A wing surface unfolding structure for a folding wing aircraft

Abstract

The application provides a wing surface unfolding structure of a folding wing aircraft applied to the technical field of folding wing unmanned aerial vehicles, wherein a rotating part is arranged between a front wing and a rear wing and a fuselage, a hook spring in the rotating part can pull the front wing and the rear wing in a folded state to quickly unfold, a driving unfolding part is arranged to drive the front wing and the rear wing in a storage state to synchronously unfold to both sides, after unfolding to a certain angle, the front wing and the rear wing can be quickly and completely unfolded under the pulling of the rotating part, a manual unfolding part is arranged, when the driving unfolding part cannot unfold the wings, the manual driving ensures that the wings can be smoothly unfolded, a moving block is arranged at the top of the fuselage to limit a tail fin, and a magnetic sheet one and a magnetic sheet two that can attract each other are arranged at the end of the moving block and the front wing that are close to each other, in the process of rotating and unfolding of the front wing, the moving block is driven to move to release the limitation on the tail fin, and the tail fin is automatically unfolded in the process of unfolding of the front wing.

Description

Technical Field

[0001] This application relates to the field of folding-wing unmanned aerial vehicle (UAV) technology, and in particular to a wing deployment structure for a folding-wing aircraft. Background Technology

[0002] Foldable-wing aircraft are aircraft that use foldable wings or wing surfaces to reduce their size when not in use, making them easy to store or transport, and to quickly unfold when needed to provide aerodynamic lift and control capabilities. Their core feature is the ability to dynamically transform their structure, combining compactness, portability, and efficient flight performance. The unfolding mechanism of a foldable-wing aircraft is a key component that ensures that its wings or wing surfaces can be quickly and reliably unfolded from the folded state when needed. Such mechanisms are widely used in drones, spacecraft, military aircraft, and other fields to achieve compact storage, efficient aerodynamic performance, or mission adaptability.

[0003] While existing folding-wing drones achieve folding wings for easy storage when not in use, some parts require manual unfolding, which is very cumbersome. Other parts can unfold automatically, but the front wing, rear wing, and tail fin unfold sequentially, not simultaneously. This not only reduces the wing unfolding efficiency but also affects the drone's stability during takeoff due to the asynchronous unfolding of the front wing, rear wing, and tail fin.

[0004] To address these issues, we propose a wing deployment structure for a folding-wing aircraft. Summary of the Invention

[0005] To address the problems existing in the prior art, the purpose of this application is to set up a wing surface deployment mechanism to drive the two front wings and two rear wings to deploy simultaneously, and to drive the tail vertical shaft to deploy simultaneously during the wing deployment process, so as to achieve the simultaneous deployment of the front wings, rear wings and tail vertical shaft, making the front wings, rear wings and tail vertical shaft deploy faster and with higher deployment efficiency, and providing a wing surface deployment structure for a folding wing aircraft compared with the prior art.

[0006] To solve the above-mentioned technical problems, the present invention adopts the following technical solution.

[0007] A wing deployment structure for a folding wing aircraft includes a fuselage, a front wing rotatably connected to the top of the fuselage, a rear wing rotatably connected to the bottom of the fuselage, and a tail fin rotatably connected to the side of the fuselage. Rotating components are provided between the front wing and the rear wing and the fuselage. The rotating components include mounting posts, lugs, and hook springs. Multiple mounting posts are provided and are fixedly connected to the fuselage. Multiple mounting lugs are provided, and each of the front and rear wings is fixedly connected to one mounting lug. The hook spring is connected between the mounting lug and the mounting post.

