Folding device for folding rudder wings

Abstract

The present invention discloses a folding device for folding rudder wings, comprising an aircraft and a folding structure. The aircraft includes a main body, a plurality of rudder wings and a fixing structure. The rudder wings are pivotally connected to the main body and have a deployed state and a folded state. The fixing structure has a locked state and an unlocked state. When the fixing structure is in the locked state, the rudder wings in the deployed state can be kept deployed. The aircraft can move up and down relative to the folding structure. When the aircraft moves downward relative to the folding structure, the folding structure can adjust the fixing structure to make the fixing structure in the unlocked state, and then the folding structure can fold the rudder wings. By driving the aircraft to move downward relative to the folding structure, the folding structure can simultaneously drive a plurality of rudder wings to turn upward and fold inside the main body. The folding device does not need to fold each rudder wing separately, and can fold a plurality of rudder wing surfaces of the aircraft at one time, realizing the operation of one person and one aircraft, and saving a large amount of labor force.

Description

Technical Field

[0001] The present invention relates to the field of aerospace, and particularly to a folding device for folding rudder wings. Background Art

[0002] In the field of aerospace, in order to save occupied space, it is usually necessary to fold the rudder wings of a certain aircraft and then install them in a launch tube. Existing aircraft generally have a cylindrical shape, and four rudder wings are rotatably connected to the side wall of the aircraft. When the rudder wings need to be folded inward, a manual folding method is usually adopted. The folding process requires folding the four rudder wings in sequence, which is complicated and wastes a large amount of assembly time, and is not conducive to the mass assembly of the aircraft. Summary of the Invention

[0003] The present invention aims to solve at least one of the technical problems existing in the prior art. For this purpose, the present invention provides a folding device for folding rudder wings.

[0004] A folding device for folding rudder wings according to an embodiment of the first aspect of the present invention includes an aircraft and a folding structure. The aircraft includes a main body, a plurality of rudder wings, and a fixing structure. The rudder wings are pivotally connected to the main body and have a deployed state and a folded state. The fixing structure has a locked state and an unlocked state. When the fixing structure is in the locked state, the rudder wings in the deployed state can be kept deployed; a folding structure. The aircraft can move up and down relative to the folding structure. When the aircraft moves downward relative to the folding structure, the folding structure can adjust the fixing structure to make the fixing structure in the unlocked state, and then the folding structure can fold the rudder wings.

[0005] The folding device for folding rudder wings according to an embodiment of the present invention has at least the following technical effects: driving the aircraft to move downward relative to the folding structure, the folding structure makes the fixing structure for locking the rudder wings in the unlocked state, and then the folding structure simultaneously drives a plurality of rudder wings to flip upward and fold into the main body. The folding device does not need to fold each rudder wing separately, and can fold a plurality of rudder wing surfaces of the aircraft at one time, realizing the operation of one person and one machine, and saving a large amount of labor.

[0006] According to some embodiments of the present invention, the folding structure includes a guiding portion and an unlocking member that reciprocates in the radial direction of the main body. The aircraft can drive the unlocking member to move downward so that the guiding portion can drive the unlocking member to abut against the fixing structure in the radial direction of the main body.

[0007] According to some embodiments of the present invention, the fixing structure includes a first spring and a guiding screw that can move in the radial direction of the main body. The main body has a guiding groove, and the guiding screw is slidably engaged with the guiding groove. The first spring is disposed between the guiding screw and the bottom of the first guiding groove. One end of the rudder wing close to the guiding screw is provided with a concave position that cooperates with the guiding screw.

[0008] According to some embodiments of the present invention, the folding structure includes a fixed seat, a lifting platform that can move up and down, and a second spring. The fixed seat has a sliding groove, and the lifting platform is slidably engaged with the sliding groove. A second spring is disposed between the lifting platform and the bottom of the sliding groove. The main body can be placed on the lifting platform so that the main body can drive the lifting platform to move downward along the sliding groove, and further the fixed seat can cause multiple rudder wings to rotate upward.

[0009] According to some embodiments of the present invention, the lifting platform is provided with a placement groove, and the aircraft can be placed on the placement groove. The placement groove includes a vertical through groove for placing the rudder wing, and the sliding groove has a driving portion that is slidably engaged with the vertical through groove.

