CN214930609U

CN214930609U - Wing structure of bionic aircraft

Info

Publication number: CN214930609U
Application number: CN202120269834.8U
Authority: CN
Inventors: 甘坤家
Original assignee: Shanghai Bailin Industrial Design Co ltd
Current assignee: Shanghai Bailin Industrial Design Co ltd
Priority date: 2021-01-31
Filing date: 2021-01-31
Publication date: 2021-11-30
Anticipated expiration: 2031-01-31

Abstract

The utility model relates to a bionic aircraft's wing structure. The bionic aircraft wing solves the problems that the wing structural design of the existing bionic aircraft is not reasonable enough and the like. The wing-folding device comprises a wing installation frame body, a plurality of wing frameworks and a wing folding driving mechanism, wherein a wing sub-sheet body with a sub-sheet body fanning surface is arranged between two adjacent wing frameworks, the sub-sheet body fanning surface of each wing sub-sheet body is positioned on the same horizontal plane so as to form the wing fanning surface, the wing sub-sheet body is movably connected with any one wing framework in the two adjacent wing frameworks, and a wing fanning auxiliary mechanism is arranged between the wing installation frame body and the wing frameworks. Has the advantages that: the wings can be folded at the side part of the aircraft body so as to realize the sliding function, so that the aircraft has multiple flight modes, simulates the sliding posture of birds, and has good bionic effect; when the wings are flapped upwards, the wing split bodies can be arranged in parallel to reduce the upward resistance, so that the resistance of the whole wings during flapping is reduced, and the power is saved.

Description

Wing structure of bionic aircraft

Technical Field

The utility model belongs to the technical field of the aircraft, especially, relate to a bionic aircraft's wing structure.

Background

With the development of aircraft technology, the research on bionic aircrafts has become a leading topic in the field of aircraft research. For example, the bionic flapping wing aircraft can simulate the flying of birds, dragonflies and the like in nature, has certain flying efficiency, is superior to a multi-rotor wing and a fixed wing in hovering property, wind resistance and maneuverability, is a subversive technology and a hot spot direction developed by the existing aircraft, and has wide application prospect.

The wings of the existing bionic flapping wing aircraft are in an integral structure, the wings are reciprocated during flight, when the rising force needs to be obtained, the wings are swung downwards, the aircraft obtains the upward force by virtue of the reaction force of air on the wings, but the wings can also receive the downward resistance of the same size when the wings are swung upwards, so that the resistance is larger when the wings are swung upwards, and a part of power is wasted.

In order to solve the problems of the prior art, people have long searched for and put forward various solutions. For example, chinese patent document discloses a novel wing structure of a bionic aircraft [ application No.: 200720062664.6], the wing comprises a skeleton, a movable wing surface, a control connecting rod, a control pull wire and a fixed stop lever, wherein one side of the movable wing surface of the wing is fixed on the skeleton, the movable wing surface can rotate around the side as the axis center, the control connecting rod is arranged at one side of the movable wing surface and connects the movable wing surface in series, the control pull wire connects the skeleton and the control connecting rod, and the fixed stop lever is fixed with the skeleton.

Above-mentioned scheme has solved the big problem of resistance when current bionic aircraft's wing upwards flares to a certain extent, nevertheless still exists because in this scheme: the wings can not be furled and are not flexible enough, the sliding function can not be realized, the bionic effect is not good, and the like.

Disclosure of Invention

The utility model aims at the above-mentioned problem, provide a bionic aircraft's wing structure that simple structure is reasonable, and flight resistance is little and can realize the function of slideing.

In order to achieve the above purpose, the utility model adopts the following technical proposal: the wing structure of the bionic aircraft comprises a wing installation frame body movably arranged on the side part of an aircraft body, it is characterized in that a plurality of wing skeletons are sequentially and movably arranged on one side of the wing installation frame body, a wing folding driving mechanism which can lead each wing skeleton to synchronously swing towards the wing installation frame body so as to realize folding is arranged between the wing installation frame body and the wing skeletons, a wing sub-sheet body with a sub-sheet body fan surface is arranged between two adjacent wing skeletons, the sub-sheet body fan surfaces of each wing sub-sheet body are positioned on the same horizontal plane so as to form the wing fan surface, the wing sub-body is movably connected with any one of the two adjacent wing skeletons, and a wing flapping auxiliary mechanism which can enable all the synchronous wing split bodies to rotate circumferentially in the same direction relative to the wing framework so as to enable all the wing split bodies to be arranged in parallel is arranged between the wing installation frame body and the wing framework.

