Foldable fixed wing of unmanned aerial vehicle
By combining an electric telescopic rod with a locking mechanism, the unmanned aerial vehicle (UAV) wing can be adjusted at multiple angles and locked stably, solving the problems of complex operation and inconvenient storage of traditional fixed-wing aircraft and improving the flexibility and stability of the aircraft.
Patent Information
- Application Number
- CN202512034682.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-31
- Publication Date
- 2026-03-03
AI Technical Summary
Traditional fixed-wing unmanned aerial vehicles have complex wing structures, are cumbersome to operate, lack stability when locked after folding, and cannot flexibly adjust the wing deployment angle, affecting flight attitude stability and control precision. They are also inconvenient to store and transport.
The system employs an electric telescopic rod to drive the adjustment plate and rotating column, enabling multi-angle wing adjustment. Combined with a fixing mechanism using a fixed spring and a limit ring, and a dual-axis motor locking pin, the wing is locked to ensure flight stability. The folding wing can be quickly disassembled by pulling a block.
It enables flexible adjustment of wing angle, reduces storage space occupation, lowers the risk of transportation damage, improves transfer flexibility and flight stability, and facilitates maintenance and disassembly.
Smart Images
Figure CN121590788A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of unmanned aerial vehicle technology, and specifically relates to a foldable fixed wing for an unmanned aerial vehicle. Background Technology
[0002] Unmanned aerial vehicles (UAVs), with their advantages of flexibility, maneuverability, and ease of operation, have been widely used in various fields such as aerial surveying and mapping, agricultural plant protection, power line inspection, and emergency rescue. Fixed-wing UAVs, due to their characteristics of high flight speed, long endurance, and high payload efficiency, are particularly important in long-distance, large-scale operational scenarios. However, the wings of traditional fixed-wing UAVs are mostly integrated fixed structures with a large span, which requires a lot of space for storage. During transportation, this not only presents problems with loading and unloading but also makes the wings susceptible to damage from external collisions, greatly limiting their flexibility in transporting them in complex terrain and confined spaces.
[0003] Meanwhile, some existing foldable fixed-wing designs have obvious defects: on the one hand, the folding mechanism is complex and cumbersome to operate, and the locking stability after folding is insufficient. During flight, the wings are prone to loosening and angle deviation, which affects the stability of the flight attitude and the control precision. On the other hand, most foldable wings can only achieve folding and storage at a single angle, and cannot flexibly adjust the wing deployment angle according to the flight environment (such as wind speed and load) and operational requirements, which limits the adaptability and flight efficiency of the aircraft. Summary of the Invention
[0004] The purpose of this invention is to provide a foldable fixed wing for unmanned aerial vehicles, in order to solve the problems mentioned in the background art, such as the complex folding mechanism structure, cumbersome operation, and the fact that most foldable wings can only achieve folding and storage at a single angle.
[0005] To achieve the above objectives, the present invention provides the following technical solution: a foldable fixed wing for an unmanned aerial vehicle, comprising a fuselage and a drive motor installed inside the fuselage, a propeller fixed to the output shaft of the drive motor, two fixed wings fixed to the surface of the fuselage, two mounting holes opened at the bottom of the fuselage, a rotating column rotatably connected to the mounting holes, and a drive gear fixed to the outer wall of the rotating column; A connecting sleeve is fixed to the bottom of the rotating column. A folding wing is movably connected to the outside of the connecting sleeve, and a limiting ring for restricting the position of the folding wing is movably connected to the outside of the connecting sleeve. A fixing hole is opened on the surface of the folding wing, and a displacement sensor is installed in the fixing hole. A fixing mechanism is provided inside the connecting sleeve. An electric telescopic rod is installed on the bottom wall of the inner cavity of the fuselage, and an adjusting plate is fixed to the output end of the electric telescopic rod. The outer walls on both sides of the adjusting plate are provided with tooth grooves that mesh with the drive gear. A locking mechanism is fixed inside the fuselage.
