JP6926543B2 - Morphing wings and aircraft - Google Patents

Description

The present invention relates to morphing wings and aircraft.

A morphing blade that can change the airfoil (cross-sectional shape of the blade) to an arbitrary shape is known (see Patent Document 1). In Patent Document 1, the airfoil shape is changed to an arbitrary shape by using a link mechanism.

Japanese Unexamined Patent Publication No. 2015-214328

By the way, in the morphing blade disclosed in Patent Document 1, since the airfoil shape is changed by using the link mechanism, the structure is complicated, and there is a possibility that measures for preventing the link mechanism from sticking are required.

An object of the present invention is to provide a morphing wing and an aircraft whose airfoil can be changed with a simple structure.

The morphing blade of the first aspect of the present invention covers the upper surface of the blade body and the blade body, holds the liquid in a liquid-tight state in a closed space formed between the blade body, and is inside the closed space. It is provided with an elastic outer skin in which the amount of swelling to the outside of the wing body changes according to the amount of the liquid.

In the morphing blade of the first aspect, the amount of swelling (bulging deformation amount) of the elastic outer skin to the outside of the wing body changes according to the amount of liquid in the enclosed space (hereinafter, appropriately referred to as "liquid amount"). However, the wing shape changes according to the amount of bulging deformation of the elastic outer skin. As described above, in the morphing blade, the airfoil can be changed by a simple configuration in which the upper surface of the blade body is covered with the elastic outer skin to hold the liquid in the closed space in a liquid-tight state.

The morphing wing of the second aspect of the present invention further comprises an adjusting means for adjusting the amount of the liquid in the enclosed space in the morphing wing of the first aspect.

In the morphing blade of the second aspect, since the amount of liquid in the closed space is adjusted by the adjusting means, the airfoil can be changed even during flight as compared with the configuration in which the amount of liquid in the closed space is manually adjusted, for example. can.

The morphing wing according to the third aspect of the present invention is the morphing wing according to the second aspect, wherein the adjusting means includes a storage portion for the liquid, a feed pump for sending the liquid from the storage portion to the closed space, and the closed space. A return pump for returning the liquid to the storage unit is provided.

In the morphing blade of the third aspect, when the liquid is sent from the storage portion to the closed space by the feed pump, the elastic outer skin swells (swells and deforms). On the other hand, when the liquid is returned from the closed space to the reservoir by the return pump, the elastic outer skin contracts (contracts and deforms). As described above, in the morphing blade, the elastic outer skin can be expanded (expanded) and contracted with a simple configuration using a feed pump and a return pump.

The morphing wing of the fourth aspect of the present invention is the morphing wing of the third aspect, wherein the adjusting means drives a pressure sensor for detecting the pressure of the liquid in the enclosed space, and the feed pump and the return pump. A control device for controlling and adjusting the amount of the liquid in the enclosed space according to the pressure information of the liquid sent from the pressure sensor is further provided.

In the morphing blade of the fourth aspect, the control device controls the drive of the feed pump and the return pump according to the pressure information of the liquid sent from the pressure sensor, and adjusts the amount of the liquid in the enclosed space. Therefore, in the morphing blade, the amount of liquid in the closed space is automatically adjusted by the control device.

The morphing wing according to the fifth aspect of the present invention is the morphing wing according to any one of the first to fourth aspects, wherein the elastic outer skin covers the front upper surface of the wing body.

In the morphing blade of the fifth aspect, the elastic outer skin covers the upper surface of the front part of the blade body in which the pressure distribution on the surface of the blade changes significantly during flight. Therefore, a high lift-resilience ratio can be obtained even with a small amount of swelling deformation.

The morphing blade of the sixth aspect of the present invention is the morphing blade of any one of the first to fifth aspects, in which the liquid is impregnated in the enclosed space and follows the bulging deformation of the elastic outer skin. A porous body is arranged.

In the morphing wing of the sixth aspect, since the porous body impregnated with the liquid and following the bulging deformation of the elastic outer skin is arranged in the closed space, for example, the porous body is not arranged in the closed space. Compared with, the rigidity is improved.

The morphing wing according to the seventh aspect of the present invention is the morphing wing according to any one of the first to sixth aspects, in which the portion of the wing body forming the closed space is protected against the liquid. It is covered with a film.

In the morphing blade of the seventh aspect, since the portion forming the closed space of the blade body is covered with a protective film having corrosion resistance against the liquid, it is possible to suppress the defect of the blade body caused by the corrosion by the liquid.

