Morphing wing surface support using pantograph structure, morphing wing including the same and aircraft including morphing wing

Abstract

A deformable wing surface support using a pantograph structure according to one embodiment of the present invention may include: an upper pantograph structure portion provided to support the upper outer surface of the wing surface of an aircraft and arranged to be linearly deformable along the wing length direction; and a lower pantograph structure portion provided to support the lower outer surface of the wing surface and arranged to be linearly deformable along the wing length direction.

Description

Technology Field

[0001] The present invention relates to a deformable wing surface support using a pantograph structure, a deformable wing including the same, and an aircraft including the deformable wing. Background Technology

[0002] Conventional morphing wing aircraft change their shape in only one of two ways: in-plane space or out-of-plane space. Here, changes in shape in-plane include changes in wing length, wing area, wing chord length, and sweep back angle, while changes in shape out-of-plane include changes in airfoil thickness, airfoil camber, airfoil twist, and dihedral angle.

[0003] Due to limitations in structural stability, existing aircraft could not have a structure where the outer surface itself changes, as they utilized materials that do not easily deform under external forces.

[0004] In addition, conventional aircraft have operated with separate structures responsible for changes in wing shape (out-of-plane shape changes) and changes in wing surface shape (in-plane shape changes (changes in wing length and area)).

[0005] The technology forming the background of the present invention is disclosed in Korean Registered Patent Publication No. 10-1902698. The problem to be solved

[0006] The present invention aims to solve the problems of the aforementioned prior art by providing an aircraft capable of linear deformation along the wing length direction, a wing surface support capable of changing the in-plane shape (wing length and area) of the wing by creating an outer surface support for the aircraft wing, a deformable wing including the same, and an aircraft including the deformable wing.

[0007] The present invention aims to solve the problems of the aforementioned prior art by providing a wing surface support capable of simultaneously performing changes in the in-plane shape (wing length and area) and the out-plane shape (wing shape) of a wing with a single structure, a deformable wing including the same, and an aircraft including the deformable wing.

[0008] However, the technical problems that the embodiments of the present invention aim to solve are not limited to the technical problems described above, and other technical problems may exist. means of solving the problem

[0009] As a technical means for achieving the above-mentioned technical problem, a deformable wing surface support using a pantograph structure according to one embodiment of the present invention may include: an upper pantograph structure portion provided to support the upper outer surface of the wing surface of an aircraft and arranged to be linearly deformable along the wing length direction; and a lower pantograph structure portion provided to support the lower outer surface of the wing surface and arranged to be linearly deformable along the wing length direction.

[0010] Additionally, the upper pantograph structure may include a plurality of first upper rods and a plurality of second upper rods arranged to intersect each other to form an upper pantograph structure that is linearly deformed in the wing length direction; and an upper rotational joint provided to have a degree of rotational freedom at one or more of a plurality of upper intersection points between the plurality of first upper rods and the plurality of second upper rods, and the lower pantograph structure may include a plurality of first lower rods and a plurality of second lower rods arranged to intersect each other to form a lower pantograph structure that is linearly deformed in the wing length direction; and a lower rotational joint provided to have a degree of rotational freedom at one or more of a plurality of lower intersection points between the plurality of first lower rods and the plurality of second lower rods.

[0011] Additionally, the wing surface support may further include a linear actuator that linearly adjusts the positions of the upper rotational joint and the lower rotational joint along the wing length direction.

[0012] Additionally, the upper rotational joint and the lower rotational joint are positioned facing each other in an in-plane state where no out-of-plane shape change occurs, and the linear actuator may include a slider member that is configured to move linearly in the wing length direction and is connected to the upper rotational joint and the lower rotational joint in a linear movement-linked manner; and a linear driving unit that drives the slider member along the wing length direction.

[0013] Additionally, the linear drive unit comprises: a barrel cam that extends along the wing length direction and has a barrel cam groove line formed on its outer circumference; a gear unit that transmits rotational driving force to the barrel cam to rotate the barrel cam; and a gear drive unit that drives the gear unit, and the slider member may be coupled to the barrel cam so as to move linearly along the wing length direction when a follower formed inside it moves along the barrel cam groove line.

[0014] Additionally, the linear actuator further includes a fixed end for a slider guide that wraps around at least a portion of the outer surface of the slider member to guide the slider member to move linearly in the wing length direction by preventing twisting of the slider member, and the fixed end for the slider guide can be fixed to the fuselage of the aircraft.

[0015] Additionally, the linear actuator may include: an out-of-plane change drive unit mounted on the slider member to enable rotational driving with the wing length direction as an axis on the slider member; an upper interlocking member connecting the rotation axis of the out-of-plane change drive unit and the upper rotational joint; and a lower interlocking member connecting the rotation axis of the out-of-plane change drive unit and the lower rotational joint.

[0016] In addition, when the out-of-plane change driving unit is rotated in the in-plane state, the upper rotation joint and the lower rotation joint are each shifted in opposite directions, such that the wing chord direction or the front-rear direction, thereby enabling an out-of-plane shape change of the upper pantograph structure and the lower pantograph structure.

