A variable sweep retractable wing structure

Abstract

The application relates to a variable sweep telescopic wing structure, which comprises a wing platform and a wing assembly, the wing assembly comprising a first wing and a second wing, a first driving assembly, a rotating assembly and a lifting shaft, the rotating assembly comprising a first rotating shaft and a second rotating shaft which are connected in parallel on the wing platform, the first rotating shaft being coaxially sleeved on the lifting shaft, the first rotating shaft being fixedly matched with the lifting shaft in the circumferential direction and being slidably matched with the lifting shaft in the axial direction, the first wing being connected at the top of the lifting shaft, the second wing being connected at the top of the second rotating shaft, and the first wing and the second wing both being telescopic structures, the first driving assembly being transmissionally connected with the first rotating shaft and the second rotating shaft to drive the first rotating shaft and the second rotating shaft to rotate and drive the lifting shaft to lift. The structure can realize wing unfolding and folding with any sweep angle, increase the stability and flexibility of the aircraft, be telescopic to change the wing area, adapt to different flight states, improve the wing efficiency and improve the flight performance.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a variable sweep retractable wing structure. Background Technology

[0002] Unmanned aerial vehicles (UAVs) have developed into an irreplaceable piece of equipment, performing tasks such as long-endurance reconnaissance, area surveillance, search and location, and fire guidance. The storage, transportation, and use of UAVs all require minimal folding space.

[0003] Current similar technologies are all structurally complex, and their folding is simply unfolding, resulting in wings that lack anhedral angle beneficial to aerodynamic performance when unfolded. During folding, the two wings rotate to the same position and stack vertically; during unfolding, the two wings rotate and unfold. Because there is a height difference when the wings are stacked vertically during folding, there is also a height difference when they are unfolded. This height difference affects the aerodynamic performance of the aircraft.

[0004] When unmanned aerial vehicles (UAVs) are performing missions, sometimes they need to increase their speed to enhance their ability to quickly bypass defenses and launch rapid attacks, sometimes they need to decrease their speed to enhance their reconnaissance and surveillance capabilities, and sometimes they need to reduce their static stability margin to improve their pitch flexibility. These requirements are difficult to meet simply by adjusting the flight control system or control surfaces; forced adjustments may even threaten flight safety.

[0005] The wing area and sweep angle of an unmanned aerial vehicle (UAV) both affect its performance parameters such as flight speed and angle of attack. By changing the wing area and sweep angle of an UAV, it is possible to enable a single UAV to perform multiple tasks, thereby increasing its strike and defense capabilities. Summary of the Invention

[0006] To address the aforementioned shortcomings, this invention provides a variable sweep and retractable wing structure that, while maintaining a small folding volume, allows the wing to change various sweep angles, eliminates height differences after wing deployment, and retracts to change the wing area.

[0007] To achieve the above objectives, the present invention provides a variable sweep retractable wing structure, comprising: a wing platform and a wing assembly, wherein the wing assembly includes a first wing and a second wing, characterized in that it further comprises a first drive assembly, a rotation assembly, and an elevator shaft;

[0008] The wing rotation assembly includes a first rotating shaft and a second rotating shaft rotatably connected side by side to the wing platform. The first rotating shaft is coaxially sleeved on the lifting shaft. The first rotating shaft and the lifting shaft are fixedly fitted in the circumferential direction and slidingly fitted in the axial direction.

[0009] The first wing is connected to the top of the lifting shaft, and the second wing is connected to the top of the second rotating shaft, and both the first wing and the second wing are telescopic structures;

[0010] The first drive component is connected to the first rotating shaft and the second rotating shaft for driving the first rotating shaft and the second rotating shaft to rotate, and driving the lifting shaft to move up and down.

[0011] In one embodiment, the first drive assembly includes: a servo motor, a first turbine, a second turbine, and a worm gear;

[0012] The servo is fixed on the wing platform and drives the first turbine and the second turbine. The first turbine is located at the bottom of the first rotating shaft, and the second turbine is located at the bottom of the second rotating shaft. The first turbine and the second turbine are symmetrically arranged on both sides of the worm and drive the worm.