[0008] Furthermore, a drive deployment component is provided between the end of the front wing and the end of the rear wing. The drive deployment component includes a servo motor, a drive gear, a support block, a double-headed worm, a gear ring, a worm wheel one, a worm wheel two, a front gear one, a front gear two, a front friction wheel one, a front friction wheel two, a rear gear one, a rear gear two, a rear friction wheel one, and a rear friction wheel two. The servo motor is fixedly connected to the inner bottom wall of the machine body. The drive gear is fixedly connected to the output shaft of the servo motor. The support block is fixedly connected to the inner bottom wall of the machine body. The double-headed worm gear is rotatably connected to the support block. The gear ring is fixedly sleeved on the outer side of the double-headed worm gear. The first worm wheel meshes with one end of the double-headed worm gear, and the second worm wheel meshes with the other end of the double-headed worm gear. The first front gear meshes with the first worm wheel, and the second front gear meshes with the first front gear. The first front friction wheel is coaxially and fixedly connected to the first front gear. The second front friction wheel is coaxially and fixedly connected to the second front gear. The first rear gear meshes with the second worm wheel, and the second rear gear meshes with the first rear gear. The first rear friction wheel is coaxially and fixedly connected to the second rear gear. The second rear friction wheel is coaxially and fixedly connected to the second rear gear.

[0009] Furthermore, the first front friction wheel and the second front friction wheel are respectively press-fitted with the ends of the two front wings, and the first rear friction wheel and the second rear friction wheel are respectively press-fitted with the ends of the two rear wings. The ends of the front wings and the rear wings are arc-shaped. The first front friction wheel, the second front friction wheel, the first rear friction wheel, and the second rear friction wheel are all made of elastic polyurethane.

[0010] Furthermore, the worm gear one, worm gear two, front gear one, front gear two, front friction wheel one, front friction wheel two, rear gear one, rear gear two, rear friction wheel one, and rear friction wheel two are all rotatably connected to the machine body.

[0011] Furthermore, a manually deployable component is provided on one side of the machine body, the manually deployable component including a slide, a slider, a rack, a bracket, a manual gear and a return spring; The slide groove is formed on the side of the machine body, the slider passes through the slide groove and is slidably connected to the slide groove, the rack is fixedly connected to the slider, the bracket is fixedly connected to the inner bottom wall of the machine body, the manual gear is rotatably connected to the bracket, the rack meshes with the manual gear for transmission, the manual gear meshes with the gear ring for transmission, and the return spring is fixedly connected between the slider and the slide groove.

[0012] Furthermore, both ends of the top of the fuselage are provided with movable slots, and movable blocks are slidably connected in the movable slots. A magnetic sheet 1 is embedded and fixedly connected to the surface of the movable block. A magnetic sheet 2 is embedded and fixedly connected to the lower edge of the two front wings. The magnetic poles of the magnetic sheet 1 and magnetic sheet 2 are opposite at their close ends. A compression spring is fixedly connected between the movable block and the movable slot.

[0013] Furthermore, when the tail fin is unfolded, the moving block presses against the front end of the tail fin, and when the tail fin is folded, the moving block presses against the upper end of the tail fin.

[0014] Furthermore, the tail fin is rotatably connected to the fuselage via a torsion spring, and the front end of the tail fin is tilted.

[0015] Furthermore, a protective plate is provided on the outer side of the rotating component, and the protective plate is fixedly connected to the machine body. Compared with the prior art, the advantages of this application are: (1) By setting a rotating component, the rotating component can pull the front wing and rear wing in the folded state to unfold quickly. When the front wing and rear wing are in the retracted state, the hook spring is parallel to the front wing and rear wing. At this time, the direction of the spring tension on the front wing and rear wing is parallel to the front wing and rear wing. Therefore, the front wing and rear wing will not rotate, and the front wing and rear wing can be kept in the folded state. When the front wing and rear wing are in the unfolded state, the hook spring is not parallel to the front wing and rear wing. The elastic force of the hook spring acts on the front wing and rear wing, forming a tension on the front wing and rear wing, so that the front wing and rear wing can unfold quickly and maintain a stable unfolded state.

