JP2019116254A - Rotor and unmanned aircraft using the same - Google Patents

Abstract

To provide a rotor that can suppress wobbling in rotation of a rotor, and to provide an unmanned aircraft using the same.SOLUTION: A rotor 10 includes: a skin 20 formed of a carbon fiber to which a thermosetting resin is impregnated; and a core part 27 containing a foam body and disposed inside the skin 20. The skin 20 has an outside skin layer 21 formed of a carbon fiber fabric 22 with two or more shafts to which the thermosetting resin is impregnated and forming an outside surface of the rotor 10. The core part 27 is formed of the foam body to which the thermosetting resin is impregnated.SELECTED DRAWING: Figure 3

Description

  The present invention relates to a rotary wing having a core portion containing foam inside a skin containing carbon fiber, and an unmanned aerial vehicle using the same.

  In a battery-powered unmanned aerial vehicle as shown in Patent Document 1, weight reduction of the airframe is a serious problem related to battery life. In order to reduce the weight of the airframe, the rotor of a rotor (also referred to as a propeller) attached to a drive source for driving a flight has a closed-cell foam covered with carbon fiber as shown in Patent Document 2 Has been proposed. Such a rotary wing is manufactured by laminating a carbon fiber prepreg on the surface of a foam cut out into a desired shape by hot press molding or molding using an autoclave.

Japanese Patent Publication No. 2013-510614 gazette ([0024]) JP-A-2016-535689 ([0050] to [0051])

  By the way, when all the plurality of blades of the rotor are integrally formed, and the above-described rotor is an integrated blade having a center of rotation at its center, the respective blades from the center of rotation to the end in the radial direction of rotation If the density distribution is unbalanced, the rotation of the rotor may be distorted, leading to a reduction in lift. Further, in the case where the above-described rotary vane is a single-sided wing that constitutes one blade of the rotor, if variations in the weight of individual single-sided wings occur among products, a plurality of rotary wings are attached to the same rotation axis When this happens, there is a problem that the rotation of the rotor is blurred, which leads to a decrease in lift.

  The present invention has been made in view of the above circumstances, and an object of the present invention is to provide a rotary wing capable of suppressing a fluctuation of rotation of a rotor and an unmanned aerial vehicle using the rotary wing.

  The invention according to claim 1 made to achieve the above object is a rotor blade having a core portion including a foam on the inside of a skin obtained by impregnating a carbon fiber with a thermosetting resin, wherein the skin is A carbon fiber woven fabric having two or more axes is impregnated with a thermosetting resin, and has an outer skin layer forming an outer surface of the rotor, and the core portion is impregnated with the thermosetting resin in the foam. It is a rotary wing.

  The invention of claim 2 is a twill weave in which the carbon fiber woven fabric having two or more axes comprises a carbon fiber bundle having a filament number of 3000 or more, and the carbon fiber bundle is in the direction of the rotation radius of the rotor. The rotor according to claim 1, wherein the rotors are arranged in two directions 45 degrees apart.

  According to the invention of claim 3, the skin is formed by impregnating a carbon resin arranged in the radial direction of rotation of the rotor with a thermosetting resin, and the skin is arranged between the outer skin layer and the core portion It is a rotary wing according to claim 1 or 2 which has an inner skin layer.

  The invention of claim 4 is the rotary blade according to claim 3, wherein the skin is formed by laminating a plurality of the inner skin layers on the outer skin layer.

  The invention according to claim 5 is the rotor according to claim 4, wherein the outer skin layer and the inner skin layer are symmetrically stacked on the front side and the back side of the core portion.

  The invention according to claim 6 is an unmanned aerial vehicle using a rotary wing according to any one of claims 1 to 5, comprising a rotor provided with the rotary wing and rotating clockwise. It is an unmanned aerial vehicle using a rotary wing provided with two or more pairs of a first rotor generating a lifting force and a second rotor generating a lifting force by rotating in a counterclockwise direction.

  The invention according to claim 7 is an unmanned aerial vehicle using the rotor according to any one of claims 1 to 5, comprising a plurality of rotors provided with the rotor, and the tilt angle of the rotor The unmanned aerial vehicle using the rotary wings switches the rotor between a rotary wing mode that generates lift upwards of the fuselage and a fixed wing mode that generates thrusts forward of the fuselage.