[0013] In one embodiment, a guide rod is also included, the side wall of the lifting shaft is provided with a spiral groove, and the first rotating shaft is provided with a horizontal groove;

[0014] One end of the guide rod is fixedly connected to the wing platform or fuselage, and the other end passes through the transverse groove and then through the spiral groove.

[0015] In one embodiment, the first drive assembly further includes a potentiometer, the potentiometer knob being fixedly connected to the second turbine.

[0016] In one embodiment, both the first turbine and the second turbine are fan-shaped structures.

[0017] In one embodiment, a second driving component is also included;

[0018] The first wing includes a first outer wing section and a first inner wing section. One end of the first inner wing section is connected to the elevator shaft, and the other end is sleeved with the first outer wing section.

[0019] The second drive assembly includes a first drive motor and a first lead screw. The first drive motor is fixedly mounted on the top of the lifting shaft. One end of the first lead screw is connected to the first drive motor, and the other end passes through the first inner wing section and is connected to the first outer wing section.

[0020] The first lead screw is rotatably engaged with the first inner section wing, and the first lead screw is threadedly engaged with the first outer section wing.

[0021] In one embodiment, a first connector is also included;

[0022] The first end of the first connector is fixedly connected to the top of the lifting shaft, and the tail end of the first connector is fixedly connected to the first inner section wing.

[0023] The tail end of the first connector is higher than the head end of the first connector.

[0024] In one embodiment, a third driving component is also included;

[0025] The second wing includes a second outer wing section and a second inner wing section. Two ends of the second inner wing section are connected to the second pivot, and the other end is sleeved with the second outer wing section.

[0026] The third drive assembly includes a second drive motor and a second lead screw. The second drive motor is fixedly mounted on the top of the second rotating shaft. One end of the second lead screw is connected to the second drive motor, and the other end passes through the second inner wing section and is connected to the second outer wing section.

[0027] The second lead screw is rotatably engaged with the second inner section wing, and the second lead screw is threadedly engaged with the second outer section wing.

[0028] In one embodiment, a second connector is also included;

[0029] The first end of the second connector is fixedly connected to the top of the second rotating shaft, and the tail end of the second connector is fixedly connected to the second inner section wing.

[0030] The tail end of the second connector is higher than the head end of the second connector.

[0031] Compared with existing technologies, the variable sweep and retractable wing structure provided by this invention has the following advantages:

[0032] 1. To enable adjustable sweep angle during wing deployment, thereby increasing the stability and maneuverability of the aircraft;

[0033] 2. To achieve the function of eliminating height difference after the wings are deployed and having an upward dihedral angle;

[0034] 3. To enable the wings to be retractable to change the wing area, adapt to different flight conditions, improve wing efficiency, and enhance flight performance. Attached Figure Description

[0035] Figure 1 This is an axonometric view of the structure of the wing when it is deployed in an embodiment of the present invention;

[0036] Figure 2 for Figure 1 An enlarged view of the part labeled A in the middle;

[0037] Figure 3 for Figure 1A bottom view of section A marked in the middle;

[0038] Figure 4 This is an isometric view of the wing platform in an embodiment of the present invention;

[0039] Figure 5 This is a side view of the wing platform in an embodiment of the present invention;

[0040] Figure 6 This is an axial view of the rotating component in an embodiment of the present invention;

[0041] Figure 7 This is an axial view of the lifting shaft in an embodiment of the present invention;

[0042] Figure 8 This is an axial view of the first driving component and the second driving component in an embodiment of the present invention;

[0043] Figure 9 This is an axial view of the first connector and the second connector in an embodiment of the present invention;

[0044] Figure 10 This is a cross-sectional view of the junction between the first outer wing section and the first inner wing section in an embodiment of the present invention.

