JP2006248456A - Wing for flying body, flap, and controlling method of wing shape - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a wing for a flying body with high and various flexibility in a wing longitudinal direction while keeping high wing shape holding performance in a wing width direction and high different-flexibility in the wing longitudinal direction. <P>SOLUTION: On each inner surface of an upper flexible wing 10U and a lower flexible wing 10L composed of a CFRP rod 1 molded to have anisotropy in an axial direction, and an elastic member 2 filled in a clearance of the CFPR rod 1, a plurality of pressure tubes 20U, 20L are scattered in the wing longitudinal direction. The pressure tubes 20U, 20L are decompressed in an initial state. The pressure tubes 20L are compressed when the wing is deformed upward, and the pressure tubes 20U is compressed when the wing is deformed downward. The upper flexible wing 10U and the lower flexible wing 10L are oriented so as to make the axial direction of the CFRP rod 1 match the wing width direction. <P>COPYRIGHT: (C)2006,JPO&NCIPI

Description

  The present invention enables a wing and a flap for a flying object and a shape control method for a wing, and in particular, a morphing technique having a high wing shape holding ability in the wing width direction and high flexibility and changeability in the wing wing direction. The present invention relates to a flying wing and a flap, and a wing shape control method.

  Researches to improve the flight performance and flight characteristics of aircraft by arbitrarily changing the cross-section and shape of the wing by morphing technology have been actively conducted in the United States and other countries. In order for this morphing technology to be established, it is necessary for the wing structure to simultaneously satisfy structural characteristics such as high load-bearing capacity, high flexibility and changeability. Among these, there are already wing structural elements having some characteristics, but there are no wing structural elements that sufficiently satisfy all of these structural characteristics. For example, a metal or composite wing incorporating a conventional piezoelectric actuator has load-bearing capacity in the wing span direction and wing wing direction, but has flexibility in the wing wing direction. However, even if a mechanism that can freely rotate like a conventional flap is used, the flexibility of deformation of the entire wing cannot be expected. In addition, the flexible structure including the inflatable structure described in the following Patent Documents 1 to 6 has a large variable ability by using a gas pressure, a piezoelectric actuator, or the like, but lacks a load bearing ability. . Especially for auxiliary wings such as flaps among the wings, sufficient rigidity and strength to withstand the bending moment applied to the wings are required in the wing width direction. Since it also becomes rigid, that is, anti-flexible at the same time in the heel direction, a trade-off occurs between rigidity and flexibility. Further, when the blade section itself is constituted by a pressure tube, the blade section has flexibility in the blade blade direction, but it is difficult to obtain sufficient rigidity in the blade width direction. Furthermore, if any one of the pressure tubes is cracked, flight becomes difficult. As another report, an attempt to change the shape by passing a pressure tube through a flexible structure such as rubber as described in Patent Document 6 and applying an internal pressure thereto has been reported. These also essentially have a structure in which the pressure tube bears the rigidity in the wing span direction and does not solve the above problem.

U.S. Pat. No. 3,957,232 US Pat. No. 4,261,534 US Pat. No. 4,725,521 US Pat. No. 6,015,115 Japanese National Patent Publication No. 11-512998 US Pat. No. 6,082,667

As described above, it is essential that the wing structure has flexibility, airfoil retention ability, and variable ability as a condition for establishing a morphing technique different from the conventional structure including a movable mechanism and a hydraulic actuator. In particular, the flexibility of the wing structure and the airfoil retention ability are in a reciprocal relationship, and it is very difficult to achieve both. In addition, a variable drive mechanism with variable flexibility is considered to be possible in principle by dispersing small actuators, but an actuator that can be greatly deformed uses hydraulic pressure or the like, leading to an increase in weight. There are also many difficult points, such as complexity of wiring.
Accordingly, the present invention has been made in view of the above-described problems of the prior art, and the problem to be solved is that the airfoil holding ability is high in the blade width direction and the flexibility in the blade blade direction is high. It is an object to provide a wing and flap for a vehicle and a shape control method for a wing that enable a morphing technique having high variability.

In the first invention for achieving the above object, a plurality of long-axis objects made of a reinforcing material having at least one anisotropy and formed so that the maximum anisotropy coincides with the long-axis among the anisotropy, A flexible wing having an elastic member filled in a gap between the plurality of long-axis objects; and wing deforming means for changing the shape by generating stress on the flexible wing, wherein the long-axis object is a wing of the wing It is characterized by being oriented parallel to or substantially parallel to the width direction, having high rigidity in the blade width direction, and high flexibility and changeability in the blade direction.
In the aircraft wing according to the first aspect of the invention, since the long axis object is oriented parallel to the wing width direction, the rigidity of the wing in the wing width direction is determined by the rigidity of the long axis object. By the way, since the long shaft object is formed so as to have the maximum anisotropy in the axial direction, the rigidity of the flexible wing in the span direction is improved by the maximum anisotropy of the long shaft object. On the other hand, since the gap between the long shaft objects is filled with an elastic member, the rigidity with respect to the blade hook direction is lowered and the flexibility is improved. Therefore, when a stress is generated in the flexible wing, the flexible wing is deformed in the direction of the blade wing having a low rigidity to relieve the stress. Therefore, the flexible wing can be freely bent and deformed with respect to the blade wing direction by the wing deforming means. This makes it possible to simultaneously satisfy the high airfoil retention capability in the blade width direction, high flexibility in the blade blade direction, and high variability, which was impossible with conventional inflatable blades. It can be suitably applied.

In order to achieve the above object, in the second invention, the first anisotropy material having at least one anisotropy is used, and the maximum anisotropy is orthogonal or substantially orthogonal to the wave direction. The wing inner plate is formed into a wavy shape and a second reinforcing material having at least one anisotropy, and the maximum anisotropy is equal to the maximum anisotropy of the wing inner plate. A flexible wing having a wing outer plate, and wing deforming means for changing the shape by generating stress in the flexible wing, wherein the wing inner plate has a wave direction parallel to the blade direction of the wing or It is characterized by being oriented substantially in parallel and having high rigidity in the wing span direction and high flexibility and changeability in the wing span direction.
In the aircraft wing according to the second aspect of the invention, the maximum anisotropy of the wing inner plate and the wing outer plate is equal and orthogonal to the wave direction, and the wave direction of the wing inner plate is oriented parallel to the wing direction. Therefore, the rigidity in the blade width direction is improved by the maximum anisotropy of the blade inner plate and the blade outer plate. Further, since the blade inner plate is formed in a wave shape, it has an elastic action. As a result, the rigidity in the blade hook direction is lowered and the flexibility is improved. Therefore, when a stress is generated in the flexible wing, the flexible wing is deformed in the direction of the blade wing having a low rigidity to relieve the stress. Therefore, the flexible wing can be freely bent and deformed with respect to the blade wing direction by the wing deforming means. This makes it possible to simultaneously satisfy the high airfoil retention capability in the blade width direction, high flexibility in the blade blade direction, and high variability, which was impossible with conventional inflatable blades. It can be suitably applied.

In a third invention, the blade deforming means is disposed on one or both surfaces of the outer surface or the inner surface of the flexible blade and has a contractibility, and individually supplies the internal pressure of the pressure tube. The pressure adjusting means for pressurizing or depressurizing is used.
In the aircraft wing of the third invention, since the pressure tube has elasticity, the pressure of the fluid acts on the flexible wing through the pressure tube, while the pressure in the flexible wing is the pressure. Stress against this occurs. By the way, since the flexible wing has high flexibility in the wing wing direction, the stress is relieved by being deformed in the wing wing direction. Thus, by pressurizing the pressure tube, the flexible wing can be deformed with respect to the blade wing direction. Further, the pressure adjusting means for individually adjusting the internal pressure of the pressure tube makes it possible to adjust the magnitude of the stress generated at each point of the flexible wing. Combined with high flexibility, bending deformation can be freely made in proportion to the internal pressure of the pressure tube. Furthermore, when a part of the pressure tubes has a problem, the influence on the problem can be reduced by using the other part of the pressure tube, and the robustness is improved.