The aircraft of the eighth aspect of the present invention includes a fuselage portion and a morphing wing according to claims 1 to 7 attached to the fuselage portion.

In the aircraft of the eighth aspect, a problem is less likely to occur when changing the airfoil, as compared with, for example, a configuration in which a morphing wing that changes the airfoil with a complicated structure is attached.

As described above, the present invention can provide a morphing wing and an aircraft whose airfoil can be changed with a simple structure.

It is a perspective view of the morphing wing which concerns on one Embodiment of this invention. It is a perspective view which shows the internal structure of the morphing blade of FIG. It is sectional drawing which shows the 1st airfoil of the morphing blade of FIG. It is an enlarged view of the part pointed out by the arrow 4 of FIG. It is sectional drawing which shows the 2nd airfoil of the morphing blade of FIG. It is an enlarged view of the part pointed out by the arrow 6 of FIG. It is sectional drawing which shows the 3rd airfoil of the morphing blade of FIG. It is an enlarged view of the part pointed out by the arrow 8 of FIG. It is a top view of the aircraft using the morphing wing of FIG. It is sectional drawing which shows the pressure distribution of the blade surface of the morphing blade in the 1st airfoil of FIG. It is sectional drawing which shows the pressure distribution of the blade surface when the angle of attack of the morphing blade of FIG. 10 is raised. It is sectional drawing in the 2nd airfoil of the morphing blade which concerns on other embodiment of this invention. It is sectional drawing in the 3rd airfoil of the morphing blade shown in FIG. 12A. It is sectional drawing which shows the 1st airfoil type | 3rd airfoil type of the morphing blade of the Example of this invention. It is a graph which shows the relationship between the angle of attack and the lift-drag ratio in the 1st to 3rd airfoils of the morphing airfoil of the Example. It is a graph which shows the relationship between the angle of attack and lift in the 1st to 3rd airfoils of the morphing airfoil of an Example.

Hereinafter, the morphing wing and the aircraft according to the embodiment of the present invention will be described.

<Aircraft 100>
First, an aircraft 100 in which the morphing wing 20 according to the present embodiment is used as a main wing will be described with reference to FIG.

The aircraft 100 includes a fuselage portion 102, a morphing wing 20 as a main wing attached to the fuselage portion 102, and a horizontal stabilizer 104 and a vertical stabilizer 106 provided behind the fuselage portion 102. Further, the aircraft 100 further includes a propulsion device 108 for obtaining the propulsive force of the aircraft 100 under the morphing wing 20.

The aircraft 100 of the present embodiment is provided with a cabin (not shown) on the fuselage portion 102 so that a plurality of crew members can board the aircraft 100. The present invention is not limited to the above configuration. For example, a luggage compartment may be provided in the body portion 102 so that the cargo can be loaded. Further, the body portion 102 does not have to be provided with a guest room or a luggage compartment.

<Morphing wings 20>
As shown in FIGS. 1 and 2, the morphing blade 20 includes a blade body 22, a spar 24, and a rib 26.

(Wing body 22)
The wing body 22 forms the outer shell of the morphing wing 20. The wing body 22 is made of a light metal material, for example, an aluminum alloy such as duralumin. The present invention is not limited to this configuration, and the wing body 22 may be formed of a composite material, for example, a carbon fiber composite material such as carbon fiber reinforced plastic (CFRP), or a part of the wing body 22 may be composited. It may be made of a material and the other parts may be made of a light metal material.

The spar 24 is provided in the blade body 22 and extends in the blade length direction. The spar 24 is made of a light metal material, for example, an aluminum alloy such as duralumin. The present invention is not limited to this configuration, and the spar 24 may be formed of a composite material, for example, a carbon fiber composite material such as carbon fiber reinforced plastic (CFRP), or a part of the spar 24 may be made of the composite material. It may be formed and the other portion may be formed of a light metal material. The flexural rigidity and torsional rigidity of the morphing blade 20 are ensured by the spar 24. The blade length direction referred to here refers to the length direction from the base to the tip of the morphing blade 20.

A plurality of ribs 26 are provided in the blade body 22 at intervals in the blade length direction, and extend in the chord direction. The rib 26 is made of a light metal material, for example, an aluminum alloy such as duralumin. The present invention is not limited to this configuration, and the rib 26 may be formed of a composite material, for example, a carbon fiber composite material such as carbon fiber reinforced plastic (CFRP), or a part of the rib 26 may be made of the composite material. It may be formed and the other portion may be formed of a light metal material. The rib 26 holds the internal space of the wing body 22. The chord direction referred to here is the leading edge (leading edge 22A of the wing body 22) and the trailing edge (trailing edge 22B of the wing body 22) of the morphing wing 20 in a cross section orthogonal to the blade length direction of the morphing wing 20. ) And the straight line (so-called chord line) X.

