Deformable wing outer-surface support using pantograph structure, deformable wing comprising same, and aerial vehicle comprising deformable wing

Abstract

A deformable wing outer-surface support using a pantograph structure, according to one embodiment of the present application, may comprise: an upper pantograph structure part which is provided to support an upper outer-surface of a wing outer-surface of an aerial vehicle, and which is disposed to be linearly deformable in the longitudinal direction of the wing; and a lower pantograph structure part which is provided to support a lower outer-surface of the wing outer-surface, and is disposed to be linearly deformable in the longitudinal direction of the wing.

Description

A deformable wing surface support using a pantograph structure, a deformable wing including the same, and an aircraft including the deformable wing

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

[0002] This research was supported by research funds from the Ministry of Education's Key Research Institute Support Program, "Development of Zero-Carbon Future Aircraft Technology." (Project ID: 2340004172, Project No.: 2022R1A6A1A03056784, Project Implementing Institution: Korea Aerospace University, Current Research Period: March 1, 2024 - February 28, 2025, Total Research Period: June 1, 2022 - May 31, 2031)

[0003] Conventional morphing wing aircraft change shape in only one of two ways: in-plane or out-of-plane. In-plane shape changes include changes in wing length, wing area, wing chord length, and wing sweepback angle, while out-of-plane shape changes include changes in airfoil thickness, airfoil camber, airfoil twist, and wing dihedral.

[0004] Existing aircraft could not have a structure that could change the outer surface of the aircraft itself because they used materials that did not change easily due to external forces due to limitations in structural stability.

[0005] In addition, existing aircraft have operated with the structure responsible for the change in wing shape (shape change outside the plane) and the structure responsible for the change in the shape of the wing surface (shape change within the plane (change in wing length and area)) separated.

[0006] The technology underlying this application is disclosed in Korean Patent No. 10-1902698.

[0007] The present invention is intended to solve the problems of the prior art as described above, and aims to provide a wing surface support capable of changing the in-plane shape (wing length and area) of a wing by creating an aircraft body and an outer surface support of the aircraft body wing that are linearly deformable along the wing length direction, a deformable wing including the same, and an aircraft body including the deformable wing.

[0008] The present invention is intended to solve the problems of the prior art described above, and aims to provide a wing outer surface support capable of simultaneously performing changes in the in-plane shape (wing length and area) and out-of-plane shape (wing shape) of a wing with a single structure, a deformable wing including the same, and an aircraft including the deformable wing.

[0009] However, the technical tasks to be achieved by the embodiments of the present invention are not limited to the technical tasks described above, and other technical tasks may exist.

[0010] As a technical means for achieving the above-described technical task, a deformable wing surface support using a pantograph structure according to one embodiment of the present invention may include an upper pantograph structure provided to support an upper surface of an outer surface of a wing of an aircraft, and arranged to be linearly deformable along the wing length direction; and a lower pantograph structure provided to support a lower surface of the outer surface of the wing, and arranged to be linearly deformable along the wing length direction.

[0011] In addition, the upper pantograph structure may include a plurality of first upper rods and a plurality of second upper rods arranged to intersect with each other to form an upper pantograph structure that is linearly deformed in the direction of the wing length; and an upper rotary joint provided to have a rotational degree of freedom with respect to at least one 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 with each other to form a lower pantograph structure that is linearly deformed in the direction of the wing length; and a lower rotary joint provided to have a rotational degree of freedom with respect to at least one of a plurality of lower intersection points between the plurality of first lower rods and the plurality of second lower rods.

[0012] Additionally, the wing outer surface support may further include a linear actuator that linearly adjusts the positions of the upper rotation joint and the lower rotation joint along the wing length direction.

[0013] In addition, the upper rotary joint and the lower rotary joint are positioned to face each other up and down in an in-plane state in which no out-of-plane shape change occurs, and the linear actuator may include a slider member that is provided to be linearly movable in the direction of the wing length and is linearly movably connected to the upper rotary joint and the lower rotary joint; and a linear actuator that drives the slider member along the direction of the wing length.

[0014] In addition, the linear driving unit includes a barrel cam extending along the wing length direction and having a barrel cam groove line formed on the outer periphery; a gear unit transmitting a rotational driving force for rotating the barrel cam to the barrel cam; and a gear driving unit driving the gear unit, and the slider member can be coupled with the barrel cam so that when a follower formed therein moves along the barrel cam groove line, the slider member moves linearly along the wing length direction.