[0045] Icon labels:

[0046] First wing 11, first outer wing section 111, first inner wing section 112;

[0047] Second wing 12, second outer wing section 121, second inner wing section 122;

[0048] Wing platform 21: First pivot mounting hole 211, second pivot mounting hole 212;

[0049] First rotating shaft 221: First rotating shaft main shaft body 2211, first rotating shaft bottom shaft body 2212, first reinforcing seat 2511;

[0050] Second rotating shaft 222: Second rotating shaft main shaft body 2221, second rotating shaft bottom shaft body 2222, second reinforcing seat 2521;

[0051] Lifting shaft 231, guide rod 232, spiral groove 233, horizontal groove 234;

[0052] Servo 241, first turbine 2421, second turbine 2422, worm gear 243, potentiometer 244, potentiometer shaft 2441;

[0053] First drive motor 251, first lead screw 261, first transmission gear 2512, second transmission gear 2611;

[0054] Second drive motor 252, second lead screw 262, third transmission gear 2522, fourth transmission gear 2621;

[0055] First connector 271, first connector head end 2711, first connector tail end 2712, first fastener 2713;

[0056] Second connector 272, first end of second connector 2721, last end of second connector 2722, second fastener 2723.

[0057] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0058] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0059] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0060] Furthermore, in this invention, descriptions involving "first," "second," etc., are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly and specifically defined.

[0061] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two elements or the interaction between two elements, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0062] Furthermore, the technical solutions of the various embodiments of the present invention can be combined with each other, but only if they are feasible for those skilled in the art. If the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention.

[0063] like Figure 1-10 As shown, this embodiment discloses a variable sweep retractable wing structure, which mainly includes a wing platform 21, a wing assembly, a first drive assembly, a rotating assembly, and an elevator shaft 231. The wing platform 21 is provided with a first rotating shaft mounting hole 211 and a second rotating shaft mounting hole 212 arranged side by side, and the first rotating shaft mounting hole 211 and the second rotating shaft mounting hole 212 penetrate the wing platform 21 vertically.

[0064] The wing assembly includes a first wing 11 and a second wing 12. The first wing 11 is connected to the top of the elevator shaft 231, and the second wing 12 is connected to the top of the second rotating shaft 222. Both the first wing 11 and the second wing 12 are telescopic structures. Specifically, the first wing 11 includes a first outer wing section 111 and a first inner wing section 112. One end of the first inner wing section 112 is fixedly connected to the top of the elevator shaft 231 via a first connector 271, and the other end is sleeved with the first outer wing section 111. The first connector 271 includes a first connector head end 2711 and a first connector tail end 2712. The first connector head end 2711 is a ring structure and is fixedly connected to the top of the elevator shaft 231. The first connector tail end 2712 is a clamping structure with a first upper clamping plate and a first lower clamping plate. One end of the first inner wing section 112 is clamped between the first upper clamping plate and the first lower clamping plate and is fixedly connected to both the first upper clamping plate and the first lower clamping plate simultaneously via bolts or other fasteners. The second wing 12 includes a second outer wing section 121 and a second inner wing section 122. The second inner wing section 122 is fixedly connected to the top of the second rotating shaft 222 via a second connector 272, and the other end is sleeved with the second outer wing section 121. The second connector 272 includes a second connector head end 2721 and a second connector tail end 2722. The second connector head end 2721 is a ring structure and is fixedly connected to the top of the second rotating shaft 222 via a fixing structure. The second connector tail end 2722 is a clip structure with a second upper clip and a second lower clip. One end of the second inner wing section 122 is clamped between the second upper clip and the second lower clip and is fixedly connected to the second upper clip and the second lower clip simultaneously via bolts or other fasteners.

[0065] It should be noted that the angle between the axis of the first rotating shaft 221 and the plane containing the wing platform 21 is α, and the angle between the axis of the second rotating shaft 222 and the plane containing the wing platform 21 is α, where 0° < α = α < 90°. Specifically, the axes of the first rotating shaft 221 and the second rotating shaft 222 are not perpendicular to the plane containing the wing platform 21, and the top ends of the first rotating shaft 221 and the second rotating shaft 222 are tilted at the same angle towards the tail of the fuselage, so that the tail end 2712 of the first connector is higher than the head end 2711 of the first connector, and the tail end 2722 of the second connector is higher than the head end 2721 of the second connector, thereby giving the wing assembly an upward dihedral angle when it is in the deployed state.

