Airfoil surface adjusting device of unmanned aerial vehicle

Abstract

The invention relates to the technical field of airfoil adjustment, and discloses an airfoil adjusting device of an unmanned aerial vehicle, which comprises a nose, a main wing adjusting structure, a fuselage, an empennage adjusting structure and a tail, wherein two ends of the fuselage are respectively connected with the nose and the tail; the main wing adjusting structures are arranged on the two sides of the middle of the fuselage, and the main wing adjusting structures and the fuselage are adjustably installed. The empennage adjusting structure is arranged at the rear part of the fuselage and is connected with the tail; and the main wing adjusting structure and the empennage adjusting structure are used for wing surface unfolding, angle adjustment and attitude balance control of the unmanned aerial vehicle. The method has remarkable advantages in the aspects of improving the flight performance, adaptability and stability of the air-drop carrier.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of airfoil adjustment, in particular to an airfoil adjustment device of an unmanned aerial delivery vehicle. BACKGROUND

[0002] In the current technical field of unmanned aerial delivery vehicles, a key function has not been successfully developed and implemented, that is, the main wing of the aerial delivery vehicle can be flexibly adjusted within the range of 0° to 90°, thereby achieving the self-retracting and deploying of the main wing. Moreover, the technology does not have the ability to adjust the front and rear positions of the main wing, and the tail wing of the aerial delivery vehicle cannot be accurately adjusted within the range of ±45° relative to the horizontal reference plane. The existence of these technical bottlenecks limits the adaptability and flexibility of the unmanned aerial delivery vehicle in complex environments, and affects the improvement of its overall performance and the expansion of its application range.

[0003] Therefore, it is necessary to design an airfoil adjustment device of an unmanned aerial delivery vehicle to solve the problems existing in the current technology. SUMMARY

[0004] In view of this, the present application provides an airfoil adjustment device of an unmanned aerial delivery vehicle, which aims to achieve the 0° to 90° adjustment function of the main wing of the aerial delivery vehicle, thereby achieving the retracting and deploying of the main wing, and having the ability to adjust the front and rear positions of the main wing and the ±45° adjustable function of the tail wing of the aerial delivery vehicle relative to the horizontal reference.

[0005] The present application provides an airfoil adjustment device of an unmanned aerial delivery vehicle, comprising: a nose, a main wing adjustment structure, a fuselage, a tail wing adjustment structure, and a tail; wherein, both ends of the fuselage are connected to the nose and the tail, respectively; the main wing adjustment structure is arranged at both sides of the middle part of the fuselage, and the main wing adjustment structure is adjustably mounted to the fuselage; the tail wing adjustment structure is arranged at the rear of the fuselage and connected to the tail; the main wing adjustment structure and the tail wing adjustment structure are used for the airfoil deployment, angle adjustment, and attitude balance control of the unmanned aerial delivery vehicle.

[0006] Further, the main wing adjustment structure comprises: a main wing, a wing connecting plate, a wing platform, a toothed piece, a first servo motor, a motor support, a sliding plate, a reinforcing rib, a second servo motor, and a wing platform adapter hinge.

[0007] Furthermore, the main wing is connected to the wing platform via the wing connecting plate, the gear is coaxially arranged with the wing platform, the first servo motor is fixed to the wing platform via the motor bracket by bolt connection, the output end of the first servo motor is coupled to the screw, and the rotation of the screw drives the gear to mesh and rotate.

[0008] Furthermore, the sliding plate is connected to the fuselage via the reinforcing rib, the wing platform hinge is coaxially arranged with the reinforcing rib, the second servo motor is fixedly connected to the fuselage via the first bolt, and the second servo motor drives the wing platform hinge to move.

[0009] Furthermore, a limiting slide rail structure is provided between the main wing adjustment mechanism and the fuselage to limit the forward and backward movement range of the main wing. The limiting slide rail structure forms a guide with the lower end of the sliding plate, and the sliding plate and the main wing can generate a linear displacement in the range of 0 to 57 mm along the forward and backward direction of the fuselage.

