An aircraft with retractable folding wings

Abstract

The application provides a kind of aircraft with telescopic folding wing, it relates to aircraft technical field.The aircraft includes: the cavity is formed in the main wing mechanism inside chamber, and the opening is arranged at the wing tip, the aileron mechanism and the main wing gear group are arranged in the chamber, so that the wing body of aircraft becomes extensible design;Aileron outer shell is connected with the worm transmission of main wing gear group through worm nut;Power mechanism is arranged on the fuselage, and power mechanism is used to control main wing mechanism to unfold, retract;When power mechanism moves main wing outer shell rotation, through the transmission of main wing gear group, so that aileron outer shell is stretched out or shrunk from the wing tip opening of main wing outer shell.In the case where the length, width of fuselage and the space occupied after wing folding are unchanged, the wingspan is increased and it is convenient to recycle and reuse, effectively improves the range of aircraft;And, when power mechanism provides driving force, the main wing outer shell of both sides of fuselage always keeps synchronous rotation, guarantees the stability of fuselage.

Description

Technical Field

[0001] This application generally relates to the field of aircraft technology, and specifically to an aircraft with a retractable folding wing. Background Technology

[0002] Folding wing technology is primarily used in carrier-based aircraft, unmanned aerial vehicles (UAVs), and missiles. In recent years, small UAVs have seen increasingly widespread applications in disaster relief and air transport. For compound-wing UAVs, when hovering in confined spaces or flying at low speeds, the wings not only cease to provide lift but also increase drag and inertial tensor, reducing endurance, maneuverability, and stealth capabilities. Retractable folding wings can be folded when the UAV is parked, stored, or when lift is not required. When cruising without power, retractable folding wings improve stability and increase range, thus addressing the aforementioned problems and enhancing the overall performance of the UAV.

[0003] Currently, the mainstream folding wing layout for aircraft is one where the wings fold backward. Without power, the cruising range depends on the airfoil design, and the concept of extendable wing-body design is gradually becoming a popular trend in UAV development. In conventional layouts, wingspan is limited by fuselage length and folding mechanism, resulting in insufficient lift-to-drag ratio and thus limiting the range of UAVs. Summary of the Invention

[0004] In view of the above-mentioned defects or deficiencies in the prior art, it is desirable to provide an aircraft with retractable folding wings that increases wingspan and is easy to recover.

[0005] This application provides an aircraft with a retractable folding wing, comprising:

[0006] The fuselage is provided with a pair of main wing mechanisms, each main wing mechanism including a main wing outer shell and a main wing gear set. The main wing outer shell is hollow to form a cavity, and the main wing outer shell has a wingtip opening at the wingtip, which communicates with the cavity. The main wing gear set is located inside the cavity and includes a first connecting part, a second connecting part, and a third connecting part, with the third connecting part connected to the main wing outer shell.

[0007] The power mechanism is mounted on the fuselage, the drive end of the power mechanism is connected to the outer shell of the main wing, and a fuselage support gear is mounted on the fuselage, which meshes with the first connecting part;

[0008] The aileron mechanism is located inside the cavity. The aileron mechanism includes a worm nut and an aileron outer shell. One end of the worm nut is connected to the aileron outer shell, and the other end of the worm nut is connected to the second connecting part in a transmission manner.

[0009] When the power mechanism drives the main wing outer shell to rotate, the third connecting part drives the first connecting part to rotate along the fuselage support gear, which in turn drives the second connecting part to rotate, so that the worm nut moves linearly along the axis of the second connecting part, so that the aileron outer shell extends or retracts from the wingtip opening of the main wing outer shell.

[0010] According to the technical solution provided in this application, the main wing gear set includes a first transmission structure, a second transmission structure, and a main wing support structure. The main wing support structure includes a first support section, a second support section, and a third support section. The first transmission structure is rotatably connected to the first support section and meshes with the fuselage support gear. The second transmission structure is rotatably connected to the second support section and is driven by the worm gear nut. One end of the third support section is connected to the outer shell of the main wing.

[0011] When the power mechanism drives the main wing outer shell to rotate, the third support section drives the first transmission structure to rotate along the fuselage support gear, which in turn drives the second transmission structure to rotate, so that the worm nut moves linearly along the axis of the second transmission structure, so that the aileron outer shell extends or retracts from the wingtip opening of the main wing outer shell.