[0066] As a preferred embodiment, a first reinforcing seat 2511 and a first reinforcing rod are provided on the top end of the first rotating shaft 221, i.e., on the first connecting member 271. The first reinforcing seat 2511 and the first connecting member 271 are fixedly connected. One end of the first reinforcing rod is fixedly connected to the first reinforcing seat 2511, and the other end is fixedly embedded in the first wing 11. On the top end of the second rotating shaft 222, i.e., on the second connecting member 272, a second reinforcing seat 2521 and a second reinforcing rod are provided. The second reinforcing seat 2521 and the second connecting member 272 are fixedly connected. One end of the first reinforcing rod is fixedly connected to the second reinforcing seat 2521, and the other end is fixedly embedded in the second wing 12.

[0067] Furthermore, the wing assembly has both a folded state and an unfolded state:

[0068] When the wing assembly is in the folded state, the first wing 11 and the second wing 12 are stacked on top of the fuselage along the length of the fuselage, with the first wing 11 located below the second wing 12.

[0069] When the wing assembly is in the deployed state, the first wing 11 and the second wing 12 are at the same height and symmetrical along the fuselage, and the first wing 11 and the second wing 12 extend to the sides of the fuselage respectively.

[0070] In this embodiment, the switching between the folded and deployed states of the wing assembly is achieved by the counter-rotation of the first rotating shaft 221 and the second rotating shaft 222. For example, initially, the wing assembly is in the folded state; as the first rotating shaft 221 rotates counterclockwise by 90°, the second rotating shaft 222 rotates clockwise by 90° to switch to the deployed state. It should be noted that in actual operation, the rotation is not necessarily 90°; other angles less than 90° are also possible. In actual operation, the deployment angle of the wing assembly is achieved by the first drive assembly. The first drive assembly is connected to the first rotating shaft 221 and the second rotating shaft 222, driving the first rotating shaft 221 and the second rotating shaft 222 to rotate 222, and driving the lifting shaft 231 to move axially up and down, thereby raising and lowering the first wing 11.

[0071] The rotating assembly includes a first rotating shaft 221 and a second rotating shaft 222 that are rotatably connected side by side on the wing platform 21. The first rotating shaft 221 is coaxially sleeved on the lifting shaft 231. The first rotating shaft 221 and the lifting shaft 231 are fixedly fitted in the circumferential direction and slidingly fitted in the axial direction. The first wing 11 is fixedly connected to the top of the lifting shaft 231 through the first connecting piece 271. The second wing 12 is connected to the top of the second rotating shaft 222. Both the first wing 11 and the second wing 12 are telescopic structures.

[0072] Specifically, the first rotating shaft 221 and the second rotating shaft 222 are hollow structures to reduce the weight of the structure. More specifically, the first rotating shaft 221 includes a first rotating shaft main body 2211 and a first rotating shaft bottom body 2212. The first rotating shaft bottom body 2212 is coaxially fixed to the bottom of the first rotating shaft main body 2211, and the first rotating shaft main body 2211 is rotatably connected to the first rotating shaft mounting hole 211. The second rotating shaft 222 includes a second rotating shaft main body 2221 and a second rotating shaft bottom body 2222. The second rotating shaft bottom body 2222 is coaxially fixed to the bottom of the second rotating shaft main body 2221, and the first end 2721 of the second connecting member is fixed to the top of the second rotating shaft main body 2221. The second rotating shaft main body 2221 is rotatably connected to the second rotating shaft mounting hole 212. The first connector head 2711 and the second connector head 2721 are both annular structures; the diameters of the first shaft bottom body 2212 and the first connector head 2711 are both larger than the first shaft main body 2211; the diameters of the second shaft bottom body 2222 and the second connector head 2721 are both larger than the second shaft main body 2221, to prevent the first shaft main body 2211 and the second shaft main body 2221 from falling off the wing platform 21. In the actual operation, the first rotating shaft bottom body 2212 and the first rotating shaft main body 2211 can be integrally formed, and the first rotating shaft main body 2211 can be sleeved on the lifting shaft 231. The lifting shaft 231 is connected to the first end 2711 of the first connecting member through a fixing structure. Similarly, the second rotating shaft bottom body 2222 and the second rotating shaft main body 2221 can be integrally formed, and the second rotating shaft main body 2221 is connected to the first end 2721 of the second connecting member through a fixing structure. The fixing structure can be a threaded connection structure, a bolt connection structure, or a snap-fit ​​connection structure, etc.

