present invention is applied, and FIG. 2B is a view showing a supersonic mode shape.

Referring to FIGS. 2A and 2B, a pre-warp deformation system 100 according to another embodiment of the present invention includes an opening 20, a front end structure 110, an opening cover 120, and a flap structure 130.

The pre-warp deformation system 100 according to another embodiment of the present invention is the same as the pre-warp deformation system 100 of Figs. 1A to 1C except for the flap structure 130. [ Therefore, in the present embodiment, only the flap structure 130 will be described in detail, and description of other remaining components 20, 110, and 120 will be omitted.

The flap structure 130 may be connected to a top surface structure 150 forming the top of the top of the front end of the vane 10 and forming the top surface of the vane 10.

The flap structure 130 also allows flaps to form when the wing 10 is operating in a subsonic mode. A specific embodiment for forming the flap is shown in Fig.

FIG. 3A is a view showing a subsonic mode shape of an airfoil to which a pre-warp deformation system according to another embodiment of the present invention is applied, and FIG. 3B is a view showing a supersonic mode shape.

3A and 3B, a pre-warp deformation system 100 according to another embodiment of the present invention includes an opening 20, a front end structure 110, an opening cover 120, a flap structure 130, 164, a rail 170, and a rotation unit 180. Since the remaining components have been described in detail in the foregoing, only the front piston 164, the rail 170, and the rotary unit 180 will be described.

The front-end piston 164 draws the front-end structure 110 into the inside of the vane 10 or places it in the opening 20 to form a front end.

The rail (170) allows the front piston (164) to move into the interior of the vane (10).

The rotation unit 180 rotates at least one of the lower surface structure 140 forming the lower end surface of the vane 10 and the opening cover 120 by a predetermined angle.

That is, the rotation unit 180 functions to adjust the angle formed by the lower surface of the blade 10 according to the advance of the rotation.

When the air flow is introduced into the airfoil in the course of the frontal deformation, the flow becomes unstable, which may cause vibration in the vane 10, so that it is necessary to minimize the inflow of the flow into the vane .

The front drive piston 164 connected to the front end structure 110 and the drive arm 160 connected to the front end structure 110 and the front linear cam 162 connected to the drive arm 160 are connected to the front end The structure can be properly positioned in the opening 20 without creating a gap that connects to the interior of the wing.

The rail structure 172 capable of moving on the rail 170 and the flap driving part 174 connected to the driving arm 160 pull the driving arm 160 so that the front end structure 110 moves from the opening 20 to the wing 10). ≪ / RTI > In addition, movement in the opposite direction is also possible.

The rotary part 180 may be rotated by a predetermined angle by a rotary piston 182 connected to the rotary part 180. Here, the rotation can be based on the rotation center axis 184 of the rotation unit 180.

It is further contemplated that when the aperture cover 120 is positioned in the aperture 20 in the supersonic mode, the flow may flow through the gap between the lower surface structure 140 and the aperture cover 120, Can be prevented.

4 is a view illustrating an embodiment in which a front flap is formed in a subsonic mode of a variable front airfoil according to another embodiment of the present invention.

When the front structure 110 is positioned at the opening 20 and forms the front end of the vane 10, that is, when the vane 10 is operated in the subsonic mode, the front structure 110 and the flap structure 130 So that the flap can be formed to be directed downward by an angle.

The front flap prevents the flow from being separated and performs the function of raising the maximum lift coefficient.

FIG. 4 shows an embodiment in which the angle of 23 degrees is inclined. The flap driving part 174 can draw the driving arm 160 to form the front flap. The angle formed by the flap may be different depending on the degree to which the flap driving unit 174 pulls the driving arm 160. [

5 is a flowchart illustrating a pre-warp deformation method of a wing including a pre-warp deformation system according to an embodiment of the present invention.

Referring to FIG. 5, in step 510, the pre-warp deformation system 100 receives a mode switching signal for switching to a supersonic mode or a subsonic mode.

Here, the mode switching signal may be input by a flight switch or a mode switching selection unit (not shown) for automatically selecting the mode switching based on the speed of the air vehicle.

When the wing 10 is operating in the subsonic mode, the pre-warp deformation system 100 switches the wing 10 to the supersonic mode by the mode switching signal, and when the wing 10 is operating in the supersonic mode, The pre-warp deformation system 100 converts the wing 10 into a subsonic mode.