[0017] In addition, in an in-plane state where no shape change in the out-of-plane direction occurs, any one of the plurality of first lower rods and any one of the plurality of first upper rods facing any one of the plurality of first lower rods are provided to be connected to one or more of the front and rear ends in the wing chord direction, and the upper pantograph structure and the lower pantograph structure are set considering the range of shape change in the out-of-plane space so as to have elasticity capable of accommodating the difference even if a difference within a preset range occurs with respect to the wing chord direction or the front-rear direction, and the preset range may be set considering the connection relationship between any one of the plurality of first lower rods and any one of the plurality of first upper rods.

[0018] A wing according to one embodiment of the present invention may include the deformable wing surface support.

[0019] In addition, an aircraft according to one embodiment of the present invention may include the wing.

[0020] The means for solving the problem described above are merely exemplary and should not be interpreted as intended to limit the present invention. In addition to the exemplary embodiments described above, additional embodiments may exist in the drawings and the detailed description of the invention. Effects of the invention

[0021] According to the means for solving the problem of the present invention described above, by providing a pantograph structure, a rotary joint having rotational degrees of freedom, and a linear actuator that adjusts linearly along the wing length direction, a wing surface support capable of changing shape in in-plane space, a deformable wing including the same, and an aircraft including the deformable wing can be provided.

[0022] According to the means for solving the problem of the present invention described above, by providing an out-of-plane change driving unit, an upper rotational joint and a lower rotational joint are each shifted in opposite directions in the wing chord direction or the front-rear direction, thereby enabling an out-of-plane shape change of the wing surface support, a deformable wing including the same, and an aircraft including the deformable wing can be provided.

[0023] However, the effects obtainable from this invention are not limited to those described above, and other effects may exist. Brief explanation of the drawing

[0024] FIG. 1 is a drawing for explaining the configuration of an upper pantograph structure and a lower pantograph structure according to one embodiment of the present invention. FIG. 2 is a drawing for explaining a rotary joint fastening type according to one embodiment of the present invention. FIG. 3 is a drawing for explaining the principle of in-plane spatial shape change (movement in the wing length direction) of a deformable wing surface support (pantograph-type wing frame) using a pantograph structure according to one embodiment of the present invention. FIG. 4 is an isometric view of a deformable wing surface support (wing frame) using a pantograph structure according to one embodiment of the present invention. FIG. 5 is a drawing illustrating an internal driving method of a pantograph structure according to one embodiment of the present invention and a view of applying a wing surface support (pantograph structure) to an aircraft. FIG. 6 is a drawing for explaining a linear actuator according to one embodiment of the present invention. FIG. 7 is a drawing for explaining a linear driving unit according to one embodiment of the present invention. FIG. 8 is a drawing for explaining a slider member according to one embodiment of the present invention. FIG. 9 is a drawing illustrating the connection relationship between a barrel cam, a slider member, and a fixed end for a slider guide according to one embodiment of the present invention. FIGS. 10 and FIGS. 11 are drawings illustrating how a fixed end for a slider guide according to one embodiment of the present invention is connected to a body contact portion. FIG. 12 is a drawing for explaining an out-of-plane change driving unit according to one embodiment of the present invention. FIG. 13 is a drawing for explaining an embodiment of a guide member according to one embodiment of the present invention. FIG. 14 is a drawing for explaining another embodiment of a guide member according to one embodiment of the present invention. FIG. 15 is a side view of the shape change of the cross-section of a rod (bar) when the shape changes in an out-of-plane direction according to one embodiment of the present invention. FIG. 16a is an isometric projection of the overall shape change when an upper rotary joint (wing-shaped joint) according to one embodiment of the present invention is moved linearly in the forward direction. FIG. 16b is an isometric projection of the overall shape change when an upper rotary joint (wing-shaped joint) according to one embodiment of the present invention is moved linearly in the trailing edge direction. Specific details for implementing the invention

[0025] Embodiments of the present invention are described below with reference to the attached drawings to enable those skilled in the art to easily implement the invention. However, the present invention may be embodied in various different forms and is not limited to the embodiments described herein. Furthermore, in order to clearly explain the present invention in the drawings, parts unrelated to the explanation have been omitted, and similar parts throughout the specification are denoted by similar reference numerals.

[0026] Throughout this specification, when a part is described as being "connected" to another part, this includes not only cases where they are "directly connected," but also cases where they are "electrically connected" or "indirectly connected" with other elements interposed between them.

[0027] Throughout the entire specification, when a component is described as being located "on," "on top," "on top," "under," "on bottom," or "on bottom" of another component, this includes not only cases where the component is in contact with the other component but also cases where another component exists between the two components.

[0028] Throughout this specification, when a part is described as "comprising" a certain component, this means that, unless specifically stated otherwise, it does not exclude other components but may include additional components.

[0029] The present invention relates to a deformable wing surface support using a pantograph structure, a deformable wing including the same, and an aircraft including the deformable wing. Specifically, the present invention relates to a deformable wing surface support (support member) using an elastic pantograph-type surface structure and a higher configuration (wing or aircraft) including the same.

[0030] Hereinafter, a deformable wing surface support using a pantograph structure according to one embodiment of the present invention (hereinafter referred to as 'the wing surface support (100)') will be described.

[0031] FIG. 1 is a drawing for explaining the configuration of an upper pantograph structure and a lower pantograph structure according to one embodiment of the present invention.