[0012] According to the technical solution provided in this application, the first transmission structure includes a main gear and a secondary gear, the main gear and the secondary gear are connected, and the main gear is the first connecting part.

[0013] According to the technical solution provided in this application, the outer shell of the main wing is provided with a clearance hole, and the clearance hole is correspondingly provided with the main gear.

[0014] According to the technical solution provided in this application, the second transmission structure includes a helical gear and a worm gear, the helical gear and the worm gear are connected and meshed with the secondary gear; the worm gear is connected to the worm nut in a transmission manner, and the worm gear is the second connecting part.

[0015] According to the technical solution provided in this application, the main wing support structure includes two bearings arranged perpendicularly to each other and a connecting shaft. One bearing is the first support section, the other bearing is the second support section, the connecting shaft is the third support section, and the free end of the connecting shaft is the third connecting part.

[0016] According to the technical solution provided in this application, the edge cross-section of the outer shell of the main wing near the tail of the fuselage is semi-circular.

[0017] According to the technical solution provided in this application, the chord length of the outer shell of the main wing is less than the chord length of the root shell of the outer shell of the aileron.

[0018] According to the technical solution provided in this application, when the power mechanism drives the outer shell of the main wing to rotate, so that the two outer shells of the main wing are fully deployed, the root surfaces of the two outer shells of the main wing come into contact.

[0019] In summary, this application specifically discloses an aircraft with a retractable folding wing, comprising: a pair of main wing mechanisms on the fuselage, each main wing mechanism including a main wing outer shell and a main wing gear set; the main wing outer shell having a hollow cavity inside; a wingtip opening at the wingtip of the main wing outer shell communicating with the cavity; the main wing gear set located inside the cavity, comprising a first connecting part, a second connecting part, and a third connecting part, the third connecting part being connected to the main wing outer shell; and a power mechanism mounted on the fuselage, the drive end of which being connected to the main wing outer shell. A fuselage support gear is provided, which meshes with the first connecting part. The aileron mechanism is located inside the cavity and includes a worm nut and an aileron outer shell. One end of the worm nut is connected to the aileron outer shell, and the other end of the worm nut is connected to the second connecting part. When the power mechanism drives the main wing outer shell to rotate, the third connecting part drives the first connecting part to rotate along the fuselage support gear, which in turn drives the second connecting part to rotate, so that the worm nut moves linearly along the axis of the second connecting part, so that the aileron outer shell extends or retracts from the wingtip opening of the main wing outer shell.

[0020] Existing folding-wing aircraft have wingspans limited by fuselage length. Excessive wingspan leads to a large space occupied during folding and unfolding, increasing the weight of the aircraft and limiting its range. Therefore, this application designs an aircraft with a telescopic folding wing, in which the aileron mechanism is located in the cavity of the main wing mechanism, making the wing body of the aircraft extendable.

[0021] The main wing mechanism and aileron mechanism designed in this application operate in a synchronous deployment and retraction mode, which is not limited by the fuselage length and folding mechanism. It also allows the wingspan of the entire aircraft to be increased without changing the fuselage length, width, and space occupied by the wings after folding, thus effectively improving the aircraft's range. In addition, the deployment and retraction of the wings are always driven by the same power mechanism, eliminating the need to design separate power systems, reducing the overall weight of the aircraft, and making the wing space layout more compact. Moreover, when the power mechanism provides driving force, the outer shells of the main wings on both sides of the fuselage always rotate synchronously, which can also ensure the stability of the fuselage. Attached Figure Description

[0022] Other features, objects, and advantages of this application will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings.

[0023] Figure 1This is a schematic diagram of an aircraft with a retractable folding wing when the main wing mechanism is in the retracted state.

[0024] Figure 2 This is a schematic diagram of the structure of an aircraft with a telescopic folding wing when the main wing mechanism is in the deployed state.

[0025] Figure 3 This is a schematic diagram of the fuselage structure.

[0026] Figure 4 A cross-sectional view of the internal structure of the main wing mechanism.

[0027] Figure 5 This is a schematic diagram of the aileron mechanism.

[0028] Figure 6 A top view showing the connection between the main wing gear assembly and the fuselage support gears.

[0029] Figure 7 Example diagram showing the dimensions of the main wing gear set and the fuselage support gear.

[0030] Figure 8 This is a schematic diagram showing the linear distance between the worm nut and the helical gear when the main wing mechanism is in the retracted state.