[0010] According to some embodiments of the present invention, the placement groove further includes a mounting through hole. The guiding portion is a part of the inner wall of the sliding groove. The placement groove further includes a circular groove for placing the main body. The mounting through hole extends from the outer side wall of the lifting platform to the circular groove, and an unlocking member and a third spring are disposed in the mounting through hole. The third spring is used to make the unlocking member extend out of the lifting platform.

[0011] According to some embodiments of the present invention, the guiding portion includes a first inclined section, a vertical section, and a second inclined section. The first inclined section and the second inclined section are respectively located at the upper end and the lower end of the vertical section. The diameter of the first inclined section gradually decreases from top to bottom, and the diameter of the second inclined section gradually increases from top to bottom.

[0012] According to some embodiments of the present invention, when the lifting platform does not move downward, the unlocking member is located above the first inclined section.

[0013] According to some embodiments of the present invention, there is an included angle between the axis of the mounting through hole and the rudder wing.

[0014] According to some embodiments of the present invention, the main body is provided with an avoidance hole, and the avoidance hole corresponds to the positions of the rudder wing and the fixing structure.

[0015] Additional aspects and advantages of the present invention will be given in part in the following description, become apparent in part from the following description, or be learned through the practice of the invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Additional aspects and advantages of the present invention will become apparent and be readily understood from the description of embodiments in conjunction with the following drawings, wherein:

[0017] Figure 1 is a schematic structural diagram of an aircraft;

[0018] Figure 2 is a schematic structural diagram of a folding structure;

[0019] Figure 3 is a cross-sectional view of the folding device with the rudder wing not folded at the driving part;

[0020] Figure 4 is a cross-sectional view of the folding device with the rudder wing folded in half at the driving part;

[0021] Figure 5 is a cross-sectional view of the folding device with the rudder wing folded 80° at the driving part;

[0022] Figure 6 is for Figure 4 a cross-sectional view of the folding device in another direction;

[0023] Figure 7 is a cross-sectional view of the folding device with the rudder wing not folded at the unlocking part;

[0024] Figure 8 is a cross-sectional view of the folding device with the rudder wing folded in half at the unlocking part;

[0025] Figure 9 is an exploded view of the folding structure;

[0026] Figure 10 is a schematic structural diagram of the aircraft placed on the folding structure;

[0027] Figure 11 is a cross-sectional view of the folding device at the unlocking part after the unlocking part is moved to the second inclined section.

[0028] Reference numerals: aircraft 100, main body 110, guide groove 111, avoidance hole 112, rudder wing 120, concave position 121, fixing structure 200, first spring 210, guide screw 220, folding structure 300, guiding part 310, first inclined section 311, vertical section 312, second inclined section 313, unlocking part 320, fixing seat 330, sliding groove 331, driving part 3311, arc section 3312, lifting platform 340, placing groove 341, mounting through hole 342, first hole section 3421, second hole section 3422, third spring 343, vertical through groove 344, circular groove 345, second spring 350. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0029] Embodiments of the present invention will be described in detail below. Examples of the embodiments are shown in the accompanying drawings, where like or similar reference numerals denote like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0030] In the description of the present invention, it should be understood that with respect to the orientation description, such as up, down, etc., the orientation or positional relationship indicated is based on the orientation or positional relationship shown in the accompanying drawings. This is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

[0031] In the description of the present invention, the meaning of "a plurality" is two or more. If there is a description of first and second, it is only for the purpose of distinguishing technical features and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features or implicitly specifying the sequence relationship of the indicated technical features.

[0032] In the description of the present invention, unless otherwise clearly defined, words such as "set", "installed", "connected", etc. should be understood in a broad sense. Those skilled in the art can reasonably determine the specific meanings of the above words in the present invention in combination with the specific content of the technical solution.