[0015] In addition, the linear actuator further includes a slider guide fixing member that surrounds at least a portion of the outer circumference of the slider member to prevent twisting of the slider member and guide the slider member to move linearly in the wing length direction, and the slider guide fixing member can be fixed to the fuselage of the aircraft.

[0016] In addition, the linear actuator may include an out-of-plane change driving unit mounted on the slider member to enable rotational driving with the wing length direction as an axis; an upper linkage member connecting the rotational axis of the out-of-plane change driving unit and the upper rotary joint; and a lower linkage member connecting the rotational axis of the out-of-plane change driving unit and the lower rotary joint.

[0017] In addition, when the out-of-plane change driving unit is rotated in the in-plane state, the upper rotary joint and the lower rotary joint are shifted alternately in the wing chord direction or the front-back direction, so that the out-of-plane shape of the upper pantograph structure and the lower pantograph structure can be changed.

[0018] In addition, in an in-plane state where no out-of-plane shape change 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 such that at least one of the front end and the rear end in the wing chord direction is connected to each other, and the upper pantograph structure and the lower pantograph structure are set in consideration of an out-of-plane space shape change range so as to have elasticity that can accommodate a difference within a preset range even if a difference occurs in the wing chord direction or the front-back direction, and the preset range can be set in consideration of a connection relationship between any one of the plurality of first lower rods and any one of the plurality of first upper rods.

[0019] A wing according to one embodiment of the present invention may include the deformable wing outer surface support.

[0020] Additionally, an aircraft according to one embodiment of the present invention may include the wing.

[0021] The above-described problem-solving methods are merely exemplary and should not be construed as limiting the present invention. In addition to the exemplary embodiments described above, additional embodiments may be included in the drawings and detailed description of the invention.

[0022] According to the above-described means for solving the problem of the present invention, a wing outer surface support capable of changing shape in a space within a plane, a deformable wing including the same, and an aircraft including the deformable wing can be provided by including a pantograph structure, a rotary joint having a rotational degree of freedom, and a linear actuator for linearly adjusting along the wing length direction.

[0023] According to the above-described means for solving the problem of the present invention, by providing an out-of-plane change driving unit, an upper rotary joint and a lower rotary joint can be shifted alternately in the wing chord direction or the front-back direction, respectively, so that a wing outer surface support body capable of changing the shape of the wing in the out-of-plane direction, a deformable wing including the same, and an aircraft including the deformable wing can be provided.

[0024] However, the effects that can be obtained from this center are not limited to the effects described above, and other effects may exist.

[0025] Figure 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.

[0026] Figure 2 is a drawing for explaining a rotary joint fastening type according to one embodiment of the present invention.

[0027] 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 outer surface support (pantograph-type wing frame) using a pantograph structure according to one embodiment of the present invention.

[0028] FIG. 4 is an isometric projection of a deformable wing outer surface support (wing skeleton) using a pantograph structure according to one embodiment of the present invention.

[0029] FIG. 5 is a drawing for explaining an internal driving method of a pantograph structure according to one embodiment of the present invention and an appearance of a wing outer surface support (pantograph structure) applied to an aircraft.

[0030] Fig. 6 is a drawing for explaining a linear actuator according to one embodiment of the present invention.

[0031] Fig. 7 is a drawing for explaining a linear driving unit according to one embodiment of the present invention.

[0032] Fig. 8 is a drawing for explaining a slider member according to one embodiment of the present invention.

[0033] FIG. 9 is a drawing for explaining 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.

[0034] FIG. 10 and FIG. 11 are drawings for explaining a state in which a fixed end for a slider guide according to one embodiment of the present invention is connected to a body contact portion.

[0035] Fig. 12 is a drawing for explaining an out-of-plane change driving unit according to one embodiment of the present invention.

[0036] Fig. 13 is a drawing for explaining an implementation example of a guide member according to one embodiment of the present invention.

[0037] Fig. 14 is a drawing for explaining another implementation example of a guide member according to one embodiment of the present invention.

[0038] Figure 15 is a side view of the shape change of the cross-section of a rod (rod) when the shape changes in the out-of-plane direction according to one embodiment of the present invention.

[0039] Figure 16a is an isometric projection of the overall shape change when the upper rotary joint (wing joint) according to one embodiment of the present invention is linearly moved in the forward direction.

