CN111994265A - Folding wing ornithopter - Google Patents

Abstract

The embodiment of the invention provides a folding wing ornithopter, which comprises a body; the wings are symmetrically arranged on two sides of the fuselage and comprise driving arms, outer section wings and inner section wings, the inner section wings and the outer section wings are arranged into a sheet structure, and the inner section wings are hinged with the outer section wings; the elastic piece is arranged below the outer section wing and the inner section wing and is positioned at the hinged position of the inner section wing and the outer section wing, one end of the elastic piece is connected with the inner section wing, the other end of the elastic piece is connected with the outer section wing, and the maximum elastic restoring force of the elastic piece is equal to the gravity of the outer section wing. Compared with the prior art, the wing structure of the flapping-wing aircraft is simpler, a parallel connecting rod is reduced for the inner-section wing, and the weight of the wing is also reduced.

Description

Folding wing flapper

technical field

Embodiments of the present invention relate to aircraft technology, and in particular, to a folding-wing flapper.

Background technique

A flapper uses its wings to flap up and down like birds and insects to generate upward lift and rely on lift to fly. Among them, the wings of the folding-wing flapper can be unfolded when flapping downward, and can be folded when flapping upward, so that the lift force of the wing when it moves downward is greater than the resistance when it moves upward.

The wing of the existing folding-wing flapper includes an outer section wing and an inner section wing hinged with the outer section wing. The inner section wing includes two parallel connecting rods, and the two parallel connecting rods move with each other under the drive of the driving mechanism, thereby driving the outer section wing to rotate relative to the inner section wing to realize the unfolding and folding of the wing.

However, the wing structure of this connection structure is relatively complex, and the wing weight is relatively large.

SUMMARY OF THE INVENTION

In order to solve the above problems in the prior art, that is, in order to solve the problem of the existing folding wing flapping wing aircraft, the inner section wing includes two parallel connecting rods, and the two parallel connecting rods move with each other under the driving of the driving mechanism, and then The outer section wing is driven to rotate relative to the inner section wing to realize the unfolding and folding of the wing. The wing of this connection structure is relatively complicated and the weight of the wing is heavy.

According to an embodiment of the present invention, a folding wing flapper is provided, comprising:

body;

A wing symmetrically arranged on both sides of the fuselage, the wing includes a drive arm, an outer segment wing and an inner segment wing, the inner segment wing and the outer segment wing are arranged in a sheet-like structure, and the inner segment wing hingedly connected with the outer segment wing;

An elastic piece is arranged below the outer section wing and the inner section wing and is located at the hinge of the inner section wing and the outer section wing, one end of the elastic piece is connected with the inner section wing, and the other end is connected with the outer section wing. The outer section wings are connected, and the maximum elastic restoring force of the elastic member is equal to the gravity of the outer section wings.

In an optional implementation manner, the included angle between the lower surface of the inner section wing and the lower surface of the outer section wing does not exceed 180°.

In an optional implementation manner, the inner section wing and the outer section wing are connected by a hinge, and the hinge includes a first connecting part, a second connecting part and a rotating shaft, and the first connecting part and the second connecting part are connected by a hinge. The connecting part can rotate around the axis of the rotating shaft, the first connecting part is fastened with the outer section wing, the second connecting section is fastened with the inner section wing, the first connecting section and the The second connecting portion is configured such that the end faces of the two abut against each other when the relative rotation reaches 180 degrees.

In an optional implementation manner, the inner wing is an inner wing, the outer wing is an outer wing, and the inner wing is directly hinged with the outer wing; one end of the elastic member is The other end of the elastic piece is fastened with the outer flap.

In an optional implementation manner, the inner section wing includes an inner link and an inner wing, the inner wing cover is provided on the inner link and is fastened to the inner link, so The outer segment wing includes an outer link and an outer wing, the outer wing is covered on the outer link and is tightly connected with the outer link, and the inner link is directly connected to the outer link. Hinged; one end of the elastic piece is fastened with the inner link, and the other end of the elastic piece is fastened with the outer link.

In an optional implementation manner, the elastic member is a rod member made of elastic material, and the rod member is provided below the inner link and the outer link.

In an optional implementation manner, the elastic member is a spring, and the spring is sleeved on a portion of the inner link and the outer link close to the hinge.

In an optional implementation manner, the elastic member includes a spring and a rod member made of elastic material, the spring is sleeved on the parts of the inner link and the outer link close to the hinge, The rod is located within the spring.

