Hybrid blade-wing structure for aircraft, and aircraft comprising same

Abstract

The present invention provides a hybrid blade-wing structure for an aircraft, and an aircraft comprising same, the wing structure being provided on an aircraft, and comprising: a structure frame part; a biplane-type fixed wing structure part provided on the structure frame part; and a rotor blade structure part rotatably provided in the structure frame part.

Description

Hybrid blade-wing structure for aircraft and aircraft including the same

[0001] The present invention relates to a hybrid blade-wing structure for an aircraft and an aircraft including the same, and more specifically, to a hybrid blade-wing structure for an aircraft and an aircraft including the same that can efficiently generate thrust and lift through a fused wing structure of a biplane structure and a cycloplane structure, and furthermore, can perform vertical and horizontal flight like a tiltrotor, and can save space during takeoff and landing and ensure stable flight during gliding through an expandable and contractible biplane structure.

[0002] Generally, aircraft or flying vehicles are classified into fixed-wing aircraft, which obtain lift to take off while gliding a certain distance, and rotary-wing aircraft, which obtain lift from the rotation of rotors to take off and land vertically from a stationary position.

[0003] Fixed-wing aircraft are structures that generate thrust and lift through the movement of engines or propellers, and they are equipped with vertical and horizontal wings to correct attitude. In contrast, rotary-wing aircraft, such as helicopters, are structures that generate thrust and lift through the rotational movement of rotors, and control the rotation of the fuselage through the rotational movement of auxiliary rotors.

[0004] Meanwhile, as an aircraft having a different wing structure, a flapping-wing aircraft has been developed that generates lift and thrust by repeatedly swinging the left and right wings in an up-and-down direction, as disclosed in Korean Published Patent Application No. 10-2011-10234. The conventional flapping-wing aircraft disclosed in the aforementioned patent application consists of left and right wings configured as pairs of a driving wing and a driven wing, respectively, and a driving unit configured between the driving wing and the driven wing to generate electromagnetic force on the left and right wings according to the direction of the current flowing through a coil, thereby generating lift through flapping by generating attractive and repulsive forces through the electromagnetic force generated by the driving unit.

[0005] However, since these conventional flapping-wing aircraft must be configured with a leading wing and a following wing for each of the left and right wings, the wing configuration becomes complex, and the total load of the aircraft increases, leading to a problem of increased power consumption.

[0006] In addition, conventional flapping-wing aircraft can only generate repetitive swinging motions of the wings and cannot control the angle of attack, resulting in problems with low flight stability and maneuverability.

[0007] Therefore, research and development of a new concept of wing or wing (blade) structure are necessary.

[0008] [Prior Art Literature]

[0009] [Patent Literature]

[0010] Republic of Korea Registered Patent Publication No. 10-1128958 (Published March 27, 2012)

[0011] Republic of Korea Registered Patent Publication No. 10-1318865 (Published Oct. 17, 2013)

[0012] Republic of Korea Registered Patent Publication No. 10-1838796 (Published March 14, 2018)

[0013] Republic of Korea Published Patent Application 10-2008-0058405 (Published June 25, 2008)

[0014] Republic of Korea Published Patent Application 10-2023-0021076 (Published Feb. 13, 2023)

[0015] Accordingly, the present invention, which aims to solve the aforementioned conventional problems, is intended to provide a hybrid blade-wing structure for an aircraft capable of efficiently generating thrust and lift through a fused wing structure of a biplane structure and a cyclo-structure, and an aircraft including the same.

[0016] In addition, the present invention has another objective of providing a hybrid blade-wing structure for an aircraft and an aircraft including the same, which is capable of vertical and horizontal flight like a tiltrotor and can achieve space saving during takeoff and landing and stable flight during gliding through an expandable and contractible biplane structure.

[0017] The problems solved by the present invention are not limited to those mentioned above, and other problems not mentioned will be clearly understood by those skilled in the art from the description below.

[0018] According to one aspect of the present invention for achieving the above-mentioned objectives and other features of the present invention, a hybrid blade-wing structure for an aircraft is provided, comprising: a structural frame portion; a biplane fixed-wing structural portion provided on the structural frame portion; and a rotor blade structural portion rotatably provided on the structural frame portion.