[0040] Figure 16b is an isometric projection of the overall shape change when the upper rotary joint (wing joint) according to one embodiment of the present invention is linearly moved in the rearward direction.

[0041] Below, with reference to the attached drawings, embodiments of the present invention are described in detail to facilitate easy implementation by those skilled in the art. However, the present invention can be implemented in various different forms and is not limited to the embodiments described herein. In the drawings, irrelevant parts have been omitted for clarity, and similar reference numerals have been used throughout the specification to indicate similar elements.

[0042] Throughout this specification, when a part is said to be "connected" to another part, this includes not only the case where it is "directly connected," but also the case where it is "electrically connected" or "indirectly connected" with another element in between.

[0043] Throughout this specification, when it is said that a member is located “on,” “above,” “upper,” “lower,” “lower” or “lower” another member, this includes not only cases where the member is in contact with the other member, but also cases where another member exists between the two members.

[0044] Throughout this specification, whenever a part is said to "include" a component, this does not mean that it excludes other components, but rather that it may include other components, unless otherwise specifically stated.

[0045] 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) using an elastic pantograph-type surface structure, and an upper component (wing or aircraft) including the same.

[0046] 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.

[0047] Figure 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.

[0048] Referring to FIG. 1, the wing outer surface support (100) is provided to support the upper outer surface of the wing outer surface of an 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 horizontal direction in FIG. 1, and may mean a direction perpendicular to the fuselage of the aircraft (200). In addition, the aircraft (200) herein may mean an airplane, a glider, and various aircraft (200) that require morphing flight.

[0049] In addition, 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 so as 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 an inclined state (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 an inclined state (11 o'clock to 5 o'clock direction in FIG. 1) so as 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 pantograph (scissors structure) surface structure that is intertwined diagonally.

[0050] In addition, the plurality of first upper rods (111) and the plurality of second upper rods (112) may be provided with elastic members (flexible members having a predetermined bending elasticity). Accordingly, since the plurality of first upper rods (111) and the plurality of second upper rods (112) are provided with elastic members, the upper pantograph structure (110) (supporting member) is elastic but has a stable state in the target shape, so that the shape can be maintained even against external resistance.

[0051] 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 a principle of in-plane spatial shape change (movement in the wing length direction) of a deformable wing outer surface support (pantograph-type wing frame) using a pantograph structure according to one embodiment of the present invention.

[0052] In addition, referring to FIGS. 1 and 2, the upper pantograph structure (110) may include an upper rotary joint (113) provided to have a rotational degree of freedom with respect to at least one 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 rotary joint (113) is provided so that the upper rods (111, 112) that intersect with each other at the intersection points of the plurality of upper rods (111, 112) are coupled, and the plurality of upper rods (111, 112) may be woven with the upper rotary joint (113) at their upper and lower surfaces at the intersection points. In other words, each rod (the plurality of upper rods (111, 112)) of the upper surface of the wing (the upper pantograph structure (110)) may be coupled with a rotary joint (the upper rotary joint (113)) at the intersection points so as to be rotatable at the upper and lower surfaces.

[0053] Also, referring to FIGS. 2 and 3, the upper rotary joint (113) connects two upper rods (111, 112) (rods) that intersect each other, and the upper rods (111, 112) (rods) can rotate in different directions to change the overall shape. Specifically, the upper rotary joint (113) connects 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 connected first upper rod (111) and second upper rod (112) can rotate in opposite directions to change the shape in the in-plane direction of the wing. Here, the shape change in the in-plane direction can include a change in the wing length, a change in the wing area, a change in the wing chord length, and a change in the wing sweep back angle.

[0054] 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) rotates 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) rotates 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.

[0055] In other words, the upper pantograph structure (110) (wing frame) may include a plurality of elastic upper rods (111, 112) (Rod, bars), and the plurality of upper rods (111, 112) (Rods) may be connected by an upper rotary joint (113) (rotary joint) at an intersection point. The two upper rods (111, 112) (Rods) connected by one upper rotary joint (113) (joint) may rotate in opposite directions to change the overall shape. Therefore, the wing outer surface support (100) may provide an upper pantograph structure (110) (wing frame using a pantograph) that operates on a principle similar to a scissor mechanism.

