A folding configuration for a manned aircraft wing

Abstract

The application relates to the technical field of manned aircrafts, in particular to a folding structure for a manned aircraft wing, which comprises a mounting frame, a mounting plate fixedly connected to the upper end of the mounting frame, and two groups of rotor parts fixedly arranged on the two sides of the mounting frame and fixedly connected to the body of the manned aircraft; the upper end of the mounting plate is fixedly provided with a drag reduction assembly and two groups of folding assemblies, the two groups of folding assemblies respectively penetrate from the two sides of the drag reduction assembly, one side of each of the two groups of folding assemblies is provided with a wing, and the two sides of the mounting plate are fixedly connected with supporting strips and lifting frames. Through the arrangement of the drag reduction assembly, the folding assembly and the wing, the wing can be completely close to the mounting plate when being folded, the drag generated by the wing during the vertical lifting of the manned aircraft is greatly reduced, the energy consumption during the vertical lifting of the manned aircraft is reduced, the sailing time is prolonged, and self-lubrication can be realized when the first mounting block and the pin shaft rotate.

Description

Technical Field

[0001] This invention relates to the field of manned aircraft technology, and more particularly to a folding structure for the wings of manned aircraft. Background Technology

[0002] A manned aircraft is an aircraft that can carry one or more occupants and fly in the air by its own power or external lift. Existing manned aircraft are usually folded up when taking off to reduce drag.

[0003] For example, Chinese patent CN111731466A discloses an aircraft with an automatically folding wing. The aircraft includes a fuselage, and wing assemblies are respectively arranged on the left and right sides of the fuselage. The wing assembly includes an inner wing, an outer wing, and a folding drive mechanism. The inner side of the inner wing is connected to the fuselage, and the outer side of the inner wing is connected to the inner side of the outer wing. One end of the folding drive mechanism is installed on the inner wing, and the other end of the folding drive mechanism is installed on the outer wing. The folding drive mechanism unfolds or folds the outer wing.

[0004] The aforementioned device achieves the folding function of the wings of a manned aircraft by folding the wings upwards. However, in actual use, folding the wings upwards has a limited effect on reducing the wind-receiving area of ​​the wings, resulting in significant drag and high energy consumption during vertical takeoff and landing. Furthermore, the rotating structure of the wings in the existing technology requires manual lubrication, which not only increases labor costs but also easily leads to mechanical jamming when the wings are folded multiple times, making it difficult for the rotor to unfold, posing a significant safety risk. Summary of the Invention

[0005] The purpose of this invention is to solve the problems in the prior art where folding the wings upwards has a limited effect on reducing the wind-receiving area of ​​the wings and that mechanical jamming can easily occur when the wings are folded multiple times, making it difficult for the rotor to unfold. Therefore, this invention proposes a folding structure for the wings of manned aircraft.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: a folding structure for a manned aircraft wing, comprising a mounting frame and a mounting plate fixedly connected to the upper end of the mounting frame, the lower end of the mounting frame being fixedly connected to the manned aircraft body, two sets of rotors being fixedly mounted on both sides of the mounting frame, a drag reduction component and two sets of folding components being fixedly provided on the upper end of the mounting plate, and the two sets of folding components being centrally symmetrical, the two sets of folding components passing through both sides of the drag reduction component respectively, a wing being provided on one side of each set of folding components, a support bar and a lifting frame being fixedly connected to both sides of the mounting plate, and the lifting frame contacting the lower end of the wing, the support bar being located below the folding position of the wing; The folding assembly includes a linear moving part and a shielding shell fixedly connected to the upper end of the mounting plate. A transmission component is provided on one side of the linear moving part. A first limiting component is provided on the upper end of the mounting plate, and a second limiting component is provided on one side of the mounting plate. The first limiting component and the second limiting component are components made of the same structure. A connecting component is provided between the first limiting component and the second limiting component. One end of the transmission component is located inside the shielding shell. A first gear and a second gear are spaced apart on the inner side of the connecting component. The first gear is arranged perpendicular to the horizontal plane, and the second gear is arranged parallel to the horizontal plane. Both the first gear and the second gear mesh with the transmission component.