(Elastic outer skin 28)
As shown in FIGS. 1, 3, 5, and 7, the morphing blade 20 covers the upper surface 22C of the blade body 22 and liquids L in a closed space 30 formed between the morphing blade 20 and the blade body 22. It further comprises an elastic hull 28 that holds it tightly. The upper surface 22C of the blade body 22 refers to the outer surface (surface) of the blade body 22 located above the straight line X of the morphing blade 20 in the ground stationary state. The angle of attack α of the morphing blade 20 referred to below is the angle formed by the uniform flow and the straight line X with respect to the morphing blade 20 in flight.

The elastic outer skin 28 is a sheet-like member that can be elastically deformed, and has a lower rigidity than the blade main body 22. Therefore, the amount of swelling to the outside of the blade body 22 (the amount of swelling deformation) changes according to the amount of liquid L into the closed space 30 (hereinafter, appropriately referred to as "liquid amount V"). ing. The airfoil of the morphing blade 20 changes according to the amount of bulging deformation of the elastic outer skin 28.

Further, the elastic outer skin 28 covers at least the upper surface of the front portion of the wing body 22. The upper surface of the front portion of the wing body 22 referred to here is the length from the leading edge 22A to the chord length (the length from the leading edge 22A to the trailing edge 22B along the chord direction (see FIG. 3)) of the upper surface 22C. ) It points to the half position of XL. As shown in FIG. 10, the pressure acting on the blade surface (outer surface) of the morphing blade 20 during flight increases at the portion corresponding to the front upper surface of the blade body 22. Therefore, by providing the elastic outer skin 28 on the upper surface of the front portion of the wing body 22, it is possible to obtain a high lift-drag ratio while suppressing the amount of bulging deformation of the elastic outer skin 28.

In the elastic outer skin 28, the peripheral edge portion 28A (see FIG. 1) is fixed to the blade body 22 by an adhesive or welding, and a closed space 30 is formed between the elastic outer skin 28 and the blade body 22. The liquid L is held in the closed space 30.

As the material of the elastic outer skin 28, for example, a polymer material such as an elastomer, a rubber metal, a superelastic alloy, or a combination thereof may be used.

Further, as shown in FIGS. 3, 5, and 7, the morphing blade 20 further includes an adjusting device 32 for adjusting the liquid amount V in the closed space 30.

(Adjuster 32)
The adjusting device 32 includes a storage unit 34 for storing the liquid L, a feed pump 36 for sending the liquid L from the storage unit 34 to the closed space 30, and a return pump 36 for returning the liquid from the closed space 30 to the storage unit 34. ing.

The storage unit 34 stores the liquid L in a state where the dissolved gas is removed from the liquid L. As the liquid L, it is preferable to use an oil having low volatility. Examples of the oil having low volatility include a fluorine-based oil having high cold temperature performance (low temperature fluidity).

The feed pump 36 is provided in the middle of the feed flow path 40 extending from the storage unit 34 to the closed space 30. The drive of the feed pump 36 is controlled by a control device 46 described later.

The return pump 38 is provided in the middle of the return flow path 42 extending from the storage unit 34 to the closed space 30. The drive of the return pump 38 is controlled by a control device 46 described later.

Further, the adjusting device 32 has a pressure sensor 44 that detects the pressure of the liquid L in the closed space 30 (hereinafter, appropriately referred to as “hydraulic pressure”) and pressure information of the liquid L sent from the pressure sensor 44 (hereinafter, referred to as “hydraulic pressure”). A control device 46 that controls the drive of the feed pump 36 and the return pump 38 and adjusts the amount V of the liquid in the closed space 30 according to the appropriate “hydraulic pressure information”) is further provided.

The pressure sensor 44 is provided in the detection flow path 48 extending from the closed space 30.