[0010] Furthermore, the tail fin adjustment structure includes: Tail fin, connecting hinge, connecting rod hinge, bearing column, electric actuator, tail liner, first connecting rod and second connecting rod.

[0011] Furthermore, the lower part of the tail fin is fixedly connected to the tail section via the tail liner, and the upper end of the tail fin is hinged to the connecting rod hinge via the connecting hinge. The connecting rod hinge is coaxially connected to the bearing column to provide a pivot point for the tail fin's swing.

[0012] Furthermore, one end of the electric actuator is fixed to the bearing column by a second bolt, and the other end is connected to the first connecting rod by a wire. The first connecting rod and the second connecting rod are connected by a pin, and the other end of the second connecting rod is hinged to the connecting hinge of the tail fin.

[0013] Furthermore, when the electric actuator extends or retracts, it transmits driving force through the first connecting rod and the second connecting rod, causing the tail fin to swing within a range of ±45° around the axis of the connecting hinge.

[0014] Furthermore, the tail fin adjustment structure also includes a tail fin control section and a tail fin parachute compartment section; wherein, The tail fin control section and the tail fin parachute compartment section are connected by bolts through the support column, forming an integrated connection between the tail fin control section and the tail fin parachute compartment section.

[0015] Compared with existing technologies, the beneficial effects of this invention are as follows: The wing adjustment device for the unmanned airdrop vehicle provided by this invention achieves flexible adjustment of the main wing from 0° to 90° and linear displacement within the range of 0 to 57 mm in the fore-and-aft direction through the main wing adjustment structure, effectively improving the adaptability and stability of the airdrop vehicle during flight. The first and second servo motors in the main wing adjustment structure work together to precisely control the deployment angle and position of the main wing, ensuring that the airdrop vehicle maintains the optimal attitude in different flight phases. Simultaneously, the tail wing adjustment structure, through the combination design of electric actuators and connecting rods, achieves ±45° adjustable tail wing relative to the horizontal reference, further enhancing the flight control capability and maneuverability of the airdrop vehicle. The integrated connection design of the tail wing control section and the tail wing parachute compartment section simplifies the structure and improves overall reliability. In summary, the wing adjustment device for the unmanned airdrop vehicle provided by this invention has significant advantages in improving the flight performance, adaptability, and stability of the airdrop vehicle. Attached Figure Description

[0016] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 A schematic diagram of the overall structure of the wing surface adjustment device of the unmanned airdrop vehicle provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of the main wing adjustment structure provided in an embodiment of the present invention; Figure 3 A bottom view of the main wing adjustment structure provided in an embodiment of the present invention; Figure 4 This is a schematic diagram of the internal structure of the tail section provided in an embodiment of the present invention; Figure 5 This is a schematic diagram of the tail fin control section provided in an embodiment of the present invention; Figure 6 The image shows a comparison of the main wing positions of an unmanned airdrop vehicle. The left side shows the main wing at the foremost position, while the right side shows the main wing at the rearmost position. Figure 7 A schematic diagram of a main wing with a 90° deployment angle; Figure 8 A schematic diagram of a main wing with a 45° deployment angle; Figure 9 A schematic diagram of the structure with a main wing deployment angle of 0°.