[0007] Preferably, the second limiting component includes a fixing block fixedly connected to one side of the mounting plate, a second sliding plate being slidably connected to the upper end of the fixing block, an electric telescopic rod being fixedly connected inside the fixing block, one end of the electric telescopic rod being fixedly connected to one side of the second sliding plate, and a groove for the second sliding plate to slide on the upper end of the fixing block.

[0008] Preferably, the connecting component includes a first connecting member fixedly disposed on one side of the first limiting component and a fourth connecting member fixedly disposed on the upper end of the second limiting component. The second sliding plate is in contact with one side of the fourth connecting member. The first connecting member is fixedly connected to the second connecting member via a connecting rod, and the second connecting member is fixedly connected to the third connecting member via a connecting rod. A connecting rod is fixedly disposed between the third connecting member and the fourth connecting member. The first connecting member and the third connecting member are coaxially disposed. After the second connecting member is rotated 90 degrees counterclockwise, it is coaxially disposed with the fourth connecting member. The wing is fixedly disposed on the connecting rod between the second connecting member and the third connecting member via an L-shaped bracket.

[0009] Preferably, the first connector includes a first mounting block fixedly connected to one side of the first limiting component, a pin rotatably connected through the inner side of the first mounting block, a second mounting block fixedly connected through one end of the pin, and the second mounting block in contact with the first mounting block. The first mounting block has a cavity inside, and lubricating oil is placed inside the cavity. An oil inlet pipe and a sealing cap are installed on one side of the first mounting block.

[0010] Preferably, an arc-shaped sliding plate is slidably connected to the inner wall of the first mounting block, and multiple sets of liquid outlet holes are opened at the position where the first mounting block contacts the middle of the arc-shaped sliding plate. A sliding groove is opened inside the first mounting block for the arc-shaped sliding plate to slide. Springs are fixedly connected between both ends of the arc-shaped sliding plate and the sliding groove. A transmission bar is fixedly connected to the side of the arc-shaped sliding plate facing the pin shaft. Through holes are opened at both ends of the arc-shaped sliding plate that do not coincide with the liquid outlet holes.

[0011] Preferably, a protrusion is slidably connected to the outer surface of the pin, and a groove is provided inside the pin for the protrusion to slide in, with the direction of the groove being consistent with the radial direction of the pin. A spring is fixedly connected between one end of the protrusion and the groove, and the other end of the protrusion is provided as a sponge strip.

[0012] Preferably, the transmission component includes an L-shaped transmission plate fixedly connected to one side of the linear moving part, a first rack fixedly connected to the upper end of the L-shaped transmission plate, a second rack fixedly connected to the inner side of the L-shaped transmission plate, and the first rack and the second rack are staggered, with the first rack disposed between the second rack and the shielding housing.

[0013] Preferably, the first gear is fixedly connected to the end of the second mounting block away from the first mounting block via a fixing tube, and the second gear is fixedly connected to the end of the fourth connector away from the fixing block via a fixing tube. Both the first gear and the second gear are disposed inside the shielding housing. The first gear is meshed with the first rack, and the second gear is meshed with the second rack.

[0014] Preferably, the drag reduction assembly includes a first housing fixedly connected to the upper end of the mounting plate and a second housing rotatably connected to the outer surface of the first housing. Two sets of the first housing and the second housing are symmetrically arranged. A transmission rod is fixedly connected to the outer surface of the second housing, and the length direction of the transmission rod is perpendicular to the length direction of the mounting plate. A notch for placing the wing is provided on one side of the first housing.

[0015] Preferably, a baffle plate is fixedly connected between the two sets of first housings, and clearance holes are provided on both sides of the baffle plate. An arc-shaped spring telescopic rod is fixedly connected to the inner side of the first housing, and a first sliding plate is fixedly connected to one end of the arc-shaped spring telescopic rod. One end of the first sliding plate passes through the first housing and is fixedly connected to the second housing, and a sliding groove is provided on the first housing for the first sliding plate to slide.