[0006] In a further embodiment, the fixing mechanism consists of a fixing column and two limiting blocks. The fixing column is fixed inside the connecting sleeve. Two guide rods that are fixedly connected to the limiting blocks are movably connected to the outside of the fixing column. A fixing spring for supporting the guide rods is sleeved on the outside of the fixing column. Moving grooves for the limiting blocks to move are opened on both sides of the outer wall of the connecting sleeve.
[0007] In a further embodiment, a pulling block is movably connected to the bottom of the connecting sleeve, a connecting post is fixed to the surface of the pulling block and movably connected to the connecting sleeve, and a connecting plate is fixed to the end face of the connecting post located inside the connecting sleeve.
[0008] In a further embodiment, two push-pull rods are provided above the connecting plate, and both ends of the push-pull rods are rotatably connected to connecting seats that are fixedly connected to the guide rod and the connecting plate.
[0009] In a further embodiment, the locking mechanism consists of a protective shell and a dual-axis motor. The protective shell is fixed inside the machine body, and the dual-axis motor is installed inside the protective shell. Both output ends of the dual-axis motor are fixed with guide screws, and the thread grooves of the guide screws on both sides of the dual-axis motor are oriented in opposite directions.
[0010] In a further embodiment, the outer wall of the guide screw is threaded with a locking pin, and the upper half of the outer wall of the rotating column is provided with multiple locking holes at equal intervals.
[0011] In a further embodiment, two positioning posts are symmetrically fixed to the surface of the limiting ring, and two positioning holes matching the positioning posts are opened at the bottom of the folding wing.
[0012] In a further embodiment, a limit slider is fixed at each of the four bottom corners of the adjustment plate, and two sets of limit grooves are provided on the bottom wall of the inner cavity of the machine body for the limit slider to slide.
[0013] In a further embodiment, the guide rod is provided with a plurality of rolling grooves, and the rolling grooves of the guide rod are connected to sliding balls that are in contact with the fixed column.
[0014] In a further embodiment, the upper and lower outer walls of the locking pin are fixed with limit sliders 2, and the upper and lower inner walls of the protective shell are provided with two limit grooves 2 for the limit sliders 2 to slide.
[0015] The technical effects and advantages of this invention are as follows: The foldable fixed wing of this unmanned aerial vehicle is driven by an electric telescopic rod to move an adjustment plate. The toothed grooves on both sides of the adjustment plate mesh with the drive gear on the rotating column, which can drive the rotating column and the folding wing at the bottom to rotate at multiple angles. It can precisely adjust the wing deployment angle according to flight requirements (such as low-speed operation and high-speed cruise), and fold the wing to a parallel state with the fuselage after the flight, which significantly reduces the overall volume, saves storage space, reduces the risk of bumps and damage during transportation, and improves the flexibility of transfer. In the fixing mechanism, the fixing spring pushes the limiting block into the limiting groove of the limiting ring through the guide rod. It works in conjunction with the positioning pin on the limiting ring to connect with the positioning hole of the folding wing, thus achieving a stable connection between the folding wing and the connecting sleeve. After the angle adjustment is completed, the dual-axis motor drives the guide screws with opposite thread directions on both sides to rotate, which drives the two locking pins to move synchronously towards each other and insert into the locking hole of the rotating pin, thus rigidly locking the rotating pin. This effectively prevents the wing from loosening or shifting in angle due to airflow impact or vibration during flight, ensuring flight attitude stability and control precision. Pulling down the pull block moves the two guide rods towards each other via the connecting column and connecting plate, causing the limit block to retract into the connecting sleeve. This allows for quick disassembly of the limit ring and folding wing without the need for complex tools. It also facilitates cleaning, inspection, or replacement of the folding wing later, reducing maintenance time and costs. The foldable fixed wing of this unmanned aerial vehicle can flexibly adjust and fold the angle of the folding wing, improving storage and transportation convenience and flight reliability. Attached Figure Description
[0016] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.