[0073] In a preferred embodiment, the first rotating shaft main body 2211 and the first rotating shaft mounting hole 211, and the second rotating shaft main body 2221 and the second rotating shaft mounting hole 212, are both clearance fits. Of course, the first rotating shaft main body 2211 and the first rotating shaft mounting hole 211, and the second rotating shaft main body 2221 and the second rotating shaft mounting hole 212, can also be rotatably connected via bearings or other structural components to reduce frictional resistance. The method of setting bearings or other structural components to achieve rotatable connection is a conventional technique in the art and will not be described in detail in this embodiment.

[0074] In this embodiment, the first rotating shaft main body 2211 is coaxially sleeved on the lifting shaft 231. The first rotating shaft 221 and the lifting shaft 231 are fixedly fitted in the circumferential direction and slidingly fitted in the axial direction. The specific implementation process is as follows:

[0075] The lifting shaft 231 is a hollow structure with an irregular polygonal shape, preferably a floral pattern. The inner wall shape of the first rotating shaft main body 2211 matches the outer wall shape of the lifting shaft 231. A spiral groove 233 is provided on the side wall of the lifting shaft 231, and a horizontal transverse groove 234 is provided on the side wall of the first rotating shaft main body 2211. The circumferential span of the two ends of the spiral groove 233 and the transverse groove 234 on the first rotating shaft main body 2211 is related to the rotation angle of the first rotating shaft main body 2211 during the process of the wing assembly changing from the folded state to the unfolded state. For example, if the rotation angle of the first rotating shaft main body 2211 is 90° during this process, then the circumferential span of the two ends of the spiral groove 233 and the transverse groove 234 on the first rotating shaft main body 2211 is the same, which is one-quarter of the circumference of the first rotating shaft main body 2211, that is, the guiding range of the first rotating shaft main body 2211 rotating 90°. The axial span of the two ends of the spiral groove 233 on the first rotating shaft main body 2211 is equal to the height difference between the first wing 11 and the second wing 12 when the wing assembly is in the folded state.

[0076] One end of the guide rod 232 is fixedly connected to the wing platform 21 or the fuselage, and the other end passes through the transverse groove 234 and then through the helical groove 233 to be located at the first rotating shaft main body 2211. In this case, there is one transverse groove 234 and one helical groove 233. Alternatively, the other end passes through the transverse groove 234 and then through the helical groove 233 to pass through the elevator shaft 231 and connect to the first rotating shaft main body 2211. In this case, there are two transverse grooves 234 and two helical grooves 233. The two helical grooves 233 are symmetrically distributed in a cross shape on the side wall of the first rotating shaft main body 2211, that is, one helical groove 233 is in the 0-90° region of the first rotating shaft main body 2211, and the other is in the 180°-270° region. One of the two transverse grooves 234 is in the 0-90° horizontal region of the first rotating shaft main body 2211, and the other is in the 180°-270° horizontal region. The guide rod 232 is slidably connected to the helical groove 233 and the transverse groove 234.