[0016] Compared with existing technologies, the advantages of this invention are: This invention achieves automatic wing folding by setting up drag-reducing components, folding components, and wings. Compared with the upward folding effect of existing technologies, the wings in this invention can completely close to the mounting plate when folded, which greatly reduces the drag generated by the wings during the vertical takeoff and landing of the manned aircraft. This reduces the energy consumption of the manned aircraft during vertical takeoff and landing, extends the flight time, and can protect the folding component structure during horizontal flight. It also improves the situation where airflow enters through the gap of the first shell during horizontal flight. With the setting of the movable second shell, it can adapt to different wing folding states. This invention, through the design of the connecting components, enables self-lubrication when the first mounting block and the pin rotate, avoiding structural jamming due to insufficient lubrication. This allows the wing to fold and unfold stably, improving the safety of the folding structure. Furthermore, lubricating oil can only flow out from the outlet and through holes during rotation, effectively saving lubricating oil consumption and avoiding insufficient lubricating oil or the need for frequent replenishment during flight. The protrusions and sponge strips also improve the uniformity of lubricating oil distribution, enhancing the lubrication effect. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the overall structure of a folding structure for a manned aircraft wing proposed in this invention; Figure 2 This is a schematic diagram of the folded state of the wing of the present invention; Figure 3 This is a schematic diagram of a folding assembly, wing, landing gear, and support bar structure for a folding structure of a manned aircraft wing proposed in this invention; Figure 4 This is a schematic diagram of a folding assembly and wing structure for a folding structure of a manned aircraft wing proposed in this invention. Figure 5 This is a schematic diagram of the second limiting component and the fourth connecting component of a folding structure for a manned aircraft wing proposed in this invention; Figure 6 This is a schematic diagram of the first mounting block, pin, and second mounting block structure of a folding structure for a manned aircraft wing proposed in this invention. Figure 7 This invention provides a schematic diagram of the connecting component structure for a folding structure of a manned aircraft wing. Figure 1 ; Figure 8 This invention provides a schematic diagram of the connecting component structure for a folding structure of a manned aircraft wing. Figure 2 ; Figure 9 This is a schematic diagram showing the first mounting block and the arc-shaped sliding plate structure of a folding structure for a manned aircraft wing proposed in this invention. Figure 10 This is a cross-sectional view of a drag-reducing component structure for a folding structure of a manned aircraft wing proposed in this invention.

[0018] In the diagram: 1. Mounting bracket; 2. Mounting plate; 3. Rotor section; 4. Drag reduction assembly; 41. First housing; 42. Second housing; 43. Transmission rod; 44. Baffle plate; 45. Clearance hole; 46. Arc-shaped spring telescopic rod; 47. First sliding plate; 48. Clearance groove; 5. Folding assembly; 51. Linear moving part; 52. Transmission component; 521. L-shaped transmission plate; 522. First rack; 523. Second rack; 53. First limiting component; 54. Baffle housing; 55. Connecting component; 551. First connecting piece; 55 11. First mounting block; 5512. Pin; 5513. Second mounting block; 5514. Cavity; 5515. Arc-shaped sliding plate; 5516. Protrusion; 5517. Transmission bar; 5518. Liquid outlet; 5519. Through hole; 552. Second connecting piece; 553. Third connecting piece; 554. Fourth connecting piece; 56. Second limiting component; 561. Fixing block; 562. Electric telescopic rod; 563. Second sliding plate; 57. First gear; 58. Second gear; 6. Wing; 7. Lifting frame; 8. Support bar. Detailed Implementation