In foretell bionic aircraft's wing structure, wing installation support body one side that is close to wing skeleton have a skeleton mounting panel, wing skeleton one end rotate the installation mechanism through the skeleton respectively and rotate the setting on the skeleton mounting panel.

In foretell bionic aircraft's wing structure, skeleton rotate installation mechanism rotate the seat including the skeleton that forms in wing skeleton one end, skeleton mounting panel one side articulated seat that rotates seat one-to-one has with the skeleton respectively, the skeleton rotate the seat and articulate through articulated shaft and articulated the linking to each other, just articulated seat one side have respectively and rotate the spacing portion that leans on in seat one side counterbalance with the skeleton, the opposite side has the swing space that supplies the skeleton to rotate the seat and pass, and the spacing portion on each articulated seat of skeleton mounting panel all lies in same one side.

In foretell bionic aircraft's wing structure, wing draw in actuating mechanism include a plurality of draw in pull rod that link to each other and the slope sets up with the wing skeleton respectively, draw in pull rod one end all with each wing skeleton with one side articulated link to each other, be equipped with in wing installation support body inboard and draw in sliding guide, draw in sliding guide in and slide and be equipped with a plurality of sliding blocks and each draw in the pull rod other end and all articulate with the sliding block and link to each other, wing installation support body on be equipped with and drive each sliding block in drawing in sliding guide in synchronous gliding wing draw in drive assembly.

In foretell bionic aircraft's wing structure, wing draw in drive assembly including set up the drive motor that draws in that keeps away from wing skeleton one side at wing installation support body, draw in drive motor's output shaft have a circumferential direction and set up the drive lead screw that draws in at wing installation support body lateral part, just draw in drive lead screw on the cover be equipped with and draw in the drive swivel nut, link to each other through the linkage pull rod respectively between two adjacent sliding blocks, and in each sliding block arbitrary one sliding block link to each other with drawing in the drive swivel nut through wearing to locate wing installation support body lateral part and drawing in the connecting rod portion in the bar inslot on the sliding guide.

In the wing structure of the bionic aircraft, the linkage pull rods are respectively detachably arranged between the two adjacent sliding blocks, and the drawing pull rods close to the framework mounting plate penetrate through the strip-shaped notches in the framework mounting plate.

In the above-mentioned bionic aircraft's wing structure, wing section body include that one side rotates the fin framework that links to each other with arbitrary wing skeleton in two adjacent wing skeletons, fin framework opposite side set up towards another wing skeleton extension in two adjacent wing skeletons and this wing skeleton has the spacing portion of wing that leans on with fin framework opposite side, be equipped with fin cloth in the fin framework and section body fan face form in fin cloth both sides.

In foretell bionic aircraft's wing structure, wing skeleton be equipped with a plurality of longitudinal axis in proper order along length direction, longitudinal axis rotate the setting on wing skeleton through the pivot mount pad respectively, and link to each other through the shaft coupling between two adjacent longitudinal axis, be equipped with the fixed body of rod that a plurality of adjacent wing skeleton of orientation extended the setting on each longitudinal axis respectively, just two fixed body of rod one end of keeping away from wing skeleton for a set of and same fixed body of rod in group link to each other through the connecting rod body, form the fin framework between the fixed body of rod on the same wing skeleton and the connecting rod body.

In the above wing structure of the bionic aircraft, the wing flapping assisting mechanism includes longitudinal axis rotating seats respectively arranged at the end portions of the hinge shafts, the longitudinal axis at the foremost end of each wing frame is rotatably arranged in the longitudinal axis rotating seat in a penetrating manner, and a wing flapping assisting assembly capable of driving the longitudinal axis at the foremost end of each wing frame to synchronously and circumferentially rotate is arranged on the wing mounting frame body.

In the wing structure of the bionic aircraft, the wing flapping auxiliary assembly comprises an electric push rod extending along the length direction of the wing mounting frame body, an output shaft of the electric push rod is connected with a connecting elbow positioned on the lateral part of the foremost longitudinal rotating shaft on the wing framework positioned on the outermost side, an output shaft of the electric push rod is connected with a transmission connecting rod, and the transmission connecting rod is respectively connected with the foremost longitudinal rotating shaft on the rest wing frameworks in sequence.