[0032] Referring to FIG. 1, the wing surface support (100) is provided to support the upper outer surface of the wing surface of the aircraft (200) and may include an upper pantograph structure (110) arranged to be linearly deformable along the wing length direction. Here, the wing length direction may correspond to the transverse direction in FIG. 1 and may mean a direction perpendicular to the fuselage of the aircraft (200). In addition, the term aircraft (200) may refer to an airplane, a glider, and various aircraft (200) requiring morphing flight.

[0033] Additionally, the upper pantograph structure (110) may include a plurality of first upper rods (111) and a plurality of second upper rods (112) arranged to intersect each other to form an upper pantograph structure that is linearly deformed in the wing length direction. For example, referring to FIG. 1, the plurality of first upper rods (111) may be arranged parallel to each other in a tilted state (in the 1 o'clock to 7 o'clock direction in FIG. 1), and the plurality of second upper rods (112) may be arranged parallel to each other in a tilted state (in the 11 o'clock to 5 o'clock direction in FIG. 1) to intersect the plurality of first upper rods (111). In other words, the plurality of first upper rods (111) and the plurality of second upper rods (112) may be arranged to form a diagonally woven pantograph (scissor structure) surface structure.

[0034] Additionally, a plurality of first upper rods (111) and a plurality of second upper rods (112) may be provided as elastic members (flexible members having a predetermined bending elasticity). Accordingly, since a plurality of first upper rods (111) and a plurality of second upper rods (112) are provided as elastic members, the upper pantograph structure (110) (support part) is elastic but maintains a stable state in the target shape, so it can maintain its shape even against external drag.

[0035] FIG. 2 is a drawing for explaining a rotary joint fastening type according to one embodiment of the present invention, and FIG. 3 is a drawing for explaining the principle of in-plane spatial shape change (movement in the wing length direction) of a deformable wing surface support (pantograph-type wing frame) using a pantograph structure according to one embodiment of the present invention.

[0036] Additionally, referring to FIGS. 1 and 2, the upper pantograph structure (110) may include an upper rotational joint (113) provided to have a degree of rotational freedom at one or more of a plurality of upper intersection points between a plurality of first upper rods (111) and a plurality of second upper rods (112). The upper rotational joint (113) is provided to allow upper rods (111, 112) that intersect each other at the intersection points of the plurality of upper rods (111, 112) to be joined, and the plurality of upper rods (111, 112) can be connected to the upper rotational joint (113) at the respective upper and lower surfaces at the intersection points. In other words, each rod (a plurality of upper rods (111, 112)) of the upper surface of the wing (upper pantograph structure (110)) can be connected to the rotational joint (upper rotational joint (113)) at the intersection points so that they can rotate on the upper and lower surfaces.

[0037] Additionally, referring to FIGS. 2 and 3, the upper rotation joint (113) combines two upper rods (111, 112) (rods) that intersect each other, and the upper rods (111, 112) (rods) can each rotate in different directions to change the overall shape. Specifically, the upper rotation joint (113) combines the first upper rod (111) and the second upper rod (112) at the upper intersection of the first upper rod (111) and the second upper rod (112), and the combined first upper rod (111) and the second upper rod (112) can each rotate in opposite directions to change the shape of the wing in the in-plane direction. Here, the shape change in the in-plane direction may include a change in wing length, a change in wing area, a change in wing chord length, and a change in wing sweep back angle.

[0038] For example, referring to FIG. 3, when the first upper rod (111) (rod) arranged from the upper right to the lower left (1 o'clock to 7 o'clock direction) is rotated clockwise, the wing length (length in the horizontal direction in FIG. 3) may decrease and the wing chord length (length in the vertical direction in FIG. 3) may increase. As another example, when the first upper rod (111) (rod) arranged from the upper right to the lower left (1 o'clock to 7 o'clock) is rotated counterclockwise, the wing length (length in the horizontal direction in FIG. 3) may increase and the wing chord length (length in the vertical direction in FIG. 3) may decrease.

[0039] In other words, the upper pantograph structure (110) (wing frame) may include a plurality of elastic upper rods (111, 112) (rods), and the plurality of upper rods (111, 112) (rods) may be joined at an intersection point by an upper rotational joint (113) (rotational joint). Two upper rods (111, 112) (rods) joined at one upper rotational joint (113) (joint) may rotate in opposite directions to change the overall shape. Thus, the wing outer surface support (100) can provide an upper pantograph structure (110) (wing frame using a pantograph) that operates on a principle similar to a scissors mechanism.

[0040] Referring to FIG. 1, the wing outer surface support (100) may include a lower pantograph structure (120) that is provided to support the lower outer surface of the wing and is arranged to be linearly deformable along the wing length direction.

[0041] Additionally, the lower pantograph structure (120) may include a plurality of first lower rods (121) and a plurality of second lower rods (122) arranged to intersect each other to form a lower pantograph structure that is linearly deformed in the wing length direction. For example, referring to FIG. 1, the plurality of first lower rods (121) may be arranged parallel to each other in a tilted state (in the 1 o'clock to 7 o'clock direction in FIG. 1), and the plurality of second lower rods (122) may be arranged parallel to each other in a tilted state (in the 11 o'clock to 5 o'clock direction in FIG. 1) to intersect the plurality of first lower rods (121). In other words, the plurality of first lower rods (121) and the plurality of second lower rods (122) may be arranged to form a diagonally woven pantograph (scissor structure) surface structure.