The control device 46 is provided with an airfoil corresponding to each bulging deformation amount (deformation shape) of the elastic outer skin 28. Specifically, in the control device 46, the liquid amount V in the closed space 30 and the hydraulic pressure PLS in the ground stationary state are set for each airfoil. In the present embodiment, the elastic outer skin 28 and the wing body 22 shown in FIG. 3 are in close contact with each other via a liquid L film (oil film in the present embodiment) of the first wing type (liquid amount V1, hydraulic pressure PLS1). ), And the second wing type (liquid volume V2, hydraulic pressure PLS2) in which the liquid L is injected into the closed space 30 shown in FIG. 5 and the elastic outer skin 28 is expanded, and the second wing type shown in FIG. A third blade type (liquid volume V3, hydraulic pressure PLS3) in which the elastic outer skin 28 is further expanded is set in the control device 46. Further, the morphing blade 20 is preferably designed so that the first airfoil has better stall characteristics than the other airfoils.

The control device 46 compares the hydraulic pressure PLF in the closed space 30 during flight with the theoretical hydraulic pressure PREF calculated in advance, and if the hydraulic pressure PLF is larger than the theoretical hydraulic pressure PREF, there is a possibility of stall. And change the airfoil to another airfoil with good stall characteristics. For example, when the morphing airfoil 20 is a second airfoil or a third airfoil, the airfoil is changed to the first airfoil having good stall characteristics. Specifically, the control device 46 adjusts the amount V of the liquid in the closed space 30 by controlling the drive of the feed pump 36 or the return pump 38, and adjusts the amount of bulging deformation of the elastic outer skin 28 to form an airfoil. To the desired airfoil (for example, an airfoil with good stall characteristics).
As shown in FIGS. 10 and 11, the theoretical hydraulic pressure PREF referred to here is an average pressure (negative pressure) acting on the elastic outer skin 28 calculated in advance from the hydraulic pressure PLS, the angle of attack during flight, and the airflow velocity. ) It is obtained by the sum with PA (see the range of PA in FIG. 10). That is, it is obtained by theoretical hydraulic pressure PREF = hydraulic pressure PLS + average pressure PA.
Further, when the morphing blade 20 is close to the stalled state, the absolute value of the average pressure (negative pressure) acting on the elastic outer skin 28 | PAstal | (see the two-dot chain line PAstal in FIG. 11) is in a normal state (not stalled). The average pressure in the state) is lower than the average pressure | PA | (see the alternate long and short dash line PA in FIG. 11) (| PAstal | <| PA |). Therefore, the hydraulic pressure PLFstal in a state close to stall becomes a value higher than the theoretical hydraulic pressure PREF. Therefore, when the hydraulic pressure PLF is larger than the theoretical hydraulic pressure PREF, the control device 46 determines that the morphing blade 20 may stall.

Since the hydraulic pressure PLF during flight is always higher than the saturated vapor pressure PV of the liquid L, gas (vapor) does not intervene in the liquid L in all flight states.

Further, in the present embodiment, the portion of the blade body 22 forming the closed space 30 is covered with a protective film 50 (see FIGS. 4, 6, and 8) having corrosion resistance to the liquid L. When fluorine-based oil is used as the liquid L, it is preferable to use fluororubber used as a sealing material or the like as the protective film 50.

Next, the action and effect of this embodiment will be described.
In the morphing blade 20 of the present embodiment, the amount of bulge (bulge deformation amount) of the elastic outer skin 28 to the outside of the wing body 22 changes according to the amount V of the liquid in the closed space 30, and the elastic outer skin 28 is bulged and deformed. The airfoil changes according to the amount. As described above, in the morphing blade 20, the airfoil can be changed by a simple configuration in which the upper surface 22C of the blade body 22 is covered with the elastic outer skin 28 to hold the liquid L in the closed space 30 in a liquidtight state.

In particular, in the morphing blade 20, since the liquid L which is an incompressible fluid is held in the closed space 30, for example, as compared with the configuration where the gas which is a compressible fluid is held in the closed space 30, it is against an external force. It is easy to attenuate and high flight performance can be obtained stably.

Further, since the morphing blade 20 has the same configuration (blade body 22, spar 24 and rib 26) as a conventionally known airfoil whose airfoil does not change, it is possible to secure the same strength as a blade whose airfoil does not change. Furthermore, good flight performance and flight characteristics can be obtained by changing the airfoil.

Further, in the morphing blade 20, since the liquid amount V in the closed space 30 is adjusted by the adjusting device 32, for example, as compared with the configuration in which the liquid amount V in the closed space 30 is manually adjusted, the airfoil is formed even during flight. Can be changed.

Further, in the morphing blade 20, when the liquid L is sent from the storage portion 34 to the closed space 30 by the feed pump 36, the elastic outer skin 28 swells (swells and deforms). On the other hand, when the liquid L is returned from the closed space 30 to the storage portion 34 by the return pump 38, the elastic outer skin 28 contracts (contracts and deforms). As described above, in the morphing blade 20, the elastic outer skin 28 can be expanded (expanded) and contracted with a simple configuration using the feed pump 36 and the return pump 38.