  In the rotor of the present invention, since the core portion disposed inside the skin is formed by impregnating the foam with the thermosetting resin, the material obtained by impregnating the foam with the thermosetting resin in the semi-cured state is thermally treated. It becomes possible to press and shape a core part. Thereby, compared with the conventional rotary wing | blade which includes the cut-out foam, the imbalance of right and left and the variation in weight are suppressed. In addition, since the skin and the core are both impregnated with the thermosetting resin, the thermosetting resin can be made uniform at the time of hot pressing, and the imbalance and weight variation of the left and right of the rotary wing can be suppressed. . By these, the blurring of the rotation of the rotor is suppressed. Moreover, since the outer surface of the rotor is constituted by the outer skin layer formed by impregnating a thermosetting resin with a carbon fiber fabric of two or more axes, the bending strength, tensile strength and torsional strength required for the rotor are achieved. It becomes possible.

  The thermosetting resin to be impregnated into the carbon fiber is not particularly limited, but in order to enhance the rigidity of the rotor, an epoxy resin, a phenol resin, a mixture of an epoxy resin and a phenol resin, and the like are preferable. Moreover, when a flame retardance is calculated | required by a rotary blade, the phenol resin which has a favorable flame retardance is preferable.

  The foam in the core portion preferably has an open cell structure. When the foam has an open cell structure, the thermosetting resin can be impregnated, and molding at a high compression rate becomes possible. The foam can be selected from, for example, a urethane resin foam, a melamine resin foam, a polyolefin resin foam, a polyamide resin foam and the like, and is preferably a melamine resin foam or a polyamide resin foam. When the rotor is required to be flame retardant, the foam is preferably a melamine resin foam having good flame retardancy.

  The thermosetting resin to be impregnated into the foam is not particularly limited, but in order to enhance the rigidity of the rotary blade, an epoxy resin, a phenol resin, a mixture of an epoxy resin and a phenol resin, and the like are preferable. When the rotor is required to be flame retardant, a phenolic resin having good flame retardancy is preferred. In addition, it is preferable that the thermosetting resin with which a foam is impregnated, and the thermosetting resin with which carbon fiber is impregnated are the same. Delamination is suppressed as these thermosetting resins are the same.

  Examples of the carbon fiber woven fabric of the outer skin layer include plain weave composed of yarns in two directions, twill weave and satin weave, and triaxial weave composed of yarns in three directions. In the case of two-directional yarns, it is preferable that the carbon fiber bundles be arranged in two directions shifted by ± 45 degrees with respect to the rotational radius direction of the rotary wing. Thereby, the bending strength, the tensile strength and the torsional strength of the rotor can be improved. When the carbon fiber woven fabric is twill weave, the number of filaments of the carbon fiber bundle is preferably 3000 or more (the invention of claim 2), and more preferably 3000 to 12000. In the case where the carbon fiber woven fabric is a plain weave, the number of filaments of the carbon fiber bundle is preferably 3000 or more, and more preferably 3000 to 12000.

  Preferably, the skin has an inner skin layer in which a thermosetting resin is impregnated in carbon fibers arranged in the radial direction of rotation of the rotor (the invention of claim 3). According to this configuration, it is possible to improve the bending strength and the tensile strength in the rotation radius direction of the rotary wing. More preferably, the epidermis is formed by laminating a plurality of inner skin layers on the outer skin layer (the invention of claim 4).

  The outer skin layer and the inner skin layer are preferably laminated symmetrically on the front side and the back side of the core portion (the invention of claim 5). According to this configuration, it is possible to make the thickness of the layer disposed outside the core portion the same on both the front side and the back side of the rotary wing.

  The rotary blade according to the present invention is provided with two or more sets of a first rotor generating lift by rotating clockwise and a second rotor generating lift by rotating counterclockwise. It may be used for the first and second rotors in an unmanned aerial vehicle using wings (invention of claim 6), and by changing the tilt angle of the rotor, the rotor is caused to generate lift above the fuselage. The present invention may be applied to a rotor of an unmanned aerial vehicle using a rotary wing that switches between a rotary wing mode and a fixed wing mode that generates forward thrust of the airframe.

  In addition, the rotary blade of this invention can be employ | adopted to various unmanned aerial vehicles (UAV). In particular, the rotor according to the present invention can be employed in a UAV provided with a plurality of rotors because the right and left imbalances in the individual and the weight variation between the individual are suppressed. Examples of such a UAV include a rotary-wing UAV that generates thrust with a plurality of rotors, and a VTOL (Vertical Take-Off and Landing) UAV equipped with a main rotor and a plurality of tilt rotors. When the rotor of the present invention is used for a VTOL UAV, it can be used for a tilt rotor or a rotor assembled to a tilt wing. Furthermore, the rotary wing of the present invention can be applied not only to aircrafts but also to unmanned vessels and unmanned submersibles that perform remote control by wireless.