[0042] Additionally, a plurality of first lower rods (121) and a plurality of second lower rods (122) may be provided as elastic members. Accordingly, since a plurality of first lower rods (121) and a plurality of second lower rods (122) are provided as elastic members, the lower pantograph structure (120) (support member) is elastic but maintains a stable state in the target shape, so it can maintain its shape even against external drag.

[0043] In other words, the wing surface support (100) can provide a wing of a diagonally woven pantograph (scissor structure) surface structure through an upper pantograph structure (110) and a lower pantograph structure (120) using an elastic rod (material).

[0044] Additionally, referring to FIGS. 1 and 2, the lower pantograph structure (120) may include a lower rotational joint (123) provided to have a degree of rotational freedom at one or more of a plurality of lower intersection points between a plurality of first lower rods (121) and a plurality of second lower rods (122). The lower rotational joint (123) is provided to allow the lower rods (121, 122) that intersect each other at the intersection points of the plurality of lower rods (121, 122) to be joined, and the plurality of lower rods (121, 122) can be joined to the lower rotational joint (123) at the intersection points on their respective upper and lower surfaces. In other words, each rod (a plurality of lower rods (121, 122)) of the lower surface of the wing (lower pantograph structure (120)) can be joined to the rotational joint (lower rotational joint (123)) at the intersection points so that they can rotate on the upper and lower surfaces.

[0045] Additionally, referring to FIGS. 2 and 3, the lower rotation joint (123) combines two intersecting lower rods (121, 122) (rods), and the lower rods (121, 122) (rods) can each rotate in different directions to change the overall shape. Specifically, the lower rotation joint (123) combines the first lower rod (121) and the second lower rod (122) at the lower intersection of the first lower rod (121) and the second lower rod (122), and the combined first lower rod (121) and the second lower rod (122) can each rotate in opposite directions to change the shape in the in-plane direction of the wing.

[0046] For example, referring to FIG. 3, when the first lower rod (121) (rod) arranged from the upper right to the lower left (1 o'clock to 7 o'clock direction) is rotated clockwise, the wing length (length in the horizontal direction in FIG. 3) may decrease and the wing chord length (length in the vertical direction in FIG. 3) may increase. As another example, when the first lower rod (121) (rod) arranged from the upper right to the lower left (1 o'clock to 7 o'clock) is rotated counterclockwise, the wing length (length in the horizontal direction in FIG. 3) may increase and the wing chord length (length in the vertical direction in FIG. 3) may decrease.

[0047] In other words, the lower pantograph structure (120) (wing frame) may include a plurality of elastic lower rods (121, 122) (rods), and the plurality of lower rods (121, 122) (rods) may be joined at an intersection point by a lower rotational joint (123) (rotational joint). Two lower rods (121, 122) (rods) joined at one lower rotational joint (123) (joint) may rotate in opposite directions to change the overall shape. Thus, the wing outer surface support (100) can provide a lower pantograph structure (120) (wing frame using a pantograph) that operates on a principle similar to a scissors mechanism.

[0048] FIG. 4 is an isometric view of a deformable wing surface support (wing frame) using a pantograph structure according to one embodiment of the present invention.

[0049] Referring to FIG. 4, a plurality of first upper rods (111) and a plurality of first lower rods (121) may be arranged facing each other, and a plurality of second upper rods (112) and a plurality of second lower rods (122) may be arranged facing each other.

[0050] Additionally, referring to FIGS. 2 and 4, the upper rotational joint (113) and the lower rotational joint (123) may be positioned facing each other in an in-plane state where no out-of-plane shape change occurs. Here, the out-of-plane shape change may include a change in the thickness of the airfoil, a change in the airfoil camber, a change in the airfoil twist, and a change in the dihedral angle of the airfoil. At this time, the upper rotational joint (113) and the lower rotational joint (123) facing it may be connected by an elastic member provided so as to maintain a state of facing each other even in the in-plane movement direction of the airfoil.

[0051] Additionally, in an in-plane state where no shape change occurs in the out-of-plane direction, any one of the plurality of first lower rods (121) and any one of the plurality of first upper rods (111) facing any one of the plurality of first lower rods (121) may be provided such that one or more of the front and rear ends in the wing chord direction are connected to each other. Specifically, referring to FIG. 4, the front end (upper side in FIG. 4) in the wing chord direction of any one of the plurality of first lower rods (121) and any one of the plurality of first upper rods (111) facing any one of the plurality of first lower rods (121) may be connected in a curved manner, and the rear end (lower side in FIG. 4) in the wing chord direction of the first upper rod (111) and the first lower rod (121) may be connected so as to overlap each other.

[0052] Additionally, the front end (upper side in FIG. 4) in the wing chord direction of any one of the plurality of second lower rods (122) and any one of the plurality of second upper rods (112) facing any one of the plurality of second lower rods (122) can be connected in a curved manner to each other, and the rear end (lower side in FIG. 4) in the wing chord direction of any one of the plurality of second lower rods (122) and any one of the plurality of second upper rods (112) facing any one of the plurality of second lower rods (122) can be connected so as to overlap each other.

[0053] Accordingly, the framework (upper pantograph structure part (110) and lower pantograph structure part (120)) constituting the surface of the wing exhibits the characteristics of a pantograph (scissor structure) and may have an airfoil shape when viewed from the side. Since the connection of such a plurality of upper rods (111, 112) and lower rods (121, 122) facing the upper rods (111, 112) is obvious to a person skilled in the art, a detailed explanation will be omitted. Furthermore, it is preferable to understand the airfoil broadly in the sense that it encompasses a state in which any one of the plurality of lower rods (121, 122) and any one of the plurality of upper rods (111, 112) facing any one of the plurality of lower rods (121, 122) are connected to each other.