In an optional implementation manner, a side of the inner section wing close to the drive arm is connected with the fuselage shaft pin.

In an optional implementation manner, it further includes two runners symmetrically arranged on both sides of the fuselage, the two runners rotate in opposite directions synchronously, and the runners are connected to the drive arm, Each of the runners is used to drive the drive arm on the same side to rotate.

Those skilled in the art can understand that the folding-wing flapper of the present invention includes a fuselage and wings symmetrically arranged on both sides of the fuselage, and the wings include drive arms, outer wings and inner wings. The inner section wing and the outer section wing are arranged in a sheet-like structure, and the inner section wing and the outer section wing are hingedly connected. An elastic piece is arranged below the inner section wing and the outer section wing, and the elastic piece is located at the hinge joint of the inner section wing and the outer section wing. One end of the elastic piece is connected with the inner section wing, and the other end is connected with the outer section wing, and the maximum elastic restoring force of the elastic piece is equal to the gravity of the outer section wing. When the driving arm drives the inner wing to move upward, the outer wing is subject to downward air resistance. On the one hand, the air resistance and the gravity of the outer wing make the outer wing fold downward relative to the inner wing, and on the other hand, it is elastic. The load is applied to the piece to cause the elastic piece to deform. When the drive arm drives the inner wing to move downward, the outer wing is subject to upward air resistance, and the gravity of the outer wing is offset by the elastic force of the elastic member, and the air resistance causes the outer wing to wind up around the inner wing. The hinge points rotate, allowing the wings to unfold. Compared with the prior art, the structure of the wing is simplified, and in addition, the weight of the inner section of the wing is reduced by one connecting rod, and the mass is reduced.

Description of drawings

In order to illustrate the technical solutions of the embodiments of the present invention more clearly, the following briefly introduces the accompanying drawings used in the description of the embodiments. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can also be obtained from these drawings without any creative effort.

1 is a schematic structural diagram of a folding-wing flapper provided by an embodiment of the present invention;

2 is a schematic diagram of the connection between an elastic member and a wing provided by an embodiment of the present invention;

3 is a schematic diagram of another elastic member connected to a wing according to an embodiment of the present invention;

Fig. 4 is the partial enlarged schematic diagram of A place in Fig. 1;

FIG. 5 is a schematic diagram of another elastic member connected to a wing according to an embodiment of the present invention.

Description of reference numbers:

1 - the fuselage;

2 - wing;

21- drive arm;

22-outer wing;

221-outer connecting rod;

23 - inner section wing;

231-inner connecting rod;

3 - elastic parts;

31-rod;

32 - spring;

4- Runner.

Detailed ways

First of all, those skilled in the art should understand that these embodiments are only used to explain the technical principle of the present invention, and are not intended to limit the protection scope of the present invention. Those skilled in the art can make adjustments as needed to adapt to specific applications.

Secondly, it should be noted that in the description of the present invention, the terms of the direction or positional relationship indicated by the terms "inner" and "outer" are based on the direction or positional relationship shown in the accompanying drawings, which is only for the convenience of description, It is not intended to indicate or imply that a device or component must have a particular orientation, be constructed and operate in a particular orientation, and therefore should not be construed as limiting the invention.

In the existing folding wing flapper, the wing includes an outer section wing and an inner section wing hinged with the outer section wing, one end of the inner section wing is hinged with the outer section wing, and the other end is hinged with the driving arm. The inner section wing includes two parallel connecting rods, and the two parallel connecting rods form a parallelogram structure with a part of the driving arm and a part of the outer section wing. During the movement of the wing, the movement of the driving arm drives the deformation of the parallelogram structure, and the unfolding and folding of the wing is realized by the deformation of the parallelogram structure. However, the wing of this connection structure is more complicated, and the weight of the wing is also heavier.

After repeated thinking and verification, the inventor found that if the structure of the inner wing can be simplified into a sheet-like structure, the inner wing is directly hinged with the outer wing, and the wing relies on the resistance of the air during the movement to realize the wing. Expand and collapse. In this way, not only the structure of the wing can be simplified, but also the weight of the wing can be reduced as compared with the wing of the existing folding-wing flapper.