[0056] Referring to FIG. 1, the wing outer surface support (100) is provided to support the lower outer surface of the wing outer surface, and may include a lower pantograph structure (120) arranged to be linearly deformable along the wing length direction.

[0057] In addition, 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 so as 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 an inclined state (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 an inclined state (11 o'clock to 5 o'clock direction in FIG. 1) so as 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 pantograph (scissors structure) surface structure that is intertwined diagonally.

[0058] In addition, the plurality of first lower rods (121) and the plurality of second lower rods (122) may be provided with elastic members. Accordingly, since the plurality of first lower rods (121) and the plurality of second lower rods (122) are provided with elastic members, the lower pantograph structure (120) (supporting member) is elastic but has a stable state in the target shape, so that the shape can be maintained even against external drag.

[0059] In other words, the wing surface support (100) can provide a wing of a pantograph (scissor structure) surface structure in which the surface of the aircraft (200) or the wing is woven diagonally through an upper pantograph structure (110) and a lower pantograph structure (120) using elastic rods (materials).

[0060] In addition, referring to FIGS. 1 and 2, the lower pantograph structure (120) may include a lower rotary joint (123) provided to have a rotational degree of freedom for at least one 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 rotary joint (123) is provided so that the lower rods (121, 122) that intersect with each other at the intersection points of the plurality of lower rods (121, 122) are coupled, and the plurality of lower rods (121, 122) may be woven into the lower rotary joint (123) at their upper and lower surfaces at the intersection points. In other words, each rod (the plurality of lower rods (121, 122)) of the lower surface of the wing (the lower pantograph structure (120)) may be coupled to a rotary joint (the lower rotary joint (123)) at the intersection points so as to be rotatable at the upper and lower surfaces.

[0061] In addition, referring to FIGS. 2 and 3, the lower rotary joint (123) connects two lower rods (121, 122) (rods) that intersect each other, and the lower rods (121, 122) (rods) can rotate in different directions to change the overall shape. Specifically, the lower rotary joint (123) connects 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 connected first lower rod (121) and second lower rod (122) can change the shape in the in-plane direction of the wing while rotating in opposite directions.

[0062] For example, referring to FIG. 3, the first lower rod (121) (rod) arranged from the upper right to the lower left (1 o'clock to 7 o'clock) may have a wing length (length in the horizontal direction in FIG. 3) that decreases and a wing chord length (length in the vertical direction in FIG. 3) that increases when it rotates clockwise. As another example, the first lower rod (121) (rod) arranged from the upper right to the lower outward (1 o'clock to 7 o'clock) may have a wing length (length in the horizontal direction in FIG. 3) that increases and a wing chord length (length in the vertical direction in FIG. 3) that decreases when it rotates counterclockwise.

[0063] In other words, the lower pantograph structure (120) (wing frame) may include a plurality of elastic lower rods (121, 122) (Rod, bars), and the plurality of lower rods (121, 122) (Rods) may be connected by a lower rotary joint (123) (rotary joint) at an intersection point. The two lower rods (121, 122) (Rods) connected by one lower rotary joint (123) (joint) may rotate in opposite directions to change the overall shape. Therefore, the wing outer surface support (100) may provide a lower pantograph structure (120) (wing frame using a pantograph) that operates on a principle similar to a scissor mechanism.

[0064] FIG. 4 is an isometric projection of a deformable wing outer surface support (wing skeleton) using a pantograph structure according to one embodiment of the present invention.

[0065] Referring to FIG. 4, a plurality of first upper loads (111) and a plurality of first lower loads (121) may be arranged to face each other, and a plurality of second upper loads (112) and a plurality of second lower loads (122) may be arranged to face each other.

[0066] In addition, referring to FIGS. 2 and 4, the upper rotary joint (113) and the lower rotary joint (123) can be positioned to face each other vertically in an in-plane state in which 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 wing dihedral. At this time, the upper rotary joint (113) and the lower rotary joint (123) opposite thereto can be connected by an elastic member so as to maintain a state in which they face each other even in the in-plane movement direction state of the wing.

[0067] In addition, in an in-plane state where no out-of-plane shape change occurs, 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 at least one of the front end and the rear end in the wing chord direction is 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 to each other in a curved manner, and the rear ends (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 to each other so as to overlap each other.

[0068] In addition, 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) may be connected to each other in a curved manner, 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) may be connected to each other in a way that overlaps each other.

