KR102509302B1 - Variable Wing Rib and Method for Setting the Variable Wing Rib - Google Patents

Abstract

A deformable wing lip according to the present invention includes a control body; a forward deployable scissor structure connected to the control body; a rear deployable scissor structure connected to the control body; an actuator provided on the control body; One end is driveable by an actuator, and the other end is a front drive shaft rotatably connected to the foremost link section of the forward deployable scissor structure; One end can be driven by an actuator, and the other end includes a rear driving shaft rotatably connected to the rearmost link section of the rear deployable scissor structure.
One of the rearmost link nodes of the forward deployable scissor structure is rotatably connected to the control body. The other one of the rearmost link nodes of the forward deployable scissor structure is connected to the control body so as to be capable of linear movement. One of the frontmost link nodes of the rear deployable scissor structure is rotatably connected to the control body. The other one of the frontmost link nodes of the forward deployable scissor structure is connected to the control body so as to be able to move in a straight line.

Description

Variable Wing Rib and Method for Setting the Variable Wing Rib

The present invention relates to a deformable wing lip and a method of setting such a wing lip.

The need for a wing structure that can actively adapt to the flight situation is emerging. In the wing structure according to the prior art, by adding additional devices such as flaps, ailerons, and slats to the wing shape, it responds to various flight environments.

However, such an additional device inevitably imparts a discontinuity to the wing structure, resulting in a decrease in flight efficiency.

Korean Patent No. 10-1902698 (registration announcement on September 28, 2018)

An object of the present invention is to provide a deformable wing lip capable of responding to various flight environments without imparting discontinuity to the wing shape.

A deformable wing lip according to the present invention includes a control body; a forward deployable scissor structure connected to the control body; a rear deployable scissor structure connected to the control body; an actuator provided on the control body; One end is driveable by an actuator, and the other end is a front drive shaft rotatably connected to the foremost link section of the forward deployable scissor structure; One end can be driven by an actuator, and the other end includes a rear driving shaft rotatably connected to the rearmost link section of the rear deployable scissor structure.

One of the rearmost link nodes of the forward deployable scissor structure is rotatably connected to the control body. The other one of the rearmost link nodes of the forward deployable scissor structure is connected to the control body so as to be capable of linear movement. One of the frontmost link nodes of the rear deployable scissor structure is rotatably connected to the control body. The other one of the frontmost link nodes of the forward deployable scissor structure is connected to the control body so as to be able to move in a straight line.

The linear motion may follow a height direction of the control body.

The deformable wing lip according to the present invention may further include a skin support provided at the ends of the link nodes of the forward deployable scissor structure and the rear deployable scissor structure.

The skin support may be provided as a rotatable revolute joint according to the movement of the link section.

An angle formed by a line connecting the center of rotation of the actuator and a driving point of the front driving shaft and a line connecting the center of rotation and the driving point of the rear driving shaft may be maintained constant.

According to the present invention, a method for setting the shape of a deformable wing lip by means of an electronic arithmetic device is a predetermined straight line passing through the center, the center and the front for a plurality of desired airfoils to be realized by the wing lip. a first step of setting an angle formed by a driving point of the drive shaft or a line connecting the drive point of the rear drive shaft; A second step of setting at least one of the number of link nodes of the front deployable scissor structure and the rear deployable scissor structure, the radius of rotation by the actuator, the size of the skin support unit, the length of the front drive shaft and the rear drive shaft as a limiting condition; A third step of calculating the coordinates of the ends of the link nodes of the forward deployment type scissors structure and the rear deployment type scissors structure; a fourth step of calculating a minimum distance between the skin supporters and the skin for each skin supporter and calculating a sum of the calculated values; and a fifth step of determining a condition that is not set as a limiting condition by performing optimization so that the sum calculated in the fifth step is minimized.

The condition determined in the fifth step may be the length of the link clause.

The shape of the desired airfoil may be plural, and in this case, the first step may be a step of setting different angles for each shape of the plurality of airfoils, and the sum value of the fourth step is a plurality of airfoils. It can be the sum of the shapes.

According to the present invention, since the wing lip can be changed in various shapes by the operation of the actuator, there is an effect of providing a wing structure that can actively adapt to various flight environments without imparting discontinuity to the wing.