[0031] Figure 9 This is a schematic diagram showing the linear distance between the worm nut and the helical gear when the main wing mechanism is in the deployed state.

[0032] The diagram labels are as follows: 100, main fuselage mechanism; 200, main wing mechanism; 300, aileron mechanism; 110, fuselage; 121, fuselage support gear; 122, power mechanism; 210, main wing outer shell; 220, main wing gear set; 221, main gear; 222, secondary gear; 223, helical gear; 224, worm; 225, main wing support structure; 310, worm nut; 320, aileron outer shell. Detailed Implementation

[0033] The present application will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, only the parts relevant to the invention are shown in the accompanying drawings.

[0034] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0035] This application provides an aircraft with a retractable folding wing, comprising:

[0036] The fuselage 110 has a pair of main wing mechanisms 200. The main wing mechanism 200 includes a main wing outer shell 210 and a main wing gear set 220. The main wing outer shell 210 is hollow to form a cavity. The main wing outer shell 210 has a wingtip opening at the wingtip, which communicates with the cavity. The main wing gear set 220 is located inside the cavity and includes a first connecting part, a second connecting part, and a third connecting part. The third connecting part is connected to the main wing outer shell 210.

[0037] A power mechanism 122 is mounted on the fuselage 110. The drive end of the power mechanism 122 is connected to the outer shell 210 of the main wing. A fuselage support gear 121 is mounted on the fuselage 110 and meshes with the first connecting part.

[0038] A pair of aileron mechanisms 300 are located inside the cavity. The aileron mechanism 300 includes a worm nut 310 and an aileron outer shell 320. One end of the worm nut 310 is connected to the aileron outer shell 320, and the other end of the worm nut 310 is connected to the second connecting part for transmission.

[0039] When the power mechanism 122 drives the main wing outer shell 210 to rotate, the third connecting part drives the first connecting part to rotate along the fuselage support gear 121, which in turn drives the second connecting part to rotate, so that the worm nut 310 moves linearly along the axis of the second connecting part, so that the aileron outer shell 320 extends or retracts from the wingtip opening of the main wing outer shell 210.

[0040] It should be noted that when the aircraft wing is in the deployed state, the outermost end furthest from the fuselage is the wingtip, and the innermost end closest to the fuselage is the wing root. The main wing mechanism 200 and the aileron mechanism 300 together constitute the wing structure of the aircraft, and their function is to generate lift to overcome the aircraft's gravity, enabling it to fly. The principle is based on the difference in airflow velocity between the upper and lower surfaces of the wing, creating a pressure difference that generates lift. Figure 4 As shown, the main wing outer shell 210 has a hollow interior forming a chamber, which provides installation space for the main wing gear set 220 and the aileron mechanism 300. A wingtip opening is provided at the wingtip of the main wing outer shell 210, allowing the aileron outer shell 320 to extend or retract relative to the main wing outer shell 210. When the main wing outer shell 210 rotates, the third connecting part drives the first connecting part to rotate along the fuselage support gear 121. The rotational force of the first connecting part is transmitted to the second connecting part, which in turn drives the worm nut 310 to rotate, causing the aileron outer shell 320 to move relative to the main wing outer shell 210. Figure 3As shown, the power mechanism 122 is fixed to the fuselage 110. The power mechanism 122 is, for example, a servo motor. The drive shaft of the servo motor is connected to the outer shell 210 of the main wing. When the servo motor is activated, the drive shaft of the servo motor drives the outer shell 210 of the main wing to rotate until the main wing mechanism 200 is fully deployed, at which point the motor stops working. The aforementioned servo motor can be any servo motor in the art that can achieve power drive, and there are no restrictions on the specific type or model.

[0041] When the aircraft is in use, the two power mechanisms 122 provide positive torque, which drives the two main wing outer shells 210 to rotate, causing the contact area at the wing root of the main wing outer shell 210 to gradually increase, such as... Figure 2 As shown, the two main wing outer shells 210 are fully deployed until their root surfaces are in complete contact, i.e., the two main wing outer shells 210 are fully deployed. Furthermore, during the rotation of the main wing outer shells 210, the aileron outer shells 320 are simultaneously pulled out from the corresponding main wing outer shells 210 until the aileron outer shells 320 are fully deployed at the wingtip openings of the corresponding main wing outer shells 210.