[0054] FIG. 5 is a drawing for explaining the internal driving method of a pantograph structure according to one embodiment of the present invention and the appearance of applying a wing surface support (pantograph structure) to an aircraft, and FIG. 6 is a drawing for explaining a linear actuator according to one embodiment of the present invention.

[0055] Referring to FIGS. 5 and 6, the wing surface support (100) may include a linear actuator (130) that linearly adjusts the position of the upper rotational joint (113) and the lower rotational joint (123) along the wing length direction. In other words, the wing surface support (100) can move two rotational joints (upper rotational joint (113) and lower rotational joint (123)) that are symmetrically positioned (opposite to each other) from the center along the wing length direction using the linear actuator (130), thereby allowing the wing surface support (100) (pantograph surface structure) to change the shape in the in-plane space including the wing span, area, and chord length of the aircraft (200) by changing the angle between each rib.

[0056] FIG. 7 is a drawing for explaining a linear driving unit according to one embodiment of the present invention, FIG. 8 is a drawing for explaining a slider member according to one embodiment of the present invention, and FIG. 9 is a drawing for explaining the connection relationship of a barrel cam, a slider member, and a fixed end (133) for a slider guide according to one embodiment of the present invention.

[0057] Referring to FIGS. 6 and 7, the linear actuator (130) is configured to be linearly movable in the wing length direction and may include a slider member (131) connected to the upper rotational joint (113) and the lower rotational joint (123) in a linearly movable manner, and a linear driving unit (132) that drives the slider member (131) along the wing length direction. For example, an elastic member connecting the upper rotational joint (113) and the lower rotational joint (123) that are opposite each other is connected to the slider member (131), and when the slider member (131) is linearly moved by the linear driving unit (132), the upper rotational joint (113) and the lower rotational joint (123) are linearly moved together, so that a plurality of upper rods (111, 112) and a plurality of lower rods (121, 122) can move. Accordingly, the wing surface support (100) viewed through the linear actuator (130) may be able to change in the in-plane direction of the wing.

[0058] Referring to FIGS. 6 and 7, the linear drive unit (132) may include a barrel cam (132a) that extends along the wing length direction and has a barrel cam groove line (132ab) formed on its outer circumference, a gear unit (132b) that transmits rotational driving force to the barrel cam (132a) to rotate the barrel cam (132a), and a gear drive unit (132c) that drives the gear unit (132b).

[0059] For example, referring to FIGS. 6 and 7, the gear section (132b) and the gear drive unit (132c) may be located at the center of the fuselage of the aircraft (200), and two barrel cams (132a) may be provided symmetrically around the gear section (132b) so as to extend from the center of the fuselage of the aircraft (200) to both sides in the longitudinal direction of the wing. Additionally, the gear section (132b) may include a first gear connected to the gear drive unit (132c) and a second gear connected to the first gear that transmits rotational driving force to the barrel cam (132a) to rotate the barrel cam (132a). Additionally, the barrel cam (132a) may be attached to the second gear and rotate as the gear section (132b) rotates. At this time, various rotary motors capable of transmitting rotational driving force to the barrel cam (132a) may be applied to the gear drive unit (132c).

[0060] Referring to FIGS. 6 through 9, the slider member (131) can be coupled with the barrel cam (132a) so that the follower (131a) formed therein moves along the barrel cam groove line (132ab) and moves linearly along the wing length direction.

[0061] Specifically, referring to FIGS. 6, 8, and 9, the slider member (131) has a hole formed therein through which the barrel cam (132a) can pass, and a follower (131a) may be provided inside the slider member (131). Additionally, referring to FIG. 7, the barrel cam (132a) may have a barrel cam groove line (132ab), which is a groove-shaped line, provided in a spiral shape along the outer circumference of the barrel cam (132a). At this time, the follower (131a) provided inside the slider member (131) is provided to engage with the barrel cam groove line (132ab), so that as the barrel cam (132a) rotates, the follower (131a) of the slider member (131) can move in engagement with the barrel cam groove line (132ab), and accordingly, the slider member (131) can move linearly along the wing length direction on the outer circumference of the barrel cam (132a).

[0062] In other words, referring to FIGS. 5 to 9, the gear drive unit (132c) (motor) in the middle of the linear actuator (130) can be engaged with the barrel cam (132a) (a rod on which a profile line (barrel cam groove line (132ab))) to rotate the barrel cam (132a) (profile rod). At this time, the follower (131a) of the slider member (131) (slider rod) can move in a straight direction (wing length direction) along the barrel cam groove line (132ab) (profile line), and accordingly, the slider member (131) can be linearly moved along the wing length direction on the outer circumference of the barrel cam (132a).

[0063] As another example, a groove line of the slider member (131), which is a groove-shaped line inside the slider member (131), may be provided, and a follower may be provided at the end of the barrel cam (132a). In this case, the follower of the barrel cam (132a) is provided to engage with the groove line of the slider member (131), so that as the barrel cam (132a) rotates, the slider member (131) can be linearly moved along the wing length direction on the outer circumference of the barrel cam (132a) through the engaging connection between the groove line of the slider member (131) and the follower of the barrel cam (132a).