[0069] Accordingly, the skeleton (upper pantograph structure (110) and lower pantograph structure (120)) constituting the surface of the wing exhibits the characteristics of a pantograph (scissors structure) and may have an airfoil shape when viewed from the side. The connection of the plurality of upper rods (111, 112) and the lower rods (121, 122) facing the upper rods (111, 112) is obvious to those skilled in the art, so a detailed description thereof will be omitted. In addition, it is desirable to broadly understand the airfoil to mean 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.

[0070] FIG. 5 is a drawing for explaining an internal driving method of a pantograph structure according to one embodiment of the present invention and an 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.

[0071] Referring to FIGS. 5 and 6, the wing surface support (100) may include a linear actuator (130) that linearly adjusts the positions 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) may move two rotational joints (upper rotational joint (113) and lower rotational joint (123)) that are symmetrically positioned (opposed to each other) from the center in the wing length direction by using the linear actuator (130), and through this, the wing surface support (100) (pantograph surface structure) may change the angle between each rib and change the shape in the in-plane space including the wing span, area, and chord length of the aircraft (200).

[0072] 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 a connection relationship between a barrel cam, a slider member, and a fixed end (133) for a slider guide according to one embodiment of the present invention.

[0073] Referring to FIGS. 6 and 7, the linear actuator (130) may include a slider member (131) that is linearly movable in the wing length direction and is linearly connected to the upper rotary joint (113) and the lower rotary joint (123) and a linear actuator (132) that drives the slider member (131) along the wing length direction. For example, the elastic member connecting the upper rotary joint (113) and the lower rotary joint (123) that are opposed to each other as described above is connected to the slider member (131), and when the slider member (131) is linearly moved by the linear actuator (132), the upper rotary joint (113) and the lower rotary joint (123) are linearly moved together, so that the plurality of upper rods (111, 112) and the plurality of lower rods (121, 122) can move. Therefore, the wing outer surface support (100) as viewed through the linear actuator (130) can be changed in the in-plane direction of the wing.

[0074] Referring to FIGS. 6 and 7, the linear driving unit (132) may include a barrel cam (132a) extending along the wing length direction and having a barrel cam groove line (132ab) formed on the outer periphery, a gear unit (132b) that transmits a rotational driving force for rotating the barrel cam (132a) to the barrel cam (132a), and a gear driving unit (132c) that drives the gear unit (132b).

[0075] For example, referring to FIGS. 6 and 7, the gear unit (132b) and the gear drive unit (132c) may be positioned at the center of the fuselage of the aircraft (200), and two barrel cams (132a) may be provided symmetrically around the gear unit (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. In addition, the gear unit (132b) may include a first gear connected to the gear drive unit (132c) and a second gear connected to the first gear and transmitting a rotational driving force for rotating the barrel cam (132a) to the barrel cam (132a). In addition, the barrel cam (132a) may be attached to the second gear and rotate as the gear unit (132b) rotates. At this time, various rotary motors capable of transmitting a rotational driving force to the barrel cam (132a) may be applied to the gear drive unit (132c).

[0076] Referring to FIGS. 6 to 9, the slider member (131) can be coupled with the barrel cam (132a) so that the follower (131a) formed therein moves linearly along the wing length direction while moving along the barrel cam home line (132ab).

[0077] Specifically, referring to FIGS. 6, 8, and 9, the slider member (131) may have a hole formed through which the barrel cam (132a) can pass, and a follower (131a) may be provided inside the slider member (131). In addition, 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) may engage with the barrel cam groove line (132ab) and move, and accordingly, the slider member (131) may be linearly moved along the wing length direction on the outer circumference of the barrel cam (132a).

[0078] In other words, referring to FIGS. 5 to 9, the gear drive unit (132c) (motor) in the middle of the linear actuator (130) can rotate the barrel cam (132a) (profile rod) by engaging with the barrel cam (132a) (rod on which the profile line (barrel cam home line (132ab)) is drawn). At this time, the follower (131a) of the slider member (131) (slider rod) can move in a linear direction (blade length direction) along the barrel cam home line (132ab) (profile line), and accordingly, the slider member (131) can move linearly along the blade length direction on the outer periphery of the barrel cam (132a).

[0079] As another example, a groove line of the slider member (131), which is a groove-shaped line, may be provided inside the slider member (131), 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 move linearly along the wing length direction on the outer periphery of the barrel cam (132a) through the engagement connection between the groove line of the slider member (131) and the follower of the barrel cam (132a).