[0042] When the aircraft requires recovery, the two power mechanisms 122 provide reverse torque, driving the two main wing outer shells 210 to rotate in opposite directions (the reference to the aforementioned positive torque rotation direction), causing the wingtips of the main wing outer shells 210 to move closer together, such as... Figure 1 As shown, the two main wing outer shells 210 are folded into a retracted state. During the rotation of the main wing outer shell 210, the aileron outer shell 320 is simultaneously pulled into the corresponding main wing outer shell 210 and retracted until the aileron outer shell 320 is completely retracted into the internal cavity of the corresponding main wing outer shell 210.

[0043] The main wing mechanism 200 and aileron mechanism 300 designed in this application operate in a synchronous deployment and retraction mode, which is not limited by the fuselage length and folding mechanism. It also allows the entire aircraft to increase its wingspan without changing the fuselage length, width, and space occupied by the folded wings, thus effectively improving the aircraft's range. In addition, the deployment and retraction of the wings are always driven by the same power mechanism 122, making the wing's spatial layout more compact. Moreover, when the power mechanism 122 provides driving force, the outer shells 210 of the main wings on both sides of the fuselage always rotate synchronously, which can also ensure the stability of the fuselage.

[0044] Furthermore, such as Figure 4 As shown, the main wing gear set 220 includes a first transmission structure, a second transmission structure, and a main wing support structure 225. The main wing support structure 225 includes a first support section, a second support section, and a third support section. The first transmission structure is rotatably connected to the first support section and meshes with the fuselage support gear 121. The second transmission structure is rotatably connected to the second support section and is driven by the worm nut 310. One end of the third support section is connected to the main wing outer shell 210.

[0045] When the power mechanism 122 drives the main wing outer shell 210 to rotate, the third support section drives the first transmission structure to rotate along the fuselage support gear 121, which in turn drives the second transmission structure to rotate, so that the worm nut 310 moves linearly along the axis of the second transmission structure, so that the aileron outer shell 320 extends or retracts from the wingtip opening of the main wing outer shell 210.

[0046] It should be noted that the main wing gear set 220 serves as a support and force transmission mechanism. The first support section supports the first transmission structure, allowing it to rotate freely around the axis of the first support section; the second support section supports the second transmission structure, ensuring its stable rotation and power transmission; the third support section transmits the rotation of the main wing outer shell 210 to the main wing gear set 220, driving its movement.

[0047] When the power mechanism 122 drives the outer shell 210 of the main wing to rotate, the outer shell 210 of the main wing drives the entire main wing support structure 225 to rotate synchronously through the third support section. The main wing support structure 225 serves as the load-bearing and connecting foundation, and its three support sections cooperate with each other to ensure structural rigidity and provide stable support for the transmission of force.

[0048] Furthermore, the first transmission structure includes a main gear 221 and a secondary gear 222, which are connected, with the main gear 221 serving as the first connecting part.

[0049] It should be noted that, as Figure 6 As shown, the main gear 221 and the auxiliary gear 222 are fixed together and can rotate synchronously. When the first support section drives the main gear 221 to rotate, the main gear 221 rotates along the body support gear 121. The body support gear 121 provides the motion track. At the same time, the auxiliary gear 222 drives the second transmission mechanism to rotate, thereby driving the worm nut 310 to make linear motion.

[0050] Furthermore, such as Figure 4 As shown, the outer shell 210 of the main wing is provided with a clearance hole, which is correspondingly set with the main gear 221.

[0051] It should be noted that when the main wing outer shell 210 rotates, the main gear 221 needs to rotate along the fuselage support gear 121. The existence of the clearance hole provides the main gear 221 with movement space, preventing collision between the main wing outer shell 210 and the main gear 221. By setting the clearance hole, the spatial interference problem between the main wing outer shell 210 and the main gear 221 is effectively solved. Here, the cross-sectional area of ​​the clearance hole is larger than the cross-sectional area of ​​the main gear 221 to ensure that the main gear 221 can rotate normally.

[0052] Furthermore, such as Figure 4As shown, the second transmission structure includes a helical gear 223 and a worm 224. The helical gear 223 and the worm 224 are connected and mesh with the secondary gear 222. The worm 224 is connected to the worm nut 310 for transmission, and the worm 224 is the second connecting part.

[0053] It should be noted that, as Figure 5 As shown, the helical gear 223 and the worm 224 are fixedly connected. The helical gear 223 meshes with the secondary gear 222, transmitting the rotational power of the secondary gear 222 to the worm 224. Through the restriction effect of the main wing outer shell 210 on the corresponding aileron outer shell 320, the worm nut 310 moves linearly along the worm 224, thereby driving the aileron outer shell 320 to move relative to the main wing outer shell 210, realizing the deployment or retraction of the aileron outer shell 320.