[0017] Figure 1 This is a schematic diagram of the structure of the present invention; Figure 2 This is a schematic diagram of the rotating column and folding wing of the present invention; Figure 3 This is a schematic diagram of the rotating column and connecting sleeve of the present invention; Figure 4 This is a schematic diagram of the rotating column and limiting block of the present invention; Figure 5 This is a schematic diagram of the limiting ring of the present invention; Figure 6 This is a cross-sectional view of the connecting sleeve of the present invention; Figure 7This is a cross-sectional view of the locking mechanism of the present invention.
[0018] In the diagram: 1. Fuselage; 2. Drive motor; 3. Propeller; 4. Fixed wing; 5. Rotating column; 6. Connecting sleeve; 7. Folding wing; 8. Displacement sensor; 9. Drive gear; 10. Limiting ring; 11. Positioning column; 12. Fixed column; 13. Guide rod; 14. Fixed spring; 15. Sliding ball; 16. Limiting block; 17. Pulling block; 18. Connecting column; 19. Connecting plate; 20. Push-pull rod; 21. Electric telescopic rod; 22. Adjusting plate; 23. Limiting slider one; 24. Protective shell; 25. Dual-axis motor; 26. Guide screw; 27. Locking pin; 28. Limiting slider two. Detailed Implementation
[0019] In the following description, numerous specific details are set forth in order to provide a more thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention can be practiced without one or more of these details. In other instances, certain technical features well-known in the art have not been described in order to avoid obscuring the invention.
[0020] Unless otherwise defined, the directions mentioned herein, such as up, down, left, right, front, back, inside, and outside, are based on the directions shown in the figures of this invention, and are explained here together.
[0021] This invention provides, for example Figure 1-7 The diagram shows a foldable fixed-wing unmanned aerial vehicle (UAV), comprising a fuselage 1 and a drive motor 2 installed within the fuselage 1. A propeller 3 is fixed to the output shaft of the drive motor 2. Two fixed wings 4 are fixed to the surface of the fuselage 1. An electronic control system (not shown) is installed at a suitable location within the fuselage 1 to control the UAV. The electronic control system is existing technology, and its structure will not be described in detail here. Two mounting holes are provided at the bottom of the fuselage 1. A rotating column 5 is rotatably connected to the mounting holes via bearings. A drive gear 9 is fixed to the outer wall of the rotating column 5. A connecting sleeve 6 is fixed to the bottom of the rotating column 5. A folding wing 7 is movably connected to the outside of the connecting sleeve 6. The surface of the folding wing 7 has a fixing hole, and a displacement sensor 8 is installed in the fixing hole. The displacement sensor 8 is a Hall sensor with a detection accuracy of ±0.5°, which can realize precise closed-loop control of the folding angle. The connecting sleeve 6 is a cuboid structure to ensure the stability between the folding wing 7 and the connecting sleeve 6. The external part of the connecting sleeve 6 is movably connected to a limiting ring 10 for limiting the position of the folding wing 7. Two positioning posts 11 are symmetrically fixed on the surface of the limiting ring 10. Two positioning holes matching the positioning posts 11 are opened at the bottom of the folding wing 7. The positioning posts 11 are inserted into the positioning holes at the bottom of the folding wing 7 to ensure the stability of the connection between the limiting ring 10 and the folding wing 7. A fixing mechanism is provided inside the connecting sleeve 6. The fixing mechanism consists of a fixing post 12 and two limiting blocks 16. The fixing post 12 is fixed inside the connecting sleeve 6. Two guide rods 13, which are fixedly connected to the limiting blocks 16, are movably connected to the outside of the fixing post 12. A fixing spring 14 for supporting the guide rods 13 is sleeved on the outside of the fixing post 12. The elastic force of the fixing spring 14 can be set according to actual usage requirements to ensure stable support for the two guide rods 13. The outer walls on both sides of the connecting sleeve 6 are provided with moving grooves for the limiting blocks 16 to move. Multiple rolling grooves are provided inside the guide rods 13. Sliding balls 15 that are in contact with the fixing post 12 are rolled in the rolling grooves of the guide rods 13, which can make the guide rods 13 move more smoothly outside