[0080] FIG. 10 and FIG. 11 are drawings for explaining a state in which a fixed end for a slider guide according to one embodiment of the present invention is connected to the fuselage of an aircraft.

[0081] Referring to FIGS. 6 and 9 to 11, the linear actuator (130) may include a slider guide fixing member (133) that surrounds at least a portion of the outer circumferential surface of the slider member (131) to prevent twisting of the slider member (131) and guide the slider member (131) to move linearly in the wing length direction. 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 twisting due to the slider guide fixing member (133).

[0082] In addition, referring to FIGS. 6 and 9, a hole through which a slider member (131) can pass is formed in a fixed end (133) for a slider guide, and a barrel cam (132a) and a slider member (131) can be positioned inside the fixed end (133) for a slider guide. At this time, the size of the hole of the fixed end (133) for a slider guide can be set so that when the follower (131a) inside the slider member (131) moves along the barrel cam groove line (132ab) as the barrel cam (132a) rotates, the slider member (131) can be prevented from twisting and coming off, and the slider member (131) can be linearly moved in the direction of the wing length.

[0083] In addition, 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).

[0084] In other words, the fixed member (133) for the slider guide is attached to and fixed to the fuselage of the aircraft (200) and may be provided to perform a role of fixing the slider member (131) inside so that it does not twist and moves only linearly.

[0085] 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 about the wing length direction as an axis. Specifically, the out-of-plane change drive unit (134) may be mounted on both ends of the slider member (131). However, the position of the out-of-plane change drive unit (134) is not limited thereto, and may be positioned at various positions that enable out-of-plane change of the wing. In addition, 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 thereto, and various drive units that enable out-of-plane change of the airfoil may be applied.

[0086] 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 drive unit (134) (servo motor) located at the end of a slider member (131) (slide rod) for moving the position of a rotary joint (113).

[0087] Referring to FIG. 6, FIG. 13, and FIG. 14, the linear actuator (130) may include an upper linkage member (135) connecting the rotational axis of the out-of-plane change driving unit (134) and the upper rotational joint (113), and a lower linkage member (136) connecting the rotational axis of the out-of-plane change driving unit (134) and the lower rotational joint (123).

[0088] In addition, referring to FIGS. 13 and 14, the linear actuator (130) may include a guide member (137). The guide member (137) may be provided to be connected to the upper linkage member (135) and the lower linkage member (136), and may be provided 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.

[0089] Referring to FIG. 13 as an example of the guide member (137), the guide member (137) may be provided in the form of a plurality of link members that are multiply linked to 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 hinge-coupled to a rotating plate (in the form of a flat diamond-shaped plate in FIG. 13) that is linked to the rotation of the out-of-plane change drive unit (134). The first guide member may be configured to be hinge-coupled to the rotation center of the rotating plate and have both ends linked in a hinge-coupled 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 to have one end hinge-coupled to one side of the rotating plate and the other end linked in a hinge-coupled manner to the middle of the upper linkage member (135). The third guide member may have a configuration in which one end is hinge-connected to the other side of the turntable and the other end is hinge-connected to the middle of the lower linkage member (136) in a link-connected manner. Through this multi-link connection structure of the plurality of guide members (137), the movement paths of the upper linkage member (135) and the lower linkage member (136) can be guided as the out-of-plane change driving unit (134) rotates.

[0090] In addition, referring to FIG. 14 as another implementation example of the guide member (137), the linear actuator (130) may include a first bearing (138) that moves the upper linkage member (135) or the lower linkage member (136) while sliding (moving) along the guide member (137), and a second bearing (139) that connects the rotary joint (113, 123) and the corresponding linkage member (135, 136).

[0091] 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) to pull or push the upper linkage member (137) (steel wire). Accordingly, the upper linkage member (137) (steel wire) can adjust the position of the upper rotary joint (113) (rod joint), ultimately changing the position of the upper rotary joint (113). However, in the case of FIG. 14, only the connection relationship between the upper linkage member (135) and the upper rotary joint (113) is illustrated, and it goes without saying that the connection relationship between the lower linkage member (136) and the lower rotary joint (123) can also be connected (linked) with the same or similar configuration and method as needed.