[0033] Refer to Figure 1 、 2 As shown, a folding device for a folding rudder wing according to an embodiment of the present invention includes an aircraft 100 and a folding structure 300. The aircraft 100 includes a main body 110, a plurality of rudder wings 120, and a fixing structure 200. As Figure 3 、 5 shown, the rudder wing 120 is pivotally connected to the main body 110 and has a deployed state and a folded state. The fixing structure 200 has a locked state and an unlocked state. As Figure 3 shown, when the fixing structure 200 is in the locked state, the rudder wing 120 in the deployed state can be kept deployed; as Figure 3 、 4 、5 shown, for the folding structure 300, the aircraft 100 can move up and down relative to the folding structure 300. When the aircraft 100 moves downward, the folding structure 300 can adjust the fixing structure 200 to make the fixing structure 200 in the unlocked state, and then the folding structure 300 can fold the rudder wing 120.

[0034] For example, as Figure 1As shown, the main body 110 is in the shape of a cylinder. A plurality of rudder wings 120 are evenly distributed along the circumferential direction of the main body 110. The lower ends of the plurality of rudder wings 120 are all hinged to the main body 110. When the rudder wings 120 are in the unfolded state, the angle between the rudder wings 120 and the axis of the main body 110 is 90° or the rudder wings 120 are parallel to the horizontal plane. When the rudder wings 120 need to be folded, the rudder wings 120 are driven to rotate upward so that the rudder wings 120 are folded on the main body 110, making the rudder wings 120 perpendicular to the horizontal plane (folded state). Specifically, there are four rudder wings 120, and the angle between every two rudder wings 120 is 90°.

[0035] As Figure 3 shown, the fixing structure 200 is used to prevent the rudder wings 120 in the unfolded state from rotating relative to the main body 110, keeping the plurality of rudder wings 120 in the unfolded state. The fixing structure 200 can be switched between a locked state and an unlocked state by adjusting the fixing structure 200. When the rudder wings 120 are in the unfolded state and the fixing structure 200 is in the locked state, the fixing structure 200 can prevent the rudder wings 120 from rotating. As Figure 4 、 5 shown, when the rudder wings 120 need to be folded, the fixing structure 200 can be adjusted to make the fixing structure 200 in the unlocked state. The fixing structure 200 does not restrict the rotation of the rudder wings 120, and the rudder wings 120 can be freely folded.

[0036] The aircraft 100 is driven to move downward relative to the folding structure 300. The folding structure 300 is used to unlock the fixing structure 200 that locks the rudder wings 120. The folding structure 300 then simultaneously drives the plurality of rudder wings 120 to flip upward and fold into the main body 110. The folding device does not need to fold each rudder wing 120 separately. It can fold multiple rudder wing surfaces of the aircraft 100 at one time, realizing the operation of one person and one aircraft, saving a large amount of labor.

[0037] In some embodiments of the present invention, as Figure 2 shown, the folding structure 300 includes a guiding portion 310 and an unlocking member 320 that reciprocates in the radial direction of the main body 110. As Figure 3 、 6 shown, the aircraft 100 can drive the unlocking member 320 to move downward so that the guiding portion 310 can drive the unlocking member 320 to abut against the fixing structure 200 along the radial direction of the main body 110.

[0038] As Figure 3 、 6, as shown in FIGS. 7 and 8, during operation, the driving device drives the aircraft 100 to move downward. The aircraft 100 drives the unlocking member 320 to move downward. At the same time, the guiding portion 310 guides the unlocking member 320, and the guiding portion 310 drives the unlocking member 320 to move in the inner direction of the main body 110, so that the unlocking member 320 gradually abuts against the fixing structure 200. The unlocking member 320 adjusts the fixing structure 200, as Figure 4 , 5 shown, so that the fixing structure 200 is changed from the locked state to the unlocked state, and the rudder wing 120 can be driven by the folding structure 300 to rotate upward for folding. The number of the plurality of guiding portions 310 and the number of the plurality of unlocking members 320 are the same as the number of the plurality of rudder wings 120. One unlocking member 320 and one guiding portion 310 correspond to one rudder wing 120 one by one. The plurality of guiding portions 310 synchronously drive the plurality of unlocking members 320, and thus can synchronously bring the fixing structure 200 into the unlocked state, so that the folding structure 300 can synchronously drive the plurality of rudder wings 120 to rotate upward.