[0064] FIGS. 10 and FIGS. 11 are drawings illustrating how a fixed end for a slider guide according to one embodiment of the present invention is connected to the fuselage of an aircraft.

[0065] Referring to FIGS. 6 and FIGS. 9 through 11, the linear actuator (130) may include a fixed end (133) for a slider guide that wraps around at least a portion of the outer surface of the slider member (131) to guide the slider member (131) to move linearly in the wing length direction by preventing twisting of the slider member (131). Specifically, as described above, as the barrel cam (132a) rotates, the follower (131a) inside the slider member (131) can move along the barrel cam groove line (132ab). At this time, the slider member (131) can move only in the wing length direction without being twisted by the fixed end (133) for the slider guide.

[0066] Additionally, referring to FIGS. 6 and 9, a fixed end (133) for a slider guide has a hole formed therein through which a slider member (131) can pass, and a barrel cam (132a) and a slider member (131) can be positioned inside the fixed end (133) for the slider guide. At this time, the size of the hole in the fixed end (133) for the slider guide can be set so that as the barrel cam (132a) rotates, the follower (131a) inside the slider member (131) moves along the barrel cam groove line (132ab), preventing twisting and detachment of the slider member (131) and allowing the slider member (131) to move linearly in the wing length direction.

[0067] Additionally, referring to FIGS. 6, 10, and 11, the fixed end (133) for the slider guide can be fixed to the fuselage of the aircraft (200). Specifically, the fixed end (133) for the slider guide can be fixed to the fuselage of the aircraft (200) by being connected to a fuselage fixed end (133a) that is in contact with the fuselage of the aircraft (200).

[0068] In other words, the fixed end (133) for the slider guide is attached to and fixed to the body of the aircraft (200) and may be provided to perform the function of fixing the slider member (131) inside so that it moves only linearly without twisting.

[0069] Referring to FIG. 6, the linear actuator (130) may include an out-of-plane change drive unit (134) mounted on the slider member (131) to enable rotational driving with the wing length direction as an axis. Specifically, the out-of-plane change drive unit (134) may be mounted at both ends of the slider member (131). However, the position of the out-of-plane change drive unit (134) is not limited to this and may be located at various positions that enable out-of-plane change of the wing. Additionally, the out-of-plane change drive unit (134) may be a servo motor that enables out-of-plane change of the airfoil, but is not limited to this and may be a variety of drive units that enable out-of-plane change of the airfoil.

[0070] FIG. 13 is a drawing for explaining one embodiment of a guide member according to one embodiment of the present invention, and FIG. 14 is a drawing for explaining another embodiment of a guide member according to one embodiment of the present invention. Specifically, FIG. 14 is a drawing for explaining a structure installed on an out-of-plane change driving unit (134) (servo motor) located at the end of a slider member (131) (slide rod) to move the position of a rotational joint (113).

[0071] Referring to FIGS. 6, 13, and 14, the linear actuator (130) may include an upper interlocking member (135) connecting the rotation axis of the out-of-plane change drive unit (134) to the upper rotation joint (113) and a lower interlocking member (136) connecting the rotation axis of the out-of-plane change drive unit (134) to the lower rotation joint (123).

[0072] Additionally, referring to FIGS. 13 and 14, the linear actuator (130) may include a guide member (137). The guide member (137) is configured to be connected to an upper linkage member (135) and a lower linkage member (136), and may be configured to guide the movement path of the upper linkage member (135) and the lower linkage member (136) as the out-of-plane change driving unit (134) rotates.

[0073] Referring to FIG. 13 as an embodiment of the guide member (137), the guide member (137) may be provided in the form of multiple link members that are linked in multiple ways with the upper linkage member (135) and the lower linkage member (136). For example, the guide member (137) may be provided as three guide members that are hinged to a rotating plate (a flat rhombus-shaped plate in FIG. 13) that is linked to the rotation of the out-of-plane change driving unit (134). The first guide member may be configured such that it is hinged to the rotation center of the rotating plate and both ends are linked in a hinged manner to one end of each of the upper linkage member (135) and the lower linkage member (136). The second guide member may be configured such that one end is hinged to one side of the rotating plate and the other end is linked in a hinged manner to the middle of the upper linkage member (135). The third guide member may be configured such that one end is hinge-connected to the other side of the rotating plate, and the other end is linked in a hinge-connected form to the middle of the lower interlocking member (136). Through this multi-link connection structure of multiple guide members (137), the movement path of the upper interlocking member (135) and the lower interlocking member (136) can be guided as the out-of-plane change driving unit (134) rotates.

[0074] Additionally, referring to FIG. 14 as another embodiment of the guide member (137), the linear actuator (130) may include a first bearing (138) that moves the upper interlocking member (135) or the lower interlocking member (136) while sliding (moving) along the guide member (137), and a second bearing (139) that connects the rotational joint (113, 123) and the corresponding interlocking member (135, 136).