[0019] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0020] like Figures 1-10 As shown, a folding structure for a manned aircraft wing includes a mounting frame 1 and a mounting plate 2 fixedly connected to the upper end of the mounting frame 1. The lower end of the mounting frame 1 is fixedly connected to the manned aircraft body. Two sets of rotor parts 3 are fixedly installed on both sides of the mounting frame 1. A drag-reducing component 4 and two sets of folding components 5 are fixedly installed on the upper end of the mounting plate 2. The two sets of folding components 5 are centrally symmetrical and pass through both sides of the drag-reducing component 4. A wing 6 is provided on one side of each set of folding components 5. Support bars 8 and lifting frames 7 are fixedly connected to both sides of the mounting plate 2. The lifting frames 7 are positioned in contact with the lower end of the wing 6. The support bars 8 are positioned below the folded position of the wing 6. The folding components 5 are used to change the position of the wing 6. The drag-reducing component 4 is used to protect the folding components 5 and reduce the turbulence and drag generated by the folding components 5 during flight. The lifting frames 7 and support bars 8 are used to support the wing 6. Since the height of the lifting frames 7 is adjustable, it can adapt to different states of the wing 6. The folding assembly 5 includes a linear moving part 51 and a blocking housing 54 fixedly connected to the upper end of the mounting plate 2. A transmission component 52 is provided on one side of the linear moving part 51. A first limiting component 53 is provided on the upper end of the mounting plate 2, and a second limiting component 56 is provided on one side of the mounting plate 2. The first limiting component 53 and the second limiting component 56 are components made of the same structure. A connecting component 55 is provided between the first limiting component 53 and the second limiting component 56. One end of the transmission component 52 is located inside the blocking housing 54. A first gear 57 and a second gear 58 are spaced apart on the inner side of the connecting component 55. The first gear 57 is set perpendicular to the horizontal plane, and the second gear 58 is set parallel to the horizontal plane. Both the first gear 57 and the second gear 58 mesh with the transmission component 52. It should be noted that the linear reciprocating movement of the transmission component 52 is achieved by the linear moving part 51, which is a known prior art. Those skilled in the art are capable of conceiving of the specific structure. The first limiting part 53 and the second limiting part 56 are used to limit the rotation of the connecting part 55. The transmission component 52, the first gear 57 and the second gear 58 are all used to drive the connecting part 55 to rotate, thereby realizing the folding of the wing 6.

[0021] The second limiting component 56 includes a fixing block 561 fixedly connected to one side of the mounting plate 2. A second sliding plate 563 is slidably connected to the upper end of the fixing block 561. An electric telescopic rod 562 is fixedly connected inside the fixing block 561. One end of the electric telescopic rod 562 is fixedly connected to one side of the second sliding plate 563. A groove is provided on the upper end of the fixing block 561 for the second sliding plate 563 to slide. The second sliding plate 563 can be controlled to slide on the upper end of the fixing block 561 by the electric telescopic rod 562.

[0022] The connecting component 55 includes a first connecting member 551 fixedly disposed on one side of the first limiting component 53 and a fourth connecting member 554 fixedly disposed on the upper end of the second limiting component 56. A second sliding plate 563 is in contact with one side of the fourth connecting member 554. A second connecting member 552 is fixedly connected to one side of the first connecting member 551 via a connecting rod. A third connecting member 553 is fixedly connected to one side of the second connecting member 552 via a connecting rod. A connecting rod is fixedly disposed between the third connecting member 553 and the fourth connecting member 554. The first connecting member 551 and the third connecting member 553 are coaxially disposed. After the second connecting member 552 is rotated 90 degrees counterclockwise, it is coaxially disposed with the fourth connecting member 554. The wing 6 is fixedly disposed on the connecting rod between the second connecting member 552 and the third connecting member 553 via an L-shaped bracket. The first limiting component 53 and the second sliding plate 563 are used to fix the angle of the first connecting member 551 and the fourth connecting member 554. By blocking the second sliding plate 563, the rotation of the fourth connecting member 554 can be prevented, thereby achieving the limiting.