Wherein the step of converting the vane 10 into the supersonic mode comprises the step of causing the pre-warp deformation system 100 to block the opening 20 extending from the leading edge of the vane 10 to the undersurface of the vane shear, (Step 520a) and the pre-warp deformation system 100 move the openings 20 to the open space inside the vanes 10, And forming the supersonic airfoil by forming the front edge of the acute angle vane 10 and the lower surface of the front edge of the vane 10 (step 530a). When the wing 10 forms a supersonic airfoil, the air vehicle operates in supersonic mode.

The step of converting the vane 10 into the subsonic mode may also include the step of causing the pre-warp deformation system 100 to open the opening 20 by sliding the opening cover 120 rearward in the opening 20 ) And the pre-warp deformation system (100) move the front structure to the opening (20) from the inside of the wing (10) to form the lower front and front ends of the wing (10) 530b. The wing (10) forms a subsonic airfoil so that the air vehicle operates in a subsonic mode.

6 is a view illustrating a process of deforming an airfoil to which a pre-warp deformation system according to another embodiment of the present invention is applied from a subsonic mode to a supersonic mode.

FIG. 6A shows the subsonic mode, and FIG. 6H shows the supersonic mode. (a) to (h) are sequentially changed from the subsonic mode to the supersonic mode, and the process from the supersonic mode to the subsonic mode is reversed.

6 illustrates a deformation process in which the upper surface structure 150 is omitted in order to clearly show the deformation process. The subsonic airfoil including the upper surface structure 150 is similar to FIG. 3A, and the upper surface structure 150 The supersonic airfoil including the airfoil is shown in FIG. 3B.

The present invention has been described with reference to the preferred embodiments. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims. Therefore, the disclosed embodiments should be considered in an illustrative rather than a restrictive sense. The scope of the present invention is defined by the appended claims rather than by the foregoing description, and all differences within the scope of equivalents thereof should be construed as being included in the present invention.

10: wings 20: openings
100: front deflection system 110: front deflection structure
120: opening cover 130: flap structure
140: bottom surface structure 150: top surface structure
160: drive arm 162: forward linear cam
164: front-end piston 166: flap structure fixing portion
170: rail 172: rail structure
174: Flap driving part 180:
182: rotation piston 184: rotation center axis
190:

Claims (7)

A top surface structure defining an upper surface of the wing;
A bottom surface structure forming a bottom surface of the vane;
An opening formed by separating the front end of the upper surface structure and the front end of the lower surface structure;
A front end structure that moves from the inside of the vane to the opening to close the opening and one end of the front structure contacts the front end of the upper surface structure to form a front end of the vane; And
The front edge structure moves from the opening to an empty space inside the blades so that when the opening is opened, the blades are moved from the lower end of the blades to the opening to close the opening and one end comes into contact with the front end of the upper surface structure, And an opening cover that forms a leading edge.
delete The method according to claim 1,
The front-
The blades are bent so as to form a gentle curved shape, and the blunt shape forms the leading edge of the blades, so that the blades can be operated in the subsonic mode,
The opening cover
Wherein the wing is operated in a supersonic mode using a front edge of an acute angle of the wing and a leading edge of an acute angle of the wing is formed by being connected to an upper surface structure forming an upper surface of the wing at an acute angle.
The method according to claim 1,
Further comprising a flap structure that forms an upper contour of the vane shear and is connectable with a top surface structure forming an upper surface of the vane. The method of claim 4, wherein
A front-end piston that pulls the front-end structure to move into the inside of the vane or to position the opening into the opening;
A rail for allowing the front piston to move into the interior of the vane; And
Further comprising a rotating portion for rotating at least one of the lower surface structure forming the lower end surface of the vane and the opening cover by a predetermined angle. 6. The method of claim 5,
When the frontal structure is positioned at the opening to form the frontal edge of the vane,
And the flap is formed such that the frontal structure and the flap structure face downward by a predetermined angle. A method of deforming a frontal wing of a wing of a flying body,
Receiving a mode switching signal for switching to a supersonic mode or a subsonic mode;
Converting the wing into a supersonic mode when the wing is operating in a subsonic mode; And
And switching the wing to a subsonic mode when the wing is operating in a supersonic mode,
The step of converting the vane into supersonic mode comprises:
The front edge structure forming the leading edge of the upper surface structure forming the upper surface of the wing and the front edge of the lower edge surface structure forming the lower surface of the wing are blocked by forming the front edge of the blade having a blunt shape, Moving to an empty space inside the wing; And forming the supersonic airfoil by moving the opening cover to the opened opening to form a front edge of the acute angle of the vane,
The step of converting the wing into a subsonic mode
The opening cover slides rearward in the opening to open the opening; And forming the subsonic airfoil by moving the forward guard structure from the inside of the vane to the opening to plug the opening and form the front edge of the vane.

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