the fixing post 12. The bottom of the limiting block 16 is provided with The inclined surface of the limiting block 16 is flat. The bottom of the limiting ring 10 has two symmetrical limiting grooves that match the limiting block 16. The limiting ring 10 moves upward on the connecting sleeve 6 and presses the limiting block 16. Since the bottom of the limiting block 16 is inclined, it can push the two limiting blocks 16 to move towards each other and press the fixing spring 14, causing the limiting block 16 to retract into the connecting sleeve 6. When the limiting ring 10 moves above the limiting block 16, the fixing spring 14 resets and pushes the guide rod 13 and the limiting block 16 to move, so that the limiting block 16 is stuck in the limiting groove at the bottom of the limiting ring 10, thereby fixing the position of the limiting ring 10. The limiting ring 10 is close to the bottom of the folding wing 7, thereby fixing the position of the folding wing 7 and ensuring the stability of the folding wing 7. A pull block 17 is movably connected to the bottom of the connecting sleeve 6. A connecting post 18, which is movably connected to the connecting sleeve 6, is fixed on the surface of the pull block 17. A connecting plate 19 is fixed on the end face of the connecting post 18 inside the connecting sleeve 6. Two push-pull rods 20 are provided above the connecting plate 19. Both ends of the push-pull rods 20 are rotatably connected to connecting seats that are fixedly connected to the guide rods 13 and the connecting plate 19. By pulling the connecting post 18 and the connecting plate 19 downward by the pull block 17, one end of the push-pull rod 20 is moved downward, which in turn causes the two guide rods 13 and the limiting block 16 to move towards each other, so that the limiting block 16 retracts into the connecting sleeve 6, releasing the restriction on the position of the limiting ring 10. After the limiting ring 10 is removed from the connecting sleeve 6, the folding wing 7 can be quickly disassembled, which is convenient for the later maintenance and replacement of the folding wing 7. The bottom of the inner cavity of the fuselage 1 An electric telescopic rod 21 is installed on the wall, and an adjustment plate 22 is fixed at the output end of the electric telescopic rod 21. The outer walls on both sides of the adjustment plate 22 are provided with toothed grooves that mesh with the drive gear 9. The four corners of the bottom of the adjustment plate 22 are fixed with limit sliders 23. The bottom wall of the inner cavity of the fuselage 1 is provided with two sets of limit grooves for the limit sliders 23 to slide. The limit sliders 23 move in the limit grooves of the fuselage 1, which can limit the movement path of the adjustment plate 22, ensure the stability of the adjustment plate 22 during movement, and ensure the adjustment accuracy. The adjustment plate 22 is moved by the electric telescopic rod 21, which drives the drive gear 9 and the rotating column 5 to rotate. The angle of the folding wing 7 can be adjusted according to the flight status of the unmanned aerial vehicle. After the flight, the folding wing 7 can be folded to reduce space occupation and make transportation more convenient. A locking mechanism is fixed inside the body 1. The locking mechanism consists of a protective shell 24 and a dual-axis motor 25. The protective shell 24 is fixed inside the body 1, and the dual-axis motor 25 is installed inside the protective shell 24. Guide screws 26 are fixed to both output ends of the dual-axis motor 25. The threaded grooves of the guide screws 26 on both sides of the dual-axis motor 25 are opposite. Locking pins 27 are threadedly connected to the outer walls of the guide screws 26. Multiple locking holes are evenly spaced on the upper half of the outer wall of the rotating column 5. Limit sliders 28 are fixed to the upper and lower outer walls of the locking pins 27. The upper and lower inner walls of the protective shell 24 are provided with two limiting grooves for the sliding of the limiting slider 28. The limiting slider 28 moves within the limiting grooves of the protective shell 24. When the dual-axis motor 25 drives the guide screw 26 to rotate, it can restrict the movement path of the locking pin 27, ensuring that the locking pin 27 moves horizontally within the protective shell 24. After the angle of the folding wing 7 is adjusted, the locking pin 27 is inserted into the locking hole of the rotating column 5, thereby fixing the position of the rotating column 5 and ensuring the stability of the folding wing 7.