Further, in the morphing blade 20, the control device 46 controls the drive of the feed pump 36 and the return pump 38 according to the hydraulic pressure information sent from the pressure sensor 44, and adjusts the liquid amount V in the closed space 30. Therefore, in the morphing blade 20, the airfoil can be automatically changed by the control device 46. Further, the control device 46 can change the airfoil of the morphing blade 20 by simple control for controlling the drive of the feed pump 36 and the return pump 38.

In the morphing wing 20, the elastic outer skin 28 covers the front upper surface of the wing body 22 whose pressure distribution on the wing surface changes significantly during flight. Therefore, for example, the elastic outer skin 28 does not cover the front upper surface of the wing body 22. In comparison, a high lift-resilience ratio can be obtained even with a small amount of swelling deformation. In FIG. 10, the pressure distribution on the wing surface when flying with the first airfoil described later is shown by the alternate long and short dash line P.

Since the portion of the morphing blade 20 forming the closed space 30 of the blade body 22 is covered with a protective film 50 having corrosion resistance to the liquid L, the morphing blade 20 has a defect of the blade body 22 caused by corrosion by the liquid L. Can be suppressed.

Since the morphing wing 20 is attached to the fuselage portion 102 of the aircraft 100, a problem is less likely to occur when changing the airfoil, as compared with a configuration in which a morphing wing that changes the airfoil with a complicated structure is attached.

In the above-described embodiment, only the liquid L is interposed in the closed space 30, but the present invention is not limited to this configuration, and for example, as shown in FIGS. 12A and 12B, the inside of the closed space 30 is formed. A porous body 52 that is impregnated with the liquid L and follows the bulging deformation of the elastic outer skin 28 may be arranged. As the porous body 52, a porous body having a high porosity that expands following the swelling deformation of the elastic outer skin 28 and shrinks following the contraction deformation, for example, a sponge-like member such as a sponge is preferable. When such a porous body 52 is arranged in the closed space 30 (preferably the entire area in the closed space 30), the amount of expansion of the porous body changes according to the amount of expansion and deformation of the elastic outer skin 28. Therefore, for example, The flexural rigidity and the torsional rigidity of the morphing blade 20 are improved as compared with the configuration in which the porous body 52 is not arranged in the closed space 30. Further, when the porous body 52 is arranged in the entire area of the closed space 30, it is possible to prevent the liquid L in the closed space 30 from being squeezed from one side during swirling or the like.

In the above-described embodiment, the oil used in the morphing blade 20 is provided as a dedicated product, but the present invention is not limited to this configuration. For example, the oil used in the morphing wing 20 may be used in combination with the oil used in other parts of the aircraft 100. Further, in the above-described embodiment, the adjusting device 32 used in the morphing blade 20 is provided as a dedicated product, but the present invention is not limited to this configuration. For example, the adjusting device may be configured to use part or all of the existing hydraulic system in the aircraft (for example, the hydraulic system for operating the flaps and ailerons). By using the existing hydraulic system in this way, for example, the number of pumps can be reduced and the configuration of the adjusting device can be simplified.

Further, in the above-described embodiment, the morphing wing 20 in the present invention is applied to the main wing of the aircraft 100, but the present invention is not limited to this configuration. For example, the morphing wing in the present invention may be applied to the horizontal stabilizer 104, or the morphing wing in the present invention may be applied to the main wing and the horizontal stabilizer of the aircraft 100, respectively.

Further, in the above-described embodiment, the propulsion device 108 is provided in the lower part of the morphing blade 20, but the present invention is not limited to this configuration. The propulsion device 108 may be provided on the nose, or may be provided on the nose and the lower part of the morphing wing 20.

Furthermore, in the above-described embodiment, the morphing wing 20 of the present invention is applied to an aircraft provided with a propulsion device, but the present invention is not limited to this configuration. For example, the morphing wing 20 of the present invention may be applied to the wing of a glider without a propulsion device.

Further, in the above-described embodiment, the morphing wing 20 is applied to the aircraft 100 in which the main wing is in the front and the tail wing is in the rear, but the present invention is not limited to this configuration. For example, the morphing wing 20 may be applied to an aircraft having a main wing at the rear and a canard corresponding to the horizontal stabilizer at the front (so-called canard aircraft), or an aircraft without a horizontal stabilizer (so-called tailless aircraft). The morphing wing 20 may be applied to the aircraft.