Compared with the prior art, the wing structure of the bionic aircraft has the advantages that:

1. the wings can be folded at the side part of the aircraft body so as to realize the sliding function, so that the aircraft has multiple flight modes, simulates the sliding posture of birds, and has good bionic effect;

2. when the wings are flapped downwards, all the wing split bodies are transversely arranged to form a complete wing flapwise surface, so that the aircraft obtains upward force, and when the wings are flapped upwards, all the wing split bodies can be arranged in parallel to reduce upward resistance, so that the resistance of the whole wings during the flapwise motion is reduced, and the power is saved.

Drawings

Fig. 1 is a schematic structural diagram provided by the present invention.

Fig. 2 is a schematic structural diagram of another viewing angle provided by the present invention.

Fig. 3 is a schematic structural view of the present invention when no fin cloth is provided.

Fig. 4 is an enlarged view of a portion a in fig. 2.

Fig. 5 is an enlarged view of fig. 3 at B.

In the figure, a wing installation frame body 1, a frame installation plate 11, a frame rotating seat 12, a hinge seat 13, a hinge shaft 14, a limiting part 15, a swing space 16, a wing frame 2, a wing furling driving mechanism 3, a furling pull rod 31, a strip-shaped notch 311, a furling sliding guide rail 32, a sliding block 33, a furling driving motor 34, a furling driving screw 35, a furling driving screw sleeve 36, a linkage pull rod 37, a strip-shaped groove 38, a connecting rod part 39, a wing piece body 4, a piece body fanning surface 41, a fin frame body 42, a wing limiting part 43, a fin cloth 44, a longitudinal rotating shaft 45, a rotating shaft installation seat 46, a coupling 47, a fixed rod body 48, a connecting rod body 49, a wing fanning surface 5, a wing fanning auxiliary mechanism 6, a longitudinal shaft rotating seat 61, an electric push rod 62, a transmission connecting rod 63 and a connecting elbow 64.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.

As shown in fig. 1-5, the wing structure of the bionic aircraft comprises a wing installation frame body 1 movably arranged at the side part of the aircraft body, a plurality of wing skeletons 2 are movably arranged at one side of the wing installation frame body 1 in sequence, a wing folding driving mechanism 3 which can lead each wing skeleton 2 to swing towards the wing installation frame body 1 synchronously so as to realize folding is arranged between the wing installation frame body 1 and the wing skeletons 2, a wing sub-body 4 with a sub-body fan surface 41 is arranged between two adjacent wing skeletons 2, the sub-body fan surface 41 of each wing sub-body 4 is positioned at the same horizontal plane so as to form a wing fan surface 5, the wing sub-body 4 is movably connected with any one wing skeleton 2 in the two adjacent wing skeletons 2, and a wing flapping auxiliary mechanism 6 which can make all synchronous bodies rotate circumferentially in the same direction relative to the wing framework 2 so as to make all the wing sub-bodies 4 arranged in parallel is arranged between the wing installation frame body 1 and the wing framework 2.

Obviously, the wing structure can fold the wing framework 2 at the side part of the aircraft body through the wing folding driving mechanism 3, so that the aircraft can realize the sliding function, has various flight modes, simulates the sliding posture of birds, and has good bionic effect; when the wings are flapped downwards, the wing sub-bodies 4 are transversely arranged to form a complete wing flapwise surface 5, so that the aircraft obtains upward force, and when the wings are flapped upwards, the wing sub-bodies 4 can be arranged in parallel to reduce upward resistance, so that the resistance of the whole wings is reduced during the flapwise movement, the power is saved, and meanwhile, the wing sub-bodies 4 are arranged in parallel to facilitate the folding function of the wings.

Specifically, the wing mounting frame 1 has a frame mounting plate 11 on a side thereof adjacent to the wing frame 2, and one end of the wing frame 2 is rotatably mounted on the frame mounting plate 11 by frame rotation mounting means, respectively. Wherein, skeleton rotation installation mechanism here rotates seat 12 including the skeleton that forms in wing skeleton 2 one end, skeleton mounting panel 11 one side has respectively rotates articulated seat 13 of seat 12 one-to-one with the skeleton, skeleton rotates seat 12 and articulates with articulated seat 13 through articulated shaft 14 and links to each other, and articulated seat 13 one side has respectively rotates the spacing portion 15 that seat 12 one side leaned on with the skeleton, the opposite side has the swing space 16 that supplies skeleton to rotate seat 12 and pass, and spacing portion 15 on each articulated seat 13 of skeleton mounting panel 11 all lies in same side, spacing portion 15 here makes wing skeleton 2 can only swing towards one direction and realize drawing in.