[0077] It should be noted that the axial length of the first rotating shaft main body 2211 is set to be equal to the depth of the first rotating shaft mounting hole 211 to prevent axial movement of the first rotating shaft main body 2211, and the axial length of the second rotating shaft main body 2221 is set to be equal to the depth of the second rotating shaft mounting hole 212 to prevent axial movement of the second rotating shaft main body 2221. In this embodiment, it is not limited to fitting the lifting shaft 231 into the first rotating shaft main body 2211; the lifting shaft 231 can also be fitted into the second rotating shaft main body 2221 in the same way, with the connection method being the same as that of the first rotating shaft main body 2211. Similarly, the implementation is not limited to the aforementioned guide rod 232, spiral groove 233, and transverse groove 234; alternatively, threads can be provided on the first rotating shaft 221 or the second rotating shaft 222, thereby threading the first rotating shaft 221 or the second rotating shaft 222 to the wing platform 21 or the fuselage, and threading the lifting shaft 231 to the first rotating shaft 221 or the second rotating shaft 222. In this way, as the first rotating shaft 221 or the second rotating shaft 222 rotates, in conjunction with the feed effect of the threads, the lifting shaft 231 can also be raised and lowered. Further details will not be elaborated upon in this embodiment.

[0078] In this embodiment, the first drive assembly includes a servo motor 241, a first turbine 2421, a second turbine 2422, and a worm gear 243. The servo motor 241 is fixed to the wing platform 21 and engages in transmission with the first turbine 2421 and the second turbine 2422. The first turbine 2421 is located at the bottom of the first rotating shaft 221, and the second turbine 2422 is located at the bottom of the second rotating shaft 222. The first turbine 2421 and the second turbine 2422 are symmetrically arranged on both sides of the worm gear 243 and both engage in transmission with the worm gear 243. Specifically, the servo motor 241 is connected to the bottom of the wing platform 21 by bolts, clips, or other means. The first turbine 2421 has a first upper section and a first side section. The first upper section is a fan-shaped arc segment with an inner diameter slightly larger than the outer diameter of the lifting shaft 231, preventing the outer wall of the lifting shaft 231 from colliding during movement. The outer diameter of the fan-shaped arc segment is slightly larger than the outer diameter of the first rotating shaft bottom body 2212. The first side section and the first upper section form an "L" shape at the outer diameter of the fan-shaped arc segment, with the concave surface fitting against the side wall of the first rotating shaft bottom body 2212 and the convex surface having gears. The second turbine 2422 has a second upper section and a second side section. The second upper section is a fan-shaped arc segment coaxial with the second rotating shaft bottom body 2222, with an outer diameter slightly larger than the outer diameter of the second rotating shaft bottom body 2222. The second side section and the second upper section form an "L" shape at the outer diameter of the fan-shaped arc segment, with the concave surface fitting against the side wall of the second rotating shaft bottom body 2222 and the convex surface having gears. One end of the worm gear 243 is fixedly connected to the rotation shaft of the servo motor 241, and the other end is rotatably fixed to the wing platform 21. A thread is provided at the end near the wing platform 21. A convex gear on the first side section and a convex gear on the second side section are symmetrically arranged on both sides of the worm gear 243, and both mesh with the threaded teeth of the worm gear 243. In specific implementation, the circumference of the first turbine 2421 or the second turbine 2422 is the maximum angle that the first rotating shaft 221 or the second rotating shaft 222 can rotate. It should be noted that by removing the limiter of the servo motor 241, the servo motor 241 can rotate multiple times, enabling a large range of adjustment of the first turbine 2421 and the second turbine 2422, thereby enabling a large sweep angle adjustment of the first wing 11 and the second wing 21.

[0079] In this embodiment, the first drive assembly further includes a potentiometer 244, and the potentiometer shaft 2441 is fixedly connected to the second turbine 2422. Specifically, the potentiometer 244 is connected to the bottom of the wing platform 21 by bolts, clips, etc. A through hole is opened at the center of the potentiometer 244 near the shaft center of the second rotating shaft 222. The potentiometer shaft 2441 is fixedly connected to the second upper section of the second turbine 2422 at the shaft center through the through hole. The potentiometer shaft 2441 and the potentiometer 244 are clearance-fitted. The potentiometer shaft 2441 is provided with three pins. When the second turbine 2422 rotates, it drives the potentiometer shaft 2441 to rotate. The current wing sweep angle can be calculated by measuring the output relationship of the three pins.