In view of this, the inventor designed a folding wing flapper, including a fuselage and wings symmetrically arranged on both sides of the fuselage. The segment wings are arranged in a sheet-like structure, and the inner segment wings are hingedly connected with the outer segment wings. The elastic piece is arranged below the outer section wing and the inner section wing and is located at the hinge of the inner section wing and the outer section wing. One end of the elastic piece is connected with the inner section wing and the other end is connected with the outer section wing. The maximum elastic restoring force of the elastic piece is equal to the weight of the outer wing. In this way, during the movement of the wing, the gravity of the outer wing itself is offset by the elastic force of the elastic member. When the wing moves upward, relying on the air resistance and the gravity of the outer wing, the outer wing moves downward relative to the inner wing, so that the wing folds; when the wing moves downward, the wing is subject to upward air resistance, The air resistance and the elastic force of the spring make the outer section of the wing move upward relative to the inner section of the wing to realize the expansion of the wing. The structure of the wing has been simplified and the weight has been reduced.

FIG. 1 is a schematic structural diagram of the folding wing flapping aircraft provided in this embodiment. As shown in FIG. 1 , the folding-wing flapping aircraft provided in this embodiment includes a fuselage 1 and wings 2 symmetrically arranged on both sides of the fuselage 1. The fuselage 1 is used for installing the wings 2 and the wings of the folding-wing flapping-wing aircraft. Other parts such as the tail. This embodiment does not limit the specific structure of the fuselage 1, and those skilled in the art can set it according to actual needs.

As shown in FIG. 1 , the wing 2 includes a driving arm 21 , an outer segment wing 22 and an inner segment wing 23 . Exemplarily, the inner segment wing 23 and the outer segment wing 22 are arranged in a sheet-like structure. The specific shape of the structure is not limited. Exemplarily, the inner section wing 23 and the outer section wing 22 are both rectangular sheet-like structures, and the size of the sheet-like structures can be determined according to the air resistance and the weight of the flapper when it moves. Sure. The inner section wing 23 is hingedly connected with the outer section wing 22, and the driving arm 21 is used to drive the inner section wing 23 to move, and then drives the outer section wing 22 hinged with the inner section wing 23 to rotate relative to the inner section wing 23, so as to realize the movement of the wing 2. Expand and collapse.

Continuing to refer to FIG. 1 , the side of the inner section wing 23 close to the drive arm 21 is connected with the shaft pin of the fuselage 1. Exemplarily, a first bushing is provided at the connection between the fuselage 1 and the inner section wing 23 (the area indicated by the triangle). , the inner section wing 23 is provided with a second bushing, and the first bushing and the second bushing are connected by a shaft pin. The movement of the driving arm 21 can drive the inner section wing 23 to rotate around the pivot pin, thereby realizing the upward movement or downward movement of the inner section wing 23 .

A possible implementation is that the airfoils can be directly used as the inner section wings 23 and the outer section wings 22 of the airfoil 2 . Here, the fins used as the inner segment wings 23 are defined as inner fins, and the fins used as the outer segment wings 22 are defined as outer fins, and the inner fins and the outer fins are directly hinged, for example, hinged through hinges. During the flight of the flapper, the outer fins can rotate relative to the inner fins to realize the unfolding and folding of the wings 2 .

It is easy to understand that the wing 2 is used as the inner section wing 23 and the outer section wing 22, the inner section wing 23 and the outer section wing 22 are directly hinged, the weight of the wing 2 is relatively light, and the driving arm 21 directly drives the wings. Movement can realize the flight of the flapper.

Another possible implementation is that the inner wing 23 includes an inner link and an inner wing, and the inner wing covers the inner link and is fastened to the inner link, so that the inner wing 23 is formed into a sheet shape Structure, this embodiment does not limit the connection mode between the inner link and the inner wing, and those skilled in the art can select any suitable connection mode according to actual needs. The outer section wing 22 includes an outer link and an outer wing, and the outer wing is covered on the outer link and is fastened to the outer link. The inner link and the outer link are hingedly connected. During the movement of the driving arm 21, the inner link is driven to move, thereby driving the outer link to rotate relative to the inner link. When the inner link and the outer link rotate relative to each other, the inner wing is driven. It rotates relative to the outer wing to realize the unfolding and folding of the wing 2 .

It is easy to understand that the strength of the inner link is greater than the strength of the inner fin, and the strength of the outer link is greater than the strength of the outer fin. By arranging the inner link and the outer link, the inner link is used to drive the movement of the inner wing, and the outer link drives the movement of the outer wing, which increases the structural strength of the wing 2, and it is more difficult for the wing 2 to be used for a long time. deformed.