A perspective view of a rotary wing according to an embodiment of the present invention Cross section of rotor Partially broken perspective view of rotor Cross section showing manufacturing process of rotor Cross section showing manufacturing process of rotor A perspective view showing another example of a rotary wing (A) Graph showing imbalance in the longitudinal direction of the rotor shown in FIG. 1, (B) Graph showing weight variation of the rotor shown in FIG. Diagram for explaining how to measure rotor imbalance A perspective view showing an example of an unmanned aerial vehicle A perspective view showing another example of an unmanned aerial vehicle

  As shown in FIG. 1, the rotary wing 10 according to the present embodiment is used as a rotor 51 of the unmanned aerial vehicle 50 shown in FIG. The rotor 51 is attached to the rotation shaft of the motor 53 and rotationally driven, and has a structure in which a plurality of blades 52 are provided around the rotation shaft of the motor 53. The rotary wing 10 is formed by integrally molding all the blades 52 of the rotor 51, and a central hole 11 through which the rotation shaft of the motor 53 is inserted is formed at the central portion of the rotary wing 10. And, the rotary wing 10 is formed in a point symmetrical shape with the center hole 11 as a center. Further, the rotary wing 10 has a positioning hole 12 for positioning the rotary wing 10 with respect to the motor 53 in the vicinity of the center hole 11. In the present embodiment, the rotor 51 has a two-bladed structure, and the rotor 10 is formed in a straight line. And the part arrange | positioned one side and the other side of a longitudinal direction from the center hole 11 in the rotary blade 10 each comprise the left wing part 10L and the right wing part 10R. The upper and lower surfaces of the left wing 10L and the right wing 10R are gently curved so as to be upwardly convex when the rotary wing 10 is viewed in the longitudinal direction. Further, the left wing portion 10L and the right wing portion 10R are thicker at the front end side in the rotational direction (for example, in the clockwise direction side when rotating clockwise) than at the rear end side.

  The cross-sectional structure of the rotary blade 10 is shown by FIG. The rotary wing 10 covers the outside of the core portion 27 with a skin 20. The skin 20 is formed by impregnating carbon fibers with a thermosetting resin. The core portion 27 is formed by impregnating a foam with a thermosetting resin. The foam has an open cell structure, and specifically, is a melamine resin foam ("VASOTECTO G +" manufactured by Inoac Corporation). The thermosetting resin impregnated in the carbon fiber and the thermosetting resin impregnated in the foam are the same, and specifically, it is a phenol resin ("Sumilite resin PR-55791 B" manufactured by Sumitomo Bakelite Co., Ltd.).

  The skin 20 is formed by laminating the inner skin layer 25 on the inside of the outer skin layer 21 constituting the outer surface of the rotary wing 10. The laminated structure of the skin 20 disposed on the front side with respect to the core portion 27 and the laminated structure of the skin 20 disposed on the back side are the same. In the present embodiment, two inner skin layers 25 are stacked.

  The outer skin layer 21 shown in FIG. 3 is formed by impregnating a carbon fiber fabric 22 with a thermosetting resin. The carbon fiber fabric 22 is a twill weave of the carbon fiber bundle 23, and the number of filaments of the carbon fiber bundle 23 is 3,000. The carbon fiber bundles 23 are arranged in two directions shifted by ± 45 degrees with respect to the longitudinal direction of the rotary blade 10 (that is, the radial direction of the rotary blade 10). The inner skin layer 25 is formed by impregnating a carbon fiber group 26 arranged in the longitudinal direction of the rotary wing 10 with a thermosetting resin.

  In order to manufacture the rotary wing 10, first, as shown in FIG. 4, two woven fiber prepregs 31 in which a carbon fiber woven fabric 22 is impregnated with a thermosetting resin, and carbon fiber groups 26 aligned in one direction are used. The four arrayed prepregs 35 impregnated with the thermosetting resin and the one sheet of foam prepreg 37 in which the foamed resin is impregnated with the thermosetting resin are prepared. The thermosetting resin of the prepregs 31, 35, 37 is in a semi-cured state. The plan view shapes of the prepregs 31, 35, 37 are substantially the same. The thickness of the woven fabric prepreg 31 is 250 μm, and the thickness of the arrayed prepreg 35 is 250 μm.