[0022] All standard parts used in this invention can be purchased from the market, and irregularly shaped parts can be customized according to the description and drawings. The specific connection methods of each part adopt conventional methods such as bolts, rivets, and welding that are mature in the prior art. The machinery, parts, and equipment all adopt conventional models in the prior art. In addition, the circuit connection adopts conventional connection methods in the prior art, which will not be described in detail here. The control method of this invention is through a controller. The control circuit of the controller can be implemented by those skilled in the art through simple programming. It should be noted that the electrical components mentioned in this invention have been sorted according to the actual situation during manufacturing, so as not to cause the wire harness to become tangled or affect the operation. The contents not described in detail in this specification belong to the prior art known to those skilled in the art.
[0023] In the description of this invention, it should be understood that the indicated orientation or positional relationship is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this invention and simplifying the description, and is not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.
[0024] Working principle: Before flight, the foldable fixed wing of the unmanned aerial vehicle is first fitted onto the outside of the connecting sleeve 6. The limiting ring 10 is then fitted under the connecting sleeve 6 and pushed upward. The limiting ring 10 presses against the inclined surface of the limiting block 16, causing the two limiting blocks 16 to move towards each other and compress the fixing spring 14. When the limiting ring 10 moves above the limiting block 16, the fixing spring 14 resets and pushes the limiting block 16 into the limiting groove of the limiting ring 10. At the same time, the positioning pin 11 on the limiting ring 10 is inserted into the positioning hole of the foldable wing 7, thus completing the installation and fixing of the foldable wing 7. According to flight requirements, the electric telescopic rod 21 is extended and retracted by the electronic control system, which drives the adjustment plate 22 to move horizontally along the first limiting slide groove. The toothed grooves on both sides of the adjustment plate 22 mesh with the drive gear 9 on the rotating column 5, driving the rotating column 5 to rotate, thereby adjusting the unfolding angle of the folding wing 7. The displacement sensor 8 detects the wing angle in real time and feeds it back to the electronic control system to achieve precise angle control. After the angle is adjusted to the correct position, the electronic control system starts the dual-axis motor 25. The dual-axis motor 25 drives the guide screws 26 on both sides to rotate. Since the threads of the guide screws 26 are opposite, the two locking pins 27 move synchronously towards each other under the restriction of the second limiting slider 28 and the second limiting slide groove, and insert into the locking hole of the rotating column 5 to complete the locking of the rotating column 5, ensuring the stability of the wing angle during flight. After the flight, the dual-axis motor 25 rotates in the opposite direction, causing the locking pin 27 to disengage from the locking hole. The electric telescopic rod 21 drives the adjusting plate 22 to move in the opposite direction, so that the folding wing 7 is folded to the storage state. If the folding wing 7 needs to be disassembled, pull down the pulling block 17. The connecting column 18 and the connecting plate 19 drive the push-pull rod 20 to pull the guide rod 13 and the limit block 16 back, releasing the restriction on the limit ring 10. After removing the limit ring 10, the folding wing 7 can be removed.
[0025] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.