It is worth mentioning that the angle α between the lower surface of the inner section wing 23 and the lower surface of the outer section wing 22 does not exceed 180 degrees, that is to say, the maximum state of the wing 2 of the flapper is the inner section. The segment wing 23 and the outer segment wing 22 are on the same plane. At this time, the air resistance of the wing 2 is the largest.

By arranging the wing 2 of the folding wing flapper so that the angle between the lower surface of the inner wing 23 and the lower surface of the outer wing 22 does not exceed 180 degrees, during the downward flapping process of the wing 2, the When α is expanded to 180 degrees, that is, the inner section wing 23 and the outer section wing 22 are on the same plane, at this time, the contact area between the wing 2 and the air is the largest. That is to say, when α is the maximum value, that is, when 180 degrees is flapping downward, the wing 2 provides the largest upward lift for the fuselage 1, and the flapper can rise at the fastest speed.

Exemplarily, the inner section wings 23 and the outer section wings 22 are connected by hinges (not shown in the figures). It is easy to understand that the number of hinges is not limited, and it can be one or more. For example, when the inner section wing 23 includes an inner link and an inner wing, and the outer section wing 22 includes an outer link and an outer wing , the inner link and the outer link can be hinged with one hinge; when the inner wing 23 is an inner wing and the outer wing 22 is an outer wing, multiple hinges can be used for articulation, and the inner wing is connected with the multiple hinges. The outer fins are arranged at intervals on the boundary line.

The hinge includes a first connecting part, a second connecting part and a rotating shaft, the first connecting part and the second connecting part are sleeved on the rotating shaft, that is to say, the first connecting part and the second connecting part can rotate around the axis of the rotating shaft . The first connection part is fastened to the outer segment wing 22 , for example, the first connection part and the outer segment wing 22 may be connected by fasteners such as screws. The second connection portion is fastened to the inner segment wing 23 , and for example, the second connection portion and the outer segment wing 22 may also be connected by screws. When the first connecting part and the second connecting part rotate to 180 degrees around the axis of the rotating shaft, the end faces of the first connecting part and the second connecting part abut each other, thereby realizing the limit between the inner section wing 23 and the outer section wing 22 .

In this embodiment, the inner section wing 23 and the outer section wing 22 are connected by a hinge, the outer section wing 22 can rotate relative to the inner section wing 23 around the hinge axis, and the unfolding angle of the wing 2 is limited by the hinge, Compared with using other limiting structures such as limiting blocks to limit the deployment angle of the wing, the weight of the wing 2 will not be increased too much.

Continuing to refer to FIG. 1 , an elastic member 3 is provided below the inner section wing 23 and the outer section wing 22 . Specifically, the elastic member 3 is located at the hinge of the inner section wing 23 and the outer section wing 22 . One end of the elastic member 3 is connected with the inner section wing 23 , and the other end is connected with the outer section wing 22 . Specifically, when the inner wing 23 is an inner wing and the outer wing 22 is an outer wing, one end of the elastic member 3 is fastened to the inner wing, and the other end is fastened to the outer wing; 23 includes an inner link 231 and when the outer segment wing 22 includes an outer link 221 , one end of the elastic member 3 is tightly connected to the inner link 231 , and the other end is tightly connected to the outer link 221 .

It should be noted that the maximum elastic restoring force of the elastic member 3 is equal to the gravity of the outer section wing 22, that is to say, during the upward movement of the wing 2, the gravity of the outer section wing 22 and the direction of the outer section wing 22 are affected. The lower air resistance causes the elastic member 3 to deform, and the wing 2 folds; during the downward movement of the wing 2, the outer section wing 22 is subject to upward air resistance, and the elastic member 3 applies elastic force to the outer section wing 22, and the elastic member The elastic force of 3 and the gravity of the outer section wing 22 cancel each other out, and the wing 2 is unfolded by relying on air resistance.

The folding wing flapper provided by this embodiment relies on air resistance and the elastic force of the elastic member 3 to realize the unfolding and folding of the wing 2 during the flight. Compared with the prior art that relies on the deformation of the parallelogram structure to realize the wing The unfolding and folding is closer to the real bird form.

Hereinafter, the inner section wing 23 includes the inner link 231 and the outer section wing 22 includes the outer link 221 as an example to introduce several possible implementations of the elastic member 3, but those skilled in the art should understand that the following specific implementation of the elastic member 3 The manner should not be regarded as a specific limitation to the elastic member 3 .