[0092] In addition, the upper linkage member (135) and the lower linkage member (136) may be provided with elastic members. For example, the elastic members may be rotational elastic members. However, the elastic members are not limited to rotational elastic members, and the upper linkage member (135) and the lower linkage member (136) may be provided with various elastic members having elastic restoring force with respect to rotational elasticity.

[0093] FIG. 15 is a side view of a shape change in a cross-section of a rod (rod) 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 the upper rotation joint (wing-shaped joint) according to one embodiment of the present invention is linearly moved in a forward direction, and FIG. 16b is an isometric projection of the overall shape change when the upper rotation joint (wing-shaped joint) according to one embodiment of the present invention is linearly moved in a backward direction.

[0094] Referring to FIGS. 14 to 16B, when the drive unit (134) for out-of-plane change is rotated in the in-plane state, the upper rotary joint (113) and the lower rotary joint (123) are shifted alternately in the wing chord direction or the front-back direction, so that the out-of-plane shape of the upper pantograph structure (110) and the lower pantograph structure (120) can be changed. For example, referring to FIGS. 15, 16A, and 16B, the rotary joint (upper rotary joint (113)) on the upper surface of the rod (rod) moves linearly in the forward or backward direction, and accordingly, the shape of the rod (rod) can be changed in the forward and backward directions. Specifically, referring to FIGS. 15 and 16A, when the rotary joint of the upper surface (upper rotary joint (113)) is linearly moved in the forward direction (leftward 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 the original state in FIG. 16A). In addition, referring to FIGS. 15 and 16B, when the joint of the upper surface (upper rotary joint (113)) is linearly moved in the backward direction (rightward 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 the original state in FIG. 16B).

[0095] In other words, the upper rotation joint (113) (joint on the upper surface) and the lower rotation joint (123) (joint on the lower surface) that govern the change in the wing length direction of the pantograph can also move differentially in the chord direction of the wing and can also participate in the change in the shape of the out-of-plane space.

[0096] In addition, the upper pantograph structure (110) and the lower pantograph structure (120) may be set in consideration of the out-of-plane space shape change range so as to have elasticity that can accommodate differences even if differences occur within a preset range in the wing chord direction or the front-back direction. At this time, the preset range may be set in consideration of 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 provided such that at least one of the front end (upper side in FIG. 4) and the rear end (lower side in FIG. 4) in the wing chord direction is connected to each other. In addition, as described above, when the outer surface support body (100) of the wing changes its shape in the out-of-plane space, the upper rotation joint (113) (joint on the upper surface) and the lower rotation joint (123) (joint on the lower surface) move differentially in the direction of the wing's chord, and accordingly, the plurality of lower rods (121, 122) and the plurality of upper rods (111, 112) opposite thereto can also move differentially while being connected to each other. At this time, the plurality of rods (111, 112, 121, 122) are provided with elastic members (e.g., flexible rod-shaped members having bending elasticity) that can accommodate elasticity within a preset range, so that the shape change can be elastically accommodated when the outer surface support body (100) of the wing changes its shape in the out-of-plane space.

[0097] Accordingly, the wing outer surface support (100) can linearly move the wing inner spar structure in the wing length direction by the linear actuator (130). Through this, the wing outer surface support (100) can change the shape of the wing simultaneously in 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 that the camber of the wing shape faces. Accordingly, a morphing structure can be provided in which shape changes of the in-plane space and the out-of-plane space of the aircraft can be simultaneously performed.

[0098] Meanwhile, the present invention can provide a wing (hereinafter referred to as "the wing") that includes the wing outer surface support (100) and is applied to an aircraft (200). For example, the present invention can provide a composite morphing wing that can simultaneously change into an in-plane space and an out-of-plane space by using a pantograph structure (upper pantograph structure (110), lower pantograph structure (120)) and a linear actuator (130).

[0099] In addition, the present invention can provide an aircraft (200) including the wing. For example, the present invention can provide the wing by applying it to various aircraft (200) that require morphing flight, such as an airplane or glider. In the present invention, the term "aircraft" can be understood as a broad concept encompassing all vehicles capable of moving through flight.

[0100] The above description of the present invention is for illustrative purposes only, and those skilled in the art will readily appreciate that the present invention can be readily modified into other specific forms without altering the technical spirit or essential characteristics 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 entity may be implemented in a distributed manner, and similarly, components described as distributed may be implemented in a combined manner.