[0016] (2) By setting up a drive deployment component, the front and rear wings in the retracted state can be driven to deploy synchronously to both sides. After being deployed to a certain angle, they can be quickly and fully deployed under the pull of the rotating component. The servo motor is started to drive the drive gear to rotate. The drive gear rotates to drive the gear ring and the double-headed worm to rotate. The double-headed worm rotates to drive the meshing worm wheel one and worm wheel two to rotate. The worm wheel one rotates to drive the meshing front gear one to rotate. The front gear one rotates to drive the meshing front gear two to rotate, thereby driving the front friction wheel one and the front friction wheel two to rotate in opposite directions, thereby driving the two front wings to rotate and deploy to both sides. Similarly, the worm wheel two rotates to drive the rear gear one and the rear gear two to rotate, thereby driving the rear friction wheel one and the rear friction wheel two to rotate in opposite directions, thereby driving the two rear wings to rotate and deploy to both sides. Since the worm wheel one and the worm wheel two rotate synchronously, the two front wings and the two rear wings will also deploy synchronously, thereby enabling the front wings and rear wings to deploy more quickly.

[0017] (3) By setting up a manual deployment component, when the remote control fails or other situations cause the drive deployment component to fail to drive the front and rear wings to deploy, the manual deployment component can manually drive the front and rear wings to rotate and deploy, ensuring that the front and rear wings can be deployed smoothly. The slider drives the rack to move, the rack moves to drive the manual gear to rotate, the manual gear rotates to drive the gear ring and double-headed worm to rotate, thereby driving worm wheel one and worm wheel two to rotate, which in turn drives front friction wheel one and front friction wheel two, as well as rear friction wheel one and rear friction wheel two to rotate, manually driving the two front wings and two rear wings to deploy synchronously, thus realizing manual deployment of the wings.

[0018] (4) By opening a moving slot at both ends of the top of the fuselage and a moving block that is slidably connected to the moving slot, and setting magnetic sheet 1 and magnetic sheet 2 that attract each other at the lower end of the moving block and the front wing, magnetic sheet 2 at the lower edge of the front wing also moves forward of the fuselage along with the front wing during the rotation and unfolding process. Magnetic sheet 2 and magnetic sheet 1 attract each other, so the moving block will move forward of the fuselage in the moving slot until the moving block leaves the tail fin. At this time, the tail fin rotates and unfolds under the elastic force of the torsion spring, thus realizing the automatic unfolding of the tail fin during the unfolding process of the front wing, and also realizing the synchronous unfolding of the front wing, rear wing and tail fin, making the unfolding speed of the front wing, rear wing and tail fin faster and the unfolding efficiency higher.

[0019] (5) By pressing the moving block against the tail, when storing, rotating the tail can press the moving block forward until the tail rotates to a horizontal position. At this time, the moving block is above the tail and is no longer pressed. Under the elastic force of the compression spring, it resets and limits the tail, thus realizing the folding and storage of the tail. In the unfolded state, the moving block can press from the front end of the tail, making the tail more stable after unfolding.

[0020] (6) By setting the materials of front friction wheel one, front friction wheel two, rear friction wheel one and rear friction wheel two to elastic polyurethane, elastic polyurethane has high strength and elasticity, wear resistance, fatigue resistance, vibration resistance and impact resistance, which can increase the frictional resistance between front friction wheel one and front friction wheel two, rear friction wheel one and rear friction wheel two and the ends of the front wing and rear wing, so as to drive the front wing and rear wing to rotate and unfold to both sides more smoothly.

[0021] (7) By setting a protective plate on the outside of the rotating part, the protective plate can protect the rotating part and prevent it from being damaged by impact and affecting the stability of the wing. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall structure of this application in its unfolded state; Figure 2This is a schematic diagram of the overall structure of the storage state in this application; Figure 3 This is a schematic diagram of the rotating component structure in the unfolded state of this application; Figure 4 This is a schematic diagram of the rotating component structure in the folded state of this application; Figure 5 This is a schematic diagram of the drive deployment component structure of this application; Figure 6 For this application Figure 2 Enlarged view of the structural part at point A in the middle; Figure 7 For this application Figure 2 Enlarged view of the structural section at point B; Figure 8 For this application Figure 5 Enlarged view of the structural part at point C; Figure 9 This is a schematic diagram of the front wing structure viewed from below in this application.