[0019] In one aspect of the present invention, the structural frame portion is composed of a pair of X-shaped frames arranged with a gap, and the fixed wing structural portion may include an upper fixed wing provided at the top of the pair of X-shaped frames and a lower fixed wing provided at the bottom of the pair of X-shaped frames.

[0020] In one aspect of the present invention, the rotor blade structure may be configured to include a plurality of rotor blades rotatably coupled to a pair of X-shaped frames between the upper fixed wing and the lower fixed wing.

[0021] In one aspect of the present invention, the rotor blade structure may include: a pair of circular rotating plates each rotatably coupled to the intersection center of the pair of X-shaped frames; a plurality of rotor blades each having both ends coupled to the pair of circular rotating plates and having an adjustable pitch angle, spaced apart in the circumferential direction of the circular rotating plates; and a rotor blade control link portion each having one end eccentrically connected to the rotor blades and the other end connected at the same center point to change the pitch angle and phase angle of the rotor blades.

[0022] In one aspect of the present invention, the upper fixed wing and the lower fixed wing are formed as cross-sectional streamlined wings, and the structural frame part may be provided with a stopper at an initial position and at a position rotated 90° from the initial position.

[0023] In one aspect of the present invention, at least one of the upper fixed wing and the lower fixed wing may be configured so that the wing can be extended and retracted in the longitudinal direction.

[0024] In one aspect of the present invention, at least one of the upper fixed wing and the lower fixed wing may be configured to expand and contract in a telescoping manner.

[0025] In one aspect of the present invention, at least one of the upper fixed wing and the lower fixed wing may include a main wing; and an extended sub-wing provided to extend longitudinally outward from the interior of the main wing and then retract into the interior of the main wing.

[0026] In one aspect of the present invention, at least one of the upper fixed wing and the lower fixed wing may be provided with a flap at the rear end.

[0027] According to another aspect of the present invention, an aircraft is provided that includes a hybrid blade-wing structure for an aircraft according to the above-described aspect.

[0028] The hybrid blade-wing structure for an aircraft according to the present invention and the aircraft including the same provide the following effects.

[0029] First, the present invention has the effect of being able to possess both the advantages of fixed-wing and rotary-wing aircraft through a fused structure of a biplane wing structure and a cyclo-wing rotor blade structure.

[0030] Second, the present invention has the effect of enabling space saving by reducing the size during takeoff and landing through an expandable and contractible biplane structure, and stable flight by generating sufficient lift by expanding during horizontal flight such as gliding.

[0031] Third, the present invention has the effect of producing low noise, being able to switch between vertical and horizontal flight by rotating the wings like a tiltrotor during flight, and enabling stable hovering in turbulent conditions.

[0032] Fourth, the present invention provides enhanced safety in the event of an accident by having the wing structure of the biplane act as a guide, and while the externally exposed propeller poses a risk, the rotor blade structure of the cyclo is configured to be wrapped by the wing structure of the biplane, thereby having the effect of relatively improving safety.

[0033] Fifth, the present invention has the effect of providing a superior flight distance because the lift for flight is obtained through the wing structure of a biplane and the rotor blade structure of a cycloid generates thrust in the horizontal direction, using only energy for forward movement.

[0034] The effects of the present invention are not limited to those mentioned above, and other unmentioned problems will be clearly understood by those skilled in the art from the description below.

[0035] FIG. 1 is a perspective view showing a hybrid blade-wing structure for an aircraft according to the present invention.

[0036] FIG. 2 is a perspective view showing an extended state of the fixed wing structure part included in the hybrid blade-wing structure for an aircraft according to the present invention.

[0037] FIG. 3 is a perspective view showing the operating state of a hybrid blade-wing structure for an aircraft according to the present invention during vertical take-off and landing.

[0038] FIG. 4 is a side view showing the operating state of a hybrid blade-wing structure for an aircraft according to the present invention during vertical take-off and landing.

[0039] FIG. 5 is a perspective view showing the operating state of a hybrid blade-wing structure for an aircraft according to the present invention during horizontal flight.

[0040] FIG. 6 is a side view showing the operating state of a hybrid blade-wing structure for an aircraft according to the present invention during horizontal flight.

[0041] FIGS. 7 and 8 are drawings showing the control link portion and driving principle of the rotor blade structure portion included in the hybrid blade-wing structure for an aircraft according to the present invention.