In the fourth invention, each of the pressure tubes is parallel to the blade width direction and discretely or continuously dense with respect to the blade blade direction so as not to loosen on one or both surfaces of the outer surface or the inner surface of the flexible blade. It was decided that it was arranged.
In the aircraft wing according to the fourth aspect of the present invention, when the pressure tubes are arranged parallel or substantially parallel to the wing width direction and discretely with respect to the wing wing direction, each pressure tube functions like a hinge. Thus, the flexible wing can be bent and deformed in a substantially polygonal line with respect to the wing hook direction. On the other hand, when the pressure tubes are arranged densely in parallel or substantially parallel to the blade width direction, each pressure tube functions like a hinge and the flexible blades are substantially curved in the blade direction. It becomes possible to bend and deform. In addition, since the pressure tube is disposed on one or both surfaces of the outer surface or inner surface of the flexible wing without looseness, the working area of the pressure tube and the flexible wing is increased. Combined with high flexibility with respect to the direction, it becomes possible to bend and deform freely in the direction of the blade.

In the fifth aspect of the invention, the pressure tubes are arranged loosely on one or both surfaces of the outer surface or the inner surface of the flexible wing in a discrete or continuous manner in the blade width direction. .
In the aircraft wing according to the fifth aspect of the present invention, since the pressure tubes are arranged discretely or continuously densely in the wing width direction, the flexible wings are moved in the wing width direction by increasing the internal pressure of each pressure tube. A moment to bend against the flexible wing acts on the flexible wing, but since the flexible wing has high rigidity in the blade width direction, the moment escapes in the direction of the blade wing having low rigidity. Can be twisted in the direction of the wing while maintaining the airfoil shape in the wing span direction.

In the sixth invention, each of the pressure tubes has the same or different at least one of the outer diameters.
In the aircraft wing of the sixth aspect of the invention, since the magnitude of the bending moment acting on the flexible wing or the magnitude of the stress generated on the flexible wing is proportional to the mounting area of the pressure tube, Since the tube has a large mounting area, the stress generated in the flexible wing increases, and the flexible wing is greatly deformed in the blade wing direction in order to relieve the stress. On the other hand, the pressure tube having a small outer diameter has a small mounting area, so that the stress generated in the flexible wing is small, and the flexible wing is deformed small in the chord direction in order to relieve the stress. In this way, by changing the outer diameter of each pressure tube in various ways, the magnitude of the bending moment acting on the flexible blade or the magnitude of the generated stress is locally different, and the flexible blade has a high resolution continuously. Free deformation is possible.

In the seventh invention, the rigidity is completely equal or at least one is different.
In the aircraft wing of the seventh invention, since the bending moment acting on the flexible wing is due to the deformation of the pressure tube, the degree of deformation is small in the highly rigid pressure tube. The generated stress is reduced and the deformation of the flexible wing is also reduced. On the other hand, since the pressure tube with low rigidity has a large degree of deformation, the stress generated in the flexible wing increases and the deformation of the flexible wing also increases. In this way, by changing the rigidity of the pressure tube in various ways, the magnitude of the bending moment acting on the flexible wing or the magnitude of the generated stress varies locally, and the flexible wing can be continuously deformed with high resolution. Is possible.

In an eighth aspect of the invention, the pressure tube disposed on the outer surface of the flexible wing is made of a third reinforcing material having at least one anisotropy, and the maximum anisotropy among the anisotropies is It was assumed that it was covered with a thin plate fairing having a smooth surface equal to the maximum anisotropy of the long-axis object.
In the aircraft wing according to the eighth aspect of the invention, since the thin plate fairing has the same maximum anisotropy as that of the long-axis object, it has a high rigidity in the wing span direction as in the flexible wing, but in the wing wing direction. On the other hand, it has high flexibility. Accordingly, the thin plate fairing suitably protects the pressure tube disposed on the outer surface of the flexible wing while being deformed in the blade wing direction together with the flexible wing. Furthermore, since the surface of the thin fairing is smooth, the increase in air resistance can be reduced.

In the ninth invention, each of the pressure tubes is disposed in a mountain valley or peak on the inner surface of the blade inner plate or on a mountain valley portion on the outer surface of the blade inner plate inside the blade outer plate.
In the aircraft wing according to the ninth aspect of the invention, when the pressure tube is disposed in the mountain valley of the inner surface of the upper wing inner plate, the upper flexible wing is deformed upward by pressurizing the pressure tube. can do. On the other hand, when the pressure tube is arranged at the crest of the inner surface of the upper blade inner plate or the mountain valley of the outer surface of the blade inner plate, the flexible blade can be deformed downward by pressurizing the pressure tube. . Thus, since each pressure tube is appropriately arranged with respect to a flexible wing having a wavefront, high-resolution continuous free deformation is possible.

In the tenth aspect of the invention, the pressure tube disposed on the peak portion of the inner surface of the blade inner plate is fixed without looseness by the peak portions of the inner surface of at least two blade inner plates.
In the aircraft wing of the tenth aspect of the invention, a bending moment preferably acts on the flexible wing via the crest of the inner surface of the wing inner plate, and the flexible wing can be greatly deformed.

In the eleventh invention, at least one of the reinforcing material, the first reinforcing material, the second reinforcing material, and the third reinforcing material is a fiber reinforcing material.
In the aircraft wing of the eleventh aspect of the invention, since the fiber reinforcing material has the maximum anisotropy with respect to the fiber direction, the characteristic is that of a long-axis object, a wing inner plate, a wing outer plate or a thin plate fairing. Applied to at least one molding, the blade structure preferably has both high rigidity in the blade width direction and flexibility in the blade blade direction. Thereby, it becomes possible to apply a morphing technique suitably.

According to a twelfth aspect of the invention for achieving the above object, the wing for an aircraft described in the first aspect of the invention or the second aspect of the invention is used.
Since the aircraft flap of the twelfth aspect of the present invention is constituted by the wing for an aircraft described in the first or second aspect of the invention, the wing shape in the wing span direction is maintained while the wing shape in the wing width direction is maintained. High-resolution continuous free deformation.

In a thirteenth aspect of the present invention for achieving the above object, a plurality of lengths made of a reinforcing material having at least one anisotropy and molded with the maximum anisotropy coincident with the major axis among the anisotropies. The flexible blade includes a flexible member including a shaft member and an elastic member filled in a gap between the plurality of long shaft members, and the long shaft member is oriented parallel or substantially parallel to the blade width direction of the blade. The flexible wing is variably deformed with respect to the direction of the blade by applying an external force to the blade.
In the wing shape control method of the thirteenth aspect of the invention, the shape of the flying wing of the first aspect of the invention can be suitably controlled.

In a fourteenth invention for achieving the above object, the first anisotropy is made of a first reinforcing material having at least one anisotropy, and the maximum anisotropy is orthogonal or substantially orthogonal to the wave direction. And a second reinforcing material having at least one anisotropy, wherein the maximum anisotropy is equal to the maximum anisotropy of the blade inner plate. An external force acting on the flexible wing with respect to a flexible wing that is oriented with the wave direction parallel or substantially parallel to the blade blade direction of the wing. The flexible wing is variably deformed with respect to the wing wing direction.
In the wing shape control method of the fourteenth aspect of the invention, the shape of the flying wing of the second aspect of the invention can be suitably controlled.

In the fifteenth aspect, the flexible wing is individually pressurized or depressurized by individually increasing or reducing the internal pressure of at least one pressure tube disposed on one or both surfaces of the outer surface or inner surface of the flexible wing. Stress was generated on the wing, and the blade was deformed variably in the blade wing direction.
In the wing shape control method of the fifteenth aspect of the invention, the shape of the flying wing of the third aspect of the invention can be suitably controlled.