[0023] Explanation of the labels in the diagram: 1. Fuselage; 2. Forward Wing; 3. Rear Wing; 4. Tail Vertical Bar; 5. Rotating Components; 501. Mounting Post; 502. Hook; 503. Hook Spring; 6. Drive Deployment Components; 601. Servo Motor; 602. Drive Gear; 603. Support Block; 604. Double-ended Worm Gear; 605. Gear Ring; 606. Worm Gear 1; 607. Worm Gear 2; 608. Front Gear 1; 609. Front Gear 2; 610. Front Friction Wheel 1. Front friction wheel 2; 612. Rear gear 1; 613. Rear gear 2; 614. Rear friction wheel 1; 615. Rear friction wheel 2; 7. Manual unfolding component; 701. Slide groove; 702. Slider; 703. Rack; 704. Bracket; 705. Manual gear; 706. Return spring; 8. Moving groove; 9. Moving block; 10. Magnetic sheet 1; 11. Magnetic sheet 2; 12. Compression spring; 13. Protective plate. Detailed Implementation

[0024] The technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0025] This invention provides a wing deployment structure for a folding-wing aircraft. Please refer to [link / reference]. Figures 1-9The fuselage includes a fuselage 1, a front wing 2 rotatably connected to the top of the fuselage 1, a rear wing 3 rotatably connected to the bottom of the fuselage 1, and a tail fin 4 rotatably connected to the side of the fuselage 1. The rotation angles of the front wing 2, rear wing 3, and tail fin 4 are all 90°. The front wing 2 and rear wing 3 can only rotate between the deployed and folded states, and the tail fin 4 can only rotate between the vertical and horizontal states. Rotating components 5 are provided between the front wing 2 and rear wing 3 and the fuselage 1. The rotating components 5 can pull the folded front wing 2 and rear wing 3 to quickly unfold. A protective plate 13 is provided on the outside of the rotating component 5. The protective plate 13 is fixedly connected to the fuselage 1 and can protect the rotating component 5 from impact damage and affect the stability of the wing.

[0026] The rotating component 5 includes a mounting post 501, a lug 502, and a hook spring 503. Multiple mounting posts 501 are provided and are fixedly connected to the fuselage 1. Multiple lugs 502 are provided, and each front wing 2 and rear wing 3 is fixedly connected to one lug 502. The hook spring 503 is connected between the lug 502 and the mounting post 501.

[0027] Specifically, when the front wing 2 and rear wing 3 are in the retracted state, the hook spring 503 is parallel to the front wing 2 and rear wing 3. At this time, the direction of the spring tension on the front wing 2 and rear wing 3 is parallel to the front wing 2 and rear wing 3. Therefore, the front wing 2 and rear wing 3 will not rotate, and can keep the front wing 2 and rear wing 3 in the folded state. When the front wing 2 and rear wing 3 are in the unfolded state, the hook spring 503 is not parallel to the front wing 2 and rear wing 3. The elastic force of the hook spring 503 acts on the front wing 2 and rear wing 3, forming a tension on the front wing 2 and rear wing 3, so that the front wing 2 and rear wing 3 can be quickly unfolded and maintain a stable unfolded state.