[0042] FIG. 9 is a drawing showing the shapes of flaps included in the fixed wing structure part of a hybrid blade-wing structure for an aircraft according to the present invention.

[0043] Further objects, features, and advantages of the present invention can be more clearly understood from the following detailed description and the accompanying drawings.

[0044] Before providing a detailed description of the present invention, it should be understood that the present invention is capable of various modifications and may have various embodiments, and that the examples described below and illustrated in the drawings are not intended to limit the present invention to specific embodiments, but rather include all modifications, equivalents, and substitutions that fall within the spirit and scope of the present invention.

[0045] When it is stated that one component is "connected" or "connected" to another component, it should be understood that while it may be directly connected or connected to that other component, there may also be other components in between. On the other hand, when it is stated that one component is "directly connected" or "directly connected" to another component, it should be understood that there are no other components in between.

[0046] The terms used in this specification are used merely to describe specific embodiments and are not intended to limit the invention. Singular expressions include plural expressions unless the context clearly indicates otherwise. In this specification, terms such as "comprising" or "having" are intended to indicate the existence of the features, numbers, steps, actions, components, parts, or combinations thereof described in the specification, and should be understood as not precluding the existence or addition of one or more other features, numbers, steps, actions, components, parts, or combinations thereof.

[0047] Additionally, terms such as "...part," "...unit," and "...module" as described in the specification refer to a unit that processes at least one function or operation, and this may be implemented in hardware, software, or a combination of hardware and software.

[0048] Furthermore, in the description referring to the attached drawings, identical components are assigned the same reference numeral regardless of drawing symbols, and redundant descriptions thereof are omitted. In describing the present invention, if it is determined that a detailed description of related prior art could unnecessarily obscure the essence of the present invention, such detailed description is omitted.

[0049] Hereinafter, a hybrid blade-wing structure for an aircraft and an aircraft including the same according to a preferred embodiment of the present invention will be described in detail with reference to the accompanying drawings.

[0050] FIG. 1 is a perspective view showing a hybrid blade-wing structure for an aircraft according to the present invention, and FIG. 2 is a perspective view showing an extended state of a fixed wing structure part included in the hybrid blade-wing structure for an aircraft according to the present invention. FIG. 3 is a perspective view showing the operating state of the hybrid blade-wing structure for an aircraft according to the present invention during vertical take-off and landing, FIG. 4 is a side view showing the operating state of the hybrid blade-wing structure for an aircraft according to the present invention during vertical take-off and landing, FIG. 5 is a perspective view showing the operating state of the hybrid blade-wing structure for an aircraft according to the present invention during horizontal flight, and FIG. 6 is a side view showing the operating state of the hybrid blade-wing structure for an aircraft according to the present invention during horizontal flight. FIG. 7 and FIG. 8 are drawings showing the control link part and driving principle of the rotor blade structure part included in the hybrid blade-wing structure for an aircraft according to the present invention, and FIG. 9 is a drawing showing the shapes of flaps included in the fixed wing structure part of the hybrid blade-wing structure for an aircraft according to the present invention.

[0051] As shown in FIGS. 1 to 9, the hybrid blade-wing structure for an aircraft according to the present invention largely comprises a structure frame portion (100), a fixed wing structure portion (200), and a rotor blade structure portion (300), and may additionally include a flap portion (400).

[0052] Specifically, the hybrid blade-wing structure for an aircraft according to the present invention comprises, as shown in FIGS. 1 to 9, a structure frame portion (100) having a fixed wing structure portion (200) and a rotor blade structure portion (300); a biplane-type fixed wing structure portion (200) provided at the top and bottom of the structure frame portion (100); and a cyclo-type rotor blade structure portion (300) rotatably provided on the structure frame portion (100). In addition, the present invention may further include a flap (400) provided on the fixed wing structure portion (200) and configured to increase lift.

[0053] The above-mentioned structural frame part (100) is equipped with a fixed wing structural part (200) and a rotor blade structural part (300), and is rotatably coupled to the aircraft body so as to be rotated from an initial position to a 90° rotational position through a rotational driving device.

[0054] Specifically, the structural frame portion (100) may be composed of a pair of X-shaped frames spaced apart as shown in the drawing.