[0039] In a further embodiment of the present invention, as Figure 1 , 3 , FIGS. 4 and 5 show that the fixing structure 200 includes a first spring 210 and a guiding screw 220 that can move in the radial direction of the main body 110. The main body 110 has a guiding groove 111, and the guiding screw 220 is slidably engaged with the guiding groove 111. The first spring 210 is disposed between the guiding screw 220 and the bottom of the first guiding groove 111. One end of the rudder wing 120 close to the guiding screw 220 is provided with a concave portion 121 that cooperates with the guiding screw 220.

[0040] As Figure 3 , 7 shown, when the rudder wing 120 is in the unfolded state, under the elastic action of the first spring 210, the guiding screw 220 moves in the direction away from the inner direction of the main body 110, and the guiding screw 220 moves onto the concave portion 121 of the rudder wing 120. The guiding screw 220 prevents the rudder wing 120 from rotating upward, that is, the fixing structure 200 is in the locked state;

[0041] As Figure 4 , 5 , FIGS. 6 and 8 show that when the rudder wing 120 needs to be folded, the guiding screw 220 is moved in the inner direction of the main body 110, so that the guiding screw 220 is removed from the concave portion 121, and then the rudder wing 120 can be folded upward, that is, the fixing structure 200 is in the unlocked state.

[0042] It can be imagined that the number of the fixing structures 200 is the same as the number of the rudder wings 120, and thus the plurality of fixing structures 200 can fix the plurality of rudder wings 120.

[0043] In a further embodiment of the present invention, as Figure 2 ,9 As shown, the folding structure 300 includes a fixed seat 330, a vertically movable lifting platform 340, and a second spring 350. The fixed seat 330 has a sliding groove 331, and the lifting platform 340 is slidably engaged with the sliding groove 331. A second spring 350 is provided between the bottom of the lifting platform 340 and the sliding groove 331. As Figure 3 , 4 , 5, 10 shown, the main body 110 can be placed on the lifting platform 340, so that the main body 110 can drive the lifting platform 340 to move downward along the sliding groove 311, and then the fixed seat 330 can cause multiple rudder wings 120 to rotate upward.

[0044] When multiple rudder wings 120 need to be folded, as Figure 3 , 4 , 5 shown, place the aircraft 100 on the lifting platform 340, drive the aircraft 100 to move downward, and then the aircraft 100 drives the lifting platform 340 to move downward along the sliding groove 331. Since the main body 110 is located in the sliding groove 311, during the downward movement of the aircraft 100, the fixed seat 300 structure beside the main body 110 drives multiple rudder wings 120 to rotate upward, realizing synchronous folding of multiple rudder wings 120. Using such a structure to achieve synchronous folding is simple in structure and convenient to adjust.

[0045] In a further embodiment of the present invention, as Figure 2 , 9 shown, the lifting platform 340 is provided with a placement groove 341. The aircraft 100 can be placed on the placement groove 341. The placement groove 341 includes a vertical through groove 344 for placing the rudder wing 120. The sliding groove 331 has a driving portion 3311, and the driving portion 3311 is slidably engaged with the vertical through groove 344; the placement groove 341 further includes a mounting through hole 342. The guiding portion 310 is a part of the inner wall of the sliding groove 331. The placement groove 341 further includes a circular groove 345 for placing the main body 110. The mounting through hole 342 extends from the outer side wall of the lifting platform 340 to the circular groove 345. An unlocking member 320 and a third spring 343 are provided in the mounting through hole 342. The third spring 343 is used to make the unlocking member 320 extend out of the lifting platform 340.

[0046] For example, as Figure 2 , 9As shown, taking four rudder wings 120 as an example, a circular groove 345 sunken downward and a vertical through groove 344 are provided in the middle of the top of the lifting platform 340. The vertical through groove 344 communicates with the circular groove 345. There are four vertical through grooves 344, and the four vertical through grooves 344 are distributed in a cross shape outside the circular groove 345. The four vertical through grooves 344 and the circular groove 345 form a placement groove 341. The circular groove 345 is used to place the main body 110, and the vertical through groove 344 is used to place the rudder wing 120; the vertical through groove 344 moves up and down along the driving part 3311; when folding is required, the aircraft 100 is placed on the placement groove 341, and the placement groove 341 plays a role in quickly positioning and installing; the guiding part 310 refers to a part of the inner wall of the sliding groove 331 corresponding to the position of the rudder wing 120; as Figure 7 As shown, the installation through hole 342 has a first hole section 3421 and a second hole section 3422. The diameter of the first hole section 3421 is smaller than that of the second hole section 3422. The unlocking part 320 can pass through the first hole section 3421 and the second hole section 3422. The connection between the first hole section 3421 and the second hole section 3422 is far from the inner wall of the sliding groove 331. A third spring 343 is provided between the connection between the first hole section 3421 and the second hole section 3422 and the unlocking part 320. The third spring 343 can keep the unlocking part 320 abutted against the guiding part 310.