  Next, the prepregs 31, 35, 37 are stacked between the upper mold 41 and the lower mold 42. At this time, the fabric prepregs 31 and the arrayed prepregs 35 are arranged so that the front side and the back side of the foam prepreg 37 have the same number. That is, on the front and back sides of the foam prepreg 37, two arrangement prepregs 35 and one fabric prepreg 31 are laminated in order. The upper mold 41 and the lower mold 42 are heated to a temperature at which the thermosetting resin can be cured by an electric heater or the like.

  Next, as shown in FIG. 5, the upper mold 41 and the lower mold 42 are brought close to each other, clamped, and the laminated prepregs 31, 35, 37 are pressurized and heated. Then, the woven fabric prepreg 31 and the arrayed prepreg 35 pressed by the upper forming die 41 and the lower forming die 42 are formed into a shape corresponding to the forming surfaces 41M and 42M of the upper forming die 41 and the lower forming die 42 The foam prepreg 37 is compressed into the shape of a cavity formed between the upper mold 41 and the lower mold 42, and in that state, the thermosetting resin impregnated in each of the prepregs 31, 35, 37 is cured Do. At this time, a part of the thermosetting resin impregnated in the prepregs 31, 35, 37 passes through the parting line, becomes burrs, and leaks out of the mold. As a result, the woven fabric prepreg 31, the arrayed prepreg 35 and the foam prepreg 37 are integrally molded. Thereafter, the obtained molded product is removed from the mold and the burrs are removed as an unnecessary portion by cutting. By doing so, the rotor 10 is obtained. The woven fabric prepreg 31 is the outer skin layer 21, the arrayed prepreg 35 is the inner skin layer 25, and the foam prepreg 37 is the core portion 27.

  FIG. 6 shows another example of the rotor according to the present embodiment. The rotary wing 10V shown in the figure constitutes one blade 52 of the rotor 51 (in the example of FIG. 6, the rotor 51 is constituted by two rotary wings 10V). A plurality of mounting holes 13 for attaching the rotary wing 10V to the motor 53 are formed at an end of the rotary wing 10V on the side of the rotation center. The rotor 10V has the same cross-sectional structure as the rotor 10, and is manufactured in the same manner as the rotor 10V. Further, the lower surface of the rotary wing 10V is substantially flat.

  In the rotors 10 and 10 V of the present embodiment, since the core portion 27 is formed by impregnating the foam with the thermosetting resin, the foam prepreg 37 formed by impregnating the foam with the thermosetting resin in a semi-cured state is used. It is possible to form the core 27 by heat pressing. Thereby, compared with the conventional rotary wing | blade which includes the cut-out foam, the imbalance of right and left and the variation in weight are suppressed. Further, since the skin 20 and the core portion 27 are both impregnated with a thermosetting resin, the upper molding die 41 and the lower molding die 42 form a sealed space during the heat pressing, and the skin 20 and the core portion 27 Even if the liquid thermosetting resin flows, the liquid thermosetting resin is uniformly filled in the sealed space, and the amount of the thermosetting resin impregnated is appropriately adjusted. Imbalance and weight variation are suppressed. By these, the blurring of rotation of the rotor 51 provided with the rotary wings 10 and 10V as the blade | wing 52 is suppressed.

  FIG. 7A shows the measurement results of the left and right unbalance amounts ΔU of the plurality of rotary wings 10. The left and right unbalance amount ΔU was measured 26 for each of the rotary blade 10 for clockwise rotation and the rotary blade 10 for counterclockwise rotation. FIG. 8 shows a method of measuring the left and right unbalance amount ΔU. As shown in the figure, in this measurement method, the horizontal support shaft is inserted into the central hole 11 to support the rotary wing 10. When the difference in the moment of force acting on the left wing portion 10L and the right wing portion 10R is large, the rotary wing 10 is rotated such that the wing portion having the larger moment is on the lower side. Then, the wing portion abuts on the weighing scale 45 waiting below the rotary wing 10. At this time, the weight measured by the weight scale 45 is the left / right unbalance amount ΔU that is proportional to the difference between the moments of the left wing portion 10L and the right wing portion 10R. The left-right imbalance amount ΔU when the left wing portion 10L turns downward is negative, and the left-right imbalance amount ΔU when the right wing portion 10R turns downward is positive.