[0054] Furthermore, the main wing support structure 225 includes two bearings arranged perpendicularly to each other and a connecting shaft. One bearing is the first support section, the other bearing is the second support section, the connecting shaft is the third support section, and the free end of the connecting shaft is the third connecting part.

[0055] It should be noted that during the rotation of the main wing outer shell 210, the first support section of the main wing support structure 225 provides a stable rotation fulcrum for the first transmission structure, the second support section provides a stable rotation fulcrum for the second transmission structure, and the third support section is connected to the main wing outer shell 210. When the power mechanism 122 drives the main wing outer shell 210 to rotate, it plays a supporting role in the entire transmission process of the main wing gear set 220.

[0056] Furthermore, the edge section of the outer shell 210 of the main wing, near the tail of the fuselage 110, is semi-circular at the wing root.

[0057] It should be noted that, as Figure 9 As shown, the edge section of the outer shell 210 of the main wing near the tail of the fuselage 110 at the wing root is semi-circular, which ensures that the edge near the tail of the fuselage 110 does not interfere with each other during the deployment process when the outer shell 210 of the main wing rotates.

[0058] Furthermore, the wingtip chord length of the main wing outer shell 210 is less than the root chord length of the aileron outer shell 320.

[0059] It should be noted that chord length refers to the straight-line distance from the leading edge to the trailing edge of the wing section. The chord length at the wingtip of the main wing outer shell 210 is less than the chord length at the wing root of the aileron outer shell 320. When the aileron outer shell 320 extends beyond the main wing outer shell 210, this design, on the one hand, limits the position that the wing root of the aileron outer shell 320 can reach by the wingtip of the main wing outer shell 210, that is, limits the extension length of the aileron outer shell 320. On the other hand, it increases the contact area between the wing root of the aileron outer shell 320 and the wingtip of the main wing outer shell 210, improves the structural strength of the entire wing, and prevents the aileron outer shell 320 from shaking due to complex working conditions during the fully deployed operation and coming off from the wingtip opening of the main wing outer shell 210.

[0060] Furthermore, when the power mechanism 122 drives the main wing outer shell 210 to rotate, so that the two main wing outer shells 210 are fully deployed, the root surfaces of the two main wing outer shells 210 come into contact.

[0061] It should be noted that, as Figure 2 As shown, when the two main wing outer shells 210 are fully deployed, the root surfaces of the two main wing outer shells 210 are in contact, ensuring that the two main wing outer shells 210 are symmetrical after deployment, maintaining stability and structural strength during flight, and avoiding displacement due to vibration or external forces.

[0062] Furthermore, the pitch circle radius R1 of the fuselage support gear 121 and the pitch circle radius R2 of the main gear 221 are related as follows: Z2 / Z1=R2 / R1.

[0063] in, Figure 7 In this diagram, R1 is the pitch circle radius of fuselage support gear 121, R2 is the pitch circle radius of main gear 221, Z1 is the number of teeth of fuselage support gear 121, and Z2 is the number of teeth of main gear 221.

[0064] Furthermore, the pitch circle radius R3 of the secondary gear 222 and the pitch circle radius R4 of the helical gear 223 are related as follows: Z3 / Z4=R3 / R4;

[0065] in, Figure 7 In the diagram, R3 is the pitch circle radius of the secondary gear 222, R4 is the pitch circle radius of the helical gear 223, Z3 is the number of teeth of the secondary gear 222, and Z4 is the number of teeth of the helical gear 223.

[0066] Furthermore, the length by which the aileron mechanism 300 moves along the worm gear 224 after switching between the extended and retracted states is ΔL = L2 - L1;

[0067] in, Figure 8 The straight-line distance between the worm nut 310 and the helical gear 223 when the main wing mechanism 200 is in the retracted state (L1). Figure 9The straight-line distance between the worm nut 310 and the helical gear 223 when the main wing mechanism 200 is in the deployed state (L2).

[0068] Specifically, the relationship between the rotation angle α of the main wing mechanism 200 and the length ΔL of the aileron mechanism 300 moving along the worm 224 is: ΔL = R3·R1·α·P5·Z5 / (R4·R2).