Claims
1. A foldable fixed wing for an unmanned aerial vehicle, comprising a fuselage (1) and a drive motor (2) installed within the fuselage (1), characterized in that: A propeller (3) is fixed to the output shaft of the drive motor (2), two fixed wings (4) are fixed to the surface of the fuselage (1), two mounting holes are opened at the bottom of the fuselage (1), a rotating column (5) is rotatably connected in the mounting holes, and a drive gear (9) is fixed to the outer wall of the rotating column (5). The bottom of the rotating column (5) is fixed with a connecting sleeve (6), the outside of the connecting sleeve (6) is movably connected with a folding wing (7), and the outside of the connecting sleeve (6) is movably connected with a limiting ring (10) for limiting the position of the folding wing (7). The surface of the folding wing (7) is provided with a fixing hole, and a displacement sensor (8) is installed in the fixing hole. A fixing mechanism is provided inside the connecting sleeve (6). An electric telescopic rod (21) is installed on the bottom wall of the inner cavity of the fuselage (1), and an adjusting plate (22) is fixed at the output end of the electric telescopic rod (21). Both sides of the outer wall of the adjusting plate (22) are provided with tooth grooves that mesh with the drive gear (9). A locking mechanism is fixed inside the fuselage (1).
2. The foldable fixed wing of an unmanned aerial vehicle according to claim 1, characterized in that: The fixing mechanism consists of a fixing column (12) and two limiting blocks (16). The fixing column (12) is fixed inside the connecting sleeve (6). The fixing column (12) is movably connected to two guide rods (13) that are fixedly connected to the limiting blocks (16). The fixing column (12) is sleeved with a fixing spring (14) for supporting the guide rods (13). The outer walls on both sides of the connecting sleeve (6) are provided with moving grooves for the limiting blocks (16) to move.
3. The foldable fixed wing of an unmanned aerial vehicle according to claim 2, characterized in that: The bottom of the connecting sleeve (6) is movably connected to a pull block (17), and the surface of the pull block (17) is fixed with a connecting post (18) movably connected to the connecting sleeve (6). The end face of the connecting post (18) located inside the connecting sleeve (6) is fixed with a connecting plate (19).
4. The foldable fixed wing of an unmanned aerial vehicle according to claim 3, characterized in that: Two push-pull rods (20) are provided above the connecting plate (19). Both ends of the push-pull rods (20) are rotatably connected to connecting seats that are fixedly connected to the guide rod (13) and the connecting plate (19).
5. The foldable fixed wing of an unmanned aerial vehicle according to claim 1, characterized in that: The locking mechanism consists of a protective shell (24) and a dual-axis motor (25). The protective shell (24) is fixed inside the body (1). The dual-axis motor (25) is installed inside the protective shell (24), and both output ends of the dual-axis motor (25) are fixed with guide screws (26). The thread grooves of the guide screws (26) on both sides of the dual-axis motor (25) are opposite.
6. The foldable fixed wing of an unmanned aerial vehicle according to claim 5, characterized in that: The outer wall of the guide screw (26) is threaded with a locking pin (27), and the upper half of the outer wall of the rotating column (5) is provided with multiple locking holes at equal intervals.
7. The foldable fixed wing of an unmanned aerial vehicle according to claim 1, characterized in that: The surface of the limiting ring (10) is symmetrically fixed with two positioning posts (11), and the bottom of the folding wing (7) has two positioning holes that match the positioning posts (11).
8. The foldable fixed wing of an unmanned aerial vehicle according to claim 1, characterized in that: The bottom four corners of the adjustment plate (22) are fixed with limit sliders (23), and the bottom wall of the inner cavity of the body (1) is provided with two sets of limit grooves for the limit sliders (23) to slide.
9. A foldable fixed wing for an unmanned aerial vehicle according to claim 2, characterized in that: The guide rod (13) has multiple rolling grooves, and the rolling grooves of the guide rod (13) are connected to sliding balls (15) that are in contact with the fixed column (12).
10. A foldable fixed wing for an unmanned aerial vehicle according to claim 6, characterized in that: The upper and lower outer walls of the locking pin (27) are fixed with limit sliders (28), and the upper and lower inner walls of the protective shell (24) are provided with two limit grooves for the limit sliders (28) to slide.