In the sixteenth aspect of the invention, the pressure tubes are arranged in parallel with the blade width direction and discretely or continuously densely with respect to the blade wing direction, and are arranged loosely on one or both surfaces of the outer surface or inner surface of the flexible blade. The internal pressure of each pressure tube is individually increased or decreased to generate stress in the flexible wing and to be variably deformed in the direction of the blade wing.
In the wing shape control method of the sixteenth aspect of the invention, the shape of the flying wing of the fourth aspect of the invention can be suitably controlled.

In a seventeenth aspect of the present invention, the pressure tubes are discretely or continuously densely arranged in the blade width direction, and are disposed on one or both surfaces of the outer surface or the inner surface of the flexible blade without looseness. By individually increasing or decreasing the internal pressure, stress is generated in the flexible wing so as to be variably deformed in the direction of the blade wing.
In the wing shape control method of the seventeenth invention, the shape of the flying wing of the fifth invention can be suitably controlled.

In an eighteenth aspect of the invention, stress is generated in the flexible wing by individually increasing or decreasing the internal pressure of each pressure tube so that each pressure tube has the same or different at least one outer diameter. In this way, the blade is deformed so as to be variable with respect to the blade wing direction.
In the wing shape control method of the eighteenth invention, the shape of the flying wing of the sixth invention can be suitably controlled.

In a nineteenth aspect of the invention, stress is generated in the flexible wing by individually increasing or decreasing the internal pressure of each pressure tube so that each pressure tube has the same rigidity or at least one different rigidity. Therefore, it is variably deformed in the direction of the blade.
In the wing shape control method of the nineteenth invention, the shape of the flying wing of the seventh invention can be suitably controlled.

In a twentieth invention, the pressure tube disposed on the outer surface of the flexible wing is made of a third reinforcing material having at least one anisotropy, and the maximum anisotropy is the long anisotropy among the anisotropies. It was covered with a thin plate fairing having a smooth surface equal to the maximum anisotropy of the shaft.
In the wing shape control method of the twentieth invention, the shape of the flying wing of the eighth invention can be suitably controlled.

In a twenty-first aspect of the present invention, the pressure tubes are arranged in a crest or crest on the inner surface of the blade inner plate or on a crest portion on the outer surface of the blade inner plate inside the blade outer plate so that the inner pressure of each pressure tube is increased. By individually pressurizing or depressurizing the wings, stress is generated in the flexible wings so as to be variably deformed with respect to the direction of the wing blades.
In the wing shape control method of the twenty-first aspect, the shape of the flying wing of the ninth aspect can be suitably controlled.

In a twenty-second aspect of the invention, the pressure tube disposed on the peak portion of the inner surface of the blade inner plate is fixed without looseness by the peak portions of the inner surface of at least two blade inner plates.
In the wing shape control method of the twenty-second invention, the shape of the flying wing of the tenth invention can be suitably controlled.

In a twenty-third aspect, at least one of the reinforcing material, the first reinforcing material, the second reinforcing material, and the third reinforcing material is a fiber reinforcing material.
In the wing shape control method of the twenty-third invention, the shape of the flying wing of the eleventh invention can be suitably controlled.

According to the aircraft wing of the present invention, it is possible to simultaneously achieve the high load-bearing capacity in the wing span direction, the high flexibility in the wing wing direction, and the high variableness, which are problems of the conventional inflatable wing. become able to. In particular, various deformations such as free bending deformation in the wing wing direction and free torsional deformation in the wing span direction are possible, and as a result, flight performance and flight characteristics are greatly improved. Furthermore, since the pressure tube having contraction functions not as a function of a blade structure for handling a load but as an actuator for deforming the shape of the blade, the robustness as a variable blade is improved. Since a large number of pressure tubes are arranged on the wing for the flying object, even if a defect such as a crack occurs in a part, it can be suitably substituted with another pressure tube. Also, robustness as an actuator is improved. In addition, by using the flying wing of the present invention in a place where a flight load is not relatively applied, such as an aircraft flap or a control surface, the drive system is simplified, the noise of the drive source is reduced, the flight performance is changed efficiently, etc. It is possible to make a significant contribution to the environment and comfort of aircraft.
Moreover, according to the wing shape control method of the present invention, the shape of the flying wing of the present invention can be suitably controlled.

  Hereinafter, the present invention will be described in more detail with reference to embodiments shown in the drawings.

FIG. 1 is a cross-sectional perspective view of an essential part showing an inflatable variable wing 100 according to Example 1 of an aircraft wing of the present invention.
The inflatable variable wing 100 includes a plurality of CFRP rods 1 that are long-axis objects formed so as to have anisotropy in the axial direction with a carbon fiber reinforced plastic material (hereinafter referred to as “CFRP”) that is a reinforcing material, The upper flexible wing 10U and the lower flexible wing 10L formed of the elastic member 2 filled in the gap between the CFRP rods 1 and wing deformation means for bending or twisting the flexible wings 10U and 10L as will be described later. The pressure tubes 20U and 20L are configured.

  The CFRP rod 1 is oriented with its axial direction coinciding with the wing span direction. Therefore, the inflatable variable wing 100 has high rigidity in the blade width direction, but has high flexibility in the blade wing direction due to the elastic action of the elastic member 2. Thus, the inflatable variable wing 100 achieves both high airfoil retention capability in the blade width direction and high flexibility in the blade wing direction, which had a contradictory relationship. Furthermore, by applying a simple control method of increasing or decreasing the pressure of the pressure tubes 20U and 20L as will be described later, the inflatable variable blade 100 can be freely bent or twisted with respect to the blade hook direction. It is possible to improve the flight performance and flight characteristics of the aircraft.

FIG. 2 is an explanatory diagram showing a configuration example of the blade deformation means.
Here, blade deformation means for bending or twisting the upper flexible blade 10U will be described. This blade deforming means includes an airtight pressure tube 20U that can be deformed into a cylindrical shape on the inner surface of the upper flexible blade 10U, a pressure regulating valve 21 that adjusts the pressure, and an air reservoir filled with high-pressure gas. 22 and a vent valve 23 for reducing the internal pressure of the pressure tube 20U. The material of the pressure tube 20 is, for example, silicon rubber or polyester. The air reservoir 22 is filled with, for example, helium, nitrogen or air. Thus, the internal pressure of the pressure tube 20U can be freely adjusted by the pressure regulating valve 21 and the vent valve 23. The blade deformation means for bending or twisting the lower flexible blade 10L has the same configuration.

  Note that, for convenience of illustration, one pressure tube 20U is shown, but actually, a plurality of pressure tubes 20U are arranged along the blade hook direction. In this way, by configuring with a large number of pressure tubes 20U, when a crack or the like occurs in some of the pressure tubes 20U, the degree of influence on one system is reduced. Moreover, by substituting with another pressure tube, the influence with respect to a malfunction can be decreased, and it has robustness and redundancy.

  Furthermore, since each pressure tube 20U has the pressure regulation valve 21, the air accumulator 22, and the vent valve 23, it is pressurized or pressure-reduced separately. Therefore, as will be described later, the inflatable variable wing 100 can be flexibly deformed or twisted with respect to the direction of the blade wing by pressurizing or depressurizing a selected portion of the pressure tube 20 with various pressures. It becomes.

FIG. 3 is an explanatory diagram showing an adhesion state of the pressure tube 20U and an operation when an internal pressure is applied. 3A shows the bonded state, and FIG. 3B shows the operation when an internal pressure is applied.
As shown in (a) of FIG. 3, the pressure tube 20U is adhesive so as not to sag along the inner surface 10 _S of the upper flexible wings 10 U (in the state balanced with the atmospheric pressure) so as not to apply pressure S Is attached by. The adhesive is, for example, epoxy. A pressure tube 20L (not shown) is attached to the inner surface of the lower flexible wing 10L (not shown) in the same manner.