[0080] In the specific implementation process, the servo motor 241 drives the rotating shaft to rotate, which in turn drives the worm gear 243. The worm gear 243 drives the first turbine 2421 and the second turbine 2422 to rotate in opposite directions, thereby causing the first rotating shaft 221 and the second rotating shaft 222 to rotate in opposite directions. At the same time, through the sliding connection of the guide rod 232 with the spiral groove 233 and the transverse groove 234, the lifting shaft 231 is driven to rise and fall. This ensures that when the wing assembly is in the folded state, there is a height difference between the first wing 11 and the second wing 12, thus achieving wing stacking. It also eliminates the height difference between the first wing 11 and the second wing 12 when they are in the unfolded state. During the rotation of the servo motor, the rotation amplitude of the second rotating shaft 222 can be obtained in real time through the potentiometer 244. Since the first rotating shaft 221 and the second rotating shaft 222 rotate synchronously in opposite directions, the sweep angle of the wing can be obtained in real time through the potentiometer 244. By controlling the start and stop of the servo motor 241, the sweep angle of the wing assembly can be adjusted.

[0081] In this embodiment, a second drive assembly is also included. The second drive assembly includes a first drive motor 251 and a first lead screw 261. The first drive motor 251 is fixedly mounted on the top of the lifting shaft 231. One end of the first lead screw 261 is connected to the first drive motor 251 for transmission, and the other end passes through the first inner section wing 112 and is connected to the first outer section wing 111. The first lead screw 261 and the first inner section wing 112 are in a rotatable engagement, and the first lead screw 261 and the first outer section wing 111 are in a threaded engagement. Specifically, the second drive assembly also includes a first transmission gear 2512 and a second transmission gear 2611. A first fixing member 2713 is provided on the top of the first connecting member 271. The rotating shaft of the first drive motor 251 passes through the first fixing member 2713 and is fixedly connected to the first transmission gear 2512. The first lead screw 261 passes through the tail end 2712 of the first connecting member and is fixedly connected to the second transmission gear 2611. The first transmission gear 2512 and the second transmission gear 2611 are in a transmission engagement. In the specific implementation process, the first drive motor 251 starts to rotate, driving the first transmission gear 2512. The first transmission gear 2512 drives the second transmission gear 2611 to rotate, and the second transmission gear 2611 drives the first lead screw 261 to rotate. At the connection between the first inner wing section 112 and the first outer wing section 111, the first outer wing section 111 extends or shortens as the threaded hole engages with the first lead screw 261, thereby extending or retracting the first wing 11 and changing its area. The rotation shaft of the first drive motor 251 and the first fixing member 2713 are in a clearance fit.

[0082] In this embodiment, a third drive assembly is also included. The third drive assembly includes a second drive motor 252 and a second lead screw 262. The second drive motor 252 is fixedly mounted on the top of the second rotating shaft 222. One end of the second lead screw 262 is connected to the second drive motor 252 for transmission, and the other end passes through the second inner section wing 122 and is connected to the second outer section wing 121. The second lead screw 262 and the second inner section wing 122 are in a rotatable engagement, and the second lead screw 262 and the second outer section wing 121 are in a threaded engagement. Specifically, the third drive assembly also includes a third transmission gear 2522 and a fourth transmission gear 2621. A second fixing member 2723 is provided on the top of the second connecting member 272. The rotating shaft of the second drive motor 252 passes through the second fixing member 2723 and is fixedly connected to the third transmission gear 2522. The second lead screw 262 passes through the tail end 2722 of the second connecting member and is fixedly connected to the fourth transmission gear 2621. The third transmission gear 2522 and the fourth transmission gear 2621 are in a transmission engagement. In the specific implementation process, the second drive motor 252 starts to rotate, driving the third transmission gear 2522. The third transmission gear 2522 drives the fourth transmission gear 2621 to rotate, and the fourth transmission gear 2621 drives the second lead screw 262 to rotate. At the connection between the second inner wing section 122 and the second outer wing section 121, the second outer wing section 121 extends or shortens as the threaded hole engages with the second lead screw 262, thereby extending or retracting the second wing 12 and changing its area. The rotating shaft of the second drive motor 252 and the second fixing member 2723 are in a clearance fit.