[0023] The first connecting member 551 includes a first mounting block 5511 fixedly connected to one side of the first limiting member 53. A pin 5512 is rotatably connected through the inner side of the first mounting block 5511. One end of the pin 5512 is fixedly connected through a second mounting block 5513, and the second mounting block 5513 contacts the first mounting block 5511. A cavity 5514 is opened inside the first mounting block 5511, and lubricating oil is placed inside the cavity 5514. An oil inlet pipe and a sealing cap are installed on one side of the first mounting block 5511.

[0024] An arc-shaped sliding plate 5515 is slidably connected to the inner wall of the first mounting block 5511. Multiple sets of liquid outlet holes 5518 are provided at the position where the first mounting block 5511 contacts the middle of the arc-shaped sliding plate 5515. A sliding groove is provided inside the first mounting block 5511 for the arc-shaped sliding plate 5515 to slide. Springs are fixedly connected to both ends of the arc-shaped sliding plate 5515 and the sliding groove. A transmission bar 5517 is fixedly connected to the side of the arc-shaped sliding plate 5515 facing the pin shaft 5512. Through holes 5519 are provided at both ends of the arc-shaped sliding plate 5515 that do not coincide with the liquid outlet holes 5518. The two sets of springs can limit the position of the arc-shaped sliding plate 5515 when it is not under force. Moving the transmission bar 5517 can drive the arc-shaped sliding plate 5515 to rotate. When the through hole 5519 coincides with the liquid outlet hole 5518, the lubricating oil flowing out of the liquid outlet hole 5518 can pass through the through hole 5519 and contact the pin shaft 5512.

[0025] The outer surface of the pin 5512 is slidably connected to a protrusion 5516. The pin 5512 has a groove inside for the protrusion 5516 to slide, and the direction of the groove is consistent with the radial direction of the pin 5512. One end of the protrusion 5516 is fixedly connected to the groove with a spring, and the other end of the protrusion 5516 is set as a sponge strip. The arc-shaped sliding plate 5515, the protrusion 5516 and the transmission strip 5517 are symmetrically arranged in two sets. The spring is used to push the protrusion 5516 out of the surface of the mounting plate 2, and the sponge strip is used to apply lubricating oil.

[0026] The transmission component 52 includes an L-shaped transmission plate 521 fixedly connected to one side of the linear moving part 51. A first rack 522 is fixedly connected to the upper end of the L-shaped transmission plate 521, and a second rack 523 is fixedly connected to the inner side of the L-shaped transmission plate 521. The first rack 522 and the second rack 523 are staggered. The first rack 522 is located between the second rack 523 and the shielding housing 54. The linear moving part 51 can control the linear reciprocating movement of the L-shaped transmission plate 521.

[0027] The first gear 57 is fixedly connected to the end of the second mounting block 5513 away from the first mounting block 5511 via a fixing tube. The second gear 58 is fixedly connected to the end of the fourth connector 554 away from the fixing block 561 via a fixing tube. Both the first gear 57 and the second gear 58 are located inside the shielding housing 54. The first gear 57 is meshed with the first rack 522, and the second gear 58 is meshed with the second rack 523. The linear reciprocating movement of the L-shaped transmission plate 521 can drive the first gear 57 and the second gear 58 to rotate. The shielding housing 54 is used to protect the first gear 57 and the second gear 58.

[0028] The drag reduction assembly 4 includes a first housing 41 fixedly connected to the upper end of the mounting plate 2 and a second housing 42 rotatably connected to the outer surface of the first housing 41. The first housing 41 and the second housing 42 are symmetrically arranged in two sets. A transmission rod 43 is fixedly connected to the outer surface of the second housing 42, and the length direction of the transmission rod 43 is perpendicular to the length direction of the mounting plate 2. A notch for placing the wing 6 is provided on one side of the first housing 41. When the transmission rod 43 is pushed, the second housing 42 can rotate on the outer surface of the first housing 41.