  As shown in FIG. 3B, when the gas is supplied to the pressure tube 20U and the internal pressure rises, the pressure tube 20U expands to approach a circular shape, but the upper part is fixed with the adhesive S. The pressure tube 20U exerts a bending moment on the flexible wing 10U and tries to approach a circular shape. As a result, a stress against the moment is generated in the flexible wing 10U. Since the flexible blade 10U has high rigidity in the blade width direction, the stress is relieved by being deformed in the blade rigidity direction having low rigidity. The flexible wing 10U is deformed in the direction shown in the drawing with the pressure tube 20U as the center. Thus, by pressurizing the pressure tube 20U, it is possible to bend and deform as if the flexible wing 10U includes a vent mechanism such as a hinge. The amount of bending deformation is proportional to the internal pressure of the pressure tube 20U. As a matter of course, when the pressure tube 20U is depressurized, the flexible wing 10U returns to the state shown in FIG.

  On the other hand, it is also possible to change the flexible wing 10U by reducing the internal pressure of the pressure tube 20U by applying the internal pressure to the pressure tube 20U in the initial shape.

  The conventional inflatable variable wing has a structure that handles the blade load with a pressure tube, so that it has flexibility in the blade wing direction while maintaining the airfoil retention capability in the blade width direction. Was almost impossible. Alternatively, even if the pressure tube is not a structure that handles loads, the basic structure of the wing has insufficient flexibility and flexibility in the wing span direction, and the flexibility of the wing blade direction is high. Free deformation was almost impossible. However, the inflatable variable wing 100 is a pressure tube because the flexible wings 10U and 10L, which are the basic structure of the wing, have a high airfoil holding ability in the blade width direction and a high flexibility in the blade wing direction. By increasing or decreasing the internal pressure of 20U and 20L, the flexible blades 10U and 10L can be freely deformed as if they had a vent mechanism such as a hinge.

  Generally, deformation of the inflatable variable blade 100 depends on the internal pressure of the pressure tube 20, the thickness of the material, the outer diameter, the elastic modulus, and the thickness and elastic modulus of the flexible blades 10U and 10L. By appropriately designing or controlling, it is possible to deform into a target shape.

FIG. 4 is a cross-sectional view of the main part showing the inflatable variable wing 200 in which the pressure tubes 20U are arranged in a continuous and dense manner along the blade hook direction. For convenience of illustration, only the upper flexible wing 10U is shown.
In the inflatable variable wing 200, in the inflatable variable wing 100, the pressure tubes 20U and 20L are discretely arranged in the blade direction and disposed on the inner surfaces of the flexible wings 10U and 10L. It is arranged on the inner surface of the flexible wings 10U and 10L in a continuous and dense manner in the heel direction.

FIG. 4A shows a state in which no pressure is applied to the pressure tube 20U. In this state, the pressure tube 20U does not act on the upper flexible wing 10U, and therefore the upper flexible wing 10U is not deformed.
FIG. 4B shows a state in which an equal pressure is applied to all the pressure tubes 20U, and the entire surface of the upper flexible wing 10U is deformed according to the applied pressure. In this way, bending deformation with constant curvature is possible by applying equal pressure to all the pressure tubes 20U. Further, the curvature of the upper flexible blade 10U decreases as the internal pressure increases, whereas the curvature of the upper flexible blade 10U increases as the internal pressure decreases.
FIG. 4C shows a state where pressure is applied only to the selected pressure tube 20U. In this way, by applying pressure only to the selected pressure tube 20U, it is possible to deform with a partially different curvature.

  As described above, in the inflatable variable wing 200, the pressure tubes 20U and 20L are arranged densely and continuously with the flexible wings 10U and 10L. The bent blades 10U and 10L can be freely bent or twisted at any point of the flexible blades 10U and 10L as if they are provided with a vent mechanism such as a hinge.

  If it is desired to control the bending deformation locally, the outer diameter of the pressure tubes 20U, 20L may be reduced, and the outer diameters of the pressure tubes 20U, 20L can be changed variously. Bending control or twisting control is possible.

  Further, in the inflatable variable vane 200, when some of the pressure tubes 20U and 20L are in trouble due to the occurrence of cracks or the like, the degree of influence on the entire system becomes small. In addition, when only the selected pressure tubes 20U and 20L are used, the influence on the malfunction can be reduced by switching the pressure tube to which the internal pressure is applied, and the system has robustness and redundancy. Further, even if a large number of pressure tubes 20U and 20L are used, there is no complication of piping and the like, and it can be driven with a simple system.

FIG. 5 is a perspective view of a main part showing an inflatable variable blade 300 in which the pressure tubes 20U are discretely arranged along the blade width direction. For convenience of illustration, only the upper flexible wing 10U is shown.
In the inflatable variable blade 300, in the inflatable variable blades 100 and 200, pressure tubes 20U and 20L (not shown) are continuously integrated along the blade width direction on the inner surface of the flexible blades 10U and 10L (not shown). Whereas a large number of pressure tubes 20U, 20L (not shown) divided in the axial direction are dispersed along the blade width direction, the inner surfaces of the flexible blades 10U, 10L (not shown) are arranged. It is arranged.

  In this way, a large number of pressure tubes 20U are discretely arranged in the wing width direction and disposed on the inner surface of the upper flexible wing 10U. When pressure is applied to each pressure tube 20U, the pressure tubes tend to be deformed into a circle. As a result, a bending moment acts on the upper flexible wing 10U, and a stress against the bending moment is generated on the upper flexible wing 10U. However, the flexible wing 10U has high rigidity in the blade width direction. Therefore, the stress is relieved by being deformed with respect to the blade wing direction. As a result, the upper flexible wing 10U is torsionally deformed with respect to the blade hook direction. Further, by applying different pressures to the pressure tubes 20U or changing the rigidity of the pressure tubes 20U, variable torsional deformation from local to overall can be performed.

FIG. 6 is an explanatory cross-sectional view of a main part showing an application example of the inflatable variable wing 100 according to the first embodiment to the flap 110.
The flap 110 is constituted by an inflatable variable wing 100. Therefore, by controlling the internal pressure of each pressure tube 20U, 20L, it is possible to freely bend and deform the blades in the direction of the blades.
FIG. 6A shows a state in which no pressure is applied to the pressure tubes 20U and 20L. In this state, the pressure tubes 20U and 20L do not act on the upper flexible wing 10U and the lower flexible wing 10L, and thus the flap 110 maintains a neutral state.
FIG. 6B shows a state in which pressure is applied to the pressure tube 20L, and the flap 110 is deformed upward in accordance with the applied pressure.
FIG. 6C shows a state in which pressure is applied to the pressure tube 20U, and the flap 110 is deformed downward in accordance with the applied pressure.

  As described above, in the initial state, the pressure tubes 20U and 20L are depressurized, and the pressure is deformed upward by pressurizing the pressure tube 20L. Alternatively, by pressurizing the pressure tube 20U, the flap 110 is It can be deformed downward.

  Further, in the initial state, the pressure tubes 20U and 20L are pressurized and the pressure tube 20L is depressurized to deform the flap 110 downward. Alternatively, the pressure tube 20U is depressurized and the flap 110 is moved upward. It can be deformed.

  In general, the deformation of the flap 110 depends on the internal pressure of the pressure tubes 20U and 20L, the thickness of the material, the outer diameter, the elastic modulus, and the thickness and elastic modulus of the upper flexible wing 10U and the lower flexible wing 10L. Therefore, these factors can be transformed into the target shape by appropriate design or control.

  Further, the flap 110 may be configured by using the inflatable variable blade 200 or the inflatable variable blade 300 in place of the inflatable variable blade 100. In the case of the inflatable variable wing 200, the flap can be more flexibly deformed with respect to the blade hook direction. On the other hand, in the case of the inflatable variable blade 300, the flap can be twisted in addition to the bending deformation in the blade hook direction.