  As shown in FIG. 7A, in the rotary blade 10 for clockwise rotation (weight 61 g, total length 66 cm), there are 13 out of 26 0.1 g <ΔU ≦ 0.1 g, -0. There were 22 of 26 samples in which 2 g <ΔU ≦ 0.2 g. Further, in the rotor 10 for counterclockwise rotation, there are 17 pieces out of 26 with 0.1 g <ΔU ≦ 0.1 g, and all 26 pieces fall within the range of −0.2 g <ΔU ≦ 0.2 g. there were.

  Moreover, the measurement result of dispersion | variation with weight (DELTA) W of the rotary wing 10V is shown by FIG. 7 (B). The weight variation ΔW was determined by subtracting the design weight (61 g) from the measured weight of the rotor 10V. Twenty-six weight variations ΔW were measured for each of the rotary blade 10V for clockwise rotation and the rotary blade 10V for counterclockwise rotation.

  As shown in FIG. 7 (B), in the rotary blade 10V for clockwise rotation, there are 23 out of 26 those with −0.5 g <ΔW ≦ 0.5 g, and all 26 have −1.0 g < It was within the range of ΔW ≦ 1.0 g. In addition, in the rotor 10V for counterclockwise rotation, there are 22 pieces out of 26 with −0.5 g <ΔW ≦ 0.5 g, and all 26 pieces fall within the range of −1.0 g <ΔW ≦ 1.0 g Met.

  From the results of FIGS. 7A and 7B, it is confirmed that the lateral imbalance amount ΔU and the weight variation ΔW are small in the rotary wings 10 and 10 V of the present embodiment.

  As described above, the rotary wings 10, 10V of the present embodiment are used for the rotor 51 of the unmanned aerial vehicle 50 illustrated in FIG. The unmanned aerial vehicle 50 is a multicopter having a plurality of rotors 51, and has a structure in which a plurality of support arms 56 radially project from the body 55, and has a vertical rotation axis at the tip of each support arm 56. A motor 53 is provided. The rotor 51 is attached to each motor 53. A leg 57 is suspended from the tip of each support arm 56.

  The plurality of rotors 51 are provided with two types of rotors 51: a first rotor 51A that generates a lift by rotating clockwise, and a second rotor 51B that generates a lift by rotating counterclockwise. It is done. Specifically, the plurality of rotors 51 includes the same number of first rotors 51A and second rotors 51B. The first rotor 51A and the second rotor 51B are arranged adjacent to each other in the circumferential direction of the body 55. That is, the second rotor 51B is disposed on both sides of the first rotor 51A, and the first rotor 51A is disposed on both sides of the second rotor 51B.

  In FIG. 10A and FIG. 10B, an unmanned aerial vehicle 50V is shown as another example of the unmanned aerial vehicle provided with the rotor 51 consisting of the rotary wings 10 and 10V. The unmanned aerial vehicle 50V is a VTOL type UVA capable of changing the tilt angle of the rotor 51. In the unmanned aerial vehicle 50V, when the tilt angle is set so that the rotation axis of the rotor 51 is directed in the vertical direction, the rotor 51 is in the rotary wing mode (state shown in FIG. When the tilt angle is set so that the rotation axis of the rotor 51 is directed in the horizontal direction, the fixed wing mode (the state shown in FIG. 10B) in which the rotor 51 generates a thrust toward the front of the vehicle is obtained. In addition to the rotor 51, the unmanned aerial vehicle 50V is provided with a rotor (not shown) whose tilt angle is fixed so as to generate a lifting force to the upper side of the vehicle. Thus, even when the tilt angle of the rotor 51 is changed, the unmanned aerial vehicle 50V can stably fly.

  The rotary wings 10 and 10V can be used not only for the rotor of the unmanned aerial vehicle described above, but also for propellers or rotors of manned aircraft, ships and submarines, turbines of blowers, blades of agitators, and the like.

[Other embodiments]
The present invention is not limited to the above-described embodiment, and, for example, the embodiments described below are also included in the technical scope of the present invention, and various other variations are possible without departing from the scope of the invention. It can be changed and implemented.

  (1) In the above embodiment, the two directions in which the carbon fiber bundles 23 are arrayed deviate by ± 45 degrees with respect to the longitudinal direction of the rotary wing 10, but any angle may be used. For example, it may be +30 degrees and -60 degrees. The two directions in which the carbon fiber bundles 23 are arranged may be perpendicular to the direction parallel to the longitudinal direction of the rotary wing 10.

  (2) In the above-described embodiment, the number of laminated layers of the inner skin layer 25 in the skin 20 is two, but it may be one or three or more. The inner skin layer 25 may not be laminated. At this time, the epidermis 20 consists only of the outer skin layer 21.