More specifically, the wing furling driving mechanism 3 includes a plurality of furling rods 31 which are respectively connected with the wing frameworks 2 and are obliquely arranged, one end of each furling rod 31 is hinged with the same side of each wing framework 2, a furling sliding guide rail 32 is arranged on the inner side of the wing installation frame body 1, a plurality of sliding blocks 33 are arranged in the furling sliding guide rail 32 in a sliding manner, the other end of each furling rod 31 is hinged with the sliding block 33, and the wing installation frame body 1 is provided with a wing furling driving component which can drive each sliding block 33 to synchronously slide in the furling sliding guide rail 32.

Preferably, the wing furling driving assembly herein includes a furling driving motor 34 disposed on one side of the wing installation frame body 1 far from the wing frame 2, an output shaft of the furling driving motor 34 is connected with a furling driving screw 35 circumferentially rotatably disposed on a side portion of the wing installation frame body 1, and a furling driving screw 36 is sleeved on the furling driving screw 35, two adjacent sliding blocks 33 are respectively connected through a linkage pull rod 37, and any one sliding block 33 of the sliding blocks 33 is connected with the furling driving screw 36 through a connecting rod portion 39 disposed in a strip-shaped groove 38 disposed on the side portion of the wing installation frame body 1 and the furling sliding guide rail 32, wherein the linkage pull rod 37 is respectively detachably disposed between the two adjacent sliding blocks 33, and each pull rod furling 31 close to the frame installation plate 11 is disposed in a strip-shaped notch 311 disposed on the frame installation plate 11. Obviously, when the furling driving motor 34 drives the furling driving screw 35 to rotate circumferentially so that the furling driving screw 36 drives one of the sliding blocks 33 to slide in the furling sliding guide rail 32, since the sliding blocks 33 are connected through the linkage rod 37 to slide together, the sliding block 33 drives the furling rod 31 to swing towards the wing frame 2 to realize the wing furling function.

Further, the wing piece body 4 includes a fin frame 42 having one side rotatably connected to any one wing frame 2 of the two adjacent wing frames 2, the other side of the fin frame 42 extends toward the other wing frame 2 of the two adjacent wing frames 2, the wing frame 2 has a wing limiting portion 43 abutting against the other side of the fin frame 42, a fin cloth 44 is disposed on the fin frame 42, and the piece body fan surfaces 41 are formed on both sides of the fin cloth 44, preferably, the fin cloth 44 may be made of a special nylon cloth, thereby improving the structural strength and reducing the weight.

Preferably, a plurality of longitudinal rotating shafts 45 are sequentially arranged on the wing frame 2 along the length direction, the longitudinal rotating shafts 45 are respectively rotatably arranged on the wing frame 2 through rotating shaft mounting seats 46, two adjacent longitudinal rotating shafts 45 are connected through a coupling 47, each longitudinal rotating shaft 45 is respectively provided with a plurality of fixing rod bodies 48 extending towards one adjacent wing frame 2, two fixing rod bodies 48 are in one group, one ends, far away from the wing frame 2, of the fixing rod bodies 48 in the same group are connected through connecting rod bodies 49, and a fin frame body 42 is formed between the fixing rod bodies 48 and the connecting rod bodies 49 on the same wing frame 2.

The wing-flapping auxiliary mechanism 6 in this embodiment includes longitudinal axis rotating seats 61 respectively disposed at the end portions of the hinge shafts 14, the longitudinal axis 45 located at the foremost end of each wing frame 2 is rotatably disposed through the longitudinal axis rotating seats 61, and a wing-flapping auxiliary assembly capable of driving the longitudinal axis 45 located at the foremost end of each wing frame 2 to synchronously and circumferentially rotate is disposed on the wing mounting frame body 1.