FIG. 7 is a cross-sectional explanatory view of a main part showing an inflatable variable wing 400 according to Embodiment 2 of an aircraft wing of the present invention.
The inflatable variable wing 400 includes a plurality of CFRP rods 1 which are long-axis objects formed so as to have anisotropy in the axial direction with CFRP which is a reinforcing material, and an elastic member 2 which is filled in a gap between the CFRP rods 1. An upper flexible wing 10U and a lower flexible wing 10L, a pressure tube 20 as a blade deforming means for deforming the upper flexible wing 10U and the lower flexible wing 10L with respect to the blade wing direction, and a pressure tube 20 And a thin fairing 30 to be coated. The pressure tube 20 is disposed on the outer surface of the lower flexible wing 10, the pressure tube 20 _OU disposed on the outer surface of the upper flexible wing 10, the pressure tube 20 _IU disposed on the inner surface thereof. The pressure tube 20 _OL is formed, and the pressure tube 20 _IL disposed on the inner surface.

In the inflatable variable wings 100, 200, and 300 of the first embodiment, the pressure tubes 20 are disposed on the inner surfaces of the upper flexible wing 10U and the lower flexible wing 10L. Pressure tubes 20 are arranged on both surfaces of the wing 10U and the lower flexible wing 10L. The pressure tubes 20 _OU and 20 _OL arranged on the outer surfaces of the upper flexible wing 10U and the lower flexible wing 10L are resistant to the air flow flowing on the outer surfaces of the upper flexible wing 10U and the lower flexible wing 10L. These pressure tubes 20 _OU and 20 _OL are covered with a thin fairing 30 having a smooth surface. The thin fairing 30 has the same anisotropy as the CFRP rod 1 and is formed of, for example, a reinforcing material CFRP.

In the above inflatable variable vane 400, the pressure tube _{20 OU, 20 IU, 20 OL} , 20 on the _IL flexible blades 10U and lower flexible wings 10L is controlled, is excellent in shape controllability, also, the upper flexible Since these many pressure tubes 20 _OU , 20 _IU , 20 _OL , 20 _IL handle the bending moment acting on the wing 10U and the lower flexible wing 10L, the load on each pressure tube is reduced and further problems such as cracks occur. When this occurs, the bending moment that the other pressure tubes are insufficient can be compensated suitably, and the robustness is further improved.

FIG. 8 is an explanatory cross-sectional view of a main part showing an application example of the inflatable variable blade 400 according to the second embodiment to the flap 410.
The flap 410 is constituted by an inflatable variable wing 400. Therefore, by freely controlling the internal pressures of the pressure tubes 20 _OU , 20 _IU , 20 _OL , and 20 _IL , flexible bending deformation is possible.

FIG. 8A shows a state in which pressure is applied to the pressure tubes 20 _OU , 20 _IU , 20 _OL , and 20 _IL . In this case, the upper flexible wing 10U and the lower flexible wing 10L receive bending moments from the respective pressure tubes, but the bending moments cancel each other and apparently the flap 410 does not receive the bending moment. Therefore, the flap 410 is kept in a neutral state.

FIG. 8B shows a state in which the internal pressures of the pressure tube 20 _IU disposed on the inner surface of the upper flexible wing 10U and the pressure tube 20 _OL disposed on the outer surface of the lower flexible wing 10L are reduced. Is shown. In this case, the lower flexible wings 10L together with the upper flexible blade 10U is subjected to bending moments from the pressure tube _{20 OU} receives a bending moment from the pressure tube _{20 IL.} Accordingly, the flap 410 is deformed upward in accordance with the applied pressure. Further, since the magnitude of the bending moment is about twice that of the flap 110 of the first embodiment, the upward deformation amount is larger than that of the flap 110 of the first embodiment.

(C) in FIG. 8 shows a state where internal pressure of the pressure tube 20 _IL disposed on the inner surface of the pressure tube 20 _OU and lower flexible blades 10L disposed on the outer surface of the upper flexible blade 10U is decompressed Is shown. In this case, the lower flexible wings 10L together with the upper flexible blade 10U is subjected to bending moments from the pressure tube _{20 IU} receives a bending moment from the pressure tube _{20 OL.} Accordingly, the flap 410 is deformed downward in accordance with the applied pressure. Further, since the magnitude of the bending moment is about twice that of the flap 110 of the first embodiment, the downward deformation amount is larger than that of the flap 110 of the first embodiment.

Thus, keep in pressurizing the pressure tube _{20 OU, 20 IU, 20 IL} , 20 OL in the initial state, by reducing the pressure tube _{20 IU} and the pressure tube _{20 OL,} the flap 410 is deformed upward, Alternatively, by reducing the pressure tube _{20 OU} and the pressure tube _{20 IL,} flap 410 can be deformed downward.

Also, keep in the pressure was reduced tube _{20 OU, 20 IU, 20 IL} , 20 OL in the initial state, by pressurizing the pressure tube _{20 IU} and the pressure tube _{20 OL,} the flap 410 is deformed downward, or, by pressurizing the pressure tube _{20 OU} and the pressure tube _{20 IL,} flap 410 may be deformed upward.

In general, the deformation of the flap 410 is caused by the internal pressure of the pressure tubes 20 _OU , 20 _IU , 20 _IL , and 20 _OL , the thickness of the material, the outer diameter, the elastic modulus, the thickness of the upper flexible wing 10U, the lower flexible wing 10L, and the like. Since it depends on the elastic modulus, it can be deformed to a desired shape by appropriately designing or controlling these factors.

The upper flexible wing 10U and the lower flexible wing 10L may be formed of the wing composite material 50 shown in FIG.
The wing composite material 50 binds the CFRP rod 1 formed by CFRP so as to have anisotropy in the axial direction, the elastic member 2 filled in the gap between the CFRP rods 1, and the CFRP rod 1. A knitting yarn 3 is provided. The elastic member 2 is, for example, silicon rubber, and the knitting yarn 3 is, for example, a yarn obtained by twisting an aramid fiber.

  Since the CFRP rod 1 is braided and tied in the form of a braid with the knitting yarn 3, peeling between the CFRP rod 1 and the elastic member 2 is preferably prevented, and the tear strength of the upper flexible wing 10U and the lower flexible wing 10L is reduced. improves.

The upper flexible wing 10U and the lower flexible wing 10L may be formed of the wing composite material 51 shown in FIG.
The wing composite material 51 includes a CFRP rod 1 formed by CFRP so as to have anisotropy in the axial direction, an elastic member 2 filled in a gap between the CFRP rods 1 and the CFRP rod 1 in a comb shape. A knitting yarn 3 to be secured and a knitting stop yarn 4 to join the knitting yarn 3 are provided. The elastic member 2 is, for example, silicon rubber, the knitting yarn 3 is, for example, a yarn in which carbon fibers are twisted, and the knitting yarn 4 is, for example, a yarn in which aramid fibers are twisted.

  Since the CFRP rod 1 is knitted and tied up with a knitting yarn 3 and the CFRP rod 1 is formed with a plurality of layers and the layers are joined by a knitting yarn 4, the separation between the CFRP rod 1 and the elastic member 2 can be prevented. It is suitably prevented and the tear strength of the upper flexible wing 10U and the lower flexible wing 10L is further improved.

The upper flexible wing 10U and the lower flexible wing 10L may be formed of the wing composite material 52 shown in FIG.
The wing composite material 52 includes a CFRP rod 1 formed of CFRP, an elastic member 2 filled in a gap between the CFRP rods 1, and an interlock yarn 5 that forms an interlock three-dimensional fabric together with the CFRP rod 1. It comprises. The elastic member 2 is, for example, silicon rubber, and the interlock yarn 5 is, for example, a carbon fiber yarn.