[0017] In the diagram: 100, Nose; 200, Main wing adjustment structure; 201, Main wing; 202, Wing connecting plate; 203, Gear; 204, First servo motor; 205, Motor bracket; 206, Sliding plate; 207, Reinforcing rib; 208, Second servo motor; 209, Wing platform adapter hinge; 300, Fuselage; 400, Tail wing adjustment structure; 401, Tail wing; 402, Connecting hinge; 403, Connecting rod hinge; 404, Bearing column; 405, Electric actuator; 406, Tail liner; 407, First connecting rod; 408, Second connecting rod; 500, Tail; 501, Tail wing control section; 502, Tail wing parachute compartment section. Detailed Implementation

[0018] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the disclosure to those skilled in the art. It should be noted that, unless otherwise specified, embodiments and features in the embodiments of the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0019] See Figures 1-9 As shown in some embodiments of this application, this embodiment provides a wing adjustment device for an unmanned airdrop vehicle, including: The fuselage consists of a nose section 100, a main wing adjustment structure 200, a fuselage 300, a tail wing adjustment structure 400, and a tail section 500; among which, The two ends of the fuselage 300 are connected to the head 100 and the tail 500, respectively; The main wing adjustment structure 200 is located on both sides of the middle part of the fuselage 300, and the main wing adjustment structure 200 and the fuselage 300 can be adjusted and installed. The tail fin adjustment structure 400 is located at the rear of the fuselage 300 and is connected to the tail 500; The main wing adjustment structure 200 and the tail wing adjustment structure 400 are used for the wing deployment, angle adjustment and attitude balance control of the unmanned airdrop vehicle.

[0020] It is understood that the wing adjustment device of the unmanned airdrop vehicle provided in this embodiment achieves flexible adjustment of the main wing 201° to 90° and linear displacement within the range of 0 to 57 mm in the fore-and-aft direction through the main wing adjustment structure 200, effectively improving the adaptability and stability of the airdrop vehicle during flight. The first servo motor 204 and the second servo motor 208 in the main wing adjustment structure 200 work together to precisely control the deployment angle and position of the main wing 201, ensuring that the airdrop vehicle maintains the optimal attitude in different flight phases. At the same time, the tail wing adjustment structure 400, through the combination design of the electric actuator 405 and the connecting rod, realizes the ±45° adjustable function of the tail wing 401 relative to the horizontal reference, further enhancing the flight control capability and maneuverability of the airdrop vehicle. The integrated connection design of the tail wing control part 501 and the tail wing parachute compartment part 502 simplifies the structure and improves the overall reliability. In summary, the wing adjustment device of the unmanned airdrop vehicle provided in this embodiment has significant advantages in improving the flight performance, adaptability and stability of the airdrop vehicle.

[0021] Specifically, the main wing adjustment structure 200 includes: The main wing 201, wing connecting plate 202, wing platform, gear 203, first servo motor 204, motor bracket 205, sliding plate 206, reinforcing rib 207, second servo motor 208, and wing platform transition hinge 209.

[0022] Understandably, the main wing 201, as the primary lifting surface of the airdrop vehicle, is designed with aerodynamic performance and structural strength in mind. The wing connecting plate 202 securely connects the main wing 201 to the wing platform, ensuring it does not loosen or detach during flight. The wing platform, as the foundation of the main wing adjustment structure 200, provides a mounting platform for other components. The gear plate 203 cooperates with the first servo motor 204, achieving precise angle adjustment of the main wing 201 through gear transmission. The motor bracket 205 secures the first servo motor 204, ensuring its stable operation. The sliding plate 206 allows the main wing 201 to perform linear displacement within a certain range to adapt to different flight requirements. The reinforcing rib 207 enhances the rigidity and stability of the entire main wing adjustment structure 200. The second servo motor 208 is connected to the main wing 201 via the wing platform adapter hinge 209, further refining the adjustment precision of the main wing 201.

[0023] Specifically, the main wing 201 is connected to the wing platform through the wing connecting plate 202, the gear 203 is coaxially set with the wing platform, the first servo motor 204 is fixed to the wing platform by bolts through the motor bracket 205, the output end of the first servo motor 204 is coupled to the screw, and the rotation of the screw drives the gear 203 to mesh and rotate.