[0055] Here, as previously described, the structural frame part (100) is rotatably coupled to the aircraft body and can be rotated from an initial position to a rotational position of 90° through a rotational drive device (see FIG. 3 and FIG. 5). A stopper (not shown) protruding to one side of the structural frame part (100) is provided to limit rotation beyond the aforementioned rotational angle when the structural frame part (100) is rotated. The stopper contacts a limit switch (initial position and rotational position) provided on the aircraft body, and based on the contact signal, the rotational operation of the structural frame part (100) can be performed stably.

[0056] Next, the fixed wing structure part (200) is configured in a biplane shape and is a component provided at the top and bottom of the structure frame part (100).

[0057] Specifically, the fixed wing structure (200) includes an upper fixed wing (210) provided at the top of the pair of X-shaped frames (100) and a lower fixed wing (220) provided at the bottom of the pair of X-shaped frames (100).

[0058] The upper fixed wing (210) and the lower fixed wing (220) are formed as cross-sectional streamlined wings, similar to the shape of a conventional fixed wing.

[0059] Here, the fixed wing structure (200) of the present invention can be configured such that the wing can be extended and shortened in the longitudinal direction, that is, the length of the wing can be extended and shortened in a direction perpendicular to the front and rear directions of the aircraft.

[0060] In other words, at least one of the upper fixed wing (210) and the lower fixed wing (220) of the fixed wing structure part (200) of the present invention can be configured to expand and contract in a telescoping manner.

[0061] Specifically, in the present invention, the fixed wing structure (200) includes a main wing (201) and an extended sub-wing (202) that extends outward in the longitudinal direction from the interior of the main wing (200) and is retracted back into the interior of the main wing (200).

[0062] The above-mentioned extension sub-wing (202) is configured to be extended and retracted from the main wing (201) through a known driving device while being received within the main wing (201).

[0063] In this way, the fixed wing structure (200) is configured to be expandable and contractable, thereby enabling space saving by contracting the wings during takeoff, landing, and mooring of the aircraft, and enabling stable flight by expanding them to generate sufficient lift during horizontal flight.

[0064] Next, the rotor blade structure part (300) is a cyclo-type component that is rotatably provided on the structure frame part (100).

[0065] Specifically, the rotor blade structure (300) comprises a pair of circular rotating plates (310) rotatably coupled to the intersection center of the pair of X-shaped frames (100), rotor blades (320) having multiple ends coupled to the pair of circular rotating plates (310) with adjustable pitch angles and spaced apart in the circumferential direction of the circular rotating plates (310), and a rotor blade control link (330) configured such that one end is eccentrically connected to each of the rotor blades (320) and the other end is connected at the same center point to change the pitch angle and phase angle of the rotor blades (320) to control thrust and lift. The rotor blade control link (330) is connected to an operating link connected to a control stick provided on the aircraft body.

[0066] The operation of the rotor blade structure (300) configured as described above is explained.

[0067] As shown in FIGS. 7 and 8, the rotor blade (320) rotates around a horizontal axis, and each rotor blade performs a pitch motion with a constant trajectory along a phase angle, thereby obtaining thrust in a desired direction.

[0068] Each end of the rotor blade control link (330) of the rotor blade structure (300) is connected to the rotor blade (320), and the other end is connected to a single point (point P in FIG. 7). At point P, the magnitude of the thrust is determined by the amount (e) of eccentricity from the central axis O, and the direction of the thrust is determined according to the eccentric azimuth (ε). In this way, the direction of the thrust is controlled by changing the trajectory of the pitch angle.

[0069] Meanwhile, the present invention may further include a flap (400) configured to increase lift by being provided on the fixed wing structure (200).

[0070] The flap (400) may be provided on one side of the rear end of at least one of the upper fixed wing (210) and the lower fixed wing (220) of the fixed wing structure part (200).

[0071] The above flap (400) may be a plain flap type as shown in (A) of FIG. 9, a split flap type as shown in (B) of FIG. 9, a Fowler flap as shown in (C) of FIG. 9, or a slotted flap type as shown in (D) of FIG. 9.