In order to verify the effect of the present invention, a morphing wing to which the present invention can be applied in which the airfoil can be changed from the first airfoil to the third airfoil is prepared, and the angle of attack α and lift in the first to third airfoils are prepared. The relationship between the resistance ratio Cl / Cd and the relationship between the angle of attack α and the lift Cl in the first to third airfoils are shown graphically in FIGS. 14 and 15, respectively. The horizontal axis of FIG. 14 indicates the angle of attack α, and the vertical axis indicates the lift-drag ratio. Further, the horizontal axis of FIG. 15 indicates the angle of attack α, and the vertical axis indicates the lift Cl. The graphs of the airfoils shown in FIGS. 14 and 15 are based on the calculated values using the two-dimensional airfoils.

First airfoil A ... An airfoil in which the elastic outer skin and the wing body are in close contact with each other via a film of liquid L (the airfoil shown by the two-point chain line in FIG. 13 (the first airfoil of the morphing wing 20 of the embodiment). The wing type corresponding to)).
Second airfoil B ... Airfoil in a state where the liquid L is supplied to the closed space and the elastic outer skin is moderately swollen and deformed (the airfoil shown by the solid line in FIG. 13 (the second airfoil of the morphing blade 20 of the embodiment). It is an airfoil corresponding to the type) and is the same airfoil as the NACA4412 airfoil).
Third airfoil C ... Airfoil with the elastic outer skin bulging and deformed compared to the second airfoil (the airfoil shown by the one-point chain line in FIG. 13 (corresponding to the third airfoil of the morphing wing 20 of the embodiment). It is an airfoil).
Here, the NACA airfoil refers to the airfoil defined by the National Advisory Committee for Aerospace (NACA), which is the predecessor of NASA.

As shown in FIG. 14, the first to third airfoils have different regions where the lift ratio is higher than the angle of attack α. Therefore, by changing the airfoil of the morphing wing to the first airfoil A and the third airfoil C based on the second airfoil, which is the same airfoil as the NACA4412 airfoil, the second airfoil can be compared with the second airfoil. The region having a high lift-drag ratio (region X1 and region X2 in FIG. 14) can be expanded.

As shown in FIG. 15, the first airfoil can delay the angle of attack (stall angle) leading to the stall state as compared with the second and third airfoils. Therefore, when the stall angles of the 2nd and 3rd airfoils approach each other, it is possible to avoid the stall state by delaying the stall angle by changing the airfoil of the morphing airfoil to the 1st airfoil. Become.

The embodiments of the present invention have been described above with reference to the embodiments, but these embodiments are examples and can be modified in various ways without departing from the gist. Needless to say, the scope of rights of the present invention is not limited to these embodiments.

20 Morphing wing 22 Wing body 22A Leading edge 22B Trailing edge 22C Top surface 28 Elastic outer skin 30 Sealed space 32 Regulator 34 Storage 36 Feed pump 38 Return pump 44 Pressure sensor 46 Control device 50 Protective membrane 100 Aircraft

Claims (7)

With the wing body
The upper surface of the wing body is covered, the liquid is held in a liquid-tight state in the closed space formed between the wing body and the wing body, and the liquid expands to the outside of the wing body according to the amount of the liquid in the closed space. With an elastic hull that changes the amount of output,
Bei to give a,
A morphing blade in which the liquid is impregnated and a porous body that follows the bulging deformation of the elastic exodermis is arranged in the closed space. The morphing wing according to claim 1, further comprising an adjusting means for adjusting the amount of the liquid in the enclosed space. The adjusting means includes a storage part for the liquid, a feed pump for sending the liquid from the storage part to the closed space, and a return pump for returning the liquid from the closed space to the storage part. Described morphing wings. The adjusting means controls the drive of the feed pump and the return pump with a pressure sensor that detects the pressure of the liquid in the sealed space, and seals the liquid according to the pressure information of the liquid sent from the pressure sensor. The morphing wing according to claim 3, further comprising a control device for adjusting the amount of the liquid in the space. The morphing wing according to any one of claims 1 to 4, wherein the elastic outer skin covers the upper surface of the front portion of the wing body. The morphing blade according to any one of claims 1 to 5 , wherein the portion of the blade body forming the closed space is coated with a protective film having corrosion resistance to the liquid. With the torso
The morphing wing according to claim 1 to 6 , which is attached to the fuselage portion.
Aircraft equipped with.

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