[0024] Understandably, after the first servo motor 204 is started, its output drives the screw to rotate. The meshing action between the screw and the gear 203 converts the rotational motion into the rotation of the gear 203. Since the gear 203 is coaxially set with the wing platform and the main wing 201 is connected to the wing platform through the wing connecting plate 202, the rotation of the gear 203 will drive the main wing 201 to adjust its angle, so as to realize the flexible rotation of the main wing 201 from 0° to 90°.

[0025] Specifically, the sliding plate 206 is connected to the fuselage 300 via the reinforcing rib 207, the wing platform transition hinge 209 is coaxially arranged with the reinforcing rib 207, the second servo motor 208 is fixedly connected to the fuselage 300 via the first bolt, and the second servo motor 208 drives the wing platform transition hinge 209 to move.

[0026] Understandably, after the second servo motor 208 starts, it drives the wing platform hinge 209 to move. Since the wing platform hinge 209 is coaxially arranged with the reinforcing rib 207, and the sliding plate 206 is connected to the fuselage 300 through the reinforcing rib 207, the movement of the wing platform hinge 209 will cause the sliding plate 206 to move linearly, thereby enabling the main wing 201 to move linearly within a certain range (0-57mm forward and backward). This allows the main wing 201 to not only adjust its angle but also adjust its forward and backward position according to flight requirements, thereby further improving the flight adaptability and stability of the airdrop vehicle. At the same time, the setting of the reinforcing rib 207 not only enhances the rigidity of the structure but also ensures a stable connection between the components, improving the overall structural reliability.

[0027] Specifically, a limiting slide rail structure is provided between the main wing 201 adjustment mechanism and the fuselage 300 to limit the forward and backward movement range of the main wing 201. The limiting slide rail structure forms a guide with the lower end of the sliding plate 206, and the sliding plate 206 and the main wing 201 can produce linear displacement in the range of 0 to 57 mm along the forward and backward direction of the fuselage 300.

[0028] Understandably, the limiting rail structure provides precise guidance and range limitation for the forward and backward movement of the sliding plate 206 and the main wing 201. During the linear displacement of the main wing 201 within the range of 0-57mm, the limiting rail structure ensures that the sliding plate 206 and the main wing 201 always move along the predetermined trajectory, avoiding problems such as flight instability or structural damage that may be caused by movement deviation. At the same time, this design also makes the adjustment of the main wing 201 more precise and reliable, further improving the flight performance and safety of the airdrop vehicle. In practical applications, the limiting rail structure can be customized and optimized according to the specific needs of the airdrop vehicle and the flight environment to adapt to different flight scenarios and mission requirements.

[0029] Specifically, the tail fin adjustment structure 400 includes: Tail fin 401, connecting hinge 402, connecting rod hinge 403, bearing column 404, electric actuator 405, tail liner 406, first connecting rod 407, and second connecting rod 408.

[0030] Understandably, the tail fin 401, as a crucial control surface of the airdrop vehicle, is designed with aerodynamic characteristics and structural stability in mind. The connecting hinge 402 and the connecting rod hinge 403 together form a flexible connection mechanism between the tail fin 401 and the fuselage 300, allowing for precise angular adjustment of the tail fin 401 relative to the fuselage 300. The support column 404, as a key supporting component of the tail fin adjustment structure 400, provides a stable mounting base for the electric actuator 405 and other components. The electric actuator 405, through its precise telescoping motion, drives the tail fin 401 to be adjustable within ±45° relative to the horizontal reference, thereby achieving precise control of the airdrop vehicle's flight attitude. The tail liner 406 not only enhances the structural strength of the tail fin 401 area but also provides additional protection for other components. The first connecting rod 407 and the second connecting rod 408 are connected to the tail fin 401 and the support column 404 via hinges, forming the transmission chain of the tail fin adjustment structure 400, which ensures the accuracy and reliability of the tail fin 401 adjustment.

[0031] Specifically, the lower part of the tail fin 401 is fixedly connected to the tail 500 via the tail liner 406, and the upper end of the tail fin 401 is hinged to the connecting rod hinge 403 via the connecting hinge 402. The connecting rod hinge 403 is coaxially connected to the support column 404 to provide a pivot point for the tail fin 401 to swing.