[0028] A drive deployment component 6 is provided between the end of the front wing 2 and the end of the rear wing 3. The drive deployment component 6 can drive the front wing 2 and the rear wing 3 in their retracted state to expand synchronously to both sides. After expanding to a certain angle, they can be quickly and fully expanded under the pull of the rotating component 5. The drive deployment component 6 includes a servo motor 601, a drive gear 602, a support block 603, a double-headed worm gear 604, a gear ring 605, a first worm gear 606, a second worm gear 607, a first front gear 608, a second front gear 609, a first front friction wheel 610, a second front friction wheel 611, a first rear gear 612, a second rear gear 613, a first rear friction wheel 614, and a second rear friction wheel 615; the servo motor 601... 01 is fixedly connected to the inner bottom wall of the body 1. The drive gear 602 is fixedly connected to the output shaft of the servo motor 601. The support block 603 is fixedly connected to the inner bottom wall of the body 1. The double-headed worm gear 604 is rotatably connected to the support block 603. The gear ring 605 is fixedly sleeved on the outer side of the double-headed worm gear 604. Worm wheel 606 meshes with one end of the double-headed worm gear 604 for transmission. Worm wheel 607 meshes with the other end of the double-headed worm gear 604 for transmission. Front gear 608 meshes with worm wheel 606 for transmission. Front gear 609 meshes with front gear 608 for transmission. Front friction wheel 610 is coaxially fixedly connected to front gear 608. Front friction wheel 611 is coaxially fixedly connected to front gear 608. 09. Coaxial fixed connection, rear gear 1 612 meshes with worm gear 2 607 for transmission, rear gear 2 613 meshes with rear gear 1 612 for transmission, rear friction wheel 1 614 is coaxially fixedly connected with rear gear 1 612, rear friction wheel 2 615 is coaxially fixedly connected with rear gear 2 613, front friction wheel 1 610 and front friction wheel 2 611 are respectively pressed into the ends of the two front wings 2, and rear friction wheel 1 614 and rear friction wheel 2 615 are respectively pressed into the ends of the two rear wings 3. The ends of the front wings 2 and rear wings 3 are arc-shaped. The materials of front friction wheel 1 610, front friction wheel 2 611, rear friction wheel 1 614 and rear friction wheel 2 615 are all... Elastic polyurethane possesses high strength, elasticity, wear resistance, fatigue resistance, vibration resistance, and impact resistance. It can increase the frictional resistance between the front friction wheel 1 610 and the front friction wheel 2 611, the rear friction wheel 1 614 and the rear friction wheel 2 615, and the ends of the front wing 2 and the rear wing 3. This allows for smoother driving of the front wing 2 and the rear wing 3 to rotate and unfold to both sides. The worm gear 1 606, worm gear 2 607, front gear 1 608, front gear 2 609, front friction wheel 1 610, front friction wheel 2 611, rear gear 1 612, rear gear 2 613, rear friction wheel 1 614, and rear friction wheel 2 615 are all rotatably connected to the fuselage 1.

[0029] Specifically, the servo motor 601 is started, driving the drive gear 602 to rotate. The drive gear 602 rotates, driving the gear ring 605 and the double-headed worm 604 to rotate. The double-headed worm 604 rotates, driving the meshing worm gear 1 606 and worm gear 2 607 to rotate. The rotation of worm gear 1 606 drives the meshing front gear 1 608 to rotate. The rotation of front gear 1 608 drives the meshing front gear 2 609 to rotate, thereby driving the front friction wheel 1 610 and front friction wheel 2 611 to rotate in opposite directions, thus driving the two front wings 2 to rotate and unfold to both sides. Similarly, the rotation of worm gear 2 607 drives the rear gear 1 612 and rear gear 2 613 to rotate, thereby driving the rear friction wheel 1 614 and rear friction wheel 2 615 to rotate in opposite directions, thus driving the two rear wings 3 to rotate and unfold to both sides. Since worm gear 1 606 and worm gear 2 607 rotate synchronously, the two front wings 2 and the two rear wings 3 will also unfold synchronously, thus enabling the front wings 2 and rear wings 3 to unfold more quickly.

[0030] A manual deployment component 7 is provided on one side of the fuselage 1. When the remote control fails or other situations prevent the drive deployment component 6 from deploying the front wing 2 and rear wing 3, the manual deployment component 7 can manually drive the front wing 2 and rear wing 3 to rotate and deploy, ensuring that the front wing 2 and rear wing 3 can be deployed smoothly. The manual deployment component 7 includes a slide groove 701, a slider 702, a rack 703, a bracket 704, a manual gear 705, and a return spring 706. The slide groove 701 is opened on the side of the fuselage 1. The slider 702 passes through the slide groove 701 and is slidably connected to the slide groove 701. The rack 703 is fixedly connected to the slider 702. The bracket 704 is fixedly connected to the inner bottom wall of the fuselage 1. The manual gear 705 is rotatably connected to the bracket 704. The rack 703 meshes with the manual gear 705 for transmission. The manual gear 705 meshes with the gear ring 605 for transmission. The return spring 706 is fixedly connected between the slider 702 and the slide groove 701.