1 is a perspective view of a wing to which a wing lip according to the present invention is applied.
Figure 2 is a view for explaining the degree of freedom provided by the deployable scissors structure and the actuator according to the present invention.
Figure 3 is a view for explaining the unit structure of the unfolding type scissors structure according to the present invention.
Figure 4 is a view for explaining a method for obtaining the end coordinates of the link clause of the unfolding type scissors structure according to the present invention.
5 is a view for explaining the separation distance between the skin support part and the skin in the wing lip according to the present invention.
Figure 6 is a view for explaining the separation orientation of the skin support portion and the skin on the wing lip according to the present invention.
7 is a view simulating the deformation of a wing lip implemented by the present invention into a plurality of airfoil shapes.

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

In this specification, only the minimum components required for the description of the present invention are described, and components not related to the essence of the present invention are not mentioned. And it should not be interpreted as an exclusive meaning that includes only the mentioned components, but should be interpreted as a non-exclusive meaning that may include other components not mentioned.

“First”, “second” or similar expressions used in this specification are used to distinguish the same or similar components or to distinguish the names of the steps constituting the present invention, and the order It does not mean or mean that it is plural.

The method for setting the shape of the deformable wing lip according to the present invention may be executed by an electronic computing device such as a computer, tablet PC, mobile phone, portable computing device, or stationary computing device. Also, it should be understood that one or more methods or aspects of the invention may be executed by at least one processor. The processor may be installed in a computer, tablet PC, mobile device, portable computing device, or the like. A memory configured to store computer program instructions may be installed in such a device and may be specially programmed to cause a processor to execute the program instructions stored therein to execute one or more processes as described herein. In addition, it should be understood that the information and methods described in this specification may be executed by a computer, tablet PC, mobile device, portable computing device, etc. including one or more additional components and processors. In addition, the control logic may be implemented as a non-volatile computer readable medium including program instructions executable by a processor, a controller/control unit, or the like. Examples of computer readable media include, but are not limited to, ROM, RAM, CD-ROM, magnetic tape, floppy disk, flash drive, smart card, optical data storage device, and the like. In addition, the computer readable recording medium may be distributed to computers connected through a network, and the computer readable medium may be stored and executed in a distributed manner, for example, by a remote server or a controller area network (CAN).

The exemplary embodiments described herein provide a general understanding of the principles of the structure, function, fabrication and use of the devices and methods disclosed herein. One or more such embodiments are shown in the accompanying drawings. Those skilled in the art will understand that the devices and methods specifically described herein and illustrated in the accompanying drawings are non-limiting and illustrative examples, the scope of which is defined by the claims. Features shown and described in connection with one exemplary embodiment may also be combined with features of other embodiments. Such modifications or variations are intended to be included within the scope of the present invention.

1 shows an example of a wing (1; skin not shown) to which the deformable wing lip according to the present invention is applied, and FIG. 2 shows the structure of an individual wing lip. As shown in FIG. 1, a plurality of wing ribs constitute the inside of the wing, and according to the present invention, each wing rib can be deformed into a plurality of wing ribs.

Each individual wing lip has a control body 10, a front deployable scissor structure 20 connected to the control body 10, and a rear deployable scissor structure connected to the control body 10. It includes a rear deployable scissor structure (30) and an actuator (40) provided on the control body (10). The control body 10 may be provided on a spar. In addition, the individual wing lip may further include a front fixing shape portion 2 connected to the forward deployment type scissors structure 20 and a rear fixation shape portion 3 connected to the rear deployment type scissors structure 30 there is.

In the wing lip according to the present invention, one end 51 can be driven by an actuator 40, and the other end 52 is rotatably connected to the foremost link section 21 of the forward deployable scissor structure 20 The front drive shaft 50 and one end 61 are driven by the actuator 40, and the other end 62 is rotatable to the rearmost link section 31 of the rear deployable scissor structure 30 It further includes a rear drive shaft 60 connected thereto.

One of the rearmost link nodes 210 of the forward deployment type scissor structure 20 is rotatably connected to the control body 10, and the other one of the rearmost link nodes 220 of the front deployment type scissors structure 20 ) is connected to the control body 10 to enable linear motion. Linear motion may be implemented to be possible along the height direction (y-axis) of the control body 10 . In this specification, the meaning of following a predetermined direction includes not only the case of matching the corresponding direction, but also the case of following the corresponding direction at a predetermined angle.

One of the frontmost link nodes 310 of the rear deployment type scissor structure 30 is rotatably connected to the control body 10, and the other one 320 of the front most link nodes of the rear deployment type scissors structure 30 is It is connected to the control body 10 to enable linear motion. Linear motion may be implemented to be possible along the height direction (y-axis) of the control body 10 .