[0032] Understandably, the fixed connection between the lower part of the tail fin 401 and the tail section 500 via the tail liner 406 ensures the structural stability of the tail fin 401 during flight, preventing loosening or detachment due to vibration or airflow impact. The hinged design of the upper part of the tail fin 401, connecting hinge 402 and connecting rod hinge 403, allows the tail fin 401 to swing flexibly around the coaxial connection point between the connecting rod hinge 403 and the support column 404. This design not only enables precise angle adjustment of the tail fin 401 relative to the fuselage 300 but also ensures the stability and reliability of the tail fin 401 during swinging. The coaxial connection between the connecting rod hinge 403 and the support column 404 provides a stable rotation fulcrum for the tail fin 401, making its adjustment more precise and controllable.

[0033] Specifically, one end of the electric actuator 405 is fixed to the bearing column 404 by the second bolt, and the other end is connected to the first connecting rod 407 by the wire. The first connecting rod 407 and the second connecting rod 408 are connected by a pin. The other end of the second connecting rod 408 is hinged to the connecting hinge 402 of the tail fin 401.

[0034] Understandably, one end of the electric actuator 405 is securely fixed to the support column 404 by the second bolt, providing a stable power output point for the entire tail fin adjustment structure 400. Its other end is connected to the first connecting rod 407 via a wire. This design allows the telescopic movement of the electric actuator 405 to be precisely transmitted to the first connecting rod 407. The first connecting rod 407 and the second connecting rod 408 are connected by a pin, forming a flexible transmission joint that ensures smooth and precise power transmission. The other end of the second connecting rod 408 is hinged to the connecting hinge 402 of the tail fin 401, allowing the telescopic movement of the electric actuator 405 to be converted into precise angle adjustment of the tail fin 401.

[0035] Specifically, when the electric actuator 405 extends or retracts, it transmits driving force through the first connecting rod 407 and the second connecting rod 408, causing the tail fin 401 to swing within a range of ±45° around the axis of the connecting hinge 402.

[0036] Understandably, when the electric actuator 405 extends or retracts, the driving force it generates is precisely transmitted to the tail fin 401 through the transmission chain formed by the first connecting rod 407 and the second connecting rod 408. Since the second connecting rod 408 is hinged to the connecting hinge 402 of the tail fin 401, this driving force will drive the tail fin 401 to swing around the axis of the connecting hinge 402. Through the precise control of the electric actuator 405, the tail fin 401 can achieve flexible and stable angle adjustment within a range of ±45°. This design allows the airdrop vehicle to quickly adjust the angle of the tail fin 401 according to actual needs during flight, thereby achieving precise control of the flight attitude and further enhancing the flight stability and maneuverability of the airdrop vehicle. At the same time, the design of this tail fin adjustment structure 400 also fully considers structural strength and reliability, ensuring stable operation under various flight conditions.

[0037] Specifically, the tail fin adjustment structure 400 also includes a tail fin control section 501 and a tail fin parachute compartment section 502; wherein... The tail wing control section 501 and the tail wing parachute compartment section 502 are connected by bolts through the support column 404, forming an integrated connection between the tail wing control section 501 and the tail wing parachute compartment section 502.

[0038] Understandably, the tail control unit 501 and the tail parachute compartment 502 are integrated via bolts through the support column 404. This design not only simplifies the overall structure and reduces connection gaps and potential failure points between components, but also significantly improves the overall rigidity and reliability of the tail adjustment structure 400. During flight, this integrated connection can better withstand airflow impacts and vibrations, ensuring the accuracy and stability of the tail 401 adjustment. Simultaneously, the bolted connection facilitates subsequent maintenance and repair, reducing maintenance costs and time. Furthermore, the tail control unit 501 receives commands from the flight control system and precisely controls the extension and retraction of the electric actuator 405, thereby achieving fine adjustment of the tail 401 angle. The tail parachute compartment 502 integrates safety devices such as parachutes, providing strong protection for the safe landing of the airdrop vehicle in emergency situations. The integrated design of both significantly improves the flight control and safety performance of the airdrop vehicle.