[0031] Specifically, pushing the slider 702 causes the rack 703 to move, the rack 703 moves and causes the manual gear 705 to rotate, the manual gear 705 rotates and causes the gear ring 605 and the double-headed worm 604 to rotate, thereby causing the first worm wheel 606 and the second worm wheel 607 to rotate, which in turn causes the first front friction wheel 610 and the second front friction wheel 611, as well as the first rear friction wheel 614 and the second rear friction wheel 615 to rotate, manually driving the two front wings 2 and the two rear wings 3 to deploy simultaneously, thus realizing the manual deployment of the wings.

[0032] The top of the fuselage 1 has a movable slot 8 at both ends. A movable block 9 is slidably connected in the movable slot 8. A magnetic sheet 10 is embedded and fixedly connected to the surface of the movable block 9. A magnetic sheet 21 is embedded and fixedly connected to the lower edge of the two front wings 2. The magnetic poles of the magnetic sheet 10 and the magnetic sheet 21 are opposite at their close ends. A compression spring 12 is fixedly connected between the movable block 9 and the movable slot 8.

[0033] Specifically, during the rotation and deployment of the forewing 2, the magnetic plate 11 at the lower edge of the forewing 2 also moves forward toward the fuselage 1 along with the rotation of the forewing 2. The magnetic plate 11 and the magnetic plate 10 attract each other, thus driving the moving block 9 to move forward toward the fuselage 1 within the moving slot 8 until the moving block 9 leaves the tail 4. At this time, the tail 4 rotates and deploys under the elastic force of the torsion spring, thereby realizing the automatic deployment of the tail 4 during the deployment of the forewing 2. At the same time, the synchronous deployment of the forewing 2, the rear wing 3 and the tail 4 are also realized, making the deployment speed of the forewing 2, the rear wing 3 and the tail 4 faster and the deployment efficiency higher.

[0034] When the tail 4 is unfolded, the moving block 9 presses against the front end of the tail 4. When the tail 4 is folded, the moving block 9 presses against the upper end of the tail 4. The tail 4 is rotatably connected to the body 1 by a torsion spring. The front end of the tail 4 is tilted. When stored, rotating the tail 4 can press the moving block 9 forward until the tail 4 is rotated to a horizontal position. At this time, the moving block 9 is above the tail 4 and is no longer pressed. It returns to its original position under the elastic force of the compression spring 12, thereby limiting the tail 4 and realizing the folding and storage of the tail 4. In the unfolded state, the moving block 9 can press from the front end of the tail 4, making the tail 4 more stable after unfolding.