[0047] Combined with the above description, as Figure 3 、 10 As shown, when the folding structure 300 is not folded, the lifting platform 340 is at the highest position of the sliding groove 331 under the action of the second spring 350, as Figure 3 、 7 As shown, the unlocking part 320 extends out of the lifting platform 340 under the action of the third spring 343, that is, the unlocking part 320 does not adjust the fixing structure 200; when the rudder wing 120 needs to be folded, as Figure 10 As shown, the aircraft 100 in the unfolded state is placed on the placement groove 341, the main body 110 is placed in the circular groove 345, and the four rudder wings 120 are respectively placed in the four vertical through grooves 344. The positions of the fixing structure 200, the rudder wing 120, the unlocking part 320 and the guiding part 310 correspond to each other. Drive the aircraft 100 to move downward, as Figure 4 、 6, as shown in FIGS. 8, when the lifting platform 340 moves downward, the guiding portion 310 (the inner wall corresponding to the position of the sliding groove 331 and the guiding portion 310) causes the unlocking member 320 to gradually move in the direction of the inside of the lifting platform 340, so that the unlocking member 320 adjusts the fixing structure 200 (the unlocking member 320 extends into the main body 110 to drive the guiding screw 220 to move in the direction of the inside of the main body 110, so that the guiding screw 220 moves out of the concave position 121), making the fixing structure 200 in an unlocked state, enabling the rudder wing 120 to move upward. At the same time, during the downward movement of the aircraft 100, since the fixing structure 200 is in an unlocked state, as Figure 9 shown, the vertical through groove 344 moves downward along the driving portion 3311, as Figure 4 , 5 , 10 shown, the driving portion 3311 gradually rotates and folds a plurality of rudder wings 120 upward synchronously.

[0048] In a further embodiment of the present invention, as Figure 6 , 11 shown, the guiding portion 310 includes a first inclined section 311, a vertical section 312, and a second inclined section 313. The first inclined section 311 and the second inclined section 313 are respectively located at the upper end and the lower end of the vertical section 312. The diameter of the first inclined section 311 gradually decreases from top to bottom, and the diameter of the second inclined section 313 gradually increases from top to bottom.

[0049] When the lifting platform 340 gradually moves downward, as Figure 6 shown, the first inclined section 311 can gradually drive the unlocking member 320 to move in the direction of the inside of the lifting platform 340, so that the unlocking member 320 drives the guiding screw 220 to move in the direction of the inside of the main body 110, as Figure 4 , 8 shown, to move the guiding screw 220 out of the concave position 121. As Figure 6 , 8 shown, when the lifting platform 340 moves to the vertical section 312, the vertical section 312 can keep the unlocking member 320 inside the lifting platform 340 all the time, enabling the driving portion 3311 to continuously drive a plurality of rudder wings 120 to rotate upward. As Figure 11 shown, when the lifting platform 340 moves to the second inclined section 313, a plurality of rudder wings 120 are folded. The unlocking member 320 extends out of the lifting platform 340 under the action of the elastic recovery of the third spring 343, so that the unlocking member 320 moves out of the main body 110, enabling the folded aircraft 100 to be removed from the lifting platform 340 and the fixed seat 330; after the aircraft 100 is taken out, the lifting platform 340 moves upward under the action of the second spring 350 to return to the original position, facilitating the folding of the next aircraft 100; among them, before taking out the folded aircraft 100, it is only necessary to fix a plurality of folded rudder wings 120 and then the folded aircraft 100 can be taken out from the folding structure 300.