FIG. 2 is a schematic diagram of the connection between an elastic member and an airfoil provided in this embodiment. As shown in FIG. 2 , a possible implementation is to use a spring 32 as the elastic member 3 , for example, the spring 32 is sleeved on the parts of the inner link 231 and the outer link 221 close to the hinge. Both ends of the spring 32 are fixedly connected to the inner link 231 and the outer link 221 respectively. When the inner link 231 on the left moves upwards driven by the driving arm 21, the outer link 221 on the right rotates clockwise around the hinge point with the inner link 231 under the action of air resistance and its own gravity, and the outer link 221 on the right rotates clockwise. During the rotation of the connecting rod 221, the spring 32 is bent and deformed, the elastic potential energy of the spring 32 increases, and the wing 2 of the flapper is folded; During the movement, the outer link 221 on the right side rotates counterclockwise around the hinge point with the inner link 231 under the action of air resistance and the elastic force of the spring 32. During the counterclockwise rotation of the outer link 221, the spring 32 is an external connection. The rod 221 provides elastic force, and the spring 32 is gradually reset, so that the wing 2 of the flapper can be stretched.

FIG. 3 is a schematic diagram of the connection between another elastic member and an airfoil provided in this embodiment. As shown in FIG. 3 , another possible implementation is to use a rod 31 made of elastic material as the elastic member 3 , and the rod 31 is arranged below the inner link 231 and the outer link 221 , specifically , the rod 31 is located at the hinged joint between the inner link 231 and the outer link 221 . This embodiment does not limit the specific material of the rod member 31 , for example, elastic rubber can be used as the material of the rod member 31 . When the elastic member 3 is a rod member 31 made of elastic material, its working principle is similar to that of the spring 32 being sleeved at the hinge between the inner link 231 and the outer link 221, relying on the bending deformation of the rod 31 to provide elastic force, It will not be repeated here.

FIG. 4 is a partial enlarged schematic diagram of the position A in FIG. 1 . As shown in FIG. 4 , the elastic member 3 may also include a spring 32 and a rod member 31 made of elastic material. The spring 32 is sleeved on the part of the inner link 231 and the outer link 221 near the hinge, and the rod 31 is located in Inside the spring 32 , two ends of the rod 31 are respectively connected to the inner link 231 and the outer link 221 . The elastic force is applied to the outer link 221 by the deformation of the spring 32 and the rod 31 .

It is easy to understand that, when the elastic member 3 is the spring 32 sleeved on the hinge of the inner link 231 and the outer link 221, the elastic force that the elastic member 3 can exert on the outer link 221 is relatively small; the elastic member 3 is made of elastic material. When the rod member 31 is formed, the elastic force that the elastic member 3 can provide is relatively large; when the elastic member 3 includes the spring 32 and the rod member 31, the elastic force that the elastic member 3 can provide is greater than that simply using the spring 32 or the rod member 31 as the elastic member 3 . Those skilled in the art can select a suitable type of elastic member 3 according to the weight of the outer section wing 22 .

FIG. 5 is a schematic diagram of the connection between another elastic member and an airfoil provided in this embodiment. As shown in FIG. 5 , in other possible implementations, one end of the spring 32 is connected to the inner link 231 , and the other end of the spring 32 is connected to the outer link 221 . A part of the inner link 231 , a part of the outer link 221 and the spring 32 form a triangular structure. During the folding process of the wing 2, the spring 32 is compressed by the inner link 231 and the outer link 221; during the stretching of the wing 2, the spring 32 is reset, and the spring 32 applies elastic force to the outer link 221 to make the outer link 221 Rotate counterclockwise around the hinge with the inner link 231 .

As shown in FIG. 1 , the folding wing flapper provided by this embodiment also includes two runners 4 symmetrically arranged on both sides of the fuselage 1 , and the two runners 4 rotate in opposite directions synchronously, thereby driving the fuselage The wings 2 on both sides of 1 move synchronously.

A possible implementation is to use gears as the runners 4 , the two gears have the same size and the same modulus, and the two runners 4 mesh with each other, thereby ensuring that the two runners 4 rotate synchronously. The drive arm 21 is connected with the gear. Specifically, the runner 4 is tightly connected with the crank, and the end of the crank away from the axis of the runner 4 is connected to the bottom end of the drive arm 21. During the rotation of the runner 4, the crank is driven to move, and the crank drives the drive. The arm 21 moves, so that each runner 4 drives the drive arm 21 on the same side to rotate.