[0029] A baffle plate 44 is fixedly connected between the two sets of first housings 41. Both sides of the baffle plate 44 are provided with clearance holes 45. An arc-shaped spring telescopic rod 46 is fixedly connected to the inner side of the first housing 41. One end of the arc-shaped spring telescopic rod 46 is fixedly connected to a first sliding plate 47. One end of the first sliding plate 47 passes through the first housing 41 and is fixedly connected to the second housing 42. The first housing 41 is provided with a sliding groove for the first sliding plate 47 to slide. The arc-shaped spring telescopic rod 46 is used to pull the first sliding plate 47 to reset the second housing 42. The movement of the second housing 42 can adapt to the folding use of the wing 6.

[0030] In this invention, when the manned aircraft ascends vertically, the wings 6 need to be folded. The electric telescopic rod 562 moves the second sliding plate 563 away from the fourth connecting member 554, thereby releasing the restriction on the fourth connecting member 554. Similarly, the first limiting component 53 releases the restriction on the first connecting member 551. Then, the linear moving part 51 moves the transmission component 52 a certain distance. During this movement, the first rack 522 and the second rack 523 cause the first gear 57 to rotate 90 degrees first, followed by the second gear 58 rotating 90 degrees. This allows the wings 6, initially horizontal, to first rotate vertically. In this process, by adjusting the height of the lifting frame 7, the wing 6 can be supported in both horizontal and vertical positions. Then, the wing 6 will rotate towards the first housing 41. When the wing 6 rotates, it will first contact the transmission rod 43, causing the second housing 42 to rotate and embed into the clearance groove 48. At this time, the wing 6 is placed vertically on the upper end of the support bar 8. Then, the first limiting component 53 and the second limiting component 56 press and fix the first connecting member 551 and the fourth connecting member 554, thereby fixing the position of the wing 6. At this time, the four sets of rotors 3 can achieve vertical take-off and landing of the manned aircraft. Through the folding of the two sets of wings 6, there is... This effectively reduces the wind-caught area of ​​the wing 6 during vertical takeoff and landing. When the manned aircraft is flying horizontally, the wings 6 need to be deployed. At this time, the linear moving part 51 causes the transmission part 52 to move and reset, causing the first gear 57 to rotate 90 degrees first, and then the second gear 58 to rotate 90 degrees. This causes the wings 6 to rotate away from the first shell 41 first, and then rotate horizontally, thus enabling both sets of wings 6 to be deployed, thereby maintaining the horizontal flight requirements of the manned aircraft. When the wings 6 move away from the first shell 41, the elastic force of the arc-shaped spring telescopic rod 46 can pull the second shell 42 back to its original position, thus enabling... The folding component 5 provides protection for the structure during horizontal flight, improving the situation where airflow enters through the gap in the first shell 41 during horizontal flight. The movable second shell 42 allows it to adapt to different folding states of the wing 6. Through the setup of the drag reduction component 4, the folding component 5, and the wing 6, the automatic folding function of the wing 6 is achieved. Compared to the upward folding effect in the prior art, the wing 6 in this invention can completely fit close to the mounting plate 2 when folded, greatly reducing the drag generated by the wing 6 during the vertical takeoff and landing of the manned aircraft, thereby reducing the energy consumption of the manned aircraft during vertical takeoff and landing and extending the flight time. During the folding process of wing 6, pin 5512 reciprocates inside the first mounting block 5511. During this process, protrusion 5516 actuates transmission bar 5517, causing arc-shaped sliding plate 5515 to deflect. At this time, lubricating oil inside cavity 5514 can contact pin 5512 and protrusion 5516 through outlet hole 5518 and through hole 5519. As pin 5512 rotates, the overflowing lubricating oil is dispersed to the contact surface between pin 5512 and the first mounting block 5511, thus achieving lubrication. Simultaneously, the sponge strip at the end of protrusion 5516 absorbs some lubricating oil, and upon contact with the first mounting block 5511, the spring inside pin 5512 squeezes the lubricating oil out of the sponge strip and evenly coats the contact surface between the first mounting block 5511 and pin 5512, improving lubrication. The oil distribution is uniform until the protrusion 5516 is pressed into the pin 5512 by the first mounting block 5511. At this time, under the action of two sets of springs, the arc-shaped sliding plate 5515 will move and reset, and the lubricating oil cannot flow out from the outlet hole 5518. Through the setting of the connecting component 55, the first mounting block 5511 and the pin 5512 can achieve self-lubrication when they rotate, avoiding the situation of insufficient lubrication causing the structure to jam. This allows the wing 6 to fold and unfold stably, improving the safety of the folding structure. Moreover, the lubricating oil can only flow out from the outlet hole 5518 and the through hole 5519 during rotation, effectively saving the amount of lubricating oil used and avoiding the situation of insufficient lubricating oil or the need for frequent replenishment during flight. The setting of the protrusion 5516 and the sponge strip also improves the uniformity of the lubricating oil distribution and enhances the lubrication effect.