[0050] In a further embodiment of the present invention, as Figure 2 shown, when the lifting platform 340 does not move downward, the unlocking member 320 is located above the first inclined section 311, ensuring that the unlocking member 320 does not extend into the circular groove 345, and thus ensuring that the aircraft 100 can be placed.

[0051] In a further embodiment of the present invention, as Figure 7 shown, there is an included angle between the axis of the mounting through hole 342 and the rudder wing 120, so that the upward rotation of the rudder wing 120 and the movement of the unlocking member 320 do not conflict.

[0052] In a further embodiment of the present invention, as Figure 1 、 7 shown, the main body 110 is provided with an avoidance hole 112, and the avoidance hole 112 corresponds to the position of the rudder wing 120 and the position of the fixing structure 200, so as to facilitate the rotation of the rudder wing 120 and the unlocking member 320 to extend into the main body 110.

[0053] In a further embodiment of the present invention, as Figure 3 shown, the top of the sliding groove 331 has an arc section 3312 to facilitate driving a plurality of rudder wings 120 to rotate upward.

[0054] In the description of this specification, the description referring to terms such as "some embodiments" or "it is conceivable that" means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in a suitable manner in any one or more embodiments or examples.

[0055] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and purposes of the present invention, and the scope of the present invention is defined by the claims and their equivalents.

Claims

1. A folding device for a folding rudder wing, characterized in that, Comprising: An aircraft, including a main body, a plurality of rudder wings and a fixing structure, the rudder wings are pivotally connected to the main body and have a deployed state and a folded state, the fixing structure has a locked state and an unlocked state, and when the fixing structure is in the locked state, the rudder wings in the deployed state can be kept deployed; A folding structure, the aircraft can move up and down relative to the folding structure, and when the aircraft moves downward relative to the folding structure, the folding structure can adjust the fixing structure to make the fixing structure in the unlocked state, and then the folding structure can fold the rudder wings; The fixing structure includes a first spring and a guiding screw that can move in the radial direction of the main body, the main body has a guiding groove, the guiding screw is slidably matched with the guiding groove, the first spring is arranged between the guiding screw and the bottom of the guiding groove, and a concave position matched with the guiding screw is arranged at one end of the rudder wing close to the guiding screw; The folding structure includes a fixed seat, a lift platform that can move up and down, and a second spring. The fixed seat has a sliding groove, the lift platform is slidably matched with the sliding groove, and a second spring is arranged between the lift platform and the bottom of the sliding groove. The main body can be placed on the lift platform so that the main body can drive the lift platform to move downward along the sliding groove, and then the fixed seat can make the plurality of rudder wings rotate upward; The lift platform is provided with a placement groove, the aircraft can be placed on the placement groove, the placement groove includes a vertical through groove for placing the rudder wings, the sliding groove has a driving part, and the driving part is slidably matched with the vertical through groove; The placement groove further includes a mounting through hole, the guiding part is a part of the inner wall of the sliding groove, the placement groove further includes a circular groove for placing the main body, the mounting through hole extends from the outer side wall of the lift platform to the circular groove, and an unlocking part and a third spring are arranged in the mounting through hole, and the third spring is used to make the unlocking part extend out of the lift platform; 2. The folding device for a folding rudder wing according to claim 1, characterized in that: The folding structure includes a guiding part and an unlocking part that reciprocates in the radial direction of the main body, and the aircraft can drive the unlocking part to move downward so that the guiding part can drive the unlocking part to abut against the fixing structure in the radial direction of the main body; 3. The folding device for a folding rudder wing according to claim 1, characterized in that: The guiding part includes a first inclined section, a vertical section and a second inclined section. The first inclined section and the second inclined section are respectively located at the upper end and the lower end of the vertical section. The diameter of the first inclined section gradually decreases from top to bottom, and the diameter of the second inclined section gradually increases from top to bottom; 4. The folding device for a folding rudder wing according to claim 3, characterized in that: When the lift platform does not move downward, the unlocking part is located above the first inclined section; 5. The folding device for folding rudder wings according to claim 1, characterized in that: There is an included angle between the axis of the mounting through hole and the rudder wing; 6. The folding device for a folding rudder wing according to claim 5, characterized in that: The main body is provided with an avoidance hole, and the position of the avoidance hole corresponds to the position of the rudder wing and the position of the fixing structure.

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