In this embodiment, by setting the runners 4 on both sides of the fuselage 1 that rotate in opposite directions synchronously, the runners 4 are used to drive the driving arms 21 on both sides to rotate, thereby driving the wings 2 on both sides of the fuselage 1 to move, avoiding During the flight of the flapper, the movement of the wings 2 on both sides is not synchronized, causing the fuselage 1 to tilt or even crash.

In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "top", "bottom", "upper", "lower" (if any), etc. are based on the orientation or positional relationship shown in the accompanying drawings , is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the indicated device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

In the description of the present invention, it should be noted that the terms "installed", "connected" and "connected" should be understood in a broad sense, unless otherwise expressly specified and limited, for example, it may be a fixed connection or a detachable connection Connection, or integral connection; can be mechanical connection, can also be electrical connection; can be directly connected, can also be indirectly connected through an intermediate medium, can be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood through specific situations.

The terms "first" and "second" in the description and claims of the present application and the above description of the drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It is to be understood that the data so used may be interchanged under appropriate circumstances such that the embodiments of the application described herein can, for example, be practiced in sequences other than those illustrated or described herein.

Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: The technical solutions described in the foregoing embodiments can still be modified, or some or all of the technical features thereof can be equivalently replaced; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the technical solutions of the embodiments of the present invention. scope.

Claims (10)

1. a folding wing flapper, is characterized in that, comprises: body; A wing symmetrically arranged on both sides of the fuselage, the wing includes a drive arm, an outer segment wing and an inner segment wing, the inner segment wing and the outer segment wing are arranged in a sheet-like structure, and the inner segment wing hingedly connected with the outer segment wing; An elastic piece is arranged below the outer section wing and the inner section wing and is located at the hinge of the inner section wing and the outer section wing, one end of the elastic piece is connected with the inner section wing, and the other end is connected with the outer section wing. The outer section wings are connected, and the maximum elastic restoring force of the elastic member is equal to the gravity of the outer section wings. 2 . The folding wing flapper according to claim 1 , wherein the included angle between the lower surface of the inner section wing and the lower surface of the outer section wing does not exceed 180°. 3 . 3. The folding wing flapper according to claim 2, wherein the inner section wing and the outer section wing are connected by a hinge, and the hinge comprises a first connecting part, a second connecting part and a rotating shaft, The first connecting part and the second connecting part can rotate around the axis of the rotating shaft, the first connecting part is fastened with the outer section wing, and the second connecting part is fastened with the inner section wing For connection, the first connecting part and the second connecting part are configured so that their end faces are abutted when the relative rotation reaches 180 degrees. 4. The folding wing flapper according to claim 1, wherein the inner section wing is an inner wing piece, the outer section wing is an outer wing piece, the inner wing piece and the outer wing piece are Directly hinged; one end of the elastic piece is fastened to the inner flap, and the other end of the elastic piece is fastened to the outer flap. 5. The folding wing flapper according to claim 1, wherein the inner section wing comprises an inner link and an inner wing, and the inner wing is covered on the inner link and is connected with the The inner link is tightly connected, the outer segment wing includes an outer link and an outer wing, the outer wing is covered on the outer link and is tightly connected with the outer link, and the inner The connecting rod is directly hinged with the outer connecting rod; one end of the elastic piece is fastened with the inner connecting rod, and the other end of the elastic piece is fastened with the outer connecting rod. 6 . The folding wing flapper according to claim 5 , wherein the elastic member is a rod member made of elastic material, and the rod member is arranged below the inner link and the outer link. 7 . . 7 . The folding wing flapper according to claim 5 , wherein the elastic member is a spring, and the spring is sleeved on the part of the inner link and the outer link close to the hinge. 8 . 8 . The folding wing flapper according to claim 5 , wherein the elastic member comprises a spring and a rod member made of elastic material, and the spring is sleeved on the inner link and the outer link. 9 . On the portion near the hinge, the rod is located within the spring. 9 . The folding wing flapper according to claim 1 , wherein the inner section wing is connected with the fuselage shaft pin on the side close to the driving arm. 10 . 10. The folding wing flapper according to any one of claims 1-8, characterized in that it further comprises two runners symmetrically arranged on both sides of the fuselage, and the two runners are synchronously opposite to each other. The rotating wheel is connected with the driving arm, and each rotating wheel is used to drive the driving arm on the same side to rotate.

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