Preferably, the wing flapping assisting assembly comprises an electric push rod 62 extending along the length direction of the wing mounting frame 1, an output shaft of the electric push rod 62 is connected with a connecting elbow 64 positioned at the side part of the foremost longitudinal rotating shaft 45 on the outermost wing frame 2, the output shaft of the electric push rod 62 is connected with a transmission connecting rod 63, and the transmission connecting rod 63 is respectively and sequentially connected with the foremost longitudinal rotating shaft 45 on the rest wing frames 2. Obviously, the electric push rod 62 pushes the connecting elbow 64 to rotate, and since the connecting elbow 64 is connected with the longitudinal rotating shaft 45, the foremost row rotates on the longitudinal rotating shaft 45, and the later rows of the longitudinal rotating shafts 45 can rotate 90 degrees under the driving of the transmission connecting rod 63. The purpose of rotation is to enable the special nylon cloth to be horizontally arranged when the wings are flapped downwards, and to enable the special nylon cloth to be vertically arranged when the wings are flapped upwards so as to reduce upward resistance.

The specific embodiments described herein are merely illustrative of the spirit of the invention. Various modifications, additions and substitutions for the specific embodiments described herein may be made by those skilled in the art without departing from the spirit of the invention or exceeding the scope of the invention as defined in the accompanying claims.

Although the wing mounting frame 1, the frame mounting plate 11, the frame rotating base 12, the hinge base 13, the hinge shaft 14, the limiting portion 15, the swing space 16, the wing frame 2, the wing furling driving mechanism 3, the furling pull rod 31, the strip-shaped notch 311, the furling sliding guide rail 32, the sliding block 33, the furling driving motor 34, the furling driving screw 35, the furling driving screw sleeve 36, the linkage pull rod 37 and the strip-shaped groove 38 are more used herein, connecting rod portion 39, wing piece body 4, piece body sector surface 41, fin frame 42, wing limiting portion 43, fin cloth 44, longitudinal rotating shaft 45, rotating shaft mounting seat 46, coupling 47, fixed rod body 48, connecting rod body 49, wing sector surface 5, wing sector auxiliary mechanism 6, longitudinal shaft rotating seat 61, electric push rod 62, transmission connecting rod 63, connecting elbow 64 and other terms, but does not exclude the possibility of using other terms. These terms are used merely to more conveniently describe and explain the nature of the present invention; they are to be construed in a manner that is inconsistent with the spirit of the invention.

Claims

1. The utility model provides a bionic aircraft's wing structure, includes that the activity sets up wing installation support body (1) at aircraft fuselage lateral part, its characterized in that, wing installation support body (1) one side in proper order the activity be equipped with a plurality of wing skeletons (2), wing installation support body (1) and wing skeleton (2) between be equipped with and enable each wing skeleton (2) synchronous towards wing installation support body (1) swing thereby realize the wing that draws in and draw in actuating mechanism (3), be equipped with between two adjacent wing skeletons (2) and divide slice body (4) with fragmentation body fan face (41), thereby the fragmentation body fan face (41) of each wing branch body (4) are located same horizontal plane and form wing fan face (5), wing branch body (4) and any one wing skeleton (2) activity in two adjacent wing skeleton (2) link to each other, and a wing flapping auxiliary mechanism (6) which can enable all synchronous bodies to rotate circumferentially in the same direction relative to the wing framework (2) so as to enable all the wing sub-body bodies (4) to be arranged in parallel is arranged between the wing installation frame body (1) and the wing framework (2).

2. The wing structure of the bionic aircraft as claimed in claim 1, wherein a skeleton mounting plate (11) is arranged on one side of the wing mounting frame body (1) close to the wing skeleton (2), and one end of the wing skeleton (2) is rotatably arranged on the skeleton mounting plate (11) through a skeleton rotating and mounting mechanism.

3. The wing structure of the bionic aircraft as claimed in claim 2, wherein the framework rotation installation mechanism comprises a framework rotation seat (12) formed at one end of the wing framework (2), the framework installation plate (11) is provided with a hinge seat (13) corresponding to the framework rotation seat (12) one by one on one side, the framework rotation seat (12) is hinged to the hinge seat (13) through a hinge shaft (14), one side of the hinge seat (13) is provided with a limit part (15) leaning against one side of the framework rotation seat (12), the other side of the hinge seat is provided with a swing space (16) for the framework rotation seat (12) to pass through, and the limit parts (15) on each hinge seat (13) of the framework installation plate (11) are located on the same side.