[0031] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A folding structure for the wing of a manned aircraft, comprising a mounting frame (1) and a mounting plate (2) fixedly connected to the upper end of the mounting frame (1), the lower end of the mounting frame (1) being fixedly connected to the fuselage of the manned aircraft, and two sets of rotor sections (3) being fixedly mounted on both sides of the mounting frame (1), characterized in that, The upper end of the mounting plate (2) is fixedly provided with a drag-reducing component (4) and two sets of folding components (5), and the two sets of folding components (5) are symmetrically positioned. The two sets of folding components (5) pass through both sides of the drag-reducing component (4). A wing (6) is provided on one side of each set of folding components (5). Support bars (8) and lifting frames (7) are fixedly connected to both sides of the mounting plate (2). The lifting frames (7) are in contact with the lower end of the wing (6), and the support bars (8) are located below the folding position of the wing (6). The folding assembly (5) includes a linear moving part (51) and a shielding shell (54) fixedly connected to the upper end of the mounting plate (2). A transmission component (52) is provided on one side of the linear moving part (51). A first limiting component (53) is provided on the upper end of the mounting plate (2). A second limiting component (56) is provided on one side of the mounting plate (2). The first limiting component (53) and the second limiting component (56) are components made of the same structure. A connecting component (55) is provided between the first limiting component (53) and the second limiting component (56). One end of the transmission component (52) is provided inside the shielding shell (54). A first gear (57) and a second gear (58) are provided at intervals on the inner side of the connecting component (55). The first gear (57) is set perpendicular to the horizontal plane, and the second gear (58) is set parallel to the horizontal plane. Both the first gear (57) and the second gear (58) mesh with the transmission component (52).

2. The folding structure for a manned aircraft wing according to claim 1, characterized in that, The second limiting component (56) includes a fixing block (561) fixedly connected to one side of the mounting plate (2), a second sliding plate (563) is slidably connected to the upper end of the fixing block (561), an electric telescopic rod (562) is fixedly connected inside the fixing block (561), one end of the electric telescopic rod (562) is fixedly connected to one side of the second sliding plate (563), and a groove is provided on the upper end of the fixing block (561) for the second sliding plate (563) to slide.

3. The folding structure for a manned aircraft wing according to claim 2, characterized in that, The connecting component (55) includes a first connector (551) fixedly disposed on one side of the first limiting component (53) and a fourth connector (554) fixedly disposed on the upper end of the second limiting component (56). The second sliding plate (563) is in contact with one side of the fourth connector (554). The first connector (551) is fixedly connected to the second connector (552) by a connecting rod. The second connector (552) is fixedly connected to the third connector (553) by a connecting rod. A connecting rod is fixedly disposed between the third connector (553) and the fourth connector (554). The first connector (551) and the third connector (553) are coaxially disposed. The second connector (552) is coaxially disposed with the fourth connector (554) after rotating counterclockwise by 90 degrees. The wing (6) is fixedly disposed on the connecting rod between the second connector (552) and the third connector (553) by an L-shaped bracket.