[0075] Specifically, referring to FIG. 14, when the out-of-plane change drive unit (134) rotates, the guide member (137) also rotates, and the first bearing (138) (end bearing) slides (moves) along the guide member (137), thereby pulling or pushing the upper linkage member (137) (steel wire). Accordingly, the upper linkage member (137) (steel wire) can adjust the position of the upper rotational joint (113) (rod joint) to ultimately change the position of the upper rotational joint (113). However, FIG. 14 only illustrates the connection relationship between the upper linkage member (135) and the upper rotational joint (113), and it is obvious that the connection relationship between the lower linkage member (136) and the lower rotational joint (123) can also be connected (linked) in the same or similar configuration and method as needed.

[0076] Additionally, the upper interlocking member (135) and the lower interlocking member (136) may be provided as elastic members. For example, the elastic member may be a rotational elastic member. However, the elastic member is not limited only to a rotational elastic member, and the upper interlocking member (135) and the lower interlocking member (136) may be provided as various elastic members having an elastic restoring force related to rotational elasticity.

[0077] FIG. 15 is a side view of the shape change of the cross-section of a rod (rod) when the shape changes out of plane according to one embodiment of the present invention, FIG. 16a is an isometric projection of the overall shape change when the upper rotational joint (wing-shaped joint) is moved linearly in the forward direction according to one embodiment of the present invention, and FIG. 16b is an isometric projection of the overall shape change when the upper rotational joint (wing-shaped joint) is moved linearly in the trailing direction according to one embodiment of the present invention.

[0078] Referring to FIGS. 14 to 16b, when the drive unit (134) for out-of-plane change is rotated in an in-plane state, the upper rotation joint (113) and the lower rotation joint (123) are each shifted in an alternating manner in the wing chord direction or the front-back direction, so that the shape of the upper pantograph structure (110) and the lower pantograph structure (120) can change in the out-of-plane direction. For example, referring to FIGS. 15, 16a, and 16b, the rotation joint (upper rotation joint (113)) on the upper surface of the rod moves linearly in the forward or trailing direction, and accordingly, the shape of the rod can change at the forward and trailing ends. Specifically, referring to FIGS. 15 and 16a, if the rotational joint of the upper surface (upper rotational joint (113)) is moved linearly in the forward direction (left direction in FIGS. 15 and 16a), the front edge can be lowered and the trailing edge can be raised compared to the original state (before morphing in FIG. 15 or original state in FIG. 16a). Additionally, referring to FIGS. 15 and 16b, if the joint of the upper surface (upper rotational joint (113)) is moved linearly in the trailing direction (right direction in FIGS. 15 and 16b), the front edge can be raised and the trailing edge can be lowered compared to the original state (before morphing in FIG. 15 or original state in FIG. 16b).

[0079] In other words, the upper rotational joint (113) (joint on the upper surface) and the lower rotational joint (123) (joint on the lower surface), which govern the change in the wing length direction of the pantograph, also move differentially in the chord direction of the wing and can also be involved in the change in the shape of the out-of-plane space.

[0080] Additionally, the upper pantograph structure (110) and the lower pantograph structure (120) may be configured by considering the range of out-of-plane spatial shape change so as to have elasticity capable of accommodating differences even if differences within a preset range occur with respect to the wing chord direction or the front-rear direction. At this time, the preset range may be configured by considering the connection relationship between any one of the plurality of first lower rods (121) and any one of the plurality of first upper rods (111). In other words, as described above, any one of the plurality of lower rods (121, 122) and any one of the plurality of upper rods (111, 112) facing any one of the plurality of lower rods (121, 122) may be configured such that one or more of the front end (upper side in FIG. 4) and rear end (lower side in FIG. 4) in the wing chord direction are connected to each other. Additionally, as described above, when the outer surface support (100) of the wing changes shape in an out-of-plane space, the upper rotational joint (113) (joint on the upper surface) and the lower rotational joint (123) (joint on the lower surface) move differentially in the chord direction of the wing, and accordingly, a plurality of lower rods (121, 122) and a plurality of upper rods (111, 112) opposite thereto can also move differentially while connected to each other. At this time, the plurality of rods (111, 112, 121, 122) are provided as elastic members (e.g., members in the form of flexible rods having bending elasticity) capable of accommodating elasticity within a preset range, so that when the outer surface support (100) of the wing changes shape in an out-of-plane space, the shape change can be elastically accommodated.

[0081] Accordingly, the wing outer surface support (100) allows the wing internal spar structure to move linearly in the wing length direction by the linear actuator (130). Through this, the wing outer surface support (100) can cause the wing shape to change simultaneously with the wing length and chord. At the same time, the upper and lower joints (upper rotation joint (113), lower rotation joint (123)) connected to the linear actuator (130) can be differentially moved in the chord direction to change the out-of-plane space of the wing where the wing shape camber faces. Accordingly, a morphing structure can be provided in which the shape change of the in-plane space and out-of-plane space of the aircraft can occur simultaneously.

[0082] Meanwhile, the present invention may provide a wing (hereinafter referred to as the ‘wing’) applied to an aircraft (200) as a wing comprising a wing outer surface support (100). For example, the present invention may provide a composite morphing wing capable of simultaneously changing into in-plane space and out-of-plane space by using a pantograph structure (upper pantograph structure part (110), lower pantograph structure part (120)) and a linear actuator (130).

[0083] In addition, the present invention may provide an aircraft (200) including the wing. For example, the present invention may provide the wing by applying it to various aircraft (200) that require morphing flight, such as airplanes and gliders. In the present invention, the term 'aircraft' may be understood as a broad concept encompassing all mobile bodies capable of moving through flight.