A skin support 70 may be provided at an end of each link section. The skin support 70 may be provided as a rotatable revolute joint according to the movement of the link section. Although not a major component of the present invention, the skin 100 is a material that follows the shape of an airfoil that is changed according to the operation of the deployable scissors structure according to the present invention, for example, shrinks in the chordwise direction. It can be made of a composite material that is easy to expand.

)는 일정하게 유지된다. 각도(

)가 일정하게 유지되면, 액츄에이터(40)의 구동에 의해 전방 전개형 가위 구조물(20)과 후방 전개형 가위 구조물(30)의 자유도는, 회전 중심과 전방 구동축(50)의 구동 지점(51)을 잇는 선과, 회전 중심에 y축 방향으로 그은 선이 형성하는 각도(

)에 의해서 결정될 수 있다. 자유도를 결정하는 각도는, 상기 회전 중심에 y축 방향으로 그은 직선과, 후방 구동축(60)의 구동 지점(61) 및 회전 중심을 잇는 선이 이루는 각도(

-

)를 사용할 수 있다. 그 밖에도 도 2(b)에 표시된 각도 중에서 고정값인

를 제외한 다르게 변하는 각도를 사용할 수도 있다.The angle formed by the line connecting the center of the rotation direction by the actuator 40 and the driving point 51 of the front driving shaft 50 and the line connecting the center and the driving point 61 of the rear driving shaft 60 (

) remains constant. Angle(

) is kept constant, the degree of freedom of the forward deployable scissor structure 20 and the rear deployable scissor structure 30 by the driving of the actuator 40 is the center of rotation and the drive point 51 of the front drive shaft 50 The angle formed by the line connecting and the line drawn in the y-axis direction at the center of rotation (

) can be determined by The angle determining the degree of freedom is an angle formed by a straight line drawn in the y-axis direction at the center of rotation and a line connecting the drive point 61 of the rear drive shaft 60 and the center of rotation (

-

) can be used. In addition, among the angles shown in FIG. 2 (b), the fixed value

Other varying angles may be used except for .

)를 임의로 설정하고, 링크절의 개수, 액츄에이터의 회전 반경, 스킨 지지부(70)의 치수, 전방 및 후방 구동축의 길이, 전방 형상 고정부(2)와 후방 형상 고정부(3)의 위치 조건 중 적어도 어느 하나를 제한 조건으로 설정한 후에 후술하는 바와 같은 최적화 과정을 거쳐서 링크절의 길이를 결정한다. 제한 조건으로 설정되지 않은 조건은 후술하는 최적화 과정에서 결정될 수 있다.The degree of freedom for changing the shape of the deformable wing lip according to the present invention is determined by the rotation angle of the drive shaft by the actuator 40 . Wing lips can be designed to implement multiple airfoil shapes. The airfoil shape may follow the form set by the National Aeronautical Advisory Committee (NACA). The angle to set as a degree of freedom for each airfoil to be implemented (

) is arbitrarily set, and at least among the number of link nodes, the radius of rotation of the actuator, the dimensions of the skin support 70, the length of the front and rear drive shafts, and the location conditions of the front shape fixing part 2 and the rear shape fixing part 3 After setting one of the limiting conditions, the length of the link clause is determined through an optimization process described later. Conditions that are not set as limiting conditions may be determined in an optimization process described later.

Hereinafter, a method for setting the shape of the deformable wing lip according to the present invention will be described.

The unfolding type scissors structure of the present invention is a structure in which the unit structure shown in FIG. 3 is continuous. In order to become a deployable scissor structure, the condition of “a ₀ + b ₀ = c ₀ + d ₀ ” must be satisfied.

4 shows an example of a rear deployment type scissors structure 30, and a schematic diagram of this structure is shown below.

A method for obtaining end coordinates of each link section of the backward deployment type scissor structure 30 will be described.

The frontmost link section of the rear deployable scissor structure 30, the rotation point of the link section 310 rotatably connected to the control body 10, and the control body 10 capable of linear motion Consider an imaginary triangle connecting the ends of the link clause 320.

The length of the line connecting the rotation point of the link clause 310 rotatably connected to the control body 10 and the end of the link clause 320 connected to the control body 10 to allow linear movement is λ. , and consider the leftmost triangle in the lower diagram of FIG. According to the movement of the link clause 320, λ may change.

Find the coordinates of point ③ in the initial triangle first.