  Since the CFRP rod 1 and the interlock yarn 5 are knitted and secured in an interlock three-dimensional woven shape, the CFRP rod 1 and the elastic member 2 are preferably prevented from being peeled off. Thereby, in addition to the high flexibility with respect to a wing wing direction and the high airfoil maintenance capability with respect to the wing span direction, it has high tear strength.

FIG. 12 is an explanatory cross-sectional view of a main part showing an inflatable variable blade 500 according to a sixth embodiment of the present invention.
This inflatable variable blade 500 is formed into the same flat plate as the CFRP upper corrugated plate 1U which is formed into a wave shape by CFRP as a reinforcing material so that the maximum anisotropy is orthogonal to the wave direction. An upper flexible wing 11U composed of a CFRP upper thin plate 2U as an outer plate, and a CFRP lower corrugated plate 1L formed in the same wave shape and used as a blade inner plate, and a CFRP upper thin plate 2L formed into the same flat plate as a blade outer plate. And a pressure tube 20 as blade deformation means for deforming the upper flexible blade 11U and the lower flexible blade 11L with respect to the blade hook direction. In addition, the pressure tube 20 includes a pressure tube 20 _VU disposed in a crest portion on the inner surface of the CFRP upper corrugated plate 1U, a pressure tube 20 _PU disposed on the summit portion, and a CFRP lower corrugated plate 1L. It consists of a pressure tube 20 _VL disposed at the inner and outer peak portions and a pressure tube 20 _PL disposed at the summit portion.

  In the inflatable variable blades 100, 200, 300, and 400 according to the first to fifth embodiments, the upper flexible member is made of a composite material in which an elastic member is filled in a gap between the CFRP rods 1 that are formed so as to have anisotropy in the axial direction. Whereas the blade structure of the blade 10U and the lower flexible blade 10L is formed, the inflatable variable blade 500 is a so-called CFRP molded with CFRP so as to have anisotropy in a direction orthogonal to the wave direction. A wing structure of the upper flexible wing 11U and the lower flexible wing 11L is formed by the corrugated CFRP upper corrugated plate 1U and the CFRP lower corrugated plate 1L. The outer surfaces of the CFRP upper corrugated plate 1U and the CFRP lower corrugated plate 1L are smooth on the CFRP upper thin plate 2U so that the CFRP upper corrugated plate 1U and the CFRP lower corrugated plate 1L do not resist the air flow flowing on the outer surface. And the CFRP lower thin plate 2L.

  The CFRP upper corrugated plate 1U and the CFRP lower corrugated plate 1L are oriented so that the direction orthogonal to the wave direction coincides with the wing span direction. Therefore, the inflatable variable wing 500 has high rigidity in the blade width direction, but has high flexibility in the blade wing direction. As described above, the inflatable variable blade 500 achieves both high airfoil holding ability in the blade width direction and high flexibility in the blade hook direction, which have been in a contradictory relationship.

In the inflatable variable wing 500, the upper flexible wing 11U and the lower flexible wing 11L are controlled by the pressure tubes 20 _VU , 20 _PU , 20 _VL , and 20 _PL , so that the shape controllability is excellent and the upper flexible wing 500 is also flexible. Since many of these pressure tubes 20 _VU , 20 _PU , 20 _VL , and 20 _PL handle the bending moment acting on the blade 11U and the lower flexible blade 11L, the load on each pressure tube is reduced, and further problems such as cracks occur. When this occurs, the bending moment that the other pressure tubes are insufficient can be compensated suitably, and the robustness is further improved.

FIG. 13 is a partial cross-sectional view illustrating an example of shape control of the inflatable variable blade 500 according to the sixth embodiment. For convenience of illustration, only the upper flexible wing 11U is shown.
FIG. 13A shows a state in which no pressure is applied to the pressure tubes 20 _VU and 20 _PU . In this case, the CFRP upper corrugated plate 1U and the CFRP upper thin plate 2U do not receive a bending moment from each pressure tube, and thus maintain a neutral state.
FIG. 13B shows a state where the pressure tube 20 _PU disposed at the peak of the CFRP upper corrugated plate 1U is pressurized to expand its volume. In this case, the pressure tube 20 _{PU tends} to be circular and applies a bending moment to the CFRP upper corrugated plate 1U. By the way, since the CFRP upper corrugated plate 1U and the CFRP upper thin plate 2U have high flexibility with respect to the blade wing direction, the CFRP upper corrugated plate 1U and the CFRP upper thin plate 2U correspond to the pressure applied to the pressure tube 20 _PU. Deforms downward.
(C) of FIG. 13 shows a state in which the volume is expanded by pressurizing the pressure tube 20 _VU disposed in the peaks and valleys of the CFRP upper corrugated plate 1U. In this case, the pressure tube 20 _VU is going to be circular, and the CFRP upper corrugated plate 1U is going to be expanded with respect to the blade direction. Since the CFRP upper corrugated plate 1U and the CFRP upper thin plate 2U have high flexibility with respect to the blade wing direction, the CFRP upper corrugated plate 1U and the CFRP upper thin plate 2U move upward according to the pressure applied to the pressure tube _20VU. Deform.

Thus, in the initial state, the pressure tube 20 _VU and the pressure tube 20 _PU are depressurized and the pressure tube 20 _VU is pressurized, whereby the inflatable variable blade 500 is deformed upward, or the pressure tube 20 _PU is By applying pressure, the inflatable variable blade 500 can be deformed downward.

Further, in the initial state, the pressure tube 20 _VU and the pressure tube 20 _PU are pressurized and the pressure tube 20 _VU is depressurized, whereby the inflatable variable blade 500 is deformed downward, or the pressure tube 20 _PU is depressurized. Thus, the inflatable variable blade 500 can be deformed upward.

Generally, the deformation of the inflatable variable blade 500 is caused by the internal pressure of the pressure tubes 20 _VU and 20 _PU , the thickness of the material, the outer diameter, the elastic modulus, and the thickness and elastic modulus of the CFRP upper corrugated plate 1U and the CFRP lower corrugated plate 1L. Therefore, these factors can be transformed into a desired shape by appropriately designing or controlling these factors.

FIG. 14 is a cross-sectional view of a principal part showing an inflatable variable blade 600 according to the seventh embodiment.
This inflatable variable wing 600 is formed into a corrugated shape by CFRP as a reinforcing material so that the maximum anisotropy is orthogonal to the wave direction, and is formed into the same flat plate as the CFRP upper corrugated plate 1U as the blade inner plate. An upper flexible wing 11U composed of a CFRP upper thin plate 2U as an outer plate, and a CFRP upper thin plate 2L as a blade outer plate formed into the same wave and formed into the same plate as a CFRP lower corrugated plate 1L as an inner plate. A lower flexible wing 11L (not shown), and a pressure tube 20 as wing deformation means for deforming the upper flexible wing 11U and the lower flexible wing 11L with respect to the blade hook direction. Yes. In addition, the pressure tube 20 includes a pressure tube 20 _VU disposed in a crest on the inner surface of the CFRP upper corrugated plate 1U, a pressure tube 20 _VOU disposed in a crest on the outer surface, and a CFRP lower corrugated plate. A pressure tube 20 _VL (not shown) disposed in a mountain valley portion on the inner surface of 1 L and a pressure tube 20 _VOL (not shown) disposed in a mountain valley portion on the outer surface are configured.