[0084] The foregoing description of the present invention is for illustrative purposes only, and those skilled in the art will understand that other specific forms can be easily modified without altering the technical concept or essential features of the present invention. Therefore, the embodiments described above should be understood as illustrative in all respects and not restrictive. For example, each component described as a single unit may be implemented in a distributed manner, and components described as distributed may likewise be implemented in a combined form.

[0085] The scope of the present invention is defined by the claims set forth below rather than by the detailed description above, and all modifications or variations derived from the meaning and scope of the claims and the concept of equivalents thereof should be interpreted as being included within the scope of the present invention. Explanation of the symbols

[0086] 100: Deformable wing surface support using a pantograph structure 110: Upper pantograph structure 111: 1st upper rod 112: Second upper load 113: Upper rotary joint 120: Lower pantograph structure 121: 1st lower load 122: Second lower load 123: Lower rotary joint 130: Linear actuator 131: No Slider 131a: Followers 132: Linear drive unit 132a: Barrel cam 132ab: Barrel Cam Home Line 132b: Gear section 132c: Gear drive unit 133: Fixed end for slider guide 133a: Fuselage fixed end 134: Drive unit for out-of-plane change 135: Upper interlocking member 136: Lower interlocking member 137: Absence of guide 138: First bearing 139: Second bearing 200: Aircraft

Claims

Claim 1 A deformable wing surface support using a pantograph structure, comprising: an upper pantograph structure portion provided to support the upper outer surface of the wing surface of an aircraft and arranged to be linearly deformable along the wing length direction; and a lower pantograph structure portion provided to support the lower outer surface of the wing surface and arranged to be linearly deformable along the wing length direction, wherein the upper pantograph structure portion comprises a plurality of first upper rods and a plurality of second upper rods arranged to intersect each other to form an upper pantograph structure that is linearly deformable in the wing length direction; and an upper rotational joint provided to have a degree of rotational freedom at one or more of a plurality of upper intersection points between the plurality of first upper rods and the plurality of second upper rods, and wherein the lower pantograph structure portion comprises a plurality of first lower rods and a plurality of second lower rods arranged to intersect each other to form a lower pantograph structure that is linearly deformable in the wing length direction; A deformable wing surface support using a pantograph structure, comprising: a lower rotational joint provided to have a degree of rotational freedom with respect to one or more of a plurality of lower intersection points between a plurality of first lower rods and a plurality of second lower rods; wherein the wing surface support further comprises a linear actuator that linearly adjusts the positions of the upper rotational joint and the lower rotational joint along the wing length direction; wherein the upper rotational joint and the lower rotational joint are positioned opposite each other in an in-plane state in which no out-of-plane shape change occurs; and wherein the linear actuator comprises a slider member that is provided to be linearly movable in the wing length direction and is connected to the upper rotational joint and the lower rotational joint in a linearly movable manner; and a linear driving unit that drives the slider member along the wing length direction. Claim 2 delete Claim 3 delete Claim 4 delete Claim 5 A deformable wing surface support using a pantograph structure, wherein the linear drive unit comprises: a barrel cam extending along the wing length direction and having a barrel cam groove line formed on its outer circumference; a gear unit transmitting a rotational driving force to rotate the barrel cam to the barrel cam; and a gear drive unit driving the gear unit, wherein the slider member is coupled to the barrel cam so as to move linearly along the wing length direction when a follower formed inside it moves along the barrel cam groove line. Claim 6 A deformable wing surface support using a pantograph structure, wherein the linear actuator further comprises a fixed end for a slider guide that surrounds at least a portion of the outer surface of the slider member to guide the slider member to move linearly in the wing length direction by preventing twisting of the slider member, and the fixed end for the slider guide is fixed to the fuselage of the aircraft. Claim 7 A deformable wing surface support using a pantograph structure, wherein the linear actuator comprises: an out-of-plane change drive unit mounted on the slider member to enable rotational drive with the wing length direction as an axis on the slider member; an upper linkage member connecting the rotation axis of the out-of-plane change drive unit and the upper rotational joint; and a lower linkage member connecting the rotation axis of the out-of-plane change drive unit and the lower rotational joint. Claim 8 A deformable wing surface support using a pantograph structure, wherein, in claim 7, when the out-of-plane change driving unit is rotated in the in-plane state, the upper rotation joint and the lower rotation joint are each shifted in an alternating manner in the wing chord direction or the front-rear direction, thereby causing an out-of-plane shape change of the upper pantograph structure and the lower pantograph structure. Claim 9 In claim 7, in an in-plane state where no shape change in the out-of-plane direction occurs, any one of the plurality of first lower rods and any one of the plurality of first upper rods facing any one of the plurality of first lower rods are provided to be connected to one or more of the front and rear ends in the wing chord direction, and the upper pantograph structure and the lower pantograph structure are set considering the out-of-plane spatial shape change range so as to have elasticity capable of accommodating the difference even if a difference within a preset range occurs with respect to the wing chord direction or the front-rear direction, and the preset range is set considering the connection relationship between any one of the plurality of first lower rods and any one of the plurality of first upper rods, a deformable wing surface support using a pantograph structure. Claim 10 A wing comprising a deformable wing surface support according to paragraph 1, and a wing applied to an aircraft. Claim 11 A flying vehicle including wings according to Paragraph 10.

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