The unit vector of [①->② direction] is first obtained. Since the λ line is parallel to the y-axis, this unit vector is easy to find. If the unit vector thus obtained is rotated clockwise by an angle (α), the unit vector in [①->③ direction] can be obtained.

Next, by rotating the unit vector in the [②->① direction] counterclockwise by an angle (β), the unit vector in the [②->③ direction] can be obtained.

By multiplying the unit vector of [①->③ direction] and the unit vector of [②->③ direction] by length values d ₀ and c ₀ respectively, the coordinates of point ③ can be calculated.

Using the coordinates of the point ③ and the above-mentioned principle, the coordinate values of the ends of the link sections of the next rear unit structure, that is, the points ④ and ⑤ can be calculated. Using this calculation method, all the coordinates of the end of the link section thereafter can be calculated, and since such a method can use appropriate mathematical and geometric principles, detailed descriptions will be omitted herein.

)를 임의로 설정하고, 링크절의 개수, 액츄에이터의 회전 반경, 스킨 지지부(70)의 치수, 전방 및 후방 구동축의 길이, 전방 형상 고정부(2)와 후방 형상 고정부(3)의 위치 조건을 제한 조건으로 설정한다. 제한 조건으로 설정하는 변수는 상기에 열거된 이외에 추가로 설정할 수도, 또는 상기 조건 중 일부를 배제할 수도 있다.When the coordinate value of the end of each link clause is calculated, the length of the link clause that minimizes the distance between the skin supporter 70 and the skin is calculated. To this end, as described above, the angle to set the degree of freedom for each airfoil (

) is arbitrarily set, and the number of linkages, the radius of rotation of the actuator, the dimensions of the skin support unit 70, the length of the front and rear drive shafts, and the location conditions of the front shape fixing unit 2 and the rear shape fixing unit 3 are limited set as condition Variables set as limiting conditions may be additionally set in addition to those listed above, or some of the above conditions may be excluded.

)를 다음과 같이 설정할 수 있다. 이 각도는 해당 에어 포일 형상을 구현하기 위한 유일한 값은 아니며, 설계자가 임으로 설정할 수 있다.When a specific wing lip is designed to implement the following 7 airfoil shapes, the degree of freedom angle (

) can be set as follows: This angle is not the only value for implementing the corresponding airfoil shape, and the designer can set it arbitrarily.

For each angle, the above-described limiting condition may be set identically.

Next, the distance between the skin support part 70 and the skin 100 is considered. As shown in FIG. 5 , the skin support part 70 is spaced apart from the skin 100 by a predetermined distance (d _m ). Since the airfoil to be implemented is determined as described above, the separation distance can be calculated from the coordinate value of the end of the link clause calculated by the above method, the size of the skin support part 70, and the shape of the skin of the airfoil. there is.

Four orientations in which the skin supporter 70 supports the skin 100 may be considered as shown in FIG. 6 . In addition to the alignment shown in FIG. 6, other types of alignment may be considered.

Figure 6 (a) is a state in which the skin support portion 70 is disposed in the vertical direction to support the skin 100, Figure 6 (b) is a state in which the skin support portion 70 supports the skin 100 in the longitudinal direction of the left link section 6 (c) is a state in which the skin support part 70 supports the skin 100 in the longitudinal direction of the right link section, and FIG. 6 (d) is at an angle half of the angle formed by the left and right link sections. It is a state in which the skin 100 is supported.

The separation distance (d _m ) in each support state is calculated, and the distance (d _m ) between the skin support 70 and the skin 100 provided at the end of the link section is the smallest distance among them. to decide

For any one airfoil shape, assuming that the number of points where the skin supporter 70 contacts the skin 100 is n, the sum of the minimum separation distances dm for all of those points (S _a ) is calculated. do.

Next, a value (T _ta ) obtained by summing S _a in Equation 1 calculated for all airfoils to be realized by the corresponding wing lip is calculated. If the number of all airfoils is M, M = 7 in the case of Table 1.

Next, optimization is performed so that the value calculated in Equation 2 is minimized. Optimization can be performed, for example, using the Fmincon function in MATLAB ^® . Optimization can be performed by substituting an arbitrary value for the length of the link clause, and if the difference between the previous T _ta value and the immediately following T _ta value is within a predetermined value, for example, 10 ^-7 or less, the optimization is considered completed. The link section length can be determined by the length of the link section of the deformable wing lip. As described above, other conditions not set as limiting conditions may also be determined through an optimization process.

As described above, when the length of the link section for each airfoil shape is determined, the wing lip of the aforementioned structure is manufactured accordingly.