  (3) The carbon fiber groups 26 of the inner skin layer 25 are arranged in the longitudinal direction of the rotary wing 10, but may be arranged in a direction intersecting the longitudinal direction of the rotary wing 10. The inner skin layer 25 may have a configuration in which a thermosetting resin is impregnated in a non-woven fabric made of carbon fibers.

  (4) In the above-described embodiment, the number of stacked outer skin layers 21 in the skin 20 is one, but may be two or more. At this time, the carbon fiber woven fabric of the plurality of outer skin layers 21 is arbitrarily selected from plain weave, twill weave, satin weave and triaxial weave, respectively. In the case where all the carbon fiber woven fabrics of the plurality of outer skin layers 21 are twill weave, the two directions in which the carbon fiber bundles 23 are arranged may be the same between the plurality of outer skin layers 21 or are shifted. May be

  (5) In the said embodiment, although the laminated structure of the outer skin 20 arrange | positioned on the front side with respect to the core part 27 and the laminated structure of the outer skin 20 arrange | positioned on the back are the same, they may differ. At this time, the number of laminations of only one of the outer skin layer 21 and the inner skin layer 25 in the skin 20 may be different, or the number of laminations of both may be different.

  (6) In the above embodiment, the number of foam prepregs 37 forming the core portion 27 is one, but may be two or more. At this time, the density of the foam may be different among the plurality of foam prepregs 37.

  (7) In the above embodiment, the rotary vane 10 has a structure in which the two blades 52 are integrated, but may be a structure in which three or more blades 52 are integrated.

  (8) In the above embodiment, the tilt angles of some of the rotors (not shown) of the unmanned aerial vehicle 50V are fixed, but the tilt angles of all the rotors may be changeable. At this time, if an arbitrary rotor is changed from the rotorcraft mode to the fixed wing aircraft mode and the remaining rotors are kept in the rotorcraft mode, the unmanned aircraft can be operated even when the tilt angle of any rotor is changed. 50V can fly stably.

  (9) Instead of the support arm 56, the unmanned aerial vehicle 50V may be provided with a wing-like arm extending from the body 55, and the wing-like arm may be configured to generate lift above the vehicle. At this time, the rotor 51 is attached to the tip of the wing-like arm. Further, in this case, the winged arm and the rotor 51 may be integrated to change the posture with the unmanned aerial vehicle 50V as the tilt wing type, and the rotary wing aircraft mode and the fixed wing aircraft mode may be changed.

10, 10 V rotary wing 20 skin 21 outer skin layer 22 carbon fiber fabric 25 inner skin layer 27 core 50, 50 V unmanned aerial vehicle 51 rotor

Claims (7)

A rotary blade having a core portion containing a foam on the inside of a skin formed by impregnating a carbon fiber with a thermosetting resin,
The skin has an outer skin layer formed by impregnating a carbon fiber fabric of two or more axes with a thermosetting resin to form an outer surface of the rotor.
The core portion is a rotary blade formed by impregnating the foam with a thermosetting resin.   The carbon fiber woven fabric having two or more axes is a twill weave composed of carbon fiber bundles having a filament number of 3000 or more, and the carbon fiber bundles are deviated by ± 45 degrees with respect to the rotational radius direction of the rotary wing in two directions The rotor according to claim 1 arranged.   The skin is formed by impregnating carbon fibers arranged in a radial direction of rotation of the rotor with a thermosetting resin, and having an inner skin layer disposed between the outer skin layer and the core portion. The rotary wing according to 1 or 2.   The rotary blade according to claim 3, wherein the skin is formed by laminating a plurality of the inner skin layers on the outer skin layer.   The rotor according to claim 4, wherein the outer skin layer and the inner skin layer are laminated symmetrically on the front side and the back side of the core portion. An unmanned aerial vehicle using a rotor according to any one of claims 1 to 5,
It has a rotor provided with the said rotary wing,
A rotary blade provided with two or more sets of a first set of rotors generating lift by rotating clockwise and a second set of rotors generating lift by rotating counterclockwise Unmanned air vehicle. An unmanned aerial vehicle using a rotor according to any one of claims 1 to 5,
A plurality of rotors provided with the rotors,
An unmanned aerial vehicle using a rotary wing, wherein the rotor is switched between a rotary wing mode generating lift upward and a fixed wing mode generating forward thrust by changing a tilt angle of the rotor.