[0101] The scope of the present invention is indicated by the claims described below rather than the detailed description above, and all changes or modifications derived from the meaning and scope of the claims and their equivalent concepts should be interpreted as being included in the scope of the present invention.

Claims

1. A deformable wing outer surface support using a pantograph structure, An upper pantograph structure 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 deformable wing surface support using a pantograph structure, which includes a lower pantograph structure provided to support the lower surface of the wing surface and arranged to be linearly deformable along the wing length direction.

2. In paragraph 1, The above upper pantograph structure is, A plurality of first upper rods and a plurality of second upper rods arranged in a cross-sectional manner to form an upper pantograph structure that is linearly deformed in the wing length direction; and An upper rotary joint is provided to have a rotational degree of freedom with respect to at least one of a plurality of upper intersections between the plurality of first upper loads and the plurality of second upper loads, The above lower pantograph structure is, A plurality of first lower rods and a plurality of second lower rods arranged in a cross-sectional manner to form a lower pantograph structure that is linearly deformed in the wing length direction; and A deformable wing outer surface support using a pantograph structure, comprising a lower rotary joint having a rotational degree of freedom with respect to at least one of a plurality of lower intersections between the plurality of first lower loads and the plurality of second lower loads.

3. In paragraph 2, A deformable wing surface support using a pantograph structure, wherein the wing surface support further includes a linear actuator that linearly adjusts the positions of the upper rotation joint and the lower rotation joint along the wing length direction.

4. In paragraph 3, The upper rotation joint and the lower rotation joint are positioned facing each other vertically in an in-plane state where no change in shape in the out-of-plane direction occurs. The above linear actuator, A slider member that is provided to be linearly movable in the direction of the wing length and is linearly movably connected to the upper rotary joint and the lower rotary joint; and A deformable wing outer surface support using a pantograph structure, comprising a linear driving unit that drives the slider member along the wing length direction.

5. In paragraph 4, The above linear driving unit, A barrel cam extending along the wing length direction and having a barrel cam groove line formed on the outer periphery; A gear unit that transmits a rotational driving force for rotating the barrel cam to the barrel cam; and Includes a gear drive unit that drives the above gear part, A deformable wing outer surface support using a pantograph structure, wherein the slider member is coupled with the barrel cam so that the follower formed therein moves linearly along the wing length direction when the follower moves along the barrel cam home line.

6. In paragraph 4, The above linear actuator, Further comprising a slider guide fixing member that surrounds at least a portion of the outer surface of the slider member to prevent twisting of the slider member and guide the slider member to move linearly in the direction of the wing length. A changeable wing outer surface support using a pantograph structure, wherein the fixed end for the above slider guide is fixed to the fuselage of the above aircraft.

7. In paragraph 4, The above linear actuator, An out-of-plane change driving unit mounted on the slider member to enable rotational driving about the wing length direction as an axis on the slider member; An upper linkage member connecting the rotational axis of the above-mentioned out-of-plane change driving unit and the upper rotational joint; and A deformable wing outer surface support using a pantograph structure, comprising a lower linkage member connecting the rotational axis of the above-mentioned out-of-plane change driving unit and the lower rotational joint.

8. In paragraph 7, A deformable wing outer surface support using a pantograph structure, wherein when the out-of-plane change driving unit is rotated in the in-plane state, the upper rotary joint and the lower rotary joint are shifted alternately in the wing chord direction or the front-back direction, so that an out-of-plane shape change of the upper pantograph structure and the lower pantograph structure occurs.

9. In paragraph 7, In an in-plane state where no change in the out-of-plane shape occurs, any one of the plurality of first lower rods and any one of the plurality of first upper rods opposing any one of the plurality of first lower rods are provided such that at least one of the front end and the rear end in the wing chord direction is connected to each other, The upper pantograph structure and the lower pantograph structure are set in consideration of the range of changes in the shape of the out-of-plane space so that they have elasticity that can accommodate the difference even if a difference within a preset range occurs in the wing chord direction or the front-rear direction. A deformable wing outer surface support using a pantograph structure, wherein the above preset range is set in consideration of the connection relationship between any one of the plurality of first lower loads and any one of the plurality of first upper loads.

10. A wing including a deformable wing outer surface support according to paragraph 1, Wings applied to aircraft.

11. An aircraft comprising a wing according to Article 10.

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