FIG. 14A shows a state in which no pressure is applied to the pressure tubes 20 _VU and 20 _VOU . In this case, since the CFRP upper corrugated plate 1U and the CFRP upper thin plate 2U are not subjected to any action from each pressure tube, they remain neutral.
On the other hand, (b) of FIG. 14 shows a state where the pressure tube 20 _VOU disposed in the crest portion on the outer surface of the CFRP upper corrugated plate 1U is pressurized and the volume is expanded. In this case, the pressure tube 20 _VOU is going to be circular and tries to expand the CFRP upper corrugated plate 1U with respect to the blade direction. By the way, since the CFRP upper corrugated plate 1U and the CFRP upper thin plate 2U have high flexibility with respect to the blade wing direction, the CFRP upper corrugated plate 1U and the CFRP upper thin plate 2U correspond to the pressure applied to the pressure tube 20 _VOU. Deforms downward.
On the other hand, FIG. 14C shows a state in which the pressure tube 20 _VU disposed in the crests and valleys on the inner surface of the CFRP upper corrugated plate 1U is pressurized to expand the volume. In this case, the pressure tube 20 _VU is going to be circular, and the CFRP upper corrugated plate 1U is going to be expanded with respect to the blade direction. Since the CFRP upper corrugated plate 1U and the CFRP upper thin plate 2U have high flexibility with respect to the blade wing direction, the CFRP upper corrugated plate 1U and the CFRP upper thin plate 2U move upward according to the pressure applied to the pressure tube _20VU. Deform.

Thus, in the initial state, the pressure tube 20 _VU and the pressure tube 20 _VOU are depressurized and the pressure tube 20 _VOU is pressurized, whereby the inflatable variable vane 500 is deformed downward, or the pressure tube 20 _VU is By applying pressure, the inflatable variable blade 600 can be deformed upward.

Further, in the initial state, the pressure tube 20 _VU and the pressure tube 20 _VOU are pressurized, and the pressure tube 20 _VOU is depressurized, whereby the inflatable variable vane 500 is deformed upward, or the pressure tube 20 _VU is depressurized. Thus, the inflatable variable wing 600 can be deformed downward.

In general, the deformation of the inflatable variable blade 600 is caused by the internal pressure of the pressure tubes 20 _VU and 20 _VOU , the thickness of the material, the outer diameter, the elastic modulus, and the thickness and elastic modulus of the CFRP upper corrugated plate 1U and the CFRP lower corrugated plate 1L. Therefore, these factors can be transformed into a desired shape by appropriately designing or controlling these factors.

The upper flexible wing 11U and the upper flexible wing 11L may be formed of the wing composite material 53 shown in FIG.
The wing composite material 53 includes a CFRP corrugated sheet 6 formed into a wave shape with CFRP, and an elastic member 2 that fills a concave portion on the surface and forms a smooth surface. The elastic member 2 is, for example, silicon rubber. Further, the anisotropic direction of the CFRP corrugated plate 6 is parallel to the blade width direction of the blade.

  By the elastic action of the CFRP corrugated plate 6 and the elastic member 2, the flexibility in the blade hook direction is improved and the compressive strength is also improved. In particular, since the compressive strength is high, the movable range of the upper flexible wing 11U and the upper flexible wing 11L is increased.

The upper flexible wing 11U and the upper flexible wing 11L may be formed of the wing composite material 54 shown in FIG.
The wing composite material 54 includes a CFRP corrugated sheet 6 formed into a wave shape with CFRP, and the elastic member 2 that forms a smooth surface while forming cavities in concave portions on the front surface and the back surface. The elastic member 2 is, for example, synthetic rubber. Further, the anisotropic direction of the CFRP corrugated plate 6 is parallel to the blade width direction of the blade.

  Due to the elastic action of the CFRP corrugated plate 6 and the elastic member 2 and the compressibility of the air contained therein, the flexibility in the direction of the blades is improved and the compressive strength is also improved. In particular, since the compressive strength is high, the movable range of the upper flexible wing 11U and the upper flexible wing 11L is increased.

The upper flexible wing 11U and the upper flexible wing 11L may be formed of the wing composite material 55 shown in FIG.
The wing composite material 55 includes a CFRP corrugated plate 6 formed in a corrugated shape with CFRP, a CFRP rod 1 disposed in a concave portion on the front surface and the back surface, and an elastic member 2 filled in the concave portion on the surface. It is configured. The elastic member 2 is, for example, silicon rubber. The anisotropic direction of the CFRP corrugated plate 6 and the CFRP rod 1 is parallel to the blade width direction of the blade.

  Due to the elastic action of the CFRP corrugated plate 6 and the elastic member 2, the flexibility with respect to the blade hook direction is improved.

The upper flexible wing 11U and the upper flexible wing 11L may be formed of the wing composite material 56 shown in FIG.
This wing composite material 56 has a CFRP corrugated sheet 6 formed in a corrugated shape with CFRP, a CFRP rod 1 disposed in the recesses on the front and back surfaces, and a smooth surface with a cavity formed in the recesses on the front and back surfaces. And an elastic member 2 to be formed. The elastic member 2 is, for example, synthetic rubber. The anisotropic direction of the CFRP corrugated plate 6 and the CFRP rod 1 is parallel to the blade width direction of the blade.

  Due to the elastic action of the CFRP corrugated plate 6 and the elastic member 8 and the compressibility of the air contained therein, the flexibility with respect to the direction of the blades is further improved and the compressive strength is also improved.

The upper flexible wing 11U and the upper flexible wing 11L may be formed of the wing composite material 57 shown in FIG.
The wing composite material 57 includes a CFRP corrugated sheet 6 formed into a corrugated shape with CFRP, a CFRP rod 1 disposed in a concave portion on the front surface and the back surface of the CFRP corrugated sheet 6, and a CFRP thin plate 7 that forms a smooth surface. It comprises.

  Since the anisotropic directions of the CFRP corrugated plate 6, the CFRP rod 1 and the CFRP thin plate 7 are parallel to the blade span direction, the rigidity in the span direction is further improved. In addition, the elasticity of the CFRP corrugated sheet improves the flexibility in the blade wing direction and also improves the compressive strength.

  According to the inflatable variable wings 100, 200, 300, 400, 500, and 600, the high load-bearing capacity in the blade width direction, the high flexibility in the blade wing direction, and the high variability that were the problems of the conventional inflatable blades. Can be achieved at the same time. In particular, various deformations such as free bending deformation in the wing wing direction and free torsional deformation in the wing span direction are possible, and as a result, flight performance and flight characteristics are greatly improved. Furthermore, since the pressure tube having contraction functions not as a function of a blade structure for handling a load but as an actuator for deforming the shape of the blade, the robustness as a variable blade is improved. Inflatable variable blades 100, 200, 300, 400, 500, and 600 are provided with a large number of pressure tubes, so even if a defect such as a crack occurs in a part, other pressure tubes are used. Since it can be suitably substituted, robustness and redundancy as an actuator are also improved. In addition, the use of the inflatable variable wings 100, 200, 300, 400, 500, and 600 in places where relatively little flight load is applied, such as aircraft flaps and control surfaces, simplifies the drive system and reduces the noise of the drive source. It will be possible to change the flight performance efficiently and contribute significantly to the environment and comfort of the aircraft.

  The flying wing of the present invention can be suitably applied to a part of an aircraft main wing or tail wing, for example, a variable wing structure such as a flap or a control surface. In addition, an engine inlet wing, a ship screw, a windmill, etc. The present invention can also be suitably applied to wings other than the aircraft.