)를 7도로 하면 되며, 그 이후 비행 도중에 에어포일을 NACA3410으로 변경해야 하는 경우에는 액츄에이터(40)를 작동시켜서 각도(

)를 13도로 변경하기만 하면 새로운 에어포일 형상의 구현이 가능하다. 표 1의 다른 에어포일 형상도 (

)를 변경하기만 하면 구현할 수 있다.For example, in order to realize the NACA2410 airfoil, the deformable wing lip according to the present invention capable of implementing the airfoil shape of Table 1 operates the actuator 40 to adjust the angle (

) to 7 degrees, and then, if the airfoil needs to be changed to the NACA3410 mid-flight, the actuator 40 is operated to adjust the angle (

) to 13 degrees, it is possible to implement a new airfoil shape. Other airfoil shapes in Table 1 (

) can be implemented by simply changing

7 shows a state in which one wing lip according to the present invention is deformed to have various airfoils.

The length of the link section is determined through the above process so as to implement a desired airfoil for each of the plurality of wing ribs constituting the wing.

According to the present invention, since one wing lip can implement the shape of a plurality of airfoils only by driving an actuator, there is an effect of providing a wing lip that can actively adapt to various flight environments without imparting discontinuity to the wing.

Although the present invention has been described with reference to the accompanying drawings, the scope of the present invention is determined by the claims described below and should not be construed as being limited to the above-described embodiments and / or drawings. And it should be clearly understood that improvements, changes and modifications obvious to those skilled in the art of the invention described in the claims are also included in the scope of the present invention.

10: control body 20: forward deployable scissor structure
30: rear deployable scissor structure 40: actuator
50: front drive shaft 60: rear drive shaft
70: skin support 100: skin

Claims (8)

a control body;
A forward deployable scissor structure connected to the control body;
A rear deployable scissor structure connected to the control body;
an actuator provided on the control body;
One end is driveable by an actuator, and the other end is a front drive shaft rotatably connected to the frontmost link section of the forward deployable scissor structure;
One end can be driven by an actuator, and the other end includes a rear driving shaft rotatably connected to the rearmost link section of the rear deployable scissor structure,
One of the rearmost link nodes of the forward deployable scissor structure is rotatably connected to the control body,
The other one of the rearmost link nodes of the forward deployable scissor structure is connected to the control body for linear movement,
One of the frontmost linkages of the rear deployable scissor structure is rotatably connected to the control body,
The other one of the foremost linkages of the forward deployable scissor structure is connected to the control body for linear movement,
Deformable wing lip.
The method of claim 1,
The linear motion is along the height direction of the control body,
Deformable wing lip.
The method of claim 2,
Further comprising a skin support provided at the end of the link section of the forward deployment type scissors structure and the rear deployment type scissors structure,
Deformable wing lip.
The method of claim 3,
The skin support is provided as a rotatable revolute joint according to the movement of the link clause,
Deformable wing lip.
In the claim of any one of claims 1 to 3,
The angle formed by the line connecting the center of rotation by the actuator and the drive point of the front drive shaft and the line connecting the center of rotation and the drive point of the rear drive shaft is maintained constant,
Deformable wing lip.
In the method for setting the shape of the deformable wing lip of claim 5 by an electronic calculation device,
For the desired plurality of airfoils to be implemented by the wing lip, a predetermined straight line passing through the center and a line connecting the center and the drive point of the front drive shaft or the drive point of the rear drive shaft Formation of an angle Step 1;
A second step of setting at least one of the number of link nodes of the front deployable scissor structure and the rear deployable scissor structure, the radius of rotation by the actuator, the size of the skin support unit, the length of the front drive shaft and the rear drive shaft as a limiting condition;
A third step of calculating the coordinates of the ends of the link nodes of the forward deployment type scissors structure and the rear deployment type scissors structure;
A fourth step of calculating a minimum value of the distance between the skin support part and the skin for each skin support part and calculating a sum of the calculated values;
A fifth step of determining a condition that is not set as a limiting condition by performing optimization so that the sum calculated in the fourth step is minimized,
How to set the shape of the deformable wing lip.
The method of claim 6,
The condition determined in the fifth step is the length of the link clause,
How to set the shape of the deformable wing lip.
The method of claim 6,
The shape of the desired airfoil is plural,
The first step is to set different angles for each shape of a plurality of airfoils,
The sum value of the fourth step is the sum value for a plurality of airfoil shapes,
How to set the shape of the deformable wing lip.

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