[0069] Where α is the rotation angle of the main wing mechanism 200, P5 is the pitch of the worm 224, and Z5 is the number of rotations of the worm 224.

[0070] It should be noted that, as Figure 7 As shown, using a mechanical system with gear ratios (R2 / R1, R3 / R4), and taking the rotation angle α of the main wing mechanism 200 as input data, the length ΔL that the aileron mechanism 300 moves along the worm gear 224 after switching between the extended and retracted states can be accurately calculated. The conversion relationship is strictly determined by the geometric parameters of each component of the main wing gear set 220, ensuring the synchronicity and reliability of the extension or retraction of the aileron mechanism 300 when the main wing mechanism 200 rotates.

[0071] The above description is merely a preferred embodiment of this application and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of the invention involved in this application is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the inventive concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features with similar functions disclosed in this application.

Claims

1. An aircraft with retractable folding wings, characterized in that, include: The fuselage (110) is provided with a pair of main wing mechanisms (200). The main wing mechanism (200) includes a main wing outer shell (210) and a main wing gear set (220). The main wing outer shell (210) is hollow to form a cavity. The main wing outer shell (210) has a wingtip opening at the wingtip and the wingtip opening communicates with the cavity. The main wing gear set (220) is located inside the cavity and includes a first connecting part, a second connecting part and a third connecting part. The third connecting part is connected to the main wing outer shell (210). A power mechanism (122) is provided on the fuselage (110). The driving end of the power mechanism (122) is connected to the outer shell (210) of the main wing. A fuselage support gear (121) is provided on the fuselage (110). The fuselage support gear (121) is meshed with the first connecting part. A pair of aileron mechanisms (300) are located inside the cavity. The aileron mechanism (300) includes a worm nut (310) and an aileron outer shell (320). One end of the worm nut (310) is connected to the aileron outer shell (320), and the other end of the worm nut (310) is connected to the second connecting part in a transmission connection. When the power mechanism (122) drives the main wing outer shell (210) to rotate, the third connecting part drives the first connecting part to rotate along the fuselage support gear (121), which in turn drives the second connecting part to rotate, so that the worm nut (310) moves linearly along the axial direction of the second connecting part, so that the aileron outer shell (320) extends or retracts from the wingtip opening of the main wing outer shell (210); The main wing gear set (220) includes a first transmission structure, a second transmission structure, and a main wing support structure (225). The main wing support structure (225) includes a first support section, a second support section, and a third support section. The first transmission structure is rotatably connected to the first support section and meshes with the fuselage support gear (121). The second transmission structure is rotatably connected to the second support section and is driven by the worm nut (310). One end of the third support section is connected to the outer shell (210) of the main wing. When the power mechanism (122) drives the main wing outer shell (210) to rotate, the third support section drives the first transmission structure to rotate along the fuselage support gear (121), which in turn drives the second transmission structure to rotate, so that the worm nut (310) moves linearly along the axial direction of the second transmission structure, so that the aileron outer shell (320) extends or retracts from the wingtip opening of the main wing outer shell (210); The first transmission structure includes a main gear (221) and a secondary gear (222), the main gear (221) and the secondary gear (222) are connected, and the main gear (221) is the first connecting part; The second transmission structure includes a helical gear (223) and a worm (224). The helical gear (223) and the worm (224) are connected and mesh with the secondary gear (222). The worm (224) is connected to the worm nut (310) and is the second connecting part. The main wing support structure (225) includes two bearings arranged perpendicularly to each other and a connecting shaft. One bearing is the first support section, the other bearing is the second support section, the connecting shaft is the third support section, and the free end of the connecting shaft is the third connecting part.

2. An aircraft with a retractable folding wing according to claim 1, characterized in that, The outer shell (210) of the main wing is provided with a clearance hole, which is correspondingly provided with the main gear (221).

3. An aircraft with a retractable folding wing according to claim 1, characterized in that, The edge section of the outer shell (210) of the main wing near the tail of the fuselage (110) at the wing root is semi-circular.

4. An aircraft with a retractable folding wing according to claim 1, characterized in that, The chord length of the tip of the main wing outer shell (210) is less than the chord length of the root of the aileron outer shell (320).

5. An aircraft with a retractable folding wing according to claim 1, characterized in that, When the power mechanism (122) drives the main wing outer shell (210) to rotate, so that the two main wing outer shells (210) are fully deployed, the root surfaces of the two main wing outer shells (210) come into contact.

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