[0072] According to the hybrid blade-wing structure for an aircraft and the aircraft including the same as described above, through a fusion structure of a biplane wing structure and a cyclo-rotor blade structure, it is possible to have both the advantages of a fixed-wing and a rotary-wing aircraft. Additionally, through an expandable and contractible biplane structure, it is possible to reduce the size during takeoff and landing to save space, and to expand during gliding to generate sufficient lift, thereby enabling stable flight.

[0073] In addition, the present invention has the advantage of producing low noise, being able to switch between vertical and horizontal flight by rotating the wings like a tiltrotor during flight, enabling stable hovering in turbulent conditions, and providing enhanced safety in the event of an accident by having the biplane wing structure act as a guide, while the externally exposed propeller poses a risk, whereas the cyclo's rotor blade structure is configured to be enclosed by the biplane wing structure, thereby relatively improving safety, and since lift for flight is obtained through the biplane wing structure and the cyclo's rotor blade structure generates thrust in the horizontal direction, using only energy for forward movement, it can provide a superior flight distance.

[0074] Although the hybrid blade-wing structure according to the present invention described above has been explained as being applied to an aircraft, it can also be applied to a device configured with a blade, wing, or wing, such as a wind power generation device that uses wind power.

[0075] The embodiments described in this specification and the accompanying drawings are merely illustrative of a part of the technical concept included in the present invention. Accordingly, since the embodiments disclosed in this specification are intended to explain, not limit, the technical concept of the present invention, it is obvious that the scope of the technical concept of the present invention is not limited by these embodiments. All variations and specific embodiments that can be easily deduced by a person skilled in the art within the scope of the technical concept included in the specification and drawings of the present invention should be interpreted as being included within the scope of the rights of the present invention.

Claims

1. As a wing structure equipped in an aircraft. Structure frame part; A biplane fixed-wing structural part provided in the above-mentioned structural frame part; and Characterized by including a rotor blade structure portion rotatably provided on the above-mentioned structural frame portion. Hybrid blade-wing structure for aircraft.

2. In Paragraph 1, The above-mentioned structural frame portion is composed of a pair of X-shaped frames arranged with a gap, and The above fixed wing structure is characterized by including an upper fixed wing provided at the top of the pair of X-shaped frames and a lower fixed wing provided at the bottom of the pair of X-shaped frames. Hybrid blade-wing structure for aircraft.

3. In Paragraph 2, The above rotor blade structure Characterized by comprising a plurality of rotor blades rotatably coupled to a pair of X-shaped frames between the upper fixed wing and the lower fixed wing. Hybrid blade-wing structure for aircraft.

4. In Paragraph 2 or 3, The above rotor blade structure A pair of circular rotating plates, each rotatably coupled to the intersection center of the above pair of X-shaped frames; Rotor blades having both ends connected to the above-mentioned pair of circular rotating plates, connected in such a way that the pitch angle is adjustable, and a plurality of rotor blades spaced apart in the circumferential direction of the above-mentioned circular rotating plates; and A rotor blade control link section configured such that one end is eccentrically connected to each of the rotor blades and the other end is connected at the same center point to change the pitch angle and phase angle of the rotor blades. Hybrid blade-wing structure for aircraft.

5. In Paragraph 2 or 3, The above upper fixed wing and lower fixed wing are formed as cross-sectional streamlined wings, and The above-mentioned structural frame portion is characterized by having a stopper at an initial position and at a position rotated 90° from the initial position. Hybrid blade-wing structure for aircraft.

6. In Paragraph 2 or 3, At least one of the upper fixed wing and the lower fixed wing is characterized in that the wing is configured to be expandable and contractible in the longitudinal direction. Hybrid blade-wing structure for aircraft.

7. In Paragraph 2 or 3, At least one of the upper fixed wing and the lower fixed wing is configured to expand and contract in a telescoping manner. Hybrid blade-wing structure for aircraft.

8. In Paragraph 2 or 3, At least one of the upper fixed wing and the lower fixed wing is Main wing; and Characterized by including an extendable sub-wing configured to extend longitudinally outward from within the main wing and then retract back into the main wing. Hybrid blade-wing structure for aircraft.

9. In Paragraph 2 or 3, At least one of the upper fixed wing and the lower fixed wing is characterized by having a flap at the rear end. Hybrid blade-wing structure for aircraft.

10. Characterized by including a hybrid blade-wing structure for an aircraft according to any one of claims 1 to 3. aircraft.

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