[0039] In this embodiment, the operation process of the wing adjustment device of the unmanned airdrop vehicle is as follows: During the flight preparation phase, operators perform initial settings on the main wing adjustment structure 200 and the tail wing adjustment structure 400 according to the preset flight mission and vehicle performance parameters. Through the control system, the initial deployment angle and position of the main wing 201 and the initial angle of the tail wing 401 are set to ensure that the airdrop vehicle can maintain a stable flight attitude during takeoff.

[0040] Once the unmanned airdrop vehicle enters the flight phase, the wing adjustment device begins to operate in real time. During flight, the flight control system determines whether the current flight status requires adjustment of the angles of the main wing 201 and tail fin 401 based on real-time flight data and sensor feedback. For example, when encountering airflow disturbances or needing to change flight direction, the control system will quickly issue commands.

[0041] For the main wing adjustment structure 200, upon receiving an adjustment command, the first servo motor 204 and the second servo motor 208 work together. The first servo motor 204 starts, and its output drives the screw to rotate. The meshing action of the screw and the gear 203 converts the rotational motion into the rotation of the gear 203. Since the gear 203 is coaxially set with the wing platform and the main wing 201 is connected to the wing platform through the wing connecting plate 202, the rotation of the gear 203 drives the main wing 201 to adjust its angle, realizing the flexible rotation of the main wing 201 within the range of 0° to 90°. At the same time, the second servo motor 208 starts, driving the wing platform transition hinge 209 to move. Since the wing platform transition hinge 209 is coaxially set with the reinforcing rib 207 and the sliding plate 206 is connected to the fuselage 300 through the reinforcing rib 207, the movement of the wing platform transition hinge 209 drives the sliding plate 206 to make linear displacement, thereby realizing the linear movement of the main wing 201 within the range of 0 to 57 mm. The limiting slide rail structure provides precise guidance and range restriction for the forward and backward movement of the sliding plate 206 and the main wing 201, ensuring that the sliding plate 206 and the main wing 201 always move along the predetermined trajectory.

[0042] For the tail fin adjustment structure 400, upon receiving an adjustment command, the tail fin control unit 501 precisely controls the extension and retraction of the electric actuator 405. One end of the electric actuator 405 is securely fixed to the support column 404 by a second bolt, and the other end is connected to the first connecting rod 407 via a wire. When the electric actuator 405 extends or retracts, the driving force it generates is precisely transmitted to the tail fin 401 through the transmission chain formed by the first connecting rod 407 and the second connecting rod 408. Since the second connecting rod 408 is hinged to the connecting hinge 402 of the tail fin 401, this driving force drives the tail fin 401 to swing within a range of ±45° around the axis of the connecting hinge 402, achieving precise control of the flight attitude of the airdrop vehicle.

[0043] Throughout the flight, the wing surface adjustment device continuously and dynamically adjusts according to the instructions of the flight control system to ensure that the unmanned airdrop vehicle can maintain optimal flight attitude and stability under various flight conditions, and safely and accurately complete the airdrop mission. When the airdrop mission is completed or an emergency landing is required, the tail parachute compartment 502 in the tail adjustment structure 400 will release the parachute in a timely manner. At the same time, the wing surface adjustment device will adjust the angle of the main wing 201 and the tail wing 401 to assist the airdrop vehicle in landing safely.