[0035] Working principle: When the aircraft is not in use, the front wing 2, rear wing 3 and tail fin 4 are all in the retracted state. The hook spring 503 is parallel to the front wing 2 and rear wing 3. At this time, the direction of the spring tension on the front wing 2 and rear wing 3 is parallel to the front wing 2 and rear wing 3. Therefore, the front wing 2 and rear wing 3 will not rotate, keeping the front wing 2 and rear wing 3 in the folded state. The moving block 9 is located above the tail fin 4 and limits the tail fin 4, keeping the tail fin 4 in the folded state. When using the aircraft, the servo motor 601 is controlled by a remote controller to start the aircraft's power unit. The remote controller also controls the start and stop of the motor; this is existing technology and will not be described in detail here. The servo motor 601 drives the drive gear 602 to rotate, which in turn drives the gear ring 605 and the double-headed worm gear 604. The double-headed worm gear 604 then drives the meshing worm gear one 606 and worm gear two 607. The rotation of worm gear one 606 drives the meshing front gear one 608 to rotate, which in turn drives the meshing front gear two 609, thereby driving the front motor... Friction wheel 1 610 and front friction wheel 2 611 rotate in opposite directions, thereby driving the two front wings 2 to rotate and unfold to the sides. Similarly, the rotation of worm gear 2 607 drives the rear gear 1 612 and rear gear 2 613 to rotate, thereby driving the rear friction wheel 1 614 and rear friction wheel 2 615 to rotate in opposite directions, thereby driving the two rear wings 3 to rotate and unfold to the sides. Since worm gear 1 606 and worm gear 2 607 rotate synchronously, the two front wings 2 and the two rear wings 3 will also unfold synchronously, thus enabling the front wings 2 and rear wings 3 to unfold more quickly. After the two front wings 2 and the two rear wings 3 are driven to unfold, the hook spring 503 is not parallel to the front wings 2 and the rear wings 3. The elastic force of the hook spring 503 acts on the front wings 2 and the rear wings 3, forming a pulling force on the front wings 2 and the rear wings 3, so that the front wings 2 and the rear wings 3 unfold quickly and maintain a stable unfolded state. During the rotation and deployment of the forewing 2, the magnetic plate 11 at the lower edge of the forewing 2 also moves forward toward the fuselage 1 along with the rotation of the forewing 2. The magnetic plate 11 and the magnetic plate 10 attract each other, which will drive the moving block 9 to move forward toward the fuselage 1 in the moving slot 8 until the moving block 9 leaves the tail 4. At this time, the tail 4 rotates and deploys under the elastic force of the torsion spring, thus realizing the automatic deployment of the tail 4 during the deployment of the forewing 2. At the same time, the synchronous deployment of the forewing 2, the rear wing 3 and the tail 4 are also realized, making the deployment speed of the forewing 2, the rear wing 3 and the tail 4 faster and the deployment efficiency higher. When the remote control malfunctions or other situations prevent the drive deployment component 6 from deploying the front wing 2 and the rear wing 3, the slider 702 is manually pushed to move the rack 703. The rack 703 moves, causing the manual gear 705 to rotate. The manual gear 705 rotates, causing the gear ring 605 and the double-headed worm gear 604 to rotate, which in turn drives the first worm wheel 606 and the second worm wheel 607 to rotate. This, in turn, drives the first front friction wheel 610 and the second front friction wheel 611, as well as the first rear friction wheel 614 and the second rear friction wheel 615 to rotate, thus manually driving the two front wings 2 and the two rear wings 3 to deploy simultaneously, achieving manual wing deployment and ensuring that the wings can be deployed smoothly.

[0036] The above description is merely a preferred embodiment of this application, but the scope of protection of this application is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in this application, based on the technical solution and its improved concept, should be covered within the scope of protection of this application.

Claims

1. A wing deployment structure for a folding-wing aircraft, comprising a fuselage (1), a forewing (2) rotatably connected to the top of the fuselage (1), a rearwing (3) rotatably connected to the bottom of the fuselage (1), and a tail fin (4) rotatably connected to the side of the fuselage (1), characterized in that, Rotating components (5) are provided between the front wing (2) and the rear wing (3) and the fuselage (1). The rotating components (5) include mounting posts (501), lugs (502) and hook springs (503). Multiple mounting posts (501) are provided and are fixedly connected to the fuselage (1). Multiple lugs (502) are provided. Each of the front wing (2) and rear wing (3) is fixedly connected to a lug (502). The hook spring (503) is connected between the lug (502) and the mounting post (501).