4. A folding structure for a manned aircraft wing according to claim 3, characterized in that, The first connector (551) includes a first mounting block (5511) fixedly connected to one side of the first limiting component (53). A pin (5512) is rotatably connected through the inner side of the first mounting block (5511). One end of the pin (5512) is fixedly connected through a second mounting block (5513), and the second mounting block (5513) is in contact with the first mounting block (5511). A cavity (5514) is opened inside the first mounting block (5511), and lubricating oil is placed inside the cavity (5514). An oil inlet pipe and a sealing cap are installed on one side of the first mounting block (5511).

5. A folding structure for a manned aircraft wing according to claim 4, characterized in that, The inner wall of the first mounting block (5511) is fitted with an arc-shaped sliding plate (5515), and multiple sets of liquid outlet holes (5518) are opened at the position where the first mounting block (5511) and the arc-shaped sliding plate (5515) are in contact. The inside of the first mounting block (5511) is provided with a sliding groove for the arc-shaped sliding plate (5515) to slide. Springs are fixedly connected between both ends of the arc-shaped sliding plate (5515) and the sliding groove. A transmission bar (5517) is fixedly connected to the side of the arc-shaped sliding plate (5515) facing the pin (5512). Through holes (5519) are opened at both ends of the arc-shaped sliding plate (5515) that do not coincide with the liquid outlet holes (5518).

6. A folding structure for a manned aircraft wing according to claim 5, characterized in that, The outer surface of the pin (5512) is engaged and slidably connected with a protrusion (5516). The inside of the pin (5512) is provided with a sliding groove for the protrusion (5516) to slide, and the direction of the sliding groove is consistent with the radial direction of the pin (5512). One end of the protrusion (5516) is fixedly connected to the sliding groove with a spring, and the other end of the protrusion (5516) is set as a sponge strip.

7. A folding structure for a manned aircraft wing according to claim 4, characterized in that, The transmission component (52) includes an L-shaped transmission plate (521) fixedly connected to one side of the linear moving part (51). A first rack (522) is fixedly connected to the upper end of the L-shaped transmission plate (521), and a second rack (523) is fixedly connected to the inner side of the L-shaped transmission plate (521). The first rack (522) and the second rack (523) are staggered, and the first rack (522) is located between the second rack (523) and the shielding housing (54).

8. A folding structure for a manned aircraft wing according to claim 1, characterized in that, The first gear (57) is fixedly connected to the end of the second mounting block (5513) away from the first mounting block (5511) through a fixing tube. The second gear (58) is fixedly connected to the end of the fourth connector (554) away from the fixing block (561) through a fixing tube. The first gear (57) and the second gear (58) are both located inside the shielding housing (54). The first gear (57) is meshed with the first rack (522), and the second gear (58) is meshed with the second rack (523).

9. A folding structure for a manned aircraft wing according to claim 1, characterized in that, The drag reduction assembly (4) includes a first housing (41) fixedly connected to the upper end of the mounting plate (2) and a second housing (42) rotatably connected to the outer surface of the first housing (41). The first housing (41) and the second housing (42) are symmetrically arranged in two sets. A transmission rod (43) is fixedly connected to the outer surface of the second housing (42). The length direction of the transmission rod (43) is perpendicular to the length direction of the mounting plate (2). A notch for placing the wing (6) is provided on one side of the first housing (41).

10. A folding structure for a manned aircraft wing according to claim 9, characterized in that, A baffle plate (44) is fixedly connected between the two sets of first housings (41). Both sides of the baffle plate (44) are provided with clearance holes (45). An arc-shaped spring telescopic rod (46) is fixedly connected to the inner side of the first housing (41). One end of the arc-shaped spring telescopic rod (46) is fixedly connected to a first sliding plate (47). One end of the first sliding plate (47) passes through the first housing (41) and is fixedly connected to the second housing (42). A sliding groove is provided on the first housing (41) for the first sliding plate (47) to slide.

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