It is a principal part cross-sectional perspective view which shows the inflatable variable wing | blade concerning Example 1 of the wing | blade for aircrafts of this invention. It is explanatory drawing which shows the structural example of a blade deformation | transformation means. It is explanatory drawing which shows the operation | movement at the time of the adhesion state of a pressure tube, and internal pressure load. It is principal part sectional drawing which shows the inflatable variable wing | blade by which the pressure tube was arrange | positioned densely along the wing wing direction. It is a principal part perspective view which shows the inflatable variable wing | blade by which the pressure tube was discretely arrange | positioned along the wing span direction. It is principal part cross-sectional explanatory drawing which shows the example applied to the flap of the inflatable variable wing | blade which concerns on Example 1. FIG. It is principal part cross-sectional explanatory drawing which shows the inflatable variable wing | blade which concerns on Example 2 of the wing for aircrafts of this invention. It is principal part cross-sectional explanatory drawing which shows the example applied to the flap of the inflatable variable wing | blade which concerns on Example 2. FIG. FIG. 6 is a cross-sectional perspective view showing a main part of a wing composite material according to a third embodiment. FIG. 6 is a cross-sectional perspective view showing a main part of a wing composite material according to a fourth embodiment. FIG. 10 is a cross-sectional perspective view showing a main part of a wing composite material according to a fifth embodiment. It is principal part cross-section explanatory drawing which shows the inflatable variable wing | blade which concerns on Example 6 of this invention. It is a fragmentary sectional view showing an example of shape control of an inflatable variable wing concerning Example 6. It is principal part sectional drawing which shows the inflatable variable wing | blade which concerns on Example 7. FIG. FIG. 10 is a cross-sectional perspective view showing a main part of a wing composite material according to an eighth embodiment. It is a principal part cross-sectional perspective view which shows the wing | blade composite material which concerns on Example 9. FIG. It is a principal part cross-sectional perspective view which shows the wing | blade composite material which concerns on Example 10. FIG. It is a principal part cross-section perspective view which shows the wing | blade composite material which concerns on Example 11. FIG. It is a principal part cross-sectional perspective view which shows the wing | blade composite material which concerns on Example 12. FIG.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 CFRP rod 2 Elastic member 3 Knitting yarn 4 Knitting stop yarn 5 Interlock yarn 100,200,300,400,500,600 Inflatable variable wing

Claims (23)

  It is made of a reinforcing material having at least one anisotropy and is filled in a gap between the plurality of long-axis objects and the plurality of long-axis objects formed by aligning the maximum anisotropy with the long axis. A flexible wing having an elastic member, and wing deformation means for changing the shape by generating stress on the flexible wing, and the long-axis object is oriented parallel or substantially parallel to the blade width direction of the wing The aircraft wing is characterized by having high rigidity in the wing span direction and high flexibility and changeability in the wing wing direction.   A blade inner plate made of a first reinforcing material having at least one anisotropy and shaped into a wave shape so that the maximum anisotropy of the anisotropy is orthogonal or substantially orthogonal to the wave direction; A flexible wing having a blade outer plate made of a second reinforcing material having two anisotropies and having a maximum anisotropy equal to the maximum anisotropy of the blade inner plate among the anisotropies; Blade deforming means for changing the shape by generating stress on the flexible blade, and the inner plate is oriented with the wave direction parallel or substantially parallel to the blade direction of the blade, and with respect to the blade width direction. A flying wing characterized by having high rigidity and high flexibility and changeability in the direction of the wing wing.   The wing deforming means is disposed on one or both surfaces of the outer surface or the inner surface of the flexible wing and has a contractibility, and pressure for individually increasing or reducing the internal pressure of the pressure tube. The wing for an aircraft according to claim 1 or 2, comprising an adjusting means.   Each of the pressure tubes is arranged loosely on one or both surfaces of the outer surface or the inner surface of the flexible blade in parallel to the blade width direction and discretely or continuously densely with respect to the blade blade direction. Item 4. The aircraft wing according to item 3.   5. The flying object according to claim 4, wherein each of the pressure tubes is arranged loosely on one surface or both surfaces of the outer surface or the inner surface of the flexible wing in a discrete or continuous manner in the wing width direction. Wings.   6. The aircraft wing according to claim 3, wherein each of the pressure tubes has the same or different at least one outer diameter.   The wing for an aircraft according to any one of claims 3 to 6, wherein each of the pressure tubes has the same rigidity or at least one of different rigidity.   The pressure tube disposed on the outer surface of the flexible wing is made of a third reinforcing material having at least one anisotropy, and the maximum anisotropy among the anisotropies is the maximum anisotropic of the long-axis object. The aircraft wing according to any one of claims 3 to 5, which is covered with a thin plate fairing having a smooth surface equal to the property.   4. The flying body according to claim 2, wherein each of the pressure tubes is disposed in a mountain valley portion or a mountain peak portion of the inner surface of the wing inner plate or an inner portion of the blade outer plate and in a mountain valley portion of the outer surface of the wing inner plate. Wings.   The aircraft wing according to claim 9, wherein the pressure tube disposed at the peak portion of the inner surface of the wing inner plate is fixed without looseness by the peak portions of the inner surface of at least two wing inner plates.   The aircraft wing according to claim 1, wherein at least one of the reinforcing material, the first reinforcing material, the second reinforcing material, and the third reinforcing material is a fiber reinforcing material.   An aircraft flap comprising the aircraft wing according to claim 1.   It is made of a reinforcing material having at least one anisotropy and is filled in a gap between the plurality of long-axis objects and the plurality of long-axis objects formed by aligning the maximum anisotropy with the long axis. A flexible wing having an elastic member and having the long-axis object oriented parallel or substantially parallel to the wing span direction of the wing, by generating stress on the flexible wing, A wing shape control method, wherein the wing shape is variably deformed with respect to a heel direction.   A blade inner plate made of a first reinforcing material having at least one anisotropy and shaped into a wave shape so that the maximum anisotropy of the anisotropy is orthogonal or substantially orthogonal to the wave direction; A blade outer plate made of a second reinforcing material having two anisotropies and having a maximum anisotropy equal to the maximum anisotropy of the blade inner plate among the anisotropies, For flexible wings oriented with the wave direction parallel or substantially parallel to the wing blade direction, the flexible wings can be varied with respect to the wing blade direction by generating stress on the flexible wings. The shape control method of the wing | blade characterized by making it deform | transform into.   Stress is generated in the flexible wing by individually increasing or reducing the internal pressure of at least one pressure tube disposed on one or both surfaces of the outer surface or the inner surface of the flexible wing and having contractility. The wing shape control method according to claim 13 or 14.   The pressure tubes are arranged on one or both surfaces of the outer surface or the inner surface of the flexible wing so as not to loosen in parallel with the blade width direction and discretely or continuously densely with respect to the blade blade direction. The blade shape control method according to claim 15, wherein the internal pressure of the tube is individually increased or decreased.   Each pressure tube is discretely or continuously densely arranged in the blade width direction, and is arranged on one or both surfaces of the outer surface or inner surface of the flexible blade without looseness, and the internal pressure of each pressure tube is individually applied. The blade shape control method according to claim 16, wherein pressure or pressure reduction is performed.   18. The blade shape control method according to claim 15, wherein the internal pressure of each pressure tube is individually increased or reduced so that each of the pressure tubes has the same or different at least one outer diameter. .   The blade shape control method according to any one of claims 15 to 18, wherein the internal pressure of each pressure tube is individually increased or reduced so that each pressure tube has the same rigidity or at least one difference in rigidity.   The pressure tube disposed on the outer surface of the flexible wing is made of a third reinforcing material having at least one anisotropy, and the maximum anisotropy is the maximum anisotropy of the long-axis object. The wing shape control method according to any one of claims 15 to 17, wherein the wing shape is covered with a thin plate fairing having a smooth surface which is equal to.   Each of the pressure tubes is disposed at a crest or a crest of the inner surface of the blade inner plate or at a crest of the outer surface of the blade inner plate inside the blade outer plate and individually pressurizes the internal pressure of each pressure tube. The blade shape control method according to claim 14 or 15, wherein the pressure is reduced.   The blade shape control method according to claim 21, wherein the pressure tube disposed on the top of the inner surface of the blade inner plate is fixed by the at least two peak portions of the inner surface of the blade inner plate without looseness.   The wing shape control method according to claim 13, 14 or 20, wherein at least one of the reinforcing material, the first reinforcing material, the second reinforcing material, and the third reinforcing material is a fiber reinforcing material.

Images