2. The wing deployment structure of a folding-wing aircraft according to claim 1, characterized in that, A drive deployment component (6) is provided between the end of the front wing (2) and the end of the rear wing (3). The drive deployment component (6) includes a servo motor (601), a drive gear (602), a support block (603), a double-headed worm (604), a gear ring (605), a worm wheel one (606), a worm wheel two (607), a front gear one (608), a front gear two (609), a front friction wheel one (610), a front friction wheel two (611), a rear gear one (612), a rear gear two (613), a rear friction wheel one (614), and a rear friction wheel two (615). The servo motor (601) is fixedly connected to the inner bottom wall of the body (1). The drive gear (602) is fixedly connected to the output shaft of the servo motor (601). The support block (603) is fixedly connected to the inner bottom wall of the body (1). The double-headed worm (604) is rotatably connected to the support block (603). The gear ring (605) is fixedly sleeved on the outside of the double-headed worm (604). The first worm wheel (606) meshes with one end of the double-headed worm (604) for transmission. The second worm wheel (607) meshes with the other end of the double-headed worm (604) for transmission. The first front gear (608) meshes with the worm... Gear 1 (606) meshes and drives, front gear 2 (609) meshes and drives front gear 1 (608), front friction wheel 1 (610) is coaxially and fixedly connected to front gear 1 (608), front friction wheel 2 (611) is coaxially and fixedly connected to front gear 2 (609), rear gear 1 (612) meshes and drives worm gear 2 (607), rear gear 2 (613) meshes and drives rear gear 1 (612), rear friction wheel 1 (614) is coaxially and fixedly connected to rear gear 1 (612), and rear friction wheel 2 (615) is coaxially and fixedly connected to rear gear 2 (613).

3. The wing deployment structure of a folding-wing aircraft according to claim 2, characterized in that, The first front friction wheel (610) and the second front friction wheel (611) are respectively squeezed into the ends of the two front wings (2). The ends of the front wings (2) and the rear wings (3) are arc-shaped. The first rear friction wheel (614) and the second rear friction wheel (615) are respectively squeezed into the ends of the two rear wings (3). The first front friction wheel (610), the second front friction wheel (611), the first rear friction wheel (614) and the second rear friction wheel (615) are all made of elastic polyurethane.

4. The wing deployment structure of a folding-wing aircraft according to claim 2, characterized in that, The first worm gear (606), the second worm gear (607), the first front gear (608), the second front gear (609), the first front friction wheel (610), the second front friction wheel (611), the first rear gear (612), the second rear gear (613), the first rear friction wheel (614), and the second rear friction wheel (615) are all rotatably connected to the machine body (1).

5. The wing deployment structure of a folding-wing aircraft according to claim 2, characterized in that, A manual unfolding component (7) is provided on one side of the body (1). The manual unfolding component (7) includes a slide (701), a slider (702), a rack (703), a bracket (704), a manual gear (705), and a return spring (706). The slide groove (701) is formed on the side of the body (1). The slider (702) passes through the slide groove (701) and is slidably connected to the slide groove (701). The rack (703) is fixedly connected to the slider (702). The bracket (704) is fixedly connected to the inner bottom wall of the body (1). The manual gear (705) is rotatably connected to the bracket (704). The rack (703) meshes with the manual gear (705) for transmission. The manual gear (705) meshes with the gear ring (605) for transmission. The return spring (706) is fixedly connected between the slider (702) and the slide groove (701).

6. The wing deployment structure of a folding-wing aircraft according to claim 1, characterized in that, The top of the fuselage (1) is provided with a moving groove (8) at both ends. A moving block (9) is slidably connected in the moving groove (8). A magnetic sheet (10) is embedded and fixedly connected to the surface of the moving block (9). A magnetic sheet (11) is embedded and fixedly connected to the lower edge of the two front wings (2). The magnetic poles of the magnetic sheet (10) and the magnetic sheet (11) are opposite at the ends that are close to each other. A compression spring (12) is fixedly connected between the moving block (9) and the moving groove (8).

7. The wing deployment structure of a folding-wing aircraft according to claim 6, characterized in that, When the tail (4) is unfolded, the moving block (9) presses against the front end of the tail (4) and when the tail (4) is folded, the moving block (9) presses against the upper end of the tail (4).

8. The wing deployment structure of a folding-wing aircraft according to claim 1, characterized in that, The tail fin (4) is rotatably connected to the fuselage (1) by a torsion spring, and the front end of the tail fin (4) is tilted.

9. The wing deployment structure of a folding-wing aircraft according to claim 1, characterized in that, A protective plate (13) is provided on the outside of the rotating part (5), and the protective plate (13) is fixedly connected to the body (1).

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