4. The wing structure of the bionic aircraft as claimed in claim 3, wherein the wing furling driving mechanism (3) comprises a plurality of furling rods (31) which are respectively connected with the wing frameworks (2) and are obliquely arranged, one end of each furling rod (31) is hinged with the same side of each wing framework (2), a furling sliding guide rail (32) is arranged at the inner side of the wing installation frame body (1), a plurality of sliding blocks (33) are arranged in the furling sliding guide rail (32) in a sliding manner, the other end of each furling rod (31) is hinged with the sliding block (33), and a wing furling driving component which can drive each sliding block (33) to synchronously slide in the furling sliding guide rail (32) is arranged on the wing installation frame body (1).

5. The wing structure of the bionic aircraft as claimed in claim 4, wherein the wing furling driving assembly comprises a furling driving motor (34) which is arranged on one side of the wing installation frame body (1) far away from the wing framework (2), an output shaft of the furling driving motor (34) is connected with a furling driving screw rod (35) which is circumferentially and rotatably arranged on the side of the wing installation frame body (1), the furling driving screw rod (35) is sleeved with a furling driving threaded sleeve (36), two adjacent sliding blocks (33) are respectively connected through a linkage pull rod (37), and any one sliding block (33) in each sliding block (33) is connected with the furling driving threaded sleeve (36) through a connecting rod part (39) which is arranged in a strip-shaped groove (38) on the side of the wing installation frame body (1) and the furling sliding guide rail (32).

6. The wing structure of the bionic aircraft as claimed in claim 5, wherein the linkage pull rods (37) are respectively detachably arranged between two adjacent sliding blocks (33), and each furling pull rod (31) close to the framework mounting plate (11) is arranged in a strip-shaped notch (311) on the framework mounting plate (11) in a penetrating manner.

7. The wing structure of the bionic aircraft according to claim 4, wherein the wing sub-body (4) comprises a fin frame (42) one side of which is rotatably connected with any one wing frame (2) of the two adjacent wing frames (2), the other side of the fin frame (42) extends towards the other wing frame (2) of the two adjacent wing frames (2), the wing frame (2) is provided with a wing limiting part (43) which is abutted against the other side of the fin frame (42), the fin frame (42) is provided with a fin cloth (44), and the sub-body fans (41) are formed on two sides of the fin cloth (44).

8. The wing structure of the bionic aircraft as claimed in claim 7, wherein the wing skeleton (2) is provided with a plurality of longitudinal rotating shafts (45) along the length direction in sequence, the longitudinal rotating shafts (45) are respectively and rotatably arranged on the wing frameworks (2) through rotating shaft mounting seats (46), and two adjacent longitudinal rotating shafts (45) are connected through a coupling (47), each longitudinal rotating shaft (45) is respectively provided with a plurality of fixed rod bodies (48) which are arranged towards the adjacent wing framework (2) in an extending way, and the two fixed rod bodies (48) are in a group, one ends of the fixed rod bodies (48) in the same group, which are far away from the wing framework (2), are connected through a connecting rod body (49), and a fin frame body (42) is formed between the fixed rod body (48) and the connecting rod body (49) on the same wing framework (2).

9. The wing structure of the bionic aircraft as claimed in claim 8, wherein the wing-flapping auxiliary mechanism (6) comprises longitudinal axis rotating seats (61) respectively arranged at the ends of the hinge shafts (14), the longitudinal axis (45) at the foremost end of each wing frame (2) is rotatably arranged in the longitudinal axis rotating seats (61), and a wing-flapping auxiliary assembly capable of driving the longitudinal axis (45) at the foremost end of each wing frame (2) to synchronously and circumferentially rotate is arranged on the wing installation frame body (1).

10. The wing structure of the bionic aircraft as claimed in claim 9, wherein the wing flapping assisting assembly comprises an electric push rod (62) extending along the length direction of the wing installation frame body (1), the output shaft of the electric push rod (62) is connected with a connecting elbow (64) located at the side part of the foremost longitudinal rotating shaft (45) on the outermost wing frame (2), the output shaft of the electric push rod (62) is connected with a transmission connecting rod (63), and the transmission connecting rod (63) is sequentially connected with the foremost longitudinal rotating shaft (45) on the remaining wing frame (2).