[0083] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0084] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A variable-sweep retractable wing structure, comprising a wing platform and a wing assembly, wherein the wing assembly includes a first wing and a second wing, characterized in that, It also includes a first drive assembly, a rotating assembly, and a lifting shaft; The rotating assembly includes a first rotating shaft and a second rotating shaft that are rotatably connected side by side on the wing platform. The first rotating shaft is coaxially sleeved on the lifting shaft. The first rotating shaft and the lifting shaft are fixedly fitted in the circumferential direction and slidingly fitted in the axial direction. The first wing is connected to the top of the lifting shaft, and the second wing is connected to the top of the second rotating shaft. Both the first wing and the second wing are telescopic structures, and the telescopic structure is a drive structure that combines a motor and a lead screw. The first drive component is connected to the first rotating shaft and the second rotating shaft for driving the first rotating shaft and the second rotating shaft to rotate, and driving the lifting shaft to move up and down; The first drive assembly includes: a servo motor, a first turbine, a second turbine, and a worm gear; The servo is fixed on the wing platform and drives the first turbine and the second turbine. The first turbine is located at the bottom of the first rotating shaft, and the second turbine is located at the bottom of the second rotating shaft. The first turbine and the second turbine are symmetrically arranged on both sides of the worm and drive the worm. The first drive assembly further includes a potentiometer, the potentiometer knob being fixedly connected to the second turbine; It also includes a guide rod, a spiral groove is provided on the side wall of the lifting shaft, and a horizontal groove is provided on the first rotating shaft; one end of the guide rod is fixedly connected to the wing platform or fuselage, and the other end passes through the spiral groove after passing through the horizontal groove. The guide rod is slidably connected to the spiral groove and the transverse groove.

2. The variable sweep retractable wing structure according to claim 1, characterized in that, Both the first turbine and the second turbine have a fan-shaped structure.

3. The variable sweep retractable wing structure according to claim 1 or 2, characterized in that, It also includes a second drive component; The first wing includes a first outer wing section and a first inner wing section. One end of the first inner wing section is connected to the elevator shaft, and the other end is sleeved with the first outer wing section. The second drive assembly includes a first drive motor and a first lead screw. The first drive motor is fixedly mounted on the top of the lifting shaft. One end of the first lead screw is connected to the first drive motor, and the other end passes through the first inner wing section and is connected to the first outer wing section. The first lead screw is rotatably engaged with the first inner section wing, and the first lead screw is threadedly engaged with the first outer section wing.

4. The variable sweep retractable wing structure according to claim 3, characterized in that, It also includes a first connector; The first end of the first connector is fixedly connected to the top of the lifting shaft, and the tail end of the first connector is fixedly connected to the first inner wing section. The tail end of the first connector is higher than the head end of the first connector.

5. The variable sweep retractable wing structure according to claim 1 or 2, characterized in that, It also includes a third driving component; The second wing includes a second outer wing section and a second inner wing section. Two ends of the second inner wing section are connected to the second pivot, and the other end is sleeved with the second outer wing section. The third drive assembly includes a second drive motor and a second lead screw. The second drive motor is fixedly mounted on the top of the second rotating shaft. One end of the second lead screw is connected to the second drive motor, and the other end passes through the second inner wing section and is connected to the second outer wing section. The second lead screw is rotatably engaged with the second inner section wing, and the second lead screw is threadedly engaged with the second outer section wing.

6. The variable sweep retractable wing structure according to claim 5, characterized in that, It also includes a second connector; The first end of the second connector is fixedly connected to the top of the second rotating shaft, and the tail end of the second connector is fixedly connected to the second inner section wing. The tail end of the second connector is higher than the head end of the second connector.

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