[0044] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program goods. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program goods on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0045] This application is described with flowcharts and / or block diagrams of methods, apparatus (systems), and computer program goods according to embodiments of this application. It will be understood that each block of the flowcharts and / or block diagrams, and combinations of blocks in the flowcharts and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowcharts and / or block diagrams. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0046] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0047] These computer program instructions can also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0048] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the specific implementation of the present invention. Any modifications or equivalent substitutions that do not depart from the spirit and scope of the present invention should be covered within the scope of protection of the claims of the present invention.

Claims

1. A wing adjustment device for an unmanned airdrop vehicle, characterized in that, include: The nose, main wing adjustment structure, fuselage, tail wing adjustment structure, and tail; among which, The two ends of the fuselage are respectively connected to the head and the tail; The main wing adjustment structure is located on both sides of the middle part of the fuselage, and the main wing adjustment structure is adjustablely installed with the fuselage; The tail fin adjustment structure is located at the rear of the fuselage and is connected to the tail section; The main wing adjustment structure and tail wing adjustment structure are used for the wing deployment, angle adjustment and attitude balance control of the unmanned airdrop vehicle.

2. The wing adjustment device of the unmanned airdrop vehicle according to claim 1, characterized in that, The main wing adjustment structure includes: Main wing, wing connecting plate, wing platform, gear plate, first servo motor, motor bracket, sliding plate, reinforcing rib, second servo motor and wing platform transition hinge.

3. The wing adjustment device for the unmanned airdrop vehicle according to claim 2, characterized in that, The main wing is connected to the wing platform via the wing connecting plate. The gear is coaxially arranged with the wing platform. The first servo motor is fixed to the wing platform via the motor bracket by bolt connection. The output end of the first servo motor is coupled to the screw. The rotation of the screw drives the gear to mesh and rotate.

4. The wing adjustment device of the unmanned airdrop vehicle according to claim 3, characterized in that, The sliding plate is connected to the fuselage via the reinforcing rib, the wing platform hinge is coaxially arranged with the reinforcing rib, the second servo motor is fixedly connected to the fuselage via the first bolt, and the second servo motor drives the wing platform hinge to move.

5. The wing adjustment device of the unmanned airdrop vehicle according to claim 4, characterized in that, A limiting slide rail structure is provided between the main wing adjustment mechanism and the fuselage to limit the forward and backward movement range of the main wing. The limiting slide rail structure forms a guide with the lower end of the sliding plate, and the sliding plate and the main wing can generate linear displacement in the range of 0 to 57 mm along the forward and backward direction of the fuselage.

6. The wing adjustment device for the unmanned airdrop vehicle according to claim 5, characterized in that, The tail fin adjustment structure includes: Tail fin, connecting hinge, connecting rod hinge, bearing column, electric actuator, tail liner, first connecting rod and second connecting rod.

7. The wing adjustment device for the unmanned airdrop vehicle according to claim 6, characterized in that, The lower part of the tail fin is fixedly connected to the tail section via the tail liner, and the upper end of the tail fin is hinged to the connecting rod hinge via the connecting hinge. The connecting rod hinge is coaxially connected to the support column to provide a pivot point for the tail fin's swing.

8. The wing adjustment device for the unmanned airdrop vehicle according to claim 7, characterized in that, One end of the electric actuator is fixed to the bearing column by a second bolt, and the other end is connected to the first connecting rod by a wire. The first connecting rod and the second connecting rod are connected by a pin, and the other end of the second connecting rod is hinged to the connecting hinge of the tail fin.

9. The wing adjustment device for the unmanned airdrop vehicle according to claim 8, characterized in that, When the electric actuator extends or retracts, it transmits driving force through the first connecting rod and the second connecting rod, causing the tail fin to swing within a range of ±45° around the axis of the connecting hinge.

10. The wing adjustment device of the unmanned airdrop vehicle according to claim 9, characterized in that, The tail fin adjustment structure also includes a tail fin control section and a tail fin parachute compartment section; wherein... The tail fin control section and the tail fin parachute compartment section are connected by bolts through the support column, forming an integrated connection between the tail fin control section